Takeoff and Landing Distance Measurement: An Evaluation of ...

Takeoff and Landing Distance Measurement:

An Evaluation of Laser Altimetry for the Collection of

Absolute Aircraft Altitude

Christopher John Kennedy

Bachelor of Science

Aerospace Engineering

Florida Institute of Technology

A thesis submitted to the College of Engineering at

Florida Institute of Technology

in partial fulfillment of the requirements

for the degree of

Master of Science

in

Flight Test Engineering

Melbourne, Florida

May 2017

We the undersigned committee hereby recommend

that the attached document be accepted as fulfilling

in part the requirements for the degree of

Master of Science in Flight Test Engineering


An Evaluation of Laser Altimetry for the Collection of Absolute Aircraft Altitude

A thesis by Christopher John Kennedy

_________________________________________________

Brian A. Kish, Ph.D.

Assistant Professor and Chair, Flight Test Engineering

Mechanical and Aerospace Engineering

_________________________________________________

Ralph D. Kimberlin, Ph.D.

Professor


_________________________________________________

Stephen K. Cusick, J.D.

Associate Professor

College of Aeronautics

_________________________________________________

Hamid Hefazi, Ph.D.

Professor and Department Head


iii

Abstract


An Evaluation of Laser Altimetry for the Collection of Absolute Aircraft Altitude

Christopher John Kennedy

Advisor: Brian A. Kish, Ph.D.

The measurement of takeoff and landing distance during flight testing of general

aviation aircraft requires the accurate measurement of aircraft position over the

ground and altitude up to 50 feet above surface elevation. Current methods of

evaluating takeoff and landing distances include cinetheodolites, laser and radar

trackers, and Differential Global Positioning Systems (DGPS). The use of laser

altimetry to range altitude above the ground originated with military and

agricultural aircraft. The AgLaser laser module was an infrared laser ranging unit

designed for agricultural aircraft to gauge optimal spray height above a field. The

AgLaser system has a stated accuracy of 2.0 inches and a maximum range of 500

feet. [1] By integrating the AgLaser system into the Flight Test Data Acquisition

System designed at Florida Institute of Technology, the ability exists to measure

takeoff and landing distance more accurately than currently acceptable methods.

The integration of the laser module and the instrumentation unit occurred across an

RS-232 serial connection and a modified LabVIEW interface. Through a series of

ground and flight tests conducted at Florida Institute of Technology and Valkaria

Airport (X59), the integrated system was validated. Data from this research can be

presented to the Federal Aviation Administration for consideration as an accurate,

cost- effective means of measuring takeoff and landing distances for aircraft

certification per 14 CFR Part 23.

iv

Table of Contents

List of Figures ....................................................................................................................... vi

List of Tables ..................................................................................................................... viii

List of Equations ................................................................................................................... ix

List of Abbreviations ............................................................................................................. x

List of Symbols ..................................................................................................................... xi

Acknowledgements.............................................................................................................. xii

Dedication .......................................................................................................................... xiii

Chapter 1 Introduction ........................................................................................................... 1

1.1 Background .................................................................................................................. 1

1.2 Motivation ................................................................................................................... 7

1.3 Objectives .................................................................................................................... 8

Chapter 2 Test Methods ....................................................................................................... 10

2.1 Test Aircraft ............................................................................................................... 10

2.2 Data Collection System ............................................................................................. 12

2.3 Ground Testing .......................................................................................................... 18

2.4 Data Collection Procedure ......................................................................................... 19

2.5 Data reduction ............................................................................................................ 24

Chapter 3 Results ................................................................................................................. 25

3.1 Ground Test Overview .............................................................................................. 25

3.2 Flight Overview ......................................................................................................... 27

3.3 Takeoff Distance ........................................................................................................ 28

3.4 Landing Distance ....................................................................................................... 35

Chapter 4 Analysis ............................................................................................................... 42

4.1 Vertical Accuracy ...................................................................................................... 42

4.2 Takeoff Distance ........................................................................................................ 43

4.3 Landing Distance ....................................................................................................... 45

4.4 Factors of Data Variation ........................................................................................... 46

Chapter 5 Conclusions ......................................................................................................... 48

5.1 Conclusions ............................................................................................................... 48

v

5.2 Recommendations for Future Testing........................................................................ 49

References ........................................................................................................................... 51

Appendix A Advisory Circular 23-8C, Subpart B, Section 2 .............................................. 53

Appendix B Advisory Circular 23-8C, Subpart B, Section 2 .............................................. 57

Appendix C LabVIEW Code for Laser Module Input......................................................... 64

Appendix D Test Plans ........................................................................................................ 66

Appendix E Weight and Balance ......................................................................................... 68

Appendix F Ground Data ..................................................................................................... 69

Appendix G Flight Data Sample .......................................................................................... 72

Appendix H SSMG-11 [12] ................................................................................................. 90

vi

List of Figures

Figure 1. 14 CFR Part 23.53 Takeoff Performance [3] ......................................................... 2

Figure 2. 14 CFR Part 23.75 Landing Distance [3] ............................................................... 3

Figure 3. Takeoff Distance [4] ............................................................................................... 5

Figure 4. Landing Distance [4] .............................................................................................. 5

Figure 5. Variation of Force with Distance [4] ...................................................................... 6

Figure 6. Test Aircraft: Piper Warrior II N618FT ............................................................... 10

Figure 8. RS-232 Signal Cable Installed in Right Wing ...................................................... 11

Figure 7. AG Laser Installation on Test Aircraft ................................................................. 11

Figure 9. AgLaser: Laser Altimeter Module ....................................................................... 12

Figure 10. Florida Tech Data Acquisition System .............................................................. 13

Figure 11. Florida Tech Data Acquisition System: Internal ................................................ 13

Figure 12. LACM: User Interface ....................................................................................... 14

Figure 13. LACM: Internal View ........................................................................................ 14

Figure 14. MIP GPS and IMU Interface .............................................................................. 16

Figure 15. LabVIEW Serial Port Setup ............................................................................... 17

Figure 16. LabVIEW Tablet GUI: Laser Altitude ............................................................... 17

Figure 17. Theodolite Video Output .................................................................................... 19

Figure 18. Theodolite App Viewing Box ............................................................................ 20

Figure 19. Brunton Lensatic Compass ................................................................................. 20

Figure 20. Valkaria Airport Layout and Test Position ........................................................ 21

Figure 21. Laser Calibration Data ....................................................................................... 25

Figure 22. Measurement Error vs. Distance ........................................................................ 26

Figure 23. Takeoff Run 1 ..................................................................................................... 30





Figure 28. Landing Run 1 .................................................................................................... 36





Figure 33. Aircraft GPS Position ......................................................................................... 41

Figure 34. Altitude Waveform Processing .......................................................................... 64

Figure 35. Data Collection Loop ......................................................................................... 64

Figure 36. Data Recording Loop ......................................................................................... 65

Figure 37. Warrior II Weight and Balance [9] ..................................................................... 68

Figure 38. Current vs. Volts ................................................................................................ 69

Figure 39. Resistance vs. Volts ............................................................................................ 70

vii

Figure 40. Power vs. Volts .................................................................................................. 70

viii

List of Tables

Table 1. Weather Data April 5, 2017 [12] ........................................................................... 27

Table 2. Takeoff Distances .................................................................................................. 28

Table 3. Landing Data ......................................................................................................... 35

Table 4. Altitude Determination Equipment Accuracies [1] [10] [13] [6] .......................... 42

Table 5. Electrical Testing Results ...................................................................................... 69

Table 6. Laser Ground Calibration Test Data. ..................................................................... 71

Table 7. Takeoff 3 Data ....................................................................................................... 72

Table 8. Landing 3 Data ...................................................................................................... 79

ix

List of Equations

Equation 1. Corrected Laser Altitude .................................................................................. 24

Equation 2. Theodolite Observed Height Computation ....................................................... 24

x

List of Abbreviations

AC Advisory Circular

AGL Above Ground Level

CFR Code of Federal Regulations

CG Center of Gravity

DAS Data Acquisition System

DGPS Differential GPS

FAA Federal Aviation Administration

FIT Florida Institute of Technology

FT Feet

GPS Global Positioning System

IMU Inertial Measurement Unit

KIAS Knots Indicated Airspeed

LACM Laser Altimeter Control Module

MPH Miles Per Hour

POH Pilot Operating Handbook

VFR Visual Flight Rules

xi

List of Symbols HCorrected Corrected AGL Altitude

H Uncorrected Laser Altitude

H0 Laser Slant Height to Datum

θ Aircraft Pitch Angle

θ0 Installed Instrument Pitch Angle

δ Azimuth Angle

δ0 Perpendicular Azimuth Angle from Observation Point

φ Aircraft Roll Angle

φ0 Installed Instrument Roll Angle

X Horizontal Distance between Observation Point and Runway

Centerline

SA Air Distance

SG Ground Distance

DV Vertical Position Accuracy

DH Horizontal Position Accuracy

xii

Acknowledgements

The following academic pursuit would not have been possible without the support

of Dr. Kish, Dr. Kimberlin, and the Flight Test Department at Florida Tech. They

have provided an environment to learn and experiment with flight test engineering

that is paralleled by very few universities around the world. I am truly grateful for

the opportunities offered by this program and I look forward to observing growth

and development in the flight test program at Florida Tech. It is the start of a new

world class program in flight test engineering.

I would also like to thank the Florida Tech Machine Shop, Florida Tech

Makerspace, and the Harris Design Center for their equipment support and lab

space during the development phase of this endeavor. These resources proved

invaluable for this research and I am extremely grateful.

I would like to thank the airport managers of Valkaria Airport for their support

during planning and testing of this exercise. In addition, I would like to extend my

sincere thanks to Dr. Stephen Cusick for donating his time to be a member of this

thesis committee. I would like to thank FIT Aviation, LLC. Maintenance Hangar

for their expeditious work to ensure the aircraft was suitable for testing. Lastly, I

would like to thank the ground observers for their hours of volunteered time to this

research.

xiii

Dedication

I would like to dedicate this work to my family and friends, without whom the

world would not shine as bright. To my parents, Terry and Clare, thank you for

your unending love and support through all these years. You taught me the values

of a strong work ethic and patience required to chase my dreams. To my uncle,

Kevin, thank you for teaching me hands on skills and technical knowledge,

inspiring me from a young age. To the rest of my family and friends, thank you for

supporting my endeavors and for making the last five years, some of the most

memorable years of my life. I look forward to making more memories with you all!

1

Chapter 1 Introduction

1.1 Background

The measurement of takeoff and landing distance of an aircraft is required for

aircraft certification in the United States under Title 14 of the Code of Federal

Regulations [2]. 14 CFR Part 23 is applicable to general aviation aircraft with nine

or less passengers and have a maximum certificated takeoff weight not to exceed

12,500 lbs., or commuter category aircraft weighing 19,000 lbs. or less and capable

of holding no more than 19 passengers. Takeoff and landing distance measurement

are critical demonstrated tests due to their pertinence in safe and successful

operation of the aircraft. Information furnished to the pilot through a Pilot’s

Operating Handbook (POH) includes minimum takeoff and landing distance,

including ground roll and distance to clear a 50 foot obstacle for all altitude,

temperature, weight, and wind conditions within the operational limitations of the

aircraft. The regulations set forth in 14 CFR 23.53 Takeoff Performance define the

required aircraft configuration to conduct takeoff distance testing and are listed in

Figure 1.

2

Figure 1. 14 CFR Part 23.53 Takeoff Performance [3]

14 CFR 23.75 Landing Distance sets forth the required conditions to demonstrate

landing distance over a 50 foot obstacle. A steady 3° approach to 50 feet in landing

configuration is required, followed by a maintained final configuration throughout

the maneuver. Specific information in 14 CFR 23.75 is listed in Figure 2.

§23.53 Takeoff performance.

(a) For normal, utility, and acrobatic category airplanes, the takeoff

distance must be determined in accordance with paragraph (b) of this

section, using speeds determined in accordance with §23.51 (a) and (b).

(b) For normal, utility, and acrobatic category airplanes, the distance

required to takeoff and climb to a height of 50 feet above the takeoff surface

must be determined for each weight, altitude, and temperature within the

operational limits established for takeoff with—

(1) Takeoff power on each engine;

(2) Wing flaps in the takeoff position(s); and

(3) Landing gear extended.

(c) For normal, utility, and acrobatic category multiengine jets of more

than 6,000 pounds maximum weight and commuter category airplanes,

takeoff performance, as required by §§23.55 through 23.59, must be

determined with the operating engine(s) within approved operating

limitations.

3

Figure 2. 14 CFR Part 23.75 Landing Distance [3]

Additional information on suggested methods for takeoff and landing distance are

provided by the Federal Aviation Administration (FAA) through Advisory Circular

(AC) 23-8C, titled “Flight Test Guide for Certification of Part 23 Aircraft”. Per AC

23-8C, the takeoff distance can be determined by either a continuous maneuver or

the sum of the acceleration and climb segments independently gathered. Landing

distance over a 50 foot obstacle is a continuous maneuver conducted at the

maximum landing weight. Both takeoff and landing measurement have

§23.75 Landing distance.

The horizontal distance necessary to land and come to a complete stop

from a point 50 feet above the landing surface must be determined, for

standard temperatures at each weight and altitude within the operational

limits established for landing, as follows:

(a) A steady approach at not less than VREF, determined in accordance

with §23.73 (a), (b), or (c), as appropriate, must be maintained down to

the 50 foot height and—

(1) The steady approach must be at a gradient of descent not greater

than 5.2 percent (3 degrees) down to the 50-foot height.

