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CySLI

Iowa State University Controlled Decent Video Reconnaissance Vehicle (CDVRV) Flight Readiness Review. CySLI. Launch Vehicle Design Overview. Length: 103.25 in. Diameter: 7.7 in. Weight: 46 lbs. Key Design Features. Phenolic/fiberglass composite airframe.

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CySLI

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  1. Iowa State University Controlled Decent Video Reconnaissance Vehicle (CDVRV) Flight Readiness Review CySLI

  2. Launch Vehicle Design Overview • Length: 103.25 in. • Diameter: 7.7 in. • Weight: 46 lbs.

  3. Key Design Features • Phenolic/fiberglass composite airframe. • Hand-laid fiberglass composite fins. • Transparent acrylic nose dome (payload).

  4. Motor Selection • Cesaroni L1115 • Thrust: 1119 N • Total impulse: 5015 Ns • Duration: 4.5s

  5. Rocket Flight Stability • CG: 63.5 in. • CP: 78.6 in. • Margin: 1.96. • The stability margin is now significantly better for windy conditions.

  6. Thrust-to-Weight Ratio • Thrust to weight ratio is 5.5. • This is within the accepted range for a stable liftoff. • The exit velocity is 57 ft/s using an 8 ft. rail.

  7. Mass Budget • The entire launch vehicle weighs 46 lbs. in its prepped, ready-for-launch condition. • The margin is approximately ±3lb. • Mass will be added or removed depending on launch conditions.

  8. Descent Rates • Drogue parachute: 4 ft. X-form. Descent rate: 65 ft/s. • Main parachute: 18 ft. X-form. Descent rate: 13.5 ft/s.

  9. Kinetic Energies • Burnout (Max K.E.) – 2.4x10^5 ft*lb • Drogue descent – 2.7x10^3 ft*lb • Main descent – • Payload Section- 25 ft*lb • Booster Section- 50 ft*lb • Payload with parachute – 20 ft*lb

  10. Projected Altitude • 0-2 mph wind: 5210 ft. • 3-7 mph wind: 5170 ft. • 8-14 mph wind: 5120 ft. • 15-25 mph wind: 4920 ft. • Note: mass will be added or removed at competition launch to reflect launch conditions.

  11. Predicted Drift • 5 mph: -90 ft. • 10 mph: -70 ft. • 15 mph: 200 ft • 20 mph: 630 ft

  12. Test Program • Altitude: measure altitude from test flight. Backtrack in RockSim to determine Cd. • Parachute deployment: test altimeter functions before competition launch. • Tracking: test transmitter function before competition launch. • Static Deployment tests (summarized later).

  13. Full-Scale Test Launch • Rocket reached 4650 ft. in 19 mph winds. • Dual deployment worked flawlessly. • http://www.youtube.com/watch?v=H3ILbSIlc50

  14. Recovery System Tests • Static testing of ejection charges. • 5 g drogue charge • 15 g main charge • Further recovery system tests will be conducted with shear pins. • Altimeters verified and reliable.

  15. Launch Vehicle Requirements Verification (Highlights) • Altitude: full scale test launch, RockSim simulations. • Structural integrity: full scale test launch, inspection. • Vehicle meets all competition requirements. (See vehicle requirements matrix).

  16. Payload Design • Payload consists of controllable camera and quadcopter recovery.

  17. Key Design Features • Deployable arms • Lockout mechanism • Parachute release mechanism • Telemetry

  18. Payload Integration • The quadcopter arms are on spring-loaded hinges; fold up inside airframe. • Payload deploys with main parachute at 1000 ft.

  19. Interfaces with Mission Control • Live video transmission on channel 57. • Live telemetry on 434 MHz. • Quadcopter control on 2.4 GHz Spektrum DX8 transmitter. • Camera control on separate Spektrum DX8. • Video and telemetry will be recorded.

  20. Payload Requirements Verification

  21. Payload Test Program • Conducting first tethered test flights of quadcopter. • Currently designing a full-systems test (camera transmission/control + quadcopter control + data collection/transmission).

  22. Questions • Answers

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