Srr Payload Team Consept 2

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University Student Launch Initiative University Student Launch Initiative System Requirements System Requirements Review Review Payload Team September 3, 2009

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Test Upload. (UAHuntsville USLI Competition 2010)

Transcript of Srr Payload Team Consept 2

Page 1: Srr Payload Team Consept 2

University Student Launch InitiativeUniversity Student Launch Initiative

System Requirements ReviewSystem Requirements ReviewPayload Team

September 3, 2009

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OverviewOverview

• Purpose of System Requirements Review (SRR)• Mission Statement• Market Analysis and Benchmarking• Physical Requirements• Functional Description• Major Components • Design Drawing• Manufacturing Methods• Resources and Facilities• Safety Considerations• Cost Analysis• Activity Plan• Summary

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Purpose of SRRPurpose of SRR

• To review, update, and establish the mission and system requirements

• To confirm performance requirements• To establish that the cost and design are

feasible• To evaluate system safety and manufacturing

methods

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Mission StatementMission Statement

• Charger Rocket Works is a group of senior engineering students that seek to build a high power rocket designed to fly to exactly one mile for the USLI Competition.

• The payload team seeks to design a payload that will measure the condition a deployable UAV will under go in flight and deployment of a parafoil.

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Market Analysis and Market Analysis and BenchmarkingBenchmarking

• Past UAH Projects (from www.sli.uah.edu)

-All UAH Rockets have had a payload to take telemetry data and video from the flights

-2004 Carried a payload that tested the stress strain in a carbon fiber body

-2008-2009 Nosecone carried a retracting pitot tube plus the instrument to track the telemetry in the nosecone.

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Market Analysis and Market Analysis and BenchmarkingBenchmarking

-2008-2009 also carried a payload above the motor to test measure the thrust generated by the rocket.

• Last year winner Florida Institute of Technology carried a payload that measured effects of gravity on the sloshing in side a tank.

• Georgia Tech last year carried a payload that measured the separation of air around their rocket.

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Physical RequirementsPhysical Requirements

The diameter, length, and length are TBD with recover and structure teams help:

1. The diameter and length will be based for the most part on the parafoil deployment.

2. A general weight specification will be determined once specific components are chosen.

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Functional DescriptionFunctional Description

Data Gathering Function• Function:

• Telemetry – GPS– Five Hole Probe– Altimeter

• Measurement for UAV– Internal Pressure Cell– Internal Thermocouples– Load cells– Sensor to measure vibrations

• Video recording

• Objective:– Determines the conditions that

a Deployable UAV payload would have to go through

Controlled Landing Function

• Function:• Guidance

– GPS– IMU (Inertial Measurement Unit)

• Control– Parasail– Servos

• Communication– Transceiver– Antenna

• Objective:• Test Guidance & Navigation

System in Conjunction With a Parafoil

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• Telemetry (GPS, Five Hole Probe, Altimeter)

• Measurement for UAV (Pressure sensor, Thermocouple, and load cells)

Autopilot Data Acq.

Major ComponentsMajor Components

Automated Lander Controlled Landing Function

COTS = Commercial Off-The-ShelfGS = Ground Station

GPS

IMU

Guidance

Actuator

D/T Device

C&D

Comm

GS**

Sensors

• Navigation (GPS & IMU)

• Guidance (AVR/PIC MCU(s), COTS* Autopilot)

• Actuator (Servo(s), Brushless motor(s))

• Descent/Thrust Device (Parafoil, Rotors)

• Sensor (Pressure, Accelerometer, Temperature, gyroscope, etc.)

• Communication (Transceiver, Antenna)

• Command & Data (MCU, COTS Data Logger)

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Design DrawingDesign Drawing

May Have Sabot

Body Tube Experiment

Airfoil

Nose Cone

Deployable Airfoil With Experiment Pitot Tube

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Design DrawingDesign DrawingDeployable Lander

Possible Airfoil Payload

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Manufacturing Manufacturing MethodsMethods

• A few process are as follows:• Drilling• Soldering• Wiring• Machining and Assemble as needed

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Resources and Resources and FacilitiesFacilities

• Resources• MathCAD• Matlab• SolidEdge• Microcontroller IDE (AVR Studio or PICC)• PCB CAD (ExpressPCB)

• Facilities• SLI Lab• ASGC/SHC Lab• MAE Machine Shop

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Safety ConsiderationsSafety Considerations

• Possible failure modes:– Payload does not deploy at apogee

– Parachute on payload does not deploy

– Automated guidance system does not work

– Weight and size of payload could create structural instability (e.g. Vanderbilt UAV disaster)

• Initial solutions:– Create a payload deployment system similar to one used in the CanSat

competition

– Two altimeters onboard payload for redundancy purposes

– Have a manual switch for guidance system, if guidance fails, the payload will still return safely

– Payload will have a GPS system allowing fast location of payload

– This payload will be MUCH smaller than Vanderbilt’s and shouldn’t take up much more space than past payloads.

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Safety ConsiderationsSafety Considerations

• NAR Requirements:– Payload must be recovered safely– Must be made of lightweight materials– Payload cannot cause rocket to weigh more than one-third of the

average thrust of the motor.– Parafoil and instrumentation must be flame resistant.

• USLI Handbook Requirements:– Separation at apogee is allowed, but it increases the risk of floating

outside recovery area.

– Payload must be scientific in nature.

– Payload must re-coverable and re-usable.

– Be aware of hazardous materials, and environmental concerns: no hazardous materials or environmental concerns are projected for this experiment.

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Cost AnalysisCost Analysis

1. GPS: 75

2. IMU: 75

3. Parafoil: TBD

4. Pressure Sensor: 10

5. Accelerometer: 30

6. Temperature sensor: 8

7. GPS Comm: 100

8. Materials: TBD

9. Transceiver: 63

10. Servos: 60

11. Pressure Sensor: 10

12. Accelerometer: 30

13. Temperature sensor: 8

14. Transceiver: 63

15. Materials: TBD

16. Parachute: 10

17. Load cell: TBD

18. Five Hole Probe: TBD

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Activity PlanActivity Plan

SRR Task Assignments:

•Patrick Giddens (Team Leader)•Mission Statement and Review Past Team Benchmarks•Micro G Concept

•Seiya Shimizu•Automated Lander Concept•Research Concepts

•Matthew Statham•Physical Requirements•Cost Analysis•Research Concepts

•Michael MacDonald•Safety Considerations•Summary•Research Concepts

•Danny Bottoms•Design Drawing•Research Concepts

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SummarySummary

• Payload will have two functions:– In flight measurements

• Measurements will be made during thru the flight that will be useful in deterring what condition a UAV payload will ender before deployment.

– Automated return via controlled parafoil

• Measurements will be made during return and data will be useful for future UAV payload endeavors.

• The current payload concept fits the basic safety and feasibility requirements.

• Modifications and further specification of design are

required.