(2) In addition, an applicant may demonstrate by tests that a maximum

steady approach gradient steeper than 5.2 percent, down to the 50-foot

height, is safe. The gradient must be established as an operating limitation

and the information necessary to display the gradient must be available to

the pilot by an appropriate instrument.

(b) A constant configuration must be maintained throughout the

maneuver.

(c) The landing must be made without excessive vertical acceleration or

tendency to bounce, nose over, ground loop, porpoise, or water loop.

4

recommended procedures which include the collection of horizontal and vertical

path of the aircraft by either a data acquisition unit or human observers. In addition,

takeoff measurement instrumentation may include a device to measure height

above the runway, described as highly desirable in AC 23-8C. Takeoff distance and

landing distance must be corrected for wind conditions, nonstandard atmospheric

conditions, runway slope, and nonstandard weights.

The recommended procedure for gathering takeoff and landing distance data is to

conduct at least six takeoffs to 50 feet and six landings to a full stop to provide a

statistical sampling for reduction. The critical weight and center of gravity (CG)

must be applied during this testing, often the forward CG limitation at maximum

gross weight, or maximum landing weight for landing distance data. Appendix A

and Appendix B include the applicable sections of AC 23-8C with respect to

takeoff and landing distance measurement and evaluation.

Takeoff and landing distances are divided into two segments, ground distance and

air distance. Ground distance, SG, is the portion of a takeoff or landing during

which the aircraft is in contact with the ground. During takeoff this includes the

distance from when the aircraft begins motion to the moment the landing gear lift

off the runway surface. The air distance , SA, is the ground distance from the time

the landing gear lift off the surface until the aircraft clears a given obstacle height.

In aircraft certified under Part 23, this height over an obstacle is defined as 50 feet.

5

Figure 3. Takeoff Distance [4]

During landing operations, the air distance is the ground distance covered by the

aircraft from a height 50 feet above the landing surface until touchdown, including

the landing flare. The ground distance during landing is defined by the distance

required from the moment the aircraft touches down on the landing surface until

full stop is achieved. During certification testing, the landing is conducted using

maximum braking effort.

Figure 4. Landing Distance [4]

6

The analytical calculation of takeoff and landing distances is difficult due to the

constantly changing variables throughout the maneuver. As the aircraft begins to

accelerate, wheels are subject to rolling friction from their interaction with the

ground and the weight of the aircraft. As the aircraft velocity increases, lift and

aerodynamic drag are produced, reducing the weight on the wheels and decreasing

the excess power. As the aircraft is rotated, angle of attack increases, increasing

aerodynamic drag while the rolling friction becomes zero. In the rotation, the

aircraft is performing a maneuver at greater than 1G, which increases loading on

the wings. The aircraft is subject to the transition from flight in ground effect to

flight out of ground effect, increasing drag while the aircraft is climbing toward

obstacle height. During the landing, the variables involved are similar with the

addition of braking force after touchdown to decelerate the aircraft to a full stop.

The variation of these variables during a takeoff are shown below in figure 5.

Figure 5. Variation of Force with Distance [4]

While analytical models can predict the theoretical takeoff and landing distances of

an aircraft, the addition of human variables, such as pilot input requires flight

testing to verify the actual takeoff and landing distances and to show compliance

with applicable FAA regulations.

7

1.2 Motivation

The measurement of takeoff and landing distance is often a costly test for a flight

test certification program due to the instrumentation required, number of observers,

and maneuvers required. While the FAA suggests a minimum of six takeoff and six

landing maneuvers, more are often conducted due to variability in the conditions

during a given maneuver. Wind, runway slope, aircraft weight, air density, air

temperature, pilot technique, and runway surface condition all add complexity to

the collection and reduction of accurate takeoff and landing distances [4].

Cinetheodolites and differential GPS are currently used during most takeoff and

landing certification efforts today. A cinetheodolite is a tool which collects video

imagery and position information from a known ground position to determine

horizontal and vertical position over the ground. The system consists of bearings

which measure azimuth and elevation angles from the ground system to the target

[5]. Differential GPS (DGPS) is a global positioning system augmented with

ground stations to increase overall system accuracy to 1.5 meters, with a vertical

accuracy of 3.4 meters [6]. The DGPS requires a specialized receiver to be installed

in the test vehicle and a ground station within line of sight of the test area.

According to Kenneth Germann, Israel Aircraft Industries performed an evaluation

of DGPS against the FAA approved Del- Norte Transponder System, which

demonstrated that DGPS, with improved vertical accuracy, could be used to certify

takeoff and landing performance. [7] The associated costs of these systems are high

due to equipment costs and, in the case of cinetheodolites, location availability [7].

These methods also suffer from increased errors in vertical accuracy when

subjected to accelerated maneuvers such as takeoff and landing. While these

methods are acceptable to satisfy the requirements of 14CFR 23.53 and 14 CFR

23.75, direct measurement of aircraft altitude above the ground would provide

greater vertical accuracy. Current methods of direct measurement of aircraft

8

altitude above ground level include calibrated barometric altimeters, radar

altimeters, and laser altimeters. Sensitive barometric altimeters require calibration

prior to flight test and are prone to fluctuations in atmospheric pressure that may

occur during a flight test. Radar and laser altimeters measure the time of a pulse of

electromagnetic energy transmitted from the module to reflect off the surface and

return. While radar altimeters provide enhanced cloud penetration and range, they

require greater power at a higher cost than a laser altimeter. By enhancing GPS

position with altitude measurement from the aircraft, the regulations on takeoff and

landing distance can be satisfied while reducing the overall cost of data collection

and reduction.

1.3 Objectives

An examination of current flight test evaluation methods for the determination of

takeoff and landing distance measurement demonstrated an attempt to move away

from ground stations where possible to reduce cost in a lengthy development and

certification process. Through improvements in GPS coverage and accuracy as the

GPS satellite constellation is expanded and improved [8], the need for independent

horizontal measurements has been reduced. However, affordable direct vertical

measurement with similar or better resolution than DGPS, specifically through the

use of laser altimetry, have not breached the civil flight test industry. Since takeoff

and landing testing is normally conducted on dry, paved runways in visual flight

rules (VFR) conditions at low altitudes, the use of a laser altimeter to collect above

ground level (AGL) altitude is a feasible alternative, when coupled with GPS, to

current ground based data collection methods to satisfy FAA regulations in

accordance with 14 CFR 23.53 and 14 CFR 23.75.

The objectives of the research conducted at Florida Institute of Technology were to

determine a method to integrate a laser altimeter with an existing Flight Test Data

9

Acquisition System (DAS) and evaluate system performance as compared to

traditional ground based methods of takeoff and landing distance measurement.

The main objectives of instrument integration with the DAS were to power the

laser altimeter solely through the DAS, independent of the test aircraft electrical

subsystem and to integrate the instrument into the DAS LabVIEW software for

synchronized data collection with GPS position and aircraft pitch and roll angles.

The primary mission of the flight evaluation was to compare direct altitude and

position data collection with ground based measurements to evaluate installed

system performance against traditional methods for determining takeoff and

landing distances. The ultimate goal of this research was to explore a cost effective

means of evaluating takeoff and landing distance for continued flight test education

at Florida Institute of Technology.

10

Chapter 2 Test Methods

2.1 Test Aircraft

Data collection was conducted using a PA28-161 Warrior II aircraft manufactured

by Piper Aircraft Inc. in Vero Beach, Florida. The aircraft was a single engine, four

place, low wing aircraft with a maximum gross weight of 2440 pounds and a center

of gravity (CG) range of 83 to 93 inches aft of datum. The landing gear was a fixed

tricycle configuration with nose wheel steering and differential brakes on the main

landing gear. The aircraft was powered by a Lycoming O-320 engine capable of

producing 160 horsepower at 2700 RPM. The aircraft was equipped with manual

plain flaps which, in the landing configuration, extended to 40° [9]. Pictured below

is the test aircraft, N618FT, on the ramp of FIT Aviation, LLC at Melbourne

International Airport (KMLB).

Figure 6. Test Aircraft: Piper Warrior II N618FT

All aircraft limitations during testing were per the pilot’s operating handbook

(POH) (VB-1180) and all testing was conducted within the weight and CG

limitations of the aircraft. The aircraft had an experimental type certificate for the

11

purpose of Research and Development. Modifications to the aircraft for takeoff and

landing distance testing included installing a new inspection plate with a modified

aperture to accommodate the AgLaser module and a wire installed from the

AgLaser module through the wing into the cabin. The replaced inspection plate is

45 inches outboard of the aircraft centerline forward of the main spar, inboard of

the right main landing gear. The installed angles of the altimeter were 4° Pitch Up

and 6° Roll Left due to the airfoil shape and dihedral of the wing. These were

factored in to data reduction during post flight analysis. Images of installations are

included below.

Figure 8. AG Laser Installation on Test Aircraft Figure 7. RS-232 Signal Cable Installed in Right Wing

12

2.2 Data Collection System

The AgLaser Module was a GaAs Laser Diode infrared laser distance finder which

operated at a wavelength of 905 nm. The passive range of the instrument was 150

m with an accuracy of 5 cm. The measurements were taken at a 9 Hz sampling rate.

The AgLaser had an operating temperature range of -10°C to 60°C and was water

resistant to IP67 standards. The casing was made of black anodized aluminum and

was a Class 1 eye safe system. The instrument measured 108 mm x 64 mm x 41

mm with a weight of 328 g, pictured in Figure 9. The communications interface

was RS-232 serial communication with transmit, receive, signal ground, positive

power, and negative power [1].

Figure 9. AgLaser: Laser Altimeter Module

The Florida Tech Flight Test Data Acquisition System provided GPS, Inertial

Measurement Unit (IMU), and data recording capabilities through LabVIEW. The

DAS used an Intel NUC PC with 120 GB MLC internal solid state drive and a NI

USB-6212 M Series Screw Terminal DAQ. IMU and GPS data was provided by a

LORD Microstrain 3DM-GX3-35 with GPS. A Wi-Fi router transmitted collected

data to a tablet onboard the aircraft for real time parameter monitoring. The Florida

13

Tech DAS is pictured in Figures 10 and 11. The DAS was modified by adding an

auxiliary power connector at the screw terminal between the batteries and voltage

regulator. This modification enabled the laser to use DAS power for test operations.

Figure 10. Florida Tech Data Acquisition System

Figure 11. Florida Tech Data Acquisition System: Internal

14

An external Laser Altimeter Control Module (LACM) was designed to regulate

power to the laser altimeter and provide a connection point for the wires between

the DAS and the AgLaser altimeter module. The power wires from the DAS to the

laser altimeter and RS-232 wiring to the laser altimeter flow into the LACM, while

a USB connection for the DAS flows out of the LACM. The LACM contains a

single NKK S821 2 pole switch and a single one amp fuse. The fuse was designed

to protect the laser module against battery surges in excess of its operational

capacity. The switch regulated power to the altimeter and was used to cut power to

the system without the manual separation of the auxiliary power wire. Data transfer

was accomplished in the LACM through a DB-9 connection and DB-9 to USB

converter by Gearmo. The laser altimeter was continuously transmitting data while

power was ON. An internal image of the LACM can be seen below.

The software was LabVIEW based with a parameter collection loop gathering data

from the IMU and GPS on one serial input, COM3, while collecting laser altimeter

data from a second serial input, COM4. COM3 operated at 115200 Baud and set

the collection size to the bytes at port. COM4 operated at 9600 Baud, per the

AgLaser Technical Manual [1], and read 10 bytes, or one distance measurement,

Figure 12. LACM: User Interface Figure 13. LACM: Internal View

15

per loop. The result of the laser altimeter data was a string terminated by the

termination character, \n. The resulting string was fed through a spreadsheet to

array function to produce a 1-D array of altimeter measurements. This was then

processed through an array to element function to produce a 32 bit single element

which could be read in a waveform diagram. The subsequent waveform diagram

was used as the value reference for a shared variable, known as “laser alt” and a

local variable used to record the values with time in a .csv file. The variable “laser

alt” was transformed into an engineering string for processing into a text file with

other flight information, including GPS coordinates, GPS velocity, aircraft angles,

and axial accelerations. LabVIEW software modifications are included in Appendix

C LabVIEW Code Modifications.

DAS Setup Procedure:

The following procedure was required to turn on the DAS, initialize the laser

altimeter, and begin data collection.

1. Connect monitor through HDMI port on DAS exterior, also connect LACM

USB and a mouse to the DAS.

2. Connect LACM auxiliary power cord to the auxiliary power output on the

DAS.

3. Install two 20 V DeWalt Lithium Ion Batteries on DAS.

4. Depress the “System Power” button on the top surface of the DAS. The

green ring around the button will illuminate and the DAS will begin startup.

5. Once the DAS starts up, it will begin Rev14.vi. Close this file.

6. Click the MIP icon on the taskbar and right click the IMU/GPS device.

Under device settings change the gravity correction factor to 1 second.

Return to the MIP main page and right click the device. Select 3D attitude

16

and realign UP and North. Return to the gravity correction factor and set to

1000 seconds. This step reduces drift in the angles of the IMU. The

interface is displayed below in Figure 14.

Figure 14. MIP GPS and IMU Interface

7. Turn LACM ON. Open Rev14_ALT_1.vi.

8. Under tools, open Measurement and Automation Explorer. Under devices,

select COM4 and open a VISA Test Panel. Test that the instrument is able

to receive 10 bytes with 9600 Baud and select “Read” The output is the

distance from the laser module to the ground in meters. Close the VISA

Test Panel.

9. Ensure Baud and COM are 9600 and COM4 respectively for the upper

serial input prior to running. The Serial Inputs are shown in Figure 15.

17

Figure 15. LabVIEW Serial Port Setup

10. Run the code and check for proper laser altimeter measurement. The

displays have a slight lag due to the increased processing power required for

the second serial connection.

