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West Point-Beemer High School SLI Critical Design Review Presentation January 29,2008

West Point-Beemer High School SLI Critical Design Review Presentation January 29,2008. Vehicle Stability. Both Stages. Vehicle Stability. Upper Stage. Thrust to Weight Ratio.

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West Point-Beemer High School SLI Critical Design Review Presentation January 29,2008

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  1. West Point-Beemer High School SLI Critical Design Review Presentation January 29,2008

  2. Vehicle Stability Both Stages

  3. Vehicle Stability Upper Stage

  4. Thrust to Weight Ratio An AMW L1100 creates a T:W Ratio off pad: 5.4:1 in a 50 pound vehicle (that is our absolute maximum expected liftoff weight)

  5. Rail Exit Velocity Simulated Launch guide data: • Launch guide length: 9.75000 Ft. (usable length-requires a total of 12 Ft. of rail) • Velocity at launch guide departure: 53.2376 ft/s • The launch guide was cleared at : 0.386 Seconds • User specified minimum velocity for stable flight: 43.9994 ft/s • Minimum velocity for stable flight reached at: 6.78770 Ft.

  6. Parachute Sizes and Descent Rates Upper PLB - Rocketman R4 @ 25 fps Lower Sustainer - Rocketman R9 @ 15fps Booster - Rocketman R12 @ 15fps

  7. Test Plans and Procedures • Scale model flight (Complete) • Test session at Andrew’s workshop to determine flight suitability of electronics not specifically designed for rocketry use. These include the radiation monitors, voice recorders and remote backup systems. Probable tests include centrifuge and drop tests. Avionics testing will also be performed. (Partially Complete)

  8. Remote backup electronics acceleration test

  9. Test Plans and Procedures (cont) • Science experiment test session at Mount Michael. To include testing synchronization plan for voice recorders and verify operation of radiation monitors with the help of the physics teacher and radioactive materials • Pre-test flight checkout session. Includes packing parachutes and practicing launch procedures. • Full up test launch.

  10. Scale Model Test Flight • On Sunday, December 16, 2007, we successfully flew a 30% scale model of our final rocket. The vehicle was flown with an Aerotech G64-7 in the booster and an Estes E9-6 in the sustainer. An ARTS flight computer was onboard to electronically ignite the upper stage motor and deploy the upper stage parachutes.

  11. Scale Model Test Flight (cont) • The flight took place at a farm approximately 6 miles West of West Point. The vehicle left the rail cleanly and weather cocked slightly more than expected to the west. This is probably due to the slow ignition and a few choughs apparent in the video of the rocket during its assent up the rail and during flight. Stage separation was perfectly on time at T+ 2.0 seconds. From analysis of the video, the accelerometer data, and looking at the upper stage E9 post flight, it is evident the E9 blew the nozzle out at or very shortly after ignition. Other than lower than expected altitude, there was no other effect on the flight or damage to the vehicle. The final altitude was 1520’. • The flight was deemed a success by nearly all measures with the only notable problems being the motor cato and the tangled parachute, both easy fixes.

  12. Dual Deployment Avionics Test All of the deployment electronics we intend to use in this year’s rocket were flown in last year’s rocket or in various TARC rockets. All have a very high reliability. Ground testing will be done on all electronics to confirm their operation before launch.

  13. Ejection Charge Amount Test At this time, we do not have the tubing or other materials required to test the amount of ejection charge we will need. We will perform tests for all separation charges once we are able to.

  14. Payload Integration Feasibility The payload will be integrated just like any other electronic device would normally be mounted in a rocket. Since the payload consists only of three radiation monitors and paired voice recorders, the integration plan is very simple. The payload electronics will be mounted to the electronics bays with zip-ties. This hardware integration plan is simple and feasible.

  15. Payload Integration Feasibility Our two stage rocket plan was driven by the need to keep multiple radiation monitors at altitude for a longer duration. The two stages help us to achieve this goal by placing a monitor at a medium altitude and allowing a slower descent at higher altitudes.

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