University Student Launch Initiative

Transcription

1 University Student Launch Initiative HARDING UNIVERSITY Flight Readiness Review March 31, 2008

2 Launch Vehicle Summary Size: 97.7 (2.5 meters long), 3.1 diameter Motor: Contrail Rockets 54mm J-234 Recovery System: Dual Recovery from Single Section using Redundant Electronics and the Chute Tamer device.

3 Launch Vehicle Summary Electronics: PerfectFlite MAWD for altimeter and ejection charges, and R-DAS for scientific payload data acquisition and redundancy. Scientific Payload: Custom-built spectrometer for analyzing the spectra from the hybrid motor plume.

4 Launch Vehicle

5 Flight Stability Our most recent RockSim file incorporating the actual weight and dimensions of the constructed rocket projects an overstable vehicle by a margin of With the J234 hybrid motor, our vehicle will reach the velocity for stable flight at 7.92 ft from the launch.

6 Thrust to Weight Ratio The combined weight of the airframe, recovery system, control system, payload, and motor is oz, or lbs (6.19 kg). The average thrust for the J234 engine is 54 lbs. Thrust to weight ratio: 3.97:1 J234 maximum thrust is 127 lbs Thrust to weight ratio: 9.33:1

7 Rail Exit Velocity According to simulation, the velocity at departure from a 8 ft launch guide is ft/s. A 8 foot Black Sky or Extreme Rocketry rail should allow for stable flight.

8 Projected performance Projected altitude from Rocksim: 3953 feet Rocket significantly heavier than originally projected Original Rocksim altitude predictions may have used faulty mass override

9 Parachute Sizes and Descent Rates Drogue Parachute 24 Sky Angle parachute 6.3 sq ft surface area Equivalent to 34 traditional parachute 43.2 ft/sec descent rate

10 Parachute Sizes and Descent Rates Main Parachute 52 Sky Angle parachute 29.5 sq ft surface area Equivalent to 73.5 traditional parachute 20.0 ft/sec descent rate Bound in the Chute Tamer device

11 Test Plans and Procedures On March 29, a test launch of the competition rocket integrating all components, including the electronics and the J234 motor, was cancelled due to inclement weather. A test launch has been rescheduled for the next possible date, April 13. During this test, all launch procedures and safety practices will be followed, as described in the FRR.

12 Test Plans and Procedures On March 27, the Contrail Rockets J234 hybrid motor was statictested, in order to practice operating the motor safely and effectively. This test was a full success.

13 Scale Model Flight Test On March 15 th, a test flight was attempted on a subscale rocket. The vehicle incorporated the PerfectFlite MAWD and the Chute Tamer device, and was flown on a Contrail Rockets I221 hybrid motor. A poorly seated rear snap ring allowed the engine contents to eject from the motor tube under the pressure of filling, and the graphite nozzle was cracked on impact with the launch stand. This failure prevented further testing on that date.

14 Dual Deployment Avionics Test Our test scheduled for the 13 th of April will be a full test of our dual-deploy system. The recovery system involves deployment of the drogue and main parachutes on the same 5/16 tubular nylon harness. The Chute Tamer device has been ground tested, has shown effective in binding the main parachute until a predetermined time.

15 Ejection Charge Amount Test We have completed a successful test of the ejection charges. 3 teaspoons of black powder separated the rocket vigorously but safely.

16 Payload Integration Feasibility The electronics boards are housed in a clear acrylic section, which is reinforced by three 1/8 steel threaded rods, thick plywood bulkheads, and the interlocking design of the section interior.

17 Payload Integration Feasibility Payload consists of the PerfectFlite MAWD, the R-DAS, and the custom-built spectrometer. The electronics boards are housed in a clear acrylic section, which is reinforced by three 1/8 steel threaded rods, thick plywood bulkheads, and the interlocking design of the section interior.

18 Payload Integration Feasibility Our scientific payload consists of a custom-built diffraction grating spectrometer. Light from the rocket plume is fed through a fiber optic cable mounted along a fin, which then runs inside the aft section between the body and motor mount tubes.

19 Payload Integration Feasibility The R-DAS electronics system will acquire the data from the spectrometer in flight, as well as serving as a backup for parachute deployment. The spectrometer is housed in an opaque Giant Leap Rocketry tube section, reinforced with 6 oz. fiberglass and epoxy.

20 Payload Integration Feasibility We hope to observe the spectra from the hydroxyl radical and other significant combustion intermediates. This data will aid Dr. Edmond Wilson s ongoing research on hybrid rockets and their exhaust plumes.

21 Questions and Feedback