11. Turn on Tablet and ensure device is connected to network “FTE_Plane”.

12. Open LabVIEW Monitor and select play. Ensure variables are displaying as

expected. The flight test tablet display is shown below in Figure 16.

Figure 16. LabVIEW Tablet GUI: Laser Altitude

13. Disconnect monitor and mouse from DAS.

14. Select Record when data is to be recorded in a .csv file.

15. To turn DAS off, depress “GPS Fix” button until all lights flash.

16. Turn OFF LACM. Then, depress “System Power”

18

2.3 Ground Testing

Prior to flight testing, a series of ground tests were required to determine the

compatibility of the AgLaser system and the Florida Tech DAS. Two main

subsystems were integrated during these tests, power and serial communications.

The DAS is powered by two DeWalt Lithium Ion batteries capable of producing 20

volts with a capacitance of 4.0 Amp Hours each. The AgLaser altimeter required a

voltage between 10 and 28 volts of DC power. Incremental voltage measurements

of internal resistance were conducted from 10- 24 V using a laboratory DC power

supply. The results, shown in Appendix F, indicated that the AgLaser had an

estimated power requirement of 2.8 Watts, within the available power for the DAS

in its current configuration. Based on this testing, an auxiliary power connection

was added to the DAS through an existing hole near the right battery. The wires

were connected to the DAS via a screw module prior to the voltage regulator,

which led to the DAS computer power supply.

Complete system ground testing was conducted at Florida Institute of Technology

prior to flight testing. Cones were set up at intervals of 1 foot from 0 to 10 feet and

from 10 feet to 50 feet in 5 foot increments from a vertical wall. The AgLaser was

positioned horizontally above each cone, and the indicated distance was recorded.

The results of this calibration can be seen in Chapter 3.

A genuine Piper Aircraft inspection plate was modified to allow mounting of the

AgLaser through its original mount, an inspection plate designed for an Air Tractor

aircraft. The original plate was trimmed to fit within the central screws of the Piper

inspection plate. A rectangular plate was cut from the center of the Piper inspection

plate to accommodate the mounting bracket and 3/16th inch holes were drilled to

fasten the AgLaser plate to the Piper inspection Plate. The final product can be seen

in Figure 7. A fitting check of the AgLaser altimeter and its inspection plate mount

19

was conducted. After conclusion of these ground tests, the system was assessed as

flight ready by the author.

2.4 Data Collection Procedure

The collection of takeoff and landing distance measurement parameters from both

ground based and flight based methods was the primary test objective. The

experimental layout at Valkaria Regional Airport (X59) can be seen in Figure 19.

Valkaria Airport is located 10 nm south of Melbourne International Airport. X59

has two runways, 10-28 and 14-32. Both runways are paved, 4000 feet x 75 feet

with PAPI visual approach indicators. Runway 14 was used for all takeoff and

landing flight tests. Required ground instrumentation is listed and described below.

Theodolite App for iPhone: Published by Hunter Research and Technology,

provided video recording of elevation, azimuth, and GPS data from the iPhone 5S.

System accuracy for this test was 0.1° in Elevation, 10° in Azimuth and 17 feet for

GPS position [10]. A screen capture of recorded data is shown in Figure 17. A

viewing box was also made to accommodate the iPhone 5S and increase recording

stability during data collection. The viewing box is seen in Figure 18.

Figure 17. Theodolite Video Output

20

Figure 18. Theodolite App Viewing Box

Brunton Lensatic Compass: One compass was used in this experiment by the

secondary ground observer. The compass was liquid filled to damp oscillations in

azimuth and had a stated 2° magnetic resolution.

Figure 19. Brunton Lensatic Compass

The ground setup began with determining the test runway. The test runway was

determined by traffic and wind conditions at the beginning of the test. Cones were

placed off the side of the runway at 100 ft. intervals from the beginning of the

21

aiming point markers to the end of the aiming point markers for the opposing

runway. At Valkaria Airport, this is approximately 2000 feet. The observers, both

compass and theodolite, were located 308 feet from the runway centerline adjacent

to taxiway A, as shown in Figure 20.

Figure 20. Valkaria Airport Layout and Test Position

After DAS initialization, the aircraft was taxied to the upper edge of the runway

number markings and held in position while maximum power was applied. The

flight test engineer began a record and the ground coordinator collected heading to

the aircraft and began tracking the aircraft through the theodolite. After brake

release, the aircraft accelerated through the marked zone and the pilot began a

rotation at 55 KIAS [9]. Observers noted their heading to the aircraft when the

22

main landing gear left the ground and captured theodolite video for each takeoff

and landing, using the base of the aircraft as the reference marker.

A level flyby of the aircraft over the centerline of the runway at 50 ft. indicated by

the aircraft barometric altimeter was conducted once prior to the first landing. The

theodolite operator recorded the flyby for post flight processing.

The pilot then entered a 3° approach in landing configuration, the flight test

engineer indicated 50 ft. from the laser altimeter and the heading to the aircraft was

recorded. The observers indicated their heading to the aircraft when its main

landing gear touched down, and again when the aircraft came to a complete stop.

The theodolite recorded the landing for post flight processing. The aircraft was then

taxied back to the runway threshold and the takeoff and landing sequence was

repeated.

The collected data included:

1. GPS position of each ground based observer

2. Magnetic Heading for each event from each observer

3. Theodolite video recording for each maneuver.

4. Time

5. DAS GPS Coordinates

6. Laser Altitude (feet)

7. Aircraft Pitch Angle

8. Aircraft Roll Angle

9. Aircraft GPS ground velocity

All DAS data were recorded at 4 Hz.

23

All testing was performed on a dry, paved runway in VFR conditions with

winds within the crosswind limitations of the aircraft in accordance with the

POH. This was critical to reduce the number of variables and their influence on

the collected data.

24

2.5 Data reduction

The collected data were reduced to retrieve corrected laser altitude and distance, in

feet, from GPS coordinates. The raw laser altitude was corrected to account for

aircraft orientation, distance of instrument from aircraft centerline, installed angle

from ground, and height above the reference plane, set to the base of the landing

gear. The laser correction equation is shown below.

Equation 1. Corrected Laser Altitude

𝐻𝐶𝑜𝑟𝑟𝑒𝑐𝑡𝑒𝑑 = (𝐻 ∗ cos(𝜃 + 𝜃0)) ∗ cos(𝜑 + 𝜑0) − 3.75 ∗ sin(𝜑) − 𝐻0

The distance between GPS coordinates was calculated to retrieve the distance in

feet. The equations relied on the WGS-84 model of the Earth and assumed a flat

Earth due to the relatively small length being measured. The resulting error of this

method with the stated assumptions is approximately 16 inches per mile [11]. The

equations used are shown in Appendix H.

The theodolite observed height was calculated by determining the azimuth and

elevation difference from the observed point and using trigonometry to find height

through the following equations. The resulting height was then corrected for

observed elevation of the surface and target difference of the sighting reticle from

the aircraft base to the reference datum at the base of the landing gear. These values

were compared to the recorded height at the same location to determine difference

between observed and recorded altitude values. Observed height computation

equation is shown below.

Equation 2. Theodolite Observed Height Computation

𝐻 = (𝑋 ∗ tan(𝜃)

cos(𝛿 − 𝛿0)) − 𝐻0 − 𝐻𝑒𝑙

25

Chapter 3 Results

3.1 Ground Test Overview

Ground testing, including electrical range testing and laser calibration were

conducted at Florida Institute of Technology. The electrical testing provided a

baseline power requirement for the laser altimeter module for integration into the

Florida Tech DAS. The measured power requirement was 2.8 Watts, well within

the available power of the DAS power supply. See Appendix F for additional

ground test results. Laser calibration was conducted prior to flight testing in

accordance with test matrix 17-001 in Appendix D. Shown below are the results of

the laser calibration test, including error indicating the maximum deviation was 0.7

feet, shown in Figure 22.

Figure 21. Laser Calibration Data

0

10

20

30

40

50

60

0 10 20 30 40 50 60

Ob

serv

ed D

ista

nce

(fe

et)

Measured Distance (feet)

Laser Calibration

Recorded Distance (ft.) Standard

26

Figure 22. Measurement Error vs. Distance

27

3.2 Flight Overview

All flights were conducted at Valkaria Airport (X59). The testing was conducted by

flight test pilot Ralph Kimberlin and flight test engineers Christopher Kennedy and

Brian Kish. Ground measurements were conducted by Christopher Kennedy and

Warren Pittore.

The following table shows the corrected laser altitude with respect to observed

altitude from the theodolite. All headings are magnetic heading with local variation

included. Wind conditions on April 5, 2017 at Valkaria Airport are shown below.

Table 1. Weather Data April 5, 2017 [12]

Time Temperature (°F) Pressure (in Hg) Wind

11:53 AM 87.1 30.00 S at 12.7 mph

12:53 PM 89.1 29.98 SW at 11.5 mph

The experiment provided five takeoff and five landing points with the laser

altimeter installed. The following charts show aircraft corrected laser altitude,

ground velocity, and ground distance with respect to elapsed time.

28

3.3 Takeoff Distance

Table 2. Takeoff Distances

The observed and recorded takeoff parameters are displayed above. The altitude

comparison was the primary evaluation for these tests. During takeoff testing, the

maximum difference between observed aircraft height and recorded height from the

AgLaser was 3.87 feet with an average difference of 1.53 feet. This accuracy fell

within the accuracy of DGPS vertical distance measurement. Takeoffs were within

100 feet of published takeoff distances in the POH.

Takeoff Run 1 was conducted prior to the observers reaching their targets

observation point. However, altitude from the corrected point demonstrated good

trending with time. The difference in observed and recorded height can be

accounted for by instability of the theodolite during the first run. Several GPS lags

were noted during this maneuver, indicated by the flat points in distance and

velocity, while the altitude continued to operate nominally.

Takeoff 2 was conducted with observers at the observation point and the theodolite

stabilized on the target. The aircraft transited the observation point and climbed

through 50 feet. The GPS position suffered a similar lag to Takeoff 1, while

altitude continued to increase as anticipated.

Maneuver Laser

Height (ft.)

Observed

Height (ft.)

Difference (ft.) SG (ft.) SA

(ft.)

Takeoff 1 51.03 47.16 3.87 - 550

Takeoff 2 51.84 50.02 1.82 - -

Takeoff 3 49.40 49.36 0.04 820 665

Takeoff 4 51.60 50.99 0.61 831 824

Takeoff 5 51.33 50.04 1.29 - 777

29

Takeoff 3 was the first takeoff which indicated good GPS data with minimal signal

delay. An acceleration of the aircraft with a continuous increase in takeoff distance

was observed, as was the increase in altitude after aircraft lift off. The aircraft then

demonstrated a constant ground speed as it climbed through 50 feet.

Takeoff 4 produced a similar result as Takeoff 3. All measured parameters had

good trending with time with minimal GPS lagging. Altitude performed as

expected and had good correlation to recorded theodolite data.

Takeoff 5 experienced good trending of GPS data, but had a single anomalous

spike during the air phase of the takeoff maneuver. A strong correlation was

observed between laser altitude and observed theodolite altitude.

30

Figure 23. Takeoff Run 1

0

10

20

30

40

50

60

70

80

90

100

0

200

400

600

800

1000

1200

1400

60 65 70 75 80 85 90

Alt

itu

de

(ft)

, Vel

oci

ty (

MP

H)

Dis

tan

ce (

ft)

Time (seconds)

Takeoff Run 1

Distance

Velocity

Altitude

31


0

10

20

30

40

50

60

70

80

0

200

400

600

800

1000

1200

1400

930 932 934 936 938 940 942 944

Alt

itu

de

(ft)

, Vel

oci

ty (

MP

H)

Dis

tan

ce (

ft)

Time (seconds)

Takeoff Run 2

Distance

Velocity

Altitude

32


0

10

20

30

40

50

60

70

80

90

0

500

1000

1500

2000

2500

3000

3500

4000

4500

5000

1490 1492 1494 1496 1498 1500 1502 1504 1506 1508 1510

Alt

itu

de

(ft)

, Vel

oci

ty (

MP

H)

Dis

tan

ce (

ft)

Time ( seconds)

Takeoff Run 3

Distance

Height

Velocity

33


0

10

20

30

40

50

60

70

80

90

0

500

1000

1500

2000

2500

3000

3500

4000

2060 2065 2070 2075 2080 2085 2090

Alt

itu

de

(ft)

, Vel

oci

ty (

MP

H)

Dis

tan

ce (

ft)

Time ( seconds)

Takeoff Run 4

Distance

Height

Velocity

34


0

10

20

30

40

50

60

70

80

90

0

200

400

600

800

1000

1200

1400

2680 2682 2684 2686 2688 2690 2692 2694 2696 2698 2700

Alt

itu

de

(ft)

, Vel

oci

ty (

MP

H)

Dis

tan

ce (

ft)

Time ( seconds)

Takeoff Run 5

Distance

Height

Velocity

35

3.4 Landing Distance

Table 3. Landing Data

Maneuver Laser Height (ft.) SG (ft.) SA (ft.)

Landing 1 51.02 1355 1836

Landing 2 50.86 1229 2179

Landing 3 51.41 899 1933

Landing 4 50.69 1060 1731

Landing 5 50.32 2050 1175

Five landings were conducted at Valkaria Airport. The table above shows the

corrected laser altitude of the aircraft and the air and ground distances for each

maneuver. Observed elevations were not calculated due to the high viewing angle

from the observation point to the point where the aircraft was 50 feet above the

surface. The observed elevations had excessive scattering due to small differences

at high angles outside the azimuth resolution of the theodolite while recording the

50 ft. points. The overall system operated as expected during landings, as shown in

the following figures.

