University Student Launch Initiative System Requirements Review Payload Team September 3, 2009
Overview <ul><li>Purpose of System Requirements Review (SRR) </li></ul><ul><li>Mission Statement </li></ul><ul><li>Market ...
Purpose of SRR <ul><li>To review, update, and establish the mission and system requirements </li></ul><ul><li>To confirm p...
Mission Statement <ul><li>Charger Rocket Works is a group of senior engineering students that seek to build a high power r...
Market Analysis and Benchmarking <ul><li>Past UAH Projects (from www.sli.uah.edu) </li></ul><ul><li>-All UAH Rockets have ...
Market Analysis and Benchmarking <ul><li>-2008-2009 also carried a payload above the motor to test measure the thrust gene...
Physical Requirements <ul><li>The diameter, length, and length are TBD with recover and structure teams help: </li></ul><u...
Functional Description <ul><li>Data Gathering Function </li></ul><ul><li>Function: </li></ul><ul><ul><ul><li>Telemetry  </...
<ul><ul><ul><li>Telemetry  (GPS, Five Hole Probe, Altimeter) </li></ul></ul></ul><ul><ul><ul><li>Measurement for UAV  (Pre...
Design Drawing Deployable Airfoil With Experiment Pitot  Tube May Have Sabot Body Tube Experiment  Airfoil Nose Cone
Design Drawing Deployable Lander Possible Airfoil Payload
Manufacturing Methods <ul><li>A few process are as follows: </li></ul><ul><ul><ul><li>Drilling </li></ul></ul></ul><ul><ul...
Resources and Facilities <ul><li>Resources </li></ul><ul><ul><ul><li>MathCAD </li></ul></ul></ul><ul><ul><ul><li>Matlab </...
Safety Considerations <ul><li>Possible failure modes : </li></ul><ul><ul><li>Payload does not deploy at apogee </li></ul><...
Safety Considerations <ul><li>NAR Requirements: </li></ul><ul><ul><li>Payload must be recovered safely </li></ul></ul><ul>...
Cost Analysis <ul><li>GPS: 75 </li></ul><ul><li>IMU: 75 </li></ul><ul><li>Parafoil: TBD </li></ul><ul><li>Pressure Sensor:...
Activity Plan <ul><li>SRR Task Assignments: </li></ul><ul><ul><li>Patrick Giddens (Team Leader) </li></ul></ul><ul><ul><ul...
Summary <ul><li>Payload will have two functions: </li></ul><ul><ul><li>In flight measurements </li></ul></ul><ul><ul><ul><...
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Srr Payload Team Consept 2

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Test Upload. (UAHuntsville USLI Competition 2010)

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Srr Payload Team Consept 2

  1. 1. University Student Launch Initiative System Requirements Review Payload Team September 3, 2009
  2. 2. Overview <ul><li>Purpose of System Requirements Review (SRR) </li></ul><ul><li>Mission Statement </li></ul><ul><li>Market Analysis and Benchmarking </li></ul><ul><li>Physical Requirements </li></ul><ul><li>Functional Description </li></ul><ul><li>Major Components </li></ul><ul><li>Design Drawing </li></ul><ul><li>Manufacturing Methods </li></ul><ul><li>Resources and Facilities </li></ul><ul><li>Safety Considerations </li></ul><ul><li>Cost Analysis </li></ul><ul><li>Activity Plan </li></ul><ul><li>Summary </li></ul>
  3. 3. Purpose of SRR <ul><li>To review, update, and establish the mission and system requirements </li></ul><ul><li>To confirm performance requirements </li></ul><ul><li>To establish that the cost and design are feasible </li></ul><ul><li>To evaluate system safety and manufacturing methods </li></ul>
  4. 4. Mission Statement <ul><li>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. </li></ul><ul><li>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. </li></ul>
  5. 5. Market Analysis and Benchmarking <ul><li>Past UAH Projects (from www.sli.uah.edu) </li></ul><ul><li>-All UAH Rockets have had a payload to take telemetry data and video from the flights </li></ul><ul><li>-2004 Carried a payload that tested the stress strain in a carbon fiber body </li></ul><ul><li>-2008-2009 Nosecone carried a retracting pitot tube plus the instrument to track the telemetry in the nosecone. </li></ul>
