UNIVERSITY OF FLORIDA PDR PRESENTATION

OUTLINE

Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work

PROJECT ORGANIZATION

OUTLINE

Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work

MATERIAL AND DIMENSIONS Material: Reinforced Phenolic Diameter: 4 inches Length: 96.75 inches Weight: 22.55 lbs

Component Weight (lbs)

 

Fins/ Motor Mount 7.6

Electronics Bay 8.61

Recovery System 1.26

Nose Cone 1.54

Airframe/Paint 3.49

Total 22.55

Section Length (in)

Nosecone 15.75

Upper Airframe 28

Middle Airframe 13

Lower Airframe 40

Total 96.75

SYSTEM BREAKDOWN

Main Parachute

Main Piston

Avionics Bay

Aileron Deflection Package

Drogue Parachute

Drogue Piston

G10 Fins

LFD Fins

NoseconeFlight Computer

STABILITY CHARACTERISTICS

CG CP

• The center of pressure (CP) is located 79.427" from the nose tip

• The center of gravity (CG) is located 72.715" from the nose tip

• Static Stability Margin of 1.68 increasing to 2.20 at motor burnout

VEHICLE VERIFICATION

Vehicle verification focused on safe recovery and reliable platform for LFD payload

Testing will be done to allow triple redundancy for drogue and main separation events

Accurate Stress analysis for all components

OUTLINE

Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work

LATERAL FLIGHT DYNAMICS PAYLOAD

Study of Lateral Dynamics of Rocket during flight

Attempts to quantify natural roll dampening of rocket

Compares natural roll dampening to dampening due to AIM 9M passive stabilization system

Determine resulting couple moment due to unlocked rollerons

Consists of LFD Fin, ADP, and Electronics

LFD FINS

PC Fin Halves

Trim Potentiometer

Rolleron

Linear Actuator G10 Mount

¼” Barrel Bolts

•G10 Mount epoxied to motor tube•2 fin halves bolted to permanent mount•Linear Actuator and Rolleron integrated separately

AILERON DEFLECTION PACKAGE

Aileron

Servo Motor

Bevel Gears

Torsional Springs

Gearbox

ELECTRONICS

Raspberry Pi Controls servo motor

for ADP Commands unlocking

of Rollerons Collects flight

dynamics data from gyros and trim potentiometers

PAYLOAD VERIFICATION

Ensure Launch Vehicle will be stable with integrated Payload.

Reliability of all systems allows for quality data acquisition.

OUTLINE

Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work

RECOVERY

All payload systems remain with launch vehicle Drogue parachute released at apogee Wires unplug from LFD fins using umbilical

connection Main parachute released at 700 ft AGL

VEHICLE RECOVERY

Drogue parachute 24 inches in diameter (x-form)

Descent velocity: 65 ft/s Main parachute 96 inches in diameter

(circular) Descent velocity: 17 ft/s

Component Descent Velocity (ft/s)

Mass (slugs) Kinetic Energy (ft-lbf)

Nosecone 17 1.51 6.776242236Upper Airframe 17 10.16 45.59378882Lower Airframe 17 14.07 63.14021739

Kinetic Energy at Landing

RECOVERY SYSTEM INTEGRATION

Drogue parachute housed in lower airframe, below electronics bay

First separation event utilizes piston ejection and drag generated by fins for reliable separation

Main parachute housed in upper airframe, above electronics bay

Second separation event utilizes piston ejection

Shear pins prevent premature separation of nosecone and of lower airframe

RECOVERY REDUNDANCY

Dual PerfectFlite StratoLogger altimeters Two-way communication via Raspberry Pi

allows use of manual charge detonation system.

System will be tested thoroughly before put into use.

Ground/Software Testing Flight Testing

OUTLINE

Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work

FLIGHT SIMULATIONS

OpenRocket and MATLAB used to simulate the rocket’s flight

MATLAB code is 1-DOF that uses ode45 Allows the user to vary coefficient of drag for

different parts of the rocket Wind tunnel testing and full-scale

demonstration will allow more accurate Cd values

PRELIMINARY RESULTS MATLAB code is compared with OpenRocket Maximum altitude approximately 190 ft.

lower than OpenRocket but still near target High target altitude to account for drag due

to LFD Payload

MOTOR CHOICE

Cesaroni L1720 Max Thrust 394 lb Impulse 831 lb-s Powerful motor allows altitude to be met with

increased drag due to LFD Payload. Gives a thrust to weight ratio of 13.1

OUTLINE

Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work

FUTURE WORK

Refine designs and tolerance all components Successfully fulfill subscale flight

requirements while testing flight software Begin manufacturing of rollerons, LFD fins,

and ADP Continue community outreach and

educational engagement functions Name Rocket