Landing 1 through Landing 5 exhibited good correlation with GPS position and

velocity to the observed aircraft. The recorded altitude followed the expected trend

as the aircraft transitioned from the air to ground phases of the landing through the

flare. A slight balloon of the aircraft occurred in Landing 1 due to excess airspeed

during the flare. This is noted by the aircraft holding above the runway surface as

airspeed was bled off. While some scatter was evident above 100 feet in Landing 2

and Landing 4, altitude and GPS data were consistent with the maneuvers executed.

The landing maneuvers are shown in the following figures.

36

Figure 28. Landing Run 1

0

10

20

30

40

50

60

70

80

90

0

500

1000

1500

2000

2500

3000

3500

675 680 685 690 695 700 705 710 715 720 725 730

Alt

itu

de

(ft)

, Vel

oci

ty (

MP

H)

Dis

tan

ce (

ft)

Time ( seconds)

Landing Run 1

Distance

Height

Velocity

37


0

10

20

30

40

50

60

70

80

90

0

1000

2000

3000

4000

5000

6000

1210 1215 1220 1225 1230 1235 1240 1245 1250 1255 1260

Alt

itu

de

(ft)

, Vel

oci

ty (

MP

H)

Dis

tan

ce (

ft)

Time ( seconds)

Landing Run 2

Distance

Height

Velocity

38


0

10

20

30

40

50

60

70

80

90

0

1000

2000

3000

4000

5000

6000

1780 1785 1790 1795 1800 1805 1810 1815 1820 1825 1830

Alt

itu

de

(ft)

, Vel

oci

ty (

MP

H)

Dis

tan

ce (

ft)

Time ( seconds)

Landing Run 3

Distance

Height

Velocity

39


0

10

20

30

40

50

60

70

80

90

0

1000

2000

3000

4000

5000

6000

2370 2375 2380 2385 2390 2395 2400 2405 2410 2415 2420

Alt

itu

de

(ft)

, Vel

oci

ty (

MP

H)

Dis

tan

ce (

ft)

Time ( seconds)

Landing Run 4

Distance

Height

Velocity

40


0

10

20

30

40

50

60

70

80

90

0

500

1000

1500

2000

2500

3000

3500

4000

4500

2980 2985 2990 2995 3000 3005 3010 3015 3020

Alt

itu

de

(ft)

, Vel

oci

ty (

MP

H)

Dis

tan

ce (

ft)

Time ( seconds)

Landing Run 5

Distance

Height

Velocity

41

Below is the aircraft position with respect to the geographic area. The path over the

runway was used to validate the collected GPS position data. At the time of the

flight, accuracy was observed to be 17 feet. [13]

Figure 33. Aircraft GPS Position

42

Chapter 4 Analysis

4.1 Vertical Accuracy

The difference between the observed and recorded altitude data demonstrated

altitude accuracy within 4 feet with an average accuracy of 1.53 ft. The observed

data required distance from azimuth difference from the perpendicular observation

heading. Additional corrections to the observed data included removing the runway

observed elevation and target reticle correction from the base of the aircraft to the

wheel height, from which corrected laser altitude is obtained. The table below

shows the difference in accuracies of instrumentation and common methods of

measuring absolute altitude. A theodolite is capable of 0.01° in azimuth and

elevation, but vertical and horizontal accuracy are related to range to the target. The

AgLaser was capable of direct distance measurement accurate to 2.0 inches.

Table 4. Altitude Determination Equipment Accuracies [1] [10] [13] [6]

Azimuth Elevation DV DH

Theodolite 0.01° 0.01° - -

Theodolite App 10° 0.1° 10 ft. 17 ft.

AgLaser - - 2.0 in -

Brunton

Compass

2° - - -

DGPS - - 11 ft. 5 ft.

43

4.2 Takeoff Distance

The takeoff and landing data were correlated with theodolite video by the elapsed

time from the start of DAS recording. The distance measurements were calculated

using a formula to reduce GPS coordinates to distance referencing an initial start

point. The initial start point for all takeoff runs was the GPS coordinate

corresponding to the top of the runway numbers at runway centerline. Landing

distance was calculated using the difference of the 50 ft. point, touch down point,

and stop point. The reference position is a recorded point on the final approach

where the aircraft is approximately 100 ft. above ground level. Ground velocity

was calculated using the Pythagorean Theorem to determine overall ground

velocity from X and Y components recorded by the DAS GPS. Corrected laser

altitude in feet was corrected pitch and roll angles of the aircraft, the installed angle

from center of the laser aircraft, the distance of the laser from aircraft centerline,

and the apparent height of the laser above the reference plane of the wheels. These

were plotted against elapsed time to provide a time history of each maneuver.

While the overall system maintained time integrity as observed by the correlation

of the elapsed time and actual time of the test, the GPS data reduced system

sampling frequency to approximately 0.5 to 1 Hz during two takeoffs. The laser

altitude sampling continued to collect data at the specified 4 Hz sampling rate.

During all other maneuvers, collected GPS data remained dynamic with a

minimum sampling frequency of 2 Hz observed. The most likely cause for this

observation is a rise in computer processing power required for the parallel

processing of serial ports in the LabVIEW software. While the laser altimeter was

collecting 10 bits per collection cycle, the GPS IMU data required a larger data

stream to intake all parameters from the GPS IMU. The addition of the processing

steps to include the laser altimeter data led to an increase in processing power

during the data collection cycle, which could have reduced the DAS sampling to

44

accommodate for the reduction in processing power. The lagging in the system

described above had a direct effect on the recorded data as GPS data remained

stagnant while all other parameters were collected at the anticipated sampling rate.

45

4.3 Landing Distance

Observed landing distance demonstrated a large scatter due to theodolite azimuth

accuracy at increased distances. While most takeoffs reached 50 feet very close to

the observation point, the 50 ft. point during landing occurred toward the runway

threshold, approximately 2000 feet away. The observation point, being 308 feet

from the runway centerline, required large angular changes to observe the aircraft

at the runway threshold. As the magnetic compass could not determine elevation,

compass azimuth was not recorded for the 50 ft. points. The accuracy of the

theodolite azimuth at the time of the testing was ±10°. At the high azimuth

differential indicated by the recorded 50 ft. height, azimuth observation at the same

elevation rises rapidly, as seen by the variance of observed height from the

theodolite. However, the ground roll portion of the landing maneuvers were

measureable due to the magnetic compass and reduced azimuth differential from

the observation point.

46

4.4 Factors of Data Variation

The aircraft angles were affected by the IMU as a built in gravity correction factor

changed the reference gravity vector to account for average position during a

specified time period. During setup, the IMU correction factor is reduced to allow

the system to lock onto the gravity vector and orient UP and North. The gravity

correction factor is then reset to the longest time allowable to the system, 1000

seconds, to reduced correction and minimize drift during testing. However, as the

test extended past 1000 seconds, the IMU corrected to an averaged gravity position

at least three times during the test. This caused collected angles in roll to be

damped and indicate lower values than anticipated. While the pitch and roll angles

affected the corrected laser altitude, the changes of these angles were not large

during the observed periods over the runway. Because these corrections were small

angles, the error associated with IMU drift was effectively mitigated by correlating

observed aircraft behavior with recorded data.

The ground observations relied on a hand held measurement device, which

introduced variation in observation due to the steadiness of the operator. To reduce

induced variations on the theodolite, a supporting sighting box was constructed.

The box framed the iPhone 5S 9 inches from the observer’s eyes. This allowed the

observer to operate the theodolite in a manner similar to binoculars with an

improved grip to stabilize elevation angle. While the sighting box provided

improved stability for the theodolite, the observer lost the ability to quickly glance

away from the screen to acquire the target prior to focusing on the screen. This

resulted in an offset of azimuth and elevation while the target was acquired on

screen. This sighting error was minimized during the data collection periods and

occurred mostly at distant observations during final approach prior to the aircraft

reaching 50 feet above the runway.

47

When compared to classical measurement methods, such as the cinetheodolite and

differential GPS, the system accuracy of the Florida Tech DAS and the AgLaser

altimeter system is within the accuracy of DGPS and comparable to the accuracy of

a ground based theodolite system. By this comparison, the AgLaser with the

Florida Tech DAS provided a suitable means of measuring takeoff and landing data

for educational use and certification use under AC 23-8C.

48

Chapter 5 Conclusions

5.1 Conclusions

The AgLaser, coupled with the Florida Tech DAS, provided the ability to record

and measure takeoff and landing distance in accordance with AC 23-8C to satisfy

the requirements set forth in 14 CFR 23.53 and 14 CFR 23.75. The AgLaser,

coupled with the GPS data from the Florida Tech DAS, provided data within the

vertical error range of differential GPS, one of the current methods approved for

gathering takeoff and landing performance data for FAA certification. The overall

data acquisition system provided an in-flight observer with real time GPS and

altitude data while recording the parameters for post flight processing. The

collected data demonstrated good correlation to the ground based theodolite data,

validating the installed AgLaser system during both takeoff and landing maneuvers.

Through the use of laser altimetry to determine the absolute altitude of aircraft

during takeoff and landing performance testing, increased vertical accuracy can be

achieved. This increase in accuracy, coupled with the reduction in required ground

support, can reduce the overall cost of collecting takeoff and landing performance

data in support of aircraft development and certification test programs.

49

5.2 Recommendations for Future Testing

During the course of this research, improvement potential became apparent,

primarily in the optimization of the LabVIEW software in the DAS. The coding

must be optimized to reduce the delays responsible for occasional GPS parameter

lagging during test operations. By cataloguing the software and streamlining the

parallel serial port integration, an improved response and data resolution can be

achieved.

The setup process for the DAS required a monitor, mouse, and keyboard. The

addition of the laser altimeter system eliminates one available USB port, requiring

the operator to share a USB port between the mouse and keyboard. The

procurement of a 2 port USB hub would reduce the possibility of unintentionally

disconnecting the LACM from the DAS during setup. The monitor could also be

replaced by the display tablet through the Wi-Fi router from the DAS by using a 3rd

party application, eliminating the need for an independent mouse, keyboard, and

monitor.

The IMU gravity correction factor changes required during setup and through test

operation add complexity to the setup and immediate functionality of the DAS.

Future research should examine the ability to automate this process during internal

start up, similar to the initialization of the GoPro cameras upon system start. An

executable startup file featuring the gravity vector initialization prior to LabVIEW

setup and initialization could decrease startup time and eliminate the need for

interaction with the DAS beyond the depression of the “System Power” button.

Any future modifications to the box that may not be required during all phases of

testing should be made as modular devices, such as the LACM. This allows them to

be interchangeable and used only when required. This would reduce the power

50

loading on the DAS from external instrumentation and improve data collection

efficiency by reducing the number of unnecessary parameters.

During takeoff and landing distance measurement testing, ground observations with

the sighting box worked well to mitigate elevation error. However, a tripod base

could improve azimuth stability and reduce target variation while recording the

maneuvers. This would require a separate mount to adapt the device to the standard

tripod mount. Observer ability to track the target may be affected by increased glare

due to the removal of the sighting box. Additionally, a greater number of observers

capable of measuring heading or elevation would increase distance resolution as

more observers reduce the errors associated with a single observation point.

51

References

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http://www.wunderground.com/history/airport/KMLB/2017/4/5/DailyHisto

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=Florida&reqdb.zip=32919&reqdb.magic=4&reqdb.wmo=99999.

[Accessed 9 April 2017].

[2] J. D. Anderson, Aircraft Performance and Design, New York: McGraw

Hill, 1999.

[3] J. D. Anderson, Introduction to Flight, New York: McGraw-Hill, 2012.

[4] R. D. Kimberlin, Flight Testing of Fixed Wing Aircraft, Reston, Virginia:

American Institute of Aeronautics and Astronautics, 2003.

[5] D. Ward, T. Strganac and R. Niewoehner, Introduction to Flight Test

Engineering, Dubuque: Kendall/Hunt Publishing Company, 2006.

[6] R. E. McShea, Test and Evaluation of Aircraft Avionics and Weapons

Systems, Raleigh: SciTech Publishing, 2010.

[7] Federal Aviation Administration, "Advisory Circular 23-8C: Flight Test

Guide for Certification of Part 23 Airplanes," [Online]. Available:

https://www.faa.gov/documentLibrary/media/Advisory_Circular/AC%202

3-8C.pdf. [Accessed 17 March 2017].

[8] Federal Aviation Administration, Pilot's Handbook of Aeronautical

Knowledge, Oklahoma City: United States Department of Transportation,

2008.

[9] United States Navy, Aerodynamics for Naval Aviators, Washington DC:

US Government, 1960.

[10] AgLasers, LLC, Agricultural Laser Altimeter System, Rancho Cucamunga,

2007.

52

[11] Hunter Research and Technologies, "Theodolite for iPhone," [Online].

Available: http://hunter.pairsite.com/theodolite/. [Accessed 10 February

2017].

[12] Lodestone Wireless, "GPS Diagnostic," [Online]. Available:

http://www.lodestonewireless.com/gps-diagnostic.html. [Accessed 29

March 2017].

[13] United States Government, "GPS Accuracy," [Online]. Available:

http://www.gps.gov/systems/gps/performance/accuracy/. [Accessed 14

March 2017].

[14] K. P. Germann, "Flight Test Evaluation of a Differential Global

Positioning System Sensor in Runway Performance Testing," Mississippi

State University, 1998.

[15] United States Government, "Electronic Code of Federal Regulations,"

[Online]. Available: https://www.ecfr.gov/cgi-bin/text-

idx?tpl=/ecfrbrowse/Title14/14cfr23_main_02.tpl. [Accessed 14 March

2017].

