Critical Design Review Presentation Submitted by:   Boy Scout Troop 143 382 N. Grimes Giddings, Texas 78942

Agenda Team Introduction Vehicle Design Questions

Team Introduction Members - Preston Pruitt, Cody Alexander, Corbin Dillow, Skyler Newman, Taylor Blakney Members are from the same Scout Troop and high school Other activities include band, soccer, basketball & track

Rocket Flight Specifications & 2D Diagram Length: 63 inches Diameter: 6.17 inches Span Diameter: 16.1210 inches Mass (Empty): 278.891 Oz Mass with Engine: 335.5906 Oz

Stability Margin With an additional 4 pounds of ballast in the nose, the stability margin reaches .51 calibers Any and all construction measures to lighten the airframe will be considered

Thrust to Weight Motor Selection in Flight Simulation Motor Selected – Aerotech K1050W Calculations: - Motor impulse in Newtons / 4.45 = avg. thrust in pounds 1050 / 4.45 = 235.95 - Thrust (lbs) / total vehicle weight (lbs) = Thrust to Weight ratio 235.95 / 24.4 = 9.67 Thrust Ratio - Generally accepted minimum 5:1 Rail Exit Velocity : 65.77 fps

Parachute Sizes & Descent Rates Recovery system data Drogue Size – 30” Altitude at deployment – 2862 ft Time of deployment – 12.14 seconds after launch Velocity at deployment - .86 fps Predicted descent rate - 74 fps Main Size – 84” Altitude at deployment –400 ft Time of deployment – 45 seconds after launch Velocity at deployment - 74 fps Predicted descent