Srr Payload Team Consept 2
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Srr Payload Team Consept 2

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Test Upload. (UAHuntsville USLI Competition 2010)

Test Upload. (UAHuntsville USLI Competition 2010)

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Srr Payload Team Consept 2 Srr Payload Team Consept 2 Presentation Transcript

  • University Student Launch Initiative System Requirements Review Payload Team September 3, 2009
  • Overview
    • 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
  • Purpose 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
  • Mission 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.
  • Market Analysis and Benchmarking
    • 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.
  • Market Analysis and Benchmarking
    • -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.
  • Physical 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.
  • Functional 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
        • Telemetry (GPS, Five Hole Probe, Altimeter)
        • Measurement for UAV (Pressure sensor, Thermocouple, and load cells)
    Major Components
    • Automated Lander
    • Controlled Landing Function
    • 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)
    Autopilot Data Acq. COTS = Commercial Off-The-Shelf GS = Ground Station GPS IMU Guidance Actuator D/T Device C&D Comm GS** Sensors
  • 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
    • A few process are as follows:
        • Drilling
        • Soldering
        • Wiring
        • Machining and Assemble as needed
  • Resources and Facilities
    • Resources
        • MathCAD
        • Matlab
        • SolidEdge
        • Microcontroller IDE (AVR Studio or PICC)
        • PCB CAD (ExpressPCB)
    • Facilities
        • SLI Lab
        • ASGC/SHC Lab
        • MAE Machine Shop
  • Safety 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.
  • Safety 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.
  • Cost Analysis
    • GPS: 75
    • IMU: 75
    • Parafoil: TBD
    • Pressure Sensor: 10
    • Accelerometer: 30
    • Temperature sensor: 8
    • GPS Comm: 100
    • Materials: TBD
    • Transceiver: 63
    • 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
  • Activity 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
  • Summary
    • 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 .