[16] C. C.G. and D. Clay, "Site Specific Management Guidlines: The Earth

Model- Calculating Field Size and Distances between Points Using GPS

Coordinates," [Online]. Available:

www.ipni.net/publication/ssmg.nsf/0/.../$FILE/SSMG-11.pdf. [Accessed

26 March 2017].

[17] Piper Aircraft Corporation, Warrior II PA-28-161 Pilot Operating

Handbook, Vero Beach, 1982.

53

Appendix A Advisory Circular 23-8C, Subpart B, Section 2

57

Appendix B Advisory Circular 23-8C, Subpart B, Section 2

64

Appendix C LabVIEW Code for Laser Module Input

Figure 34. Altitude Waveform Processing

Figure 35. Data Collection Loop

65

Figure 36. Data Recording Loop

66

Appendix D Test Plans Test

Number Risk Test Title Regulations Test Objective

17-101 MEDIUM Laser Altimeter Evaluation and Takeoff and Landing Distance Measurement

14 CFR 23.53 14 CFR 23.75

AC 23-8C

To determine error within the installed laser altimeter system and to collect takeoff and

landing distance

Test Procedures Pass/Fail Criteria

1. Fly over runway centerline at 50 ft. AGL indicated. 2. Perform a normal takeoff from a full stop. 3. Perform a normal landing to a full stop. 4. During each takeoff and landing, record heading of

50 ft. point, wheel contact, and start or finish of the maneuver.

5. Repeat test points 02 and 03 until sufficient data has been collected.

The laser distance error must be within ±5 feet of the actual distance.

Test Point Flight Conditions Aircraft Configuration

Test Conditions

Airspeed(KIAS) Altitude(Feet AGL) Power Flaps

01 1.5 VS1(75) 50 PFLF 0° 50 foot indicated level flyby

02 Static 0 MCP 0° Perform Normal Takeoff

03 1.5VS1(75) 50 IDLE 40° Perform Normal Landing

67

Test Number Risk Test Title Regulations Test Objective

17-001 LOW Laser Altimeter Ground Calibration AC 23-8C To determine error within the uninstalled

laser altimeter

Test Procedures Pass/Fail Criteria

1. On a level surface, mount a target perpendicular to the surface.

2. In increments of 1 foot, record the indicated distance up to 10 feet.

3. From 10 ft. to 50 ft., record the indicated distance in 5 foot increments.

The laser distance error must be within ±1.0 feet of the actual distance.

Test Point Ground Conditions Test Conditions

Distance (feet)

01 1

02 2

03 3

04 4

05 5

06 6

07 7

08 8

09 9

10 10

11 15

12 20

13 25

14 30

15 35

16 40

17 45

18 50

68

Appendix E Weight and Balance

Figure 37. Warrior II Weight and Balance [9]

1100

1200

1300

1400

1500

1600

1700

1800

1900

2000

2100

2200

2300

2400

2500

2600

2700

82 84 86 88 90 92 94

Gro

ss W

eigh

t (p

ou

nd

s)

C.G. (Inches Aft of Datum)

N618FT Weight and Balance

69

Appendix F Ground Data

Table 5. Electrical Testing Results

Voltage (V) Current (mA) R (Ohms) Power (Watts)

10 258 38.75 2.58

12 216 55.55 2.59

15 175 85.71 2.62

18 150 120 2.7

21 134 156.71 2.81

24 123 195.12 2.95

27 115 234.78 3.10

Figure 38. Current vs. Volts

0

50

100

150

200

250

300

350

400

450

0 5 10 15 20 25 30

Cu

rren

t (m

A)

Volts (DC)

Current vs. Voltage

Display

Altimeter

Delta

70

Figure 39. Resistance vs. Volts

Figure 40. Power vs. Volts

0

50

100

150

200

250

0 5 10 15 20 25 30

Res

ista

nce

(O

hm

s)

Volts (DC)

Resistance vs. Voltage

Display

Altimeter

Delta

0

1

2

3

4

5

6

0 5 10 15 20 25 30

Po

wer

(W

)

Volts (DC)

Power vs, Voltage

Display

Altimeter

71

Table 6. Laser Ground Calibration Test Data.

Measured Distance (ft.) Recorded Distance (ft.) Difference (ft.)

1 1.25 0.25

2 2.25 0.25

3 3.18 0.18

4 4.16 0.16

5 5.38 0.38

6 6.07 0.07

7 7.40 0.40

8 8.20 0.20

9 9.35 0.35

10 10.30 0.30

15 15.45 0.45

20 20.28 0.28

25 25.30 0.30

30 30.38 0.38

35 35.60 0.60

40 40.45 0.45

45 45.70 0.70

50 50.40 0.40

72

Appendix G Flight Data Sample

Table 7. Takeoff 3 Data

Time (s) Roll Pitch Latitude Longitude Ground

Velocity (mph)

Laser Altitude (ft.)

Ground Distance (ft.) (deg) (deg) (deg) (deg)

1470.00 0.77 -0.31 27.9661 -80.5611 3.65 -0.19 0

1470.25 0.88 0.66 27.9661 -80.5611 3.65 -0.22 0

1470.50 1.13 -0.93 27.9661 -80.5611 3.65 -0.17 0

1470.75 1.13 -0.93 27.9661 -80.5611 3.65 -0.17 0

1471.00 1.13 -0.93 27.96609 -80.5611 3.15 -0.20 5

1471.25 1.04 -0.79 27.96609 -80.5611 3.15 -0.14 5

1471.50 1.23 -0.65 27.96608 -80.5611 2.10 -0.13 9

1471.75 0.96 0.99 27.96608 -80.5611 2.10 -0.15 9

1472.00 0.96 0.99 27.96608 -80.5611 1.85 -0.22 9

1472.25 0.96 0.99 27.96608 -80.5611 1.85 -0.18 9

1472.50 0.96 0.99 27.96608 -80.5611 1.77 -0.15 10

1472.75 1.35 1.04 27.96608 -80.5611 1.77 -0.12 10

1473.00 1.35 1.04 27.96608 -80.5611 1.77 -0.12 10

1473.25 1.35 1.04 27.96607 -80.561 1.79 -0.16 11

1473.50 1.01 1.00 27.96607 -80.561 1.74 -0.15 12

1473.75 1.01 1.00 27.96607 -80.561 1.74 -0.15 12

1474.00 1.01 1.00 27.96607 -80.561 1.74 -0.18 12

1474.25 1.31 1.09 27.96607 -80.561 1.74 -0.16 12

1474.50 1.31 1.09 27.96607 -80.561 1.67 -0.16 14

1474.75 1.31 1.09 27.96607 -80.561 1.67 -0.19 14

1475.00 1.31 1.09 27.96607 -80.561 1.67 -0.19 14

1475.25 1.15 -0.32 27.96607 -80.561 1.67 -0.13 14

1475.50 1.15 -0.32 27.96607 -80.561 1.67 -0.20 14

1475.75 1.06 0.09 27.96607 -80.561 1.67 -0.21 14

1476.00 1.06 0.09 27.96607 -80.561 1.67 -0.21 14

1476.25 1.06 0.09 27.96607 -80.561 1.67 -0.21 14

1476.50 1.06 0.09 27.96607 -80.561 1.67 -0.24 14

1476.75 1.24 -0.69 27.96607 -80.561 1.67 -0.22 14

73


Velocity (mph)



1477.00 1.24 -0.69 27.96606 -80.561 0.78 -0.22 16

1477.25 1.24 -0.69 27.96606 -80.561 0.78 -0.22 16

1477.50 1.05 -0.09 27.96606 -80.561 0.78 -0.17 16

1477.75 1.05 -0.09 27.96606 -80.561 0.49 -0.21 16

1478.00 1.05 -0.09 27.96606 -80.561 0.49 -0.21 16

1478.25 1.05 -0.09 27.96606 -80.561 0.49 -0.17 16

1478.50 1.05 -0.09 27.96606 -80.561 0.49 -0.21 16

1478.75 1.38 1.11 27.96606 -80.561 0.49 -0.19 16

1479.00 1.38 1.11 27.96606 -80.561 0.49 -0.19 16

1479.25 1.38 1.11 27.96606 -80.561 0.49 -0.19 16

1479.50 1.38 1.11 27.96606 -80.561 0.17 -0.19 17

1479.75 1.07 1.25 27.96606 -80.561 0.17 -0.21 17

1480.00 1.07 1.25 27.96606 -80.561 0.17 -0.18 17

1480.25 1.07 1.25 27.96606 -80.561 0.17 -0.18 17

1480.50 1.07 1.25 27.96606 -80.561 0.17 -0.18 17

1480.75 1.07 1.25 27.96606 -80.561 0.18 -0.18 17

1481.00 1.07 1.25 27.96606 -80.561 0.18 -0.21 17

1481.25 1.07 1.25 27.96606 -80.561 0.16 -0.21 17

1481.50 1.07 1.25 27.96606 -80.561 0.16 -0.24 17

1481.75 1.07 1.25 27.96606 -80.561 0.13 -0.14 17

1482.00 1.07 1.25 27.96606 -80.561 0.13 -0.18 17

1482.25 1.07 1.25 27.96606 -80.561 0.13 -0.18 17

1482.50 1.07 1.25 27.96606 -80.561 0.13 -0.21 17

1482.75 1.17 1.54 27.96606 -80.561 0.13 -0.17 17

1483.00 1.17 1.54 27.96606 -80.561 0.13 -0.10 17

1483.25 1.13 1.73 27.96606 -80.561 0.13 -0.14 17

1483.50 1.13 1.73 27.96606 -80.561 0.13 -0.14 17

1483.75 1.13 1.73 27.96606 -80.561 0.13 -0.14 17

1484.00 1.13 1.73 27.96606 -80.561 0.13 -0.14 17

1484.25 1.13 1.73 27.96606 -80.561 0.05 -0.17 17

1484.50 1.13 1.73 27.96606 -80.561 0.05 -0.17 17

1484.75 1.13 1.73 27.96606 -80.561 0.05 -0.14 17

74


Velocity (mph)



1485.00 1.15 1.55 27.96606 -80.561 0.05 -0.14 17

1485.25 1.15 1.55 27.96606 -80.561 0.05 -0.14 17

1485.50 1.15 1.55 27.96606 -80.561 0.04 -0.14 17

1485.75 1.15 1.55 27.96606 -80.561 0.04 -0.17 17

1486.00 1.15 1.55 27.96606 -80.561 0.04 -0.14 17

1486.25 1.15 1.55 27.96606 -80.561 0.04 -0.17 17

1486.50 1.15 1.55 27.96606 -80.561 0.02 -0.17 16

1486.75 1.15 1.55 27.96606 -80.561 0.02 0.15 16

1487.00 1.15 1.55 27.96606 -80.561 0.02 -0.01 16

1487.25 1.15 1.55 27.96606 -80.561 0.02 -0.11 16

1487.50 1.18 1.62 27.96606 -80.561 0.02 -0.10 16

1487.75 1.18 1.62 27.96606 -80.561 0.02 -0.10 16

1488.00 1.18 1.62 27.96606 -80.561 0.02 -0.07 16

1488.25 1.18 1.62 27.96606 -80.561 0.02 -0.17 16

1488.50 1.13 1.48 27.96606 -80.561 0.02 -0.07 16

1488.75 1.13 1.48 27.96606 -80.561 0.02 -0.07 16

1489.00 1.13 1.48 27.96606 -80.561 0.02 -0.24 16

1489.25 1.13 1.48 27.96606 -80.561 0.08 -0.07 17

1489.50 1.13 1.48 27.96606 -80.561 0.08 -0.07 17

1489.75 0.98 1.55 27.96606 -80.561 0.08 -0.09 17

1490.00 0.98 1.55 27.96606 -80.561 0.08 0.21 17

1490.25 0.98 1.55 27.96606 -80.561 0.08 0.21 17

1490.50 0.98 1.55 27.96606 -80.561 0.06 0.18 17

1490.75 0.98 1.55 27.96606 -80.561 0.12 0.18 17

1491.00 0.98 1.55 27.96606 -80.561 0.12 0.14 17

1491.25 0.98 1.55 27.96606 -80.561 0.97 -0.15 17

1491.50 1.16 11.36 27.96605 -80.561 3.82 -0.17 20

1491.75 0.24 12.04 27.96605 -80.561 3.82 -0.24 20

1492.00 0.24 12.04 27.96605 -80.561 3.82 -0.24 20

1492.25 -0.23 12.16 27.96602 -80.561 9.14 -0.24 33

1492.50 0.19 11.92 27.96602 -80.561 9.14 -0.18 33

1492.75 -0.10 11.28 27.96602 -80.561 9.14 -0.19 33

75


Velocity (mph)