  6. 6. Market Analysis and Benchmarking <ul><li>-2008-2009 also carried a payload above the motor to test measure the thrust generated by the rocket. </li></ul><ul><li>Last year winner Florida Institute of Technology carried a payload that measured effects of gravity on the sloshing in side a tank. </li></ul><ul><li>Georgia Tech last year carried a payload that measured the separation of air around their rocket. </li></ul>
  7. 7. Physical Requirements <ul><li>The diameter, length, and length are TBD with recover and structure teams help: </li></ul><ul><li>1. The diameter and length will be based for the most part on the parafoil deployment. </li></ul><ul><li>2. A general weight specification will be determined once specific components are chosen. </li></ul>
  8. 8. Functional Description <ul><li>Data Gathering Function </li></ul><ul><li>Function: </li></ul><ul><ul><ul><li>Telemetry </li></ul></ul></ul><ul><ul><ul><ul><li>GPS </li></ul></ul></ul></ul><ul><ul><ul><ul><li>Five Hole Probe </li></ul></ul></ul></ul><ul><ul><ul><ul><li>Altimeter </li></ul></ul></ul></ul><ul><ul><ul><li>Measurement for UAV </li></ul></ul></ul><ul><ul><ul><ul><li>Internal Pressure Cell </li></ul></ul></ul></ul><ul><ul><ul><ul><li>Internal Thermocouples </li></ul></ul></ul></ul><ul><ul><ul><ul><li>Load cells </li></ul></ul></ul></ul><ul><ul><ul><ul><li>Sensor to measure vibrations </li></ul></ul></ul></ul><ul><ul><ul><li>Video recording </li></ul></ul></ul><ul><ul><ul><li>Objective: </li></ul></ul></ul><ul><ul><ul><ul><li>Determines the conditions that a Deployable UAV payload would have to go through </li></ul></ul></ul></ul><ul><li>Controlled Landing Function </li></ul><ul><ul><li>Function: </li></ul></ul><ul><ul><ul><li>Guidance </li></ul></ul></ul><ul><ul><ul><ul><li>GPS </li></ul></ul></ul></ul><ul><ul><ul><ul><li>IMU (Inertial Measurement Unit) </li></ul></ul></ul></ul><ul><ul><ul><li>Control </li></ul></ul></ul><ul><ul><ul><ul><li>Parasail </li></ul></ul></ul></ul><ul><ul><ul><ul><li>Servos </li></ul></ul></ul></ul><ul><ul><ul><li>Communication </li></ul></ul></ul><ul><ul><ul><ul><li>Transceiver </li></ul></ul></ul></ul><ul><ul><ul><ul><li>Antenna </li></ul></ul></ul></ul><ul><ul><li>Objective: </li></ul></ul><ul><ul><ul><li>Test Guidance & Navigation System in Conjunction With a Parafoil </li></ul></ul></ul>
  9. 9. <ul><ul><ul><li>Telemetry (GPS, Five Hole Probe, Altimeter) </li></ul></ul></ul><ul><ul><ul><li>Measurement for UAV (Pressure sensor, Thermocouple, and load cells) </li></ul></ul></ul>Major Components <ul><li>Automated Lander </li></ul><ul><li>Controlled Landing Function </li></ul><ul><li>Navigation (GPS & IMU) </li></ul><ul><li>Guidance (AVR/PIC MCU(s), COTS* Autopilot) </li></ul><ul><li>Actuator (Servo(s), Brushless motor(s)) </li></ul><ul><li>Descent/Thrust Device (Parafoil, Rotors) </li></ul><ul><li>Sensor (Pressure, Accelerometer, Temperature, gyroscope, etc.) </li></ul><ul><li>Communication (Transceiver, Antenna) </li></ul><ul><li>Command & Data (MCU, COTS Data Logger) </li></ul>Autopilot Data Acq. COTS = Commercial Off-The-Shelf GS = Ground Station GPS IMU Guidance Actuator D/T Device C&D Comm GS** Sensors
  10. 10. Design Drawing Deployable Airfoil With Experiment Pitot Tube May Have Sabot Body Tube Experiment Airfoil Nose Cone
  11. 11. Design Drawing Deployable Lander Possible Airfoil Payload
  12. 12. Manufacturing Methods <ul><li>A few process are as follows: </li></ul><ul><ul><ul><li>Drilling </li></ul></ul></ul><ul><ul><ul><li>Soldering </li></ul></ul></ul><ul><ul><ul><li>Wiring </li></ul></ul></ul><ul><ul><ul><li>Machining and Assemble as needed </li></ul></ul></ul>
  13. 13. Resources and Facilities <ul><li>Resources </li></ul><ul><ul><ul><li>MathCAD </li></ul></ul></ul><ul><ul><ul><li>Matlab </li></ul></ul></ul><ul><ul><ul><li>SolidEdge </li></ul></ul></ul><ul><ul><ul><li>Microcontroller IDE (AVR Studio or PICC) </li></ul></ul></ul><ul><ul><ul><li>PCB CAD (ExpressPCB) </li></ul></ul></ul><ul><li>Facilities </li></ul><ul><ul><ul><li>SLI Lab </li></ul></ul></ul><ul><ul><ul><li>ASGC/SHC Lab </li></ul></ul></ul><ul><ul><ul><li>MAE Machine Shop </li></ul></ul></ul>
