1 / 32

Critical design review NASA University Student Launch Initiative

Overview. Critical design review NASA University Student Launch Initiative. January 24, 2011. Overview. V. Payload Integration Feasibility Vehicle Integration Electronics Deployment Testing VI. Test Plans and Procedures VII. Scale Model Flight Test Test No. 1 Test No. 2

edric
Download Presentation

Critical design review NASA University Student Launch Initiative

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Overview Critical design reviewNASA University Student Launch Initiative January 24, 2011

  2. Overview • V. Payload Integration Feasibility • Vehicle Integration • Electronics • Deployment Testing • VI. Test Plans and Procedures • VII. Scale Model Flight Test • Test No. 1 • Test No. 2 • Flight Video • VIII. Education Engagement • Plan • Status • Vehicle • Overview • Static Stability Margin • Motor • Selection • Weight to Thrust Ratio • Launch Rail • Recovery • Configuration • Deployment Sequence • Parachutes • Testing Preliminary Design Review

  3. I. Vehicle A. Overview: Configuration and Dimensions 46” Nose Cone Main Parachute Bay 36” Recovery Avionics 174.25” Drogue Chute - Payload Bay 42” Motor Bay 40” 9.5” 11.2" 18” 9.5” 3” Preliminary Design Review

  4. I. Vehicle A. Overview: Nosecone • Shape • Performance 1) Superior, 2) Good, 3) Fair, 4) Poor Von Karman Preliminary Design Review

  5. I. Vehicle A. Overview: Airframe • Cardboard and Fiberglass Preliminary Design Review

  6. I. Vehicle A. Overview: Fins Leading Edge Aft Edge Span Tang Edge Original Trapezoidal Design Fins On Motor Mount Modified Trapezoidal Design Preliminary Design Review

  7. I. Vehicle B. Static Stability Margin CG minus CP 21.94" 2.31 = = = Stability Margin Diameter of Rocket 9.48" Preliminary Design Review

  8. II. Motor A. Selection: Requirements Preliminary Design Review

  9. II. Motor A. Selection: Thrust Curve Avg. Thrust Avg. Thrust = 1,953 N Total Impulse = 9,181 N-sec Burn time = 4.7 s Preliminary Design Review

  10. II. Motor B. Thrust to Weight Ratio Mass Conversion 0.02834 kg Massrocket = 1399.68 oz. = = 39.66 kg (loaded) 1 oz. Thrust to Weight Ratio Thrust Thrust 1,953 N = = = Weight (Mass) (Gravity) (39.66 kg) (9.807 m/s2) 5.02 > 1 Preliminary Design Review

  11. III. Launch Rail Exit Velocity 66.82 ft/s Unistrut Rail Actual Launch Pad Preliminary Design Review

  12. IV. Recovery A. Configuration Separation at Nose Cone Rocket System Main Chute with Kevlar Protector PVC Black Powder Ejection Containers Recovery Avionics Payload System CO2 Ejection Cartridges Drogue Chute CO2 Release Device Main Chute (in Deployment Bag) Drogue Chute Advanced Retention and Release Device Payload Separation at Fin Can Preliminary Design Review

  13. IV. Recovery B. Deployment Sequence 3 CO2 (16 g) Black Powder (2.3g) Preliminary Design Review

  14. IV. Recovery C. Parachutes Payload(6-8lb load) Rocket(71lb load) Main Drogue Main Drogue SkyAngle Classic II Spherachute Plus SkyAngle Classic SkyAngle Cert 3, XXL Type: 17-22 ft/s 80 ft/s 17-22 ft/s 100 ft/s Descent: 64 oz. Weight: 5 oz. 13 oz. .5 oz. 105" 52" 36" 18" Preliminary Design Review

  15. IV. Recovery D. Testing: Avionics Changes in pressure simulate changes in altitude Vacuum Air Tight Bag Inflate Hose Air Pump Avionics Board Preliminary Design Review

  16. IV. Recovery D. Testing: Sub-scale Ejection Preliminary Design Review

  17. V. Payload Integration A. Vehicle Integration Preliminary Design Review

  18. V. Payload Integration B. Electronics: Integration UV Computer Serial Port Arduino Micro- Controller Solar Irradiance GPS Temp/Hum Barometer UV Gyro Preliminary Design Review

  19. V. Payload Integration B. Electronics: Testing (Solar Irradiance Sensor) Connect to computer Sensor Readings (Control) 100 101 100 101 101 101 100 100 101 100 101 100 100 Constant Readings LED verification Preliminary Design Review

  20. V. Payload Integration B. Electronics: Testing (Solar Irradiance Sensor) Test Sensor Verify Sensor Readings (Variable) 100 101 100 47 101 100 100 47 101 100 101 48 100 Reading Anomalies Preliminary Design Review

  21. V. Payload Integration C. Deployment Testing: Lab Verification Lab tests verified leg mechanism worked as designed Spring Loaded Action Leg Mechanism Components Preliminary Design Review

  22. V. Payload Integration C. Deployment Testing: Field Verification Field tests reveal flaws in design and construction Uneven Landing Even Landing Preliminary Design Review

  23. V. Payload Integration C. Deployment Testing: Conclusion • Fix legs after deployment • Add redundancy dampening system under bottom plate • Install carbon fiber tubes around rods, in between plates Preliminary Design Review

  24. VI. Test Plan and Procedures • Construction Methods • Pre – Subscale Launch • Ejection charge • Avionics (Vehicle and Payload) • Subscale Launch • RockSim Verification • Recovery • Payload Ejection and Recovery • Pre – Full Scale Launch • Ejection • Avionics (Vehicle and Payload) • Payload Landing • Full Scale Test Preliminary Design Review

  25. VII. Scale Model Flight Test A. Test No. 1 • Purpose • Verify RockSim calculations • Systems Testing: Airframe, Avionics, Recovery • Plan • Launch without payload • Launch with payload Preliminary Design Review

  26. VII. Scale Model Flight Test A. Test No. 1: Results • Main chute deployed early • Cause: Incorrect manufacturing of • avionics bay • Solution: Label and triple check • Second Launch Aborted • Cause: Unsuccessful assembly due to low temperatures and body • tube contraction • Solution: Test assembly during similar conditions prior to launch • make necessary adjustments Preliminary Design Review

  27. VII. Scale Model Flight Test B. Test No. 2 • Purpose • Verify RockSim calculations • Vehicle Tests: Avionics • Recovery • Payload Tests: Ejection • Deployment • Recovery Preliminary Design Review

  28. VII. Scale Model Flight Test B. Test No. 2: Results Recovery bay shock cord snapped Fin can descended without chute Fin can bulkhead damaged upon impact Payload ARRD fired, but payload main chute tangled did not deploy Preliminary Design Review

  29. VII. Scale Model Flight Test C. Flight Video Preliminary Design Review

  30. VIII. Educational Engagement A. Plan We strive to promote higher education in mechanical and aerospace engineering through teaching community youth about the math, science and excitement high powered rocketry. Preliminary Design Review

  31. VIII. Educational Engagement B. Status Completed Engagements Boys and Girls Club Oct 15 Oct 19 YMCA – Raleigh, NC Nov 13 Pisgah Astronomical Research Institute Jan 14 Baileywick Elementary School Planned Engagements Marbles Kid's Museum Feb 13 Baileywick Elementary School Feb 18 YMCA – Durham, NC Mar 02 NC Mathematics and Science Education Network (MSEN) Mar/Apr Baileywick Science Expo Mar/Apr Preliminary Design Review

  32. Overview Questions and Answers

More Related