1493.00 0.43 11.92 27.96602 -80.561 9.14 -0.16 33

1493.25 0.43 11.92 27.96602 -80.561 9.14 -0.10 33

1493.50 0.43 11.92 27.96599 -80.561 13.17 -0.10 50

1493.75 0.43 11.92 27.96599 -80.561 13.17 -0.10 50

1494.00 -0.12 11.68 27.96594 -80.5609 17.15 -0.14 73

1494.25 -0.12 11.68 27.96594 -80.5609 17.15 -0.10 73

1494.50 0.22 11.64 27.9659 -80.5609 20.12 -0.08 94

1494.75 0.39 11.34 27.96587 -80.5609 22.18 0.09 110

1495.00 0.83 11.65 27.96581 -80.5608 25.06 -0.04 137

1495.25 0.83 11.65 27.96581 -80.5608 25.06 -0.04 137

1495.50 0.29 11.41 27.96577 -80.5608 26.98 -0.14 156

1495.75 0.29 11.41 27.96577 -80.5608 26.98 -0.04 156

1496.00 0.29 11.41 27.96573 -80.5607 28.95 -0.04 177

1496.25 0.29 11.41 27.96573 -80.5607 28.95 -0.04 177

1496.50 -0.01 11.39 27.96573 -80.5607 28.95 -0.13 177

1496.75 0.46 11.18 27.96573 -80.5607 28.95 -0.03 177

1497.00 0.46 11.18 27.96561 -80.5606 33.60 -0.03 235

1497.25 0.46 11.18 27.96561 -80.5606 33.60 -0.03 235

1497.50 0.46 11.18 27.96561 -80.5606 33.60 -0.03 235

1497.75 1.28 10.61 27.96553 -80.5605 36.35 0.04 274

1498.00 1.28 10.61 27.96553 -80.5605 36.35 0.00 274

1498.25 -0.11 10.62 27.96544 -80.5604 39.12 -0.09 316

1498.50 -0.11 10.62 27.96544 -80.5604 39.12 -0.06 316

1498.75 0.14 10.35 27.96538 -80.5604 40.87 -0.01 346

1499.00 0.61 10.54 27.96538 -80.5604 40.87 0.21 346

1499.25 0.96 9.53 27.96538 -80.5604 40.87 0.25 346

1499.50 0.96 9.53 27.96538 -80.5604 40.87 0.15 346

1499.75 0.75 9.50 27.96522 -80.5602 45.27 0.14 426

1500.00 0.57 9.22 27.96522 -80.5602 45.27 0.16 426

1500.25 1.22 9.28 27.96522 -80.5602 45.27 0.33 426

1500.50 1.22 9.28 27.96522 -80.5602 45.27 0.33 426

1500.75 1.22 9.28 27.96522 -80.5602 45.27 0.46 426

76


Velocity (mph)



1501.00 0.01 9.01 27.96522 -80.5602 45.27 0.18 426

1501.25 -0.65 8.49 27.96493 -80.5599 51.88 0.21 570

1501.50 0.46 8.96 27.96493 -80.5599 51.88 0.28 570

1501.75 0.46 8.96 27.96485 -80.5598 53.43 0.31 609

1502.00 0.46 8.96 27.96472 -80.5597 55.79 0.28 669

1502.25 1.91 8.21 27.9646 -80.5596 58.06 0.48 732

1502.50 2.11 8.18 27.9646 -80.5596 58.06 0.50 732

1502.75 2.11 8.18 27.9646 -80.5596 58.06 0.53 732

1503.00 1.36 7.92 27.96451 -80.5595 59.48 0.64 776

1503.25 1.36 7.92 27.96442 -80.5594 61.01 1.44 820

1503.50 1.36 7.92 27.96437 -80.5593 61.70 1.44 843

1503.75 1.36 7.92 27.96437 -80.5593 61.70 2.56 843

1504.00 1.36 7.92 27.96432 -80.5593 62.47 3.81 866

1504.25 1.36 7.92 27.96432 -80.5593 62.47 6.18 866

1504.50 1.36 7.92 27.96432 -80.5593 62.47 8.96 866

1504.75 -1.90 6.40 27.96432 -80.5593 62.47 8.73 866

1505.00 -1.90 6.40 27.96413 -80.5591 65.20 12.12 960

1505.25 -0.78 7.21 27.96393 -80.5589 67.79 15.90 1058

1505.50 -0.78 7.21 27.96388 -80.5588 68.45 20.02 1083

1505.75 0.39 8.98 27.96388 -80.5588 68.45 20.00 1083

1506.00 0.39 8.98 27.96388 -80.5588 68.45 24.52 1083

1506.25 -0.06 9.49 27.96388 -80.5588 68.45 28.63 1083

1506.50 -0.08 9.39 27.96357 -80.5585 72.10 32.80 1239

1506.75 -2.53 10.20 27.96346 -80.5584 73.32 32.33 1292

1507.00 -2.53 10.20 27.96346 -80.5584 73.32 36.57 1292

1507.25 -1.09 9.30 27.96346 -80.5584 73.32 41.07 1292

1507.50 0.15 9.85 27.96324 -80.5582 75.44 45.44 1402

1507.75 0.10 9.33 27.96306 -80.558 75.94 49.41 1485

1508.00 0.10 9.33 27.96306 -80.558 75.94 49.41 1485

1508.25 0.10 9.33 27.96306 -80.558 75.94 53.22 1485

1508.50 -1.08 8.82 27.96306 -80.558 75.94 56.65 1485

1508.75 -1.08 8.67 27.96306 -80.558 75.94 59.96 1485

77


Velocity (mph)



1509.00 -1.08 8.67 27.96306 -80.558 75.94 59.96 1485

1509.25 -1.08 8.67 27.96284 -80.5578 75.91 62.94 1597

1509.50 -0.68 8.40 27.96284 -80.5578 75.91 65.89 1597

1509.75 -0.13 8.00 27.96284 -80.5578 75.91 68.78 1597

1510.00 -0.13 8.00 27.96272 -80.5576 75.62 68.78 1652

1510.25 -0.13 8.00 27.96272 -80.5576 75.62 71.27 1652

1510.50 -0.13 8.00 27.96272 -80.5576 75.62 73.38 1652

1510.75 -0.13 8.00 27.96272 -80.5576 75.62 75.77 1652

1511.00 -0.13 8.00 27.96261 -80.5575 75.52 75.77 1708

1511.25 -0.13 8.00 27.96261 -80.5575 75.52 77.97 1708

1511.50 -0.08 8.58 27.96261 -80.5575 75.52 79.56 1708

1511.75 -0.08 8.58 27.96255 -80.5575 75.36 80.99 1735

1512.00 -0.08 8.58 27.96255 -80.5575 75.36 82.24 1735

1512.25 -0.08 8.58 27.96255 -80.5575 75.36 82.24 1735

1512.50 -0.08 8.58 27.96255 -80.5575 75.36 82.90 1735

1512.75 -0.08 8.58 27.96255 -80.5575 75.36 84.05 1735

1513.00 -0.45 8.12 27.96255 -80.5575 75.36 85.39 1735

1513.25 -0.45 8.12 27.96255 -80.5575 75.36 85.39 1735

1513.50 -0.45 8.12 27.96255 -80.5575 75.36 86.64 1735

1513.75 0.24 8.62 27.96211 -80.557 74.56 87.99 1955

1514.00 -0.12 8.33 27.96211 -80.557 74.56 89.54 1955

1514.25 -0.12 8.33 27.96188 -80.5568 74.70 89.54 2064

1514.50 -0.12 8.33 27.96188 -80.5568 74.70 91.23 2064

1514.75 -0.12 8.33 27.96183 -80.5567 74.84 92.70 2091

1515.00 0.40 8.37 27.9616 -80.5565 75.50 94.53 2201

1515.25 -0.69 7.83 27.96149 -80.5564 76.02 94.45 2257

1515.50 -0.69 7.83 27.96149 -80.5564 76.02 96.08 2257

1515.75 -0.69 7.83 27.96149 -80.5564 76.02 97.77 2257

1516.00 -1.29 8.59 27.96149 -80.5564 76.02 99.25 2257

1516.25 -1.29 8.59 27.96126 -80.5561 77.79 101.28 2370

1516.50 -1.29 8.59 27.96126 -80.5561 77.79 101.28 2370

1516.75 -0.05 7.99 27.96126 -80.5561 77.79 104.77 2370

78


Velocity (mph)



1517.00 0.91 8.11 27.96126 -80.5561 77.79 108.45 2370

1517.25 0.36 7.44 27.96079 -80.5557 80.60 112.16 2604

1517.50 0.36 7.44 27.96079 -80.5557 80.60 112.16 2604

1517.75 0.11 6.99 27.96079 -80.5557 80.60 115.87 2604

1518.00 -0.14 7.04 27.9605 -80.5553 81.64 119.48 2753

1518.25 -0.23 7.94 27.96032 -80.5551 82.11 123.03 2843

1518.50 -0.23 7.94 27.96032 -80.5551 82.11 123.03 2843

1518.75 -0.23 7.94 27.96032 -80.5551 82.11 127.08 2843

1519.00 -0.23 7.94 27.96008 -80.5549 82.66 131.36 2964

1519.25 0.04 6.37 27.96008 -80.5549 82.66 136.85 2964

1519.50 2.70 5.39 27.96008 -80.5549 82.66 137.97 2964

1519.75 2.70 5.39 27.96008 -80.5549 82.66 142.33 2964

1520.00 2.40 5.64 27.96008 -80.5549 82.66 146.64 2964

1520.25 2.40 5.64 27.95958 -80.5544 82.28 150.68 3206

1520.50 1.43 5.20 27.95952 -80.5543 82.08 154.47 3236

1520.75 1.43 5.20 27.95952 -80.5543 82.08 154.47 3236

1521.00 0.92 5.31 27.95934 -80.5541 81.56 157.82 3326

1521.25 0.92 5.31 27.95927 -80.5541 81.50 161.36 3356

1521.50 0.92 5.31 27.95927 -80.5541 81.50 164.88 3356

1521.75 0.92 5.31 27.95927 -80.5541 81.50 164.88 3356

1522.00 0.92 5.31 27.95927 -80.5541 81.50 168.27 3356

1522.25 1.12 4.81 27.95927 -80.5541 81.50 171.89 3356

1522.50 1.55 4.84 27.95897 -80.5538 80.69 175.31 3505

1522.75 1.55 4.84 27.95897 -80.5538 80.69 175.31 3505

1523.00 1.55 4.84 27.95897 -80.5538 80.69 178.25 3505

1523.25 2.30 6.69 27.95897 -80.5538 80.69 180.17 3505

1523.50 2.42 7.82 27.95897 -80.5538 80.69 181.90 3505

1523.75 1.63 8.43 27.95854 -80.5533 80.85 181.25 3711

1524.00 1.63 8.43 27.95854 -80.5533 80.85 181.54 3711

1524.25 -0.94 8.68 27.95854 -80.5533 80.85 180.44 3711

1524.50 -0.94 8.68 27.95841 -80.5532 81.78 180.35 3771

1524.75 -1.15 8.19 27.95829 -80.5531 82.41 180.46 3832

79


Velocity (mph)



1525.00 -1.15 8.19 27.95829 -80.5531 82.41 180.46 3832

1525.25 -1.15 8.19 27.95829 -80.5531 82.41 180.72 3832

1525.50 -1.15 8.19 27.95829 -80.5531 82.41 181.29 3832

1525.75 -1.15 8.19 27.95822 -80.553 82.80 181.80 3862

1526.00 -1.15 8.19 27.95822 -80.553 82.80 181.80 3862

1526.25 -1.15 8.19 27.95816 -80.553 83.20 181.90 3893

1526.50 -1.15 8.19 27.9579 -80.5527 84.78 182.44 4017

1526.75 0.56 8.41 27.95777 -80.5526 85.37 184.31 4079

1527.00 0.28 7.69 27.95777 -80.5526 85.37 184.71 4079

1527.25 0.28 7.69 27.95777 -80.5526 85.37 185.86 4079

1527.50 0.28 7.69 27.95764 -80.5525 86.12 186.56 4142

1527.75 0.41 7.35 27.95764 -80.5525 86.12 187.92 4142

1528.00 0.48 7.91 27.95764 -80.5525 86.12 187.57 4142

1528.25 0.48 7.91 27.95764 -80.5525 86.12 188.31 4142

1528.50 1.79 8.00 27.95764 -80.5525 86.12 191.13 4142

1528.75 2.26 7.97 27.9573 -80.5522 87.79 195.49 4302

1529.00 2.26 7.97 27.95716 -80.552 88.45 320265.33 4367

1529.25 2.26 7.97 27.95716 -80.552 88.45 320265.33 4367

1529.50 1.30 7.67 27.95709 -80.552 88.70 320217.78 4399

1529.75 0.83 7.69 27.95709 -80.552 88.70 319973.78 4399

1530.00 0.83 7.69 27.95702 -80.5519 88.95 319973.78 4432

Table 8. Landing 3 Data


Velocity (mph)


Distance (ft.) (deg) (deg) (deg) (deg)

1770.00 1.63 -2.75 27.97081 -80.5656 85.35 199.67 0

1770.25 0.73 -3.20 27.97067 -80.5655 85.78 326660.54 63

1770.50 -0.23 -3.32 27.97067 -80.5655 85.78 197.11 63

80


Velocity (mph)



1770.75 -1.58 -3.49 27.97045 -80.5654 86.43 196.46 158

1771.00 -1.58 -3.49 27.97045 -80.5654 86.43 325205.00 158

1771.25 -1.58 -3.49 27.97038 -80.5653 86.67 185.15 190

1771.50 0.84 -3.79 27.97038 -80.5653 86.67 184.82 190

1771.75 1.52 -3.78 27.97017 -80.5651 87.09 176.42 285

1772.00 1.52 -3.78 27.97017 -80.5651 87.09 176.42 285

1772.25 1.23 -3.48 27.97017 -80.5651 87.09 177.11 285

1772.50 1.23 -3.48 27.97017 -80.5651 87.09 171.32 285

1772.75 1.23 -3.48 27.9699 -80.5649 87.52 326932.92 414

1773.00 1.23 -3.48 27.9699 -80.5649 87.52 326932.92 414

1773.25 0.89 -3.96 27.9699 -80.5649 87.52 167.00 414

1773.50 0.89 -3.96 27.9699 -80.5649 87.52 159.94 414

1773.75 0.60 -4.51 27.9699 -80.5649 87.52 326613.06 414

1774.00 -0.44 -4.40 27.9699 -80.5649 87.52 326004.59 414

1774.25 -0.44 -4.40 27.9699 -80.5649 87.52 156.18 414

1774.50 -0.44 -4.40 27.96956 -80.5646 87.27 152.59 574

1774.75 -0.44 -4.40 27.9695 -80.5645 87.17 145.58 606

1775.00 0.18 -3.97 27.9693 -80.5643 86.83 142.93 702

1775.25 0.18 -3.97 27.9693 -80.5643 86.83 142.93 702

1775.50 2.84 -4.88 27.96923 -80.5642 86.75 145.68 733

1775.75 2.57 -4.36 27.96923 -80.5642 86.75 141.74 733

1776.00 1.95 -4.12 27.96904 -80.564 86.36 140.32 829

1776.25 2.70 -3.88 27.96904 -80.564 86.36 140.49 829

1776.50 2.70 -3.88 27.96897 -80.564 86.18 135.71 860

1776.75 3.02 -4.13 27.96897 -80.564 86.18 327637.86 860

1777.00 3.02 -4.13 27.96891 -80.5639 86.19 130.60 892

1777.25 3.02 -4.13 27.96891 -80.5639 86.19 130.60 892

1777.50 3.02 -4.13 27.96891 -80.5639 86.19 137.02 892

1777.75 3.02 -4.13 27.96891 -80.5639 86.19 327637.86 892

1778.00 3.02 -4.13 27.96871 -80.5637 85.88 124.73 986

1778.25 3.02 -4.13 27.96865 -80.5636 85.56 132.36 1018

1778.50 0.43 -4.77 27.96865 -80.5636 85.56 131.73 1018

81


Velocity (mph)



1778.75 0.43 -4.77 27.96858 -80.5636 85.40 134.31 1049

1779.00 0.57 -5.34 27.96858 -80.5636 85.40 133.61 1049

1779.25 -0.42 -4.29 27.96821 -80.5632 84.71 326017.47 1236

1779.50 1.07 -4.57 27.96821 -80.5632 84.71 326851.83 1236

1779.75 1.07 -4.57 27.96821 -80.5632 84.71 326851.83 1236

1780.00 1.07 -4.57 27.96814 -80.5631 84.54 111.68 1267

1780.25 1.07 -4.57 27.96814 -80.5631 84.54 107.86 1267

1780.50 2.67 -5.61 27.96802 -80.563 84.29 95.41 1329

1780.75 2.67 -5.61 27.96802 -80.563 84.29 95.41 1329

1781.00 2.67 -5.61 27.96784 -80.5628 83.48 107.03 1421

1781.25 1.56 -4.92 27.96784 -80.5628 83.48 327054.43 1421

1781.50 -0.05 -4.61 27.96784 -80.5628 83.48 102.00 1421

1781.75 -0.05 -4.61 27.96784 -80.5628 83.48 102.00 1421

1782.00 -0.05 -4.61 27.96784 -80.5628 83.48 104.94 1421

1782.25 -0.52 -4.48 27.96784 -80.5628 83.48 103.54 1421

1782.50 -0.52 -4.48 27.96747 -80.5624 82.34 92.55 1603

1782.75 1.43 -4.28 27.96747 -80.5624 82.34 93.00 1603

1783.00 1.43 -4.28 27.96747 -80.5624 82.34 91.43 1603

1783.25 3.34 -3.79 27.96747 -80.5624 82.34 89.88 1603

1783.50 3.15 -2.29 27.96722 -80.5622 81.35 85.30 1723

1783.75 3.15 -2.29 27.96722 -80.5622 81.35 86.34 1723

1784.00 3.00 -2.40 27.96722 -80.5622 81.35 86.33 1723

1784.25 3.00 -2.40 27.96722 -80.5622 81.35 83.22 1723

1784.50 1.61 -2.96 27.96697 -80.5619 82.30 79.18 1843

1784.75 0.24 -3.28 27.96697 -80.5619 82.30 75.60 1843

1785.00 -0.34 -2.39 27.96697 -80.5619 82.30 75.45 1843

1785.25 -0.34 -2.39 27.96697 -80.5619 82.30 72.13 1843

1785.50 -0.34 -2.39 27.96697 -80.5619 82.30 68.44 1843

1785.75 -1.49 -2.32 27.9666 -80.5615 82.02 64.52 2024

1786.00 0.02 -1.81 27.96654 -80.5615 82.28 64.81 2054

1786.25 0.02 -1.81 27.96654 -80.5615 82.28 62.69 2054

1786.50 0.96 -1.35 27.96647 -80.5614 82.54 59.50 2085

82


Velocity (mph)



1786.75 -0.24 -1.03 27.96647 -80.5614 82.54 55.70 2085

1787.00 1.05 -1.52 27.96647 -80.5614 82.54 53.39 2085

1787.25 1.05 -1.52 27.96647 -80.5614 82.54 53.39 2085

1787.50 1.57 -1.05 27.96647 -80.5614 82.54 51.41 2085

1787.75 1.57 -1.05 27.96622 -80.5612 82.93 48.96 2206

1788.00 1.57 -1.05 27.96616 -80.5611 82.91 47.10 2236

1788.25 1.57 -1.05 27.96616 -80.5611 82.91 47.10 2236

1788.50 0.29 -1.10 27.96604 -80.561 82.40 45.32 2297

1788.75 0.29 -1.10 27.96597 -80.5609 82.29 43.95 2327

1789.00 0.61 -2.82 27.96579 -80.5607 82.28 42.45 2417

1789.25 0.58 -2.57 27.96579 -80.5607 82.28 42.44 2417

1789.50 0.58 -2.57 27.96572 -80.5607 82.19 40.84 2447

1789.75 -0.09 -2.66 27.96566 -80.5606 82.24 39.09 2478

1790.00 -0.63 -2.51 27.96566 -80.5606 82.24 37.51 2478

1790.25 -0.63 -2.51 27.96554 -80.5605 82.14 37.51 2538

1790.50 -0.63 -2.51 27.96554 -80.5605 82.14 36.30 2538

1790.75 -0.63 -2.51 27.96548 -80.5604 81.94 35.22 2568

1791.00 2.14 -3.08 27.96548 -80.5604 81.94 33.58 2568

1791.25 0.26 -2.83 27.96548 -80.5604 81.94 31.14 2568

1791.50 0.26 -2.83 27.96548 -80.5604 81.94 31.14 2568

1791.75 -1.03 -2.58 27.96548 -80.5604 81.94 28.59 2568

1792.00 -0.99 -2.48 27.96548 -80.5604 81.94 26.51 2568

1792.25 -0.68 -1.76 27.96548 -80.5604 81.94 24.29 2568

1792.50 -0.68 -1.76 27.96548 -80.5604 81.94 24.29 2568

1792.75 -0.26 -1.14 27.96548 -80.5604 81.94 22.67 2568

1793.00 -0.03 -2.56 27.96548 -80.5604 81.94 21.12 2568

1793.25 0.82 -3.18 27.96548 -80.5604 81.94 19.81 2568

1793.50 0.59 -3.79 27.96548 -80.5604 81.94 19.79 2568

1793.75 0.59 -3.79 27.96469 -80.5596 80.97 17.76 2957

1794.00 0.59 -3.79 27.96463 -80.5596 80.79 16.23 2986

1794.25 0.59 -3.79 27.96457 -80.5595 80.26 15.02 3016

1794.50 1.50 -4.79 27.96457 -80.5595 80.26 15.10 3016

83


Velocity (mph)



1794.75 1.50 -4.79 27.96457 -80.5595 80.26 13.92 3016

1795.00 2.84 -4.67 27.96457 -80.5595 80.26 12.43 3016

1795.25 1.61 -3.93 27.96433 -80.5593 78.85 10.89 3132

1795.50 0.24 -3.50 27.96421 -80.5591 77.97 10.78 3190

1795.75 0.24 -3.50 27.96421 -80.5591 77.97 9.63 3190

1796.00 0.08 -3.63 27.96421 -80.5591 77.97 8.61 3190

1796.25 0.08 -3.63 27.96415 -80.5591 77.36 8.12 3218

1796.50 0.08 -3.63 27.96415 -80.5591 77.36 7.73 3218

1796.75 0.63 -4.26 27.96415 -80.5591 77.36 7.77 3218

1797.00 0.63 -4.26 27.96415 -80.5591 77.36 7.35 3218

1797.25 0.99 -4.42 27.96386 -80.5588 75.27 7.18 3358

1797.50 1.58 -4.53 27.96375 -80.5587 74.17 6.93 3412

1797.75 1.58 -4.53 27.96375 -80.5587 74.17 6.93 3412

1798.00 1.58 -4.53 27.96375 -80.5587 74.17 6.61 3412

1798.25 0.39 -3.75 27.96375 -80.5587 74.17 5.92 3412

1798.50 -0.07 -3.92 27.96375 -80.5587 74.17 5.20 3412

1798.75 -0.12 -3.34 27.96375 -80.5587 74.17 5.20 3412

1799.00 -0.12 -3.34 27.96375 -80.5587 74.17 4.51 3412

1799.25 -0.23 -2.86 27.96375 -80.5587 74.17 4.01 3412

1799.50 -0.23 -2.86 27.96375 -80.5587 74.17 3.33 3412

1799.75 -0.22 -1.88 27.96327 -80.5582 69.77 2.87 3649

1800.00 -0.22 -1.88 27.96327 -80.5582 69.77 2.87 3649

1800.25 0.36 -1.75 27.96322 -80.5581 69.44 2.46 3674

1800.50 -0.27 -1.54 27.96317 -80.5581 68.90 1.73 3700

1800.75 -0.51 -0.73 27.96317 -80.5581 68.90 0.99 3700

1801.00 -0.51 -0.73 27.96317 -80.5581 68.90 0.99 3700

1801.25 -0.78 -0.85 27.96317 -80.5581 68.90 0.12 3700

1801.50 2.94 -5.19 27.96317 -80.5581 68.90 0.45 3700

1801.75 0.80 -5.29 27.96286 -80.5578 66.67 0.37 3848

1802.00 1.45 -2.47 27.96286 -80.5578 66.67 0.41 3848

1802.25 1.45 -2.47 27.96282 -80.5577 65.65 0.38 3872

1802.50 0.62 -2.87 27.96282 -80.5577 65.65 0.29 3872

84


Velocity (mph)



1802.75 0.62 -2.87 27.96282 -80.5577 65.65 0.29 3872

1803.00 0.77 -2.07 27.96267 -80.5576 64.77 0.30 3943

1803.25 0.77 -2.07 27.96267 -80.5576 64.77 0.37 3943

1803.50 0.77 -2.07 27.96267 -80.5576 64.77 0.40 3943

1803.75 0.77 -2.07 27.96257 -80.5575 63.45 0.33 3990

1804.00 0.77 -2.07 27.96253 -80.5574 62.98 0.40 4013

1804.25 0.77 -2.07 27.96253 -80.5574 62.98 0.40 4013

1804.50 0.77 -2.07 27.96243 -80.5573 62.02 0.30 4059

1804.75 3.48 -2.89 27.96243 -80.5573 62.02 0.52 4059

1805.00 3.48 -2.89 27.96243 -80.5573 62.02 0.52 4059

1805.25 1.49 -2.61 27.96243 -80.5573 62.02 0.38 4059

1805.50 1.49 -2.61 27.96243 -80.5573 62.02 0.32 4059

1805.75 -0.58 -2.69 27.96225 -80.5572 60.09 0.17 4148

1806.00 -0.58 -2.69 27.9622 -80.5571 59.55 0.11 4170

1806.25 -0.58 -2.69 27.9622 -80.5571 59.55 0.11 4170

1806.50 -0.58 -2.69 27.9622 -80.5571 59.55 0.17 4170

1806.75 -0.56 -2.04 27.9622 -80.5571 59.55 0.11 4170

1807.00 0.52 -2.29 27.9622 -80.5571 59.55 0.19 4170

1807.25 0.52 -2.29 27.96203 -80.5569 57.82 0.19 4255

1807.50 0.52 -2.29 27.96203 -80.5569 57.82 0.19 4255

1807.75 0.52 -2.29 27.96203 -80.5569 57.82 0.19 4255

1808.00 0.52 -2.29 27.96198 -80.5569 57.31 0.15 4276

1808.25 -1.18 -4.95 27.96198 -80.5569 57.31 0.04 4276

1808.50 -1.18 -4.95 27.96198 -80.5569 57.31 0.07 4276

1808.75 -1.18 -4.95 27.96186 -80.5568 55.67 0.07 4338

1809.00 -1.18 -4.95 27.96186 -80.5568 55.67 0.07 4338

1809.25 -1.18 -4.95 27.96186 -80.5568 55.67 0.07 4338

1809.50 -1.18 -4.95 27.96186 -80.5568 55.67 0.07 4338

1809.75 -1.18 -4.95 27.9617 -80.5566 53.03 0.10 4417

1810.00 1.29 -5.09 27.9617 -80.5566 53.03 0.21 4417

1810.25 1.29 -5.09 27.96162 -80.5565 51.74 0.27 4455

1810.50 1.29 -5.09 27.96155 -80.5564 50.23 0.27 4492

85


Velocity (mph)



1810.75 1.29 -5.09 27.96155 -80.5564 50.23 0.27 4492

1811.00 1.78 -5.59 27.9614 -80.5563 47.15 0.27 4563

1811.25 1.95 -5.25 27.9614 -80.5563 47.15 0.25 4563

1811.50 1.95 -5.25 27.96137 -80.5563 46.38 0.25 4580

1811.75 1.95 -5.25 27.96137 -80.5563 46.38 0.28 4580

1812.00 1.95 -5.25 27.96133 -80.5562 45.58 0.28 4596

1812.25 2.39 -5.60 27.96133 -80.5562 45.58 0.25 4596

1812.50 1.75 -5.30 27.96133 -80.5562 45.58 0.27 4596

1812.75 1.75 -5.30 27.96133 -80.5562 45.58 0.27 4596

1813.00 0.01 -5.80 27.96133 -80.5562 45.58 0.15 4596

1813.25 -0.26 -6.11 27.96133 -80.5562 45.58 0.13 4596

1813.50 -0.26 -6.11 27.96111 -80.556 40.23 0.03 4705

1813.75 -0.26 -6.11 27.96111 -80.556 40.23 0.03 4705

1814.00 -0.26 -6.11 27.96111 -80.556 40.23 0.20 4705

1814.25 -0.26 -6.11 27.96106 -80.5559 38.60 0.16 4734

1814.50 0.97 -7.02 27.961 -80.5559 36.91 0.18 4761

1814.75 1.34 -6.96 27.961 -80.5559 36.91 0.21 4761

1815.00 1.34 -6.96 27.961 -80.5559 36.91 0.17 4761

1815.25 2.07 -6.69 27.9609 -80.5558 33.74 0.26 4812

1815.50 2.07 -6.69 27.96087 -80.5557 32.98 0.23 4824

1815.75 2.07 -6.69 27.96083 -80.5557 31.53 0.23 4847

1816.00 2.07 -6.69 27.96083 -80.5557 31.53 0.23 4847

1816.25 2.59 -7.69 27.96083 -80.5557 31.53 0.23 4847

1816.50 2.59 -7.69 27.96078 -80.5556 30.02 0.29 4870

1816.75 2.38 -8.32 27.96074 -80.5556 28.42 0.21 4891

1817.00 2.38 -8.32 27.96074 -80.5556 28.42 0.21 4891

1817.25 2.38 -8.32 27.9607 -80.5556 26.68 0.24 4911

1817.50 2.38 -8.32 27.9607 -80.5556 26.68 0.28 4911

1817.75 2.99 -9.22 27.96066 -80.5555 24.88 0.28 4929

1818.00 3.26 -9.10 27.96066 -80.5555 24.88 0.30 4929

1818.25 3.26 -9.10 27.96066 -80.5555 24.88 0.33 4929

1818.50 3.22 -8.77 27.96066 -80.5555 24.88 0.36 4929

86


Velocity (mph)



1818.75 2.75 -8.51 27.96066 -80.5555 24.88 0.23 4929

1819.00 1.23 -8.41 27.96055 -80.5554 19.08 0.13 4984

1819.25 1.23 -8.41 27.96055 -80.5554 19.08 0.16 4984

1819.50 0.90 -8.29 27.96053 -80.5554 18.19 0.11 4991

1819.75 0.57 -8.13 27.96052 -80.5554 17.43 0.12 4997

1820.00 0.57 -8.13 27.96052 -80.5554 17.43 0.12 4997

1820.25 0.57 -8.13 27.96052 -80.5554 17.43 0.09 4997

1820.50 0.57 -8.13 27.96052 -80.5554 17.43 0.12 4997

1820.75 0.80 -7.91 27.96052 -80.5554 17.43 0.10 4997

1821.00 0.80 -7.91 27.96046 -80.5553 12.90 0.14 5030

1821.25 0.80 -7.91 27.96046 -80.5553 12.90 0.14 5030

1821.50 2.43 -7.25 27.96046 -80.5553 12.90 0.28 5030

1821.75 2.69 -7.33 27.96044 -80.5553 11.70 0.27 5039

1822.00 2.18 -7.91 27.96044 -80.5553 11.70 0.23 5039

1822.25 2.18 -7.91 27.96044 -80.5553 11.70 0.23 5039

1822.50 2.18 -7.91 27.96042 -80.5553 10.33 0.23 5047

1822.75 2.18 -7.91 27.96041 -80.5553 9.65 0.17 5050

1823.00 1.12 -8.79 27.9604 -80.5553 7.32 0.15 5059

1823.25 1.12 -8.79 27.9604 -80.5553 7.32 0.15 5059

1823.50 1.12 -8.79 27.9604 -80.5553 7.32 0.15 5059

1823.75 1.12 -8.79 27.96039 -80.5552 6.66 0.15 5061

1824.00 1.12 -8.79 27.96039 -80.5552 5.81 0.12 5064

1824.25 1.12 -8.79 27.96038 -80.5552 5.03 0.12 5065

1824.50 1.12 -8.79 27.96038 -80.5552 5.03 0.12 5065

1824.75 1.37 -8.45 27.96038 -80.5552 3.46 0.14 5068

1825.00 1.42 -7.79 27.96038 -80.5552 3.46 0.15 5068

1825.25 1.42 -7.79 27.96038 -80.5552 3.46 0.11 5068

1825.50 1.42 -7.79 27.96038 -80.5552 3.46 0.11 5068

1825.75 1.42 -7.79 27.96037 -80.5552 0.81 0.15 5071

1826.00 0.95 -3.42 27.96037 -80.5552 0.26 0.09 5071

1826.25 0.95 -3.42 27.96037 -80.5552 0.26 0.09 5071

1826.50 0.95 -3.42 27.96037 -80.5552 0.26 0.09 5071

87


Velocity (mph)



1826.75 0.95 -3.42 27.96037 -80.5552 0.10 0.09 5071

1827.00 0.95 -3.42 27.96037 -80.5552 0.10 0.09 5071

1827.25 0.95 -3.42 27.96037 -80.5552 0.10 0.09 5071

1827.50 0.95 -3.42 27.96037 -80.5552 0.04 0.09 5071

1827.75 0.95 -3.42 27.96037 -80.5552 0.04 0.09 5071

1828.00 0.95 -3.42 27.96037 -80.5552 0.04 0.15 5071

1828.25 0.73 -0.43 27.96037 -80.5552 0.04 0.10 5071

1828.50 0.73 -0.43 27.96037 -80.5552 0.04 0.10 5071

1828.75 0.73 -0.43 27.96037 -80.5552 0.04 0.07 5071

1829.00 0.73 -0.43 27.96037 -80.5552 0.04 0.13 5071

1829.25 0.91 -0.79 27.96037 -80.5552 0.04 0.08 5071

1829.50 0.91 -0.79 27.96037 -80.5552 0.04 0.05 5071

1829.75 0.91 -0.79 27.96037 -80.5552 0.04 0.05 5071

1830.00 0.91 -0.79 27.96037 -80.5552 0.00 0.11 5071

1830.25 0.91 -0.79 27.96037 -80.5552 0.00 0.15 5071

1830.50 1.25 -0.87 27.96037 -80.5552 0.00 0.10 5071

1830.75 1.25 -0.87 27.96037 -80.5552 0.00 0.10 5071

1831.00 1.25 -0.87 27.96037 -80.5552 0.00 0.14 5071

1831.25 1.25 -0.87 27.96037 -80.5552 0.00 0.14 5071

1831.50 1.03 -0.54 27.96037 -80.5552 0.00 0.12 5071

1831.75 1.03 -0.54 27.96037 -80.5552 0.03 0.12 5071

1832.00 1.03 -0.54 27.96037 -80.5552 0.03 0.09 5071

1832.25 1.03 -0.54 27.96037 -80.5552 0.03 0.12 5071

1832.50 1.03 -0.54 27.96037 -80.5552 0.03 0.12 5071

1832.75 1.03 -0.54 27.96037 -80.5552 0.00 0.12 5071

1833.00 1.03 -0.54 27.96037 -80.5552 0.00 0.12 5071

1833.25 1.03 -0.54 27.96037 -80.5552 0.00 0.09 5071

1833.50 1.03 -0.54 27.96037 -80.5552 0.04 0.15 5071

1833.75 1.03 -0.54 27.96037 -80.5552 0.04 0.12 5071

1834.00 1.03 -0.54 27.96037 -80.5552 0.04 0.12 5071

1834.25 1.03 -0.54 27.96037 -80.5552 0.02 0.09 5071

1834.50 0.97 -0.48 27.96037 -80.5552 0.02 0.12 5071

88


Velocity (mph)



1834.75 0.97 -0.48 27.96037 -80.5552 0.02 0.12 5071

1835.00 1.04 -0.44 27.96037 -80.5552 0.02 0.12 5071

1835.25 1.04 -0.44 27.96037 -80.5552 0.11 0.12 5071

1835.50 1.04 -0.44 27.96037 -80.5552 0.11 0.09 5071

1835.75 1.24 -1.13 27.96037 -80.5552 0.11 0.10 5071

1836.00 1.24 -1.13 27.96037 -80.5552 0.11 0.10 5071

1836.25 1.24 -1.13 27.96037 -80.5552 0.11 0.14 5071

1836.50 1.04 -0.95 27.96037 -80.5552 0.11 0.15 5071

1836.75 1.08 -0.74 27.96037 -80.5552 0.11 0.12 5071

1837.00 0.99 -0.83 27.96037 -80.5552 0.11 0.09 5071

1837.25 0.99 -0.83 27.96037 -80.5552 0.11 0.09 5071

1837.50 0.99 -0.83 27.96037 -80.5552 0.02 0.12 5071

1837.75 0.99 -0.83 27.96037 -80.5552 0.02 0.12 5071

1838.00 0.99 -0.83 27.96037 -80.5552 0.02 0.12 5071

1838.25 0.99 -0.83 27.96037 -80.5552 0.02 0.12 5071

1838.50 0.99 -0.83 27.96037 -80.5552 0.08 0.12 5071

1838.75 0.99 -0.83 27.96037 -80.5552 0.08 0.12 5071

1839.00 0.99 -0.83 27.96037 -80.5552 0.06 0.09 5071

1839.25 0.99 -0.83 27.96037 -80.5552 0.06 0.09 5071

1839.50 0.99 -0.83 27.96037 -80.5552 0.06 0.09 5071

1839.75 0.99 -0.83 -0.00587 ######## 0.06 0.09 #NUM!

1840.00 0.99 -0.83 -0.00587 ######## 0.06 0.12 #NUM!

1840.25 0.99 -0.83 27.96037 -80.5552 0.06 0.12 5071

1840.50 0.99 -0.83 27.96037 -80.5552 0.06 0.09 5071

1840.75 1.19 -0.89 27.96037 -80.5552 0.06 0.16 5071

1841.00 1.19 -0.89 27.96037 -80.5552 0.06 0.13 5071

1841.25 1.19 -0.89 27.96037 -80.5552 0.06 0.13 5071

1841.50 1.19 -0.89 27.96037 -80.5552 0.06 0.16 5071

1841.75 1.19 -0.89 27.96037 -80.5552 0.06 0.20 5071

1842.00 1.19 -0.89 27.96037 -80.5552 0.06 0.13 5071

1842.25 1.19 -0.89 27.96037 -80.5552 0.05 0.16 5071

1842.50 0.83 -0.55 27.96037 -80.5552 0.05 0.14 5071

89


Velocity (mph)



1842.75 0.83 -0.55 27.96037 -80.5552 0.05 0.14 5071

1843.00 0.83 -0.55 27.96037 -80.5552 0.05 0.14 5071

1843.25 0.83 -0.55 27.96037 -80.5552 0.09 0.11 5071

1843.50 0.83 -0.55 27.96037 -80.5552 0.09 0.11 5071

1843.75 0.83 -0.55 27.96037 -80.5552 0.04 0.11 5071

1844.00 0.99 -0.76 27.96037 -80.5552 0.04 0.18 5071

1844.25 0.99 -0.76 27.96037 -80.5552 0.04 0.15 5071

1844.50 0.88 -0.47 27.96037 -80.5552 0.00 0.14 5071

1844.75 0.88 -0.47 27.96037 -80.5552 0.00 0.18 5071

1845.00 0.88 -0.47 27.96037 -80.5552 0.00 0.14 5071

1845.25 0.88 -0.47 27.96037 -80.5552 0.02 0.11 5071

1845.50 0.88 -0.47 27.96037 -80.5552 0.02 0.11 5071

1845.75 0.88 -0.47 27.96037 -80.5552 0.02 0.14 5071

1846.00 0.88 -0.47 27.96037 -80.5552 0.00 0.18 5071

1846.25 0.88 -0.47 27.96037 -80.5552 0.00 0.18 5071

1846.50 1.03 -0.60 27.96037 -80.5552 0.00 0.12 5071

1846.75 1.03 -0.60 27.96037 -80.5552 0.00 0.12 5071

1847.00 1.03 -0.60 27.96037 -80.5552 0.00 0.15 5071

1847.25 1.03 -0.60 27.96037 -80.5552 0.00 0.19 5071

1847.50 1.03 -0.60 27.96037 -80.5552 0.00 0.15 5071

1847.75 1.03 -0.60 27.96037 -80.5552 0.00 0.15 5071

1848.00 1.03 -0.60 27.96037 -80.5552 0.00 0.22 5071

1848.25 1.03 -0.60 27.96037 -80.5552 0.00 0.12 5071

1848.50 0.93 -0.65 27.96037 -80.5552 0.00 0.15 5071

1848.75 0.93 -0.65 27.96037 -80.5552 0.00 0.15 5071

1849.00 0.93 -0.65 27.96037 -80.5552 0.00 0.11 5071

1849.25 1.10 -0.73 27.96037 -80.5552 0.00 0.13 5071

1849.50 1.10 -0.73 27.96037 -80.5552 0.00 0.13 5071

1849.75 1.10 -0.73 27.96037 -80.5552 0.00 0.13 5071

1850.00 1.10 -0.73 27.96037 -80.5552 0.00 0.16 5071

90

Appendix H SSMG-11 [12]

Takeoff and Landing Distance Measurement: An Evaluation of ...

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