  14. 14. Safety Considerations <ul><li>Possible failure modes : </li></ul><ul><ul><li>Payload does not deploy at apogee </li></ul></ul><ul><ul><li>Parachute on payload does not deploy </li></ul></ul><ul><ul><li>Automated guidance system does not work </li></ul></ul><ul><ul><li>Weight and size of payload could create structural instability (e.g. Vanderbilt UAV disaster) </li></ul></ul><ul><li>Initial solutions: </li></ul><ul><ul><li>Create a payload deployment system similar to one used in the CanSat competition </li></ul></ul><ul><ul><li>Two altimeters onboard payload for redundancy purposes </li></ul></ul><ul><ul><li>Have a manual switch for guidance system, if guidance fails, the payload will still return safely </li></ul></ul><ul><ul><li>Payload will have a GPS system allowing fast location of payload </li></ul></ul><ul><ul><li>This payload will be MUCH smaller than Vanderbilt’s and shouldn’t take up much more space than past payloads. </li></ul></ul>
  15. 15. Safety Considerations <ul><li>NAR Requirements: </li></ul><ul><ul><li>Payload must be recovered safely </li></ul></ul><ul><ul><li>Must be made of lightweight materials </li></ul></ul><ul><ul><li>Payload cannot cause rocket to weigh more than one-third of the average thrust of the motor. </li></ul></ul><ul><ul><li>Parafoil and instrumentation must be flame resistant. </li></ul></ul><ul><li>USLI Handbook Requirements: </li></ul><ul><ul><li>Separation at apogee is allowed, but it increases the risk of floating outside recovery area. </li></ul></ul><ul><ul><li>Payload must be scientific in nature. </li></ul></ul><ul><ul><li>Payload must re-coverable and re-usable. </li></ul></ul><ul><ul><li>Be aware of hazardous materials, and environmental concerns: no hazardous materials or environmental concerns are projected for this experiment. </li></ul></ul>
  16. 16. Cost Analysis <ul><li>GPS: 75 </li></ul><ul><li>IMU: 75 </li></ul><ul><li>Parafoil: TBD </li></ul><ul><li>Pressure Sensor: 10 </li></ul><ul><li>Accelerometer: 30 </li></ul><ul><li>Temperature sensor: 8 </li></ul><ul><li>GPS Comm: 100 </li></ul><ul><li>Materials: TBD </li></ul><ul><li>Transceiver: 63 </li></ul><ul><li>Servos: 60 </li></ul><ul><li>11. Pressure Sensor: 10 </li></ul><ul><li>12. Accelerometer: 30 </li></ul><ul><li>13. Temperature sensor: 8 </li></ul><ul><li>14. Transceiver: 63 </li></ul><ul><li>15. Materials: TBD </li></ul><ul><li>16. Parachute: 10 </li></ul><ul><li>17. Load cell: TBD </li></ul><ul><li>18. Five Hole Probe: TBD </li></ul>
  17. 17. Activity Plan <ul><li>SRR Task Assignments: </li></ul><ul><ul><li>Patrick Giddens (Team Leader) </li></ul></ul><ul><ul><ul><li>Mission Statement and Review Past Team Benchmarks </li></ul></ul></ul><ul><ul><ul><li>Micro G Concept </li></ul></ul></ul><ul><ul><li>Seiya Shimizu </li></ul></ul><ul><ul><ul><li>Automated Lander Concept </li></ul></ul></ul><ul><ul><ul><li>Research Concepts </li></ul></ul></ul><ul><ul><li>Matthew Statham </li></ul></ul><ul><ul><ul><li>Physical Requirements </li></ul></ul></ul><ul><ul><ul><li>Cost Analysis </li></ul></ul></ul><ul><ul><ul><li>Research Concepts </li></ul></ul></ul><ul><ul><li>Michael MacDonald </li></ul></ul><ul><ul><ul><li>Safety Considerations </li></ul></ul></ul><ul><ul><ul><li>Summary </li></ul></ul></ul><ul><ul><ul><li>Research Concepts </li></ul></ul></ul><ul><ul><li>Danny Bottoms </li></ul></ul><ul><ul><ul><li>Design Drawing </li></ul></ul></ul><ul><ul><ul><li>Research Concepts </li></ul></ul></ul>
  18. 18. Summary <ul><li>Payload will have two functions: </li></ul><ul><ul><li>In flight measurements </li></ul></ul><ul><ul><ul><li>Measurements will be made during thru the flight that will be useful in deterring what condition a UAV payload will ender before deployment. </li></ul></ul></ul><ul><ul><li>Automated return via controlled parafoil </li></ul></ul><ul><ul><ul><li>Measurements will be made during return and data will be useful for future UAV payload endeavors. </li></ul></ul></ul><ul><li>The current payload concept fits the basic safety and feasibility requirements. </li></ul><ul><li>Modifications and further specification of design are required . </li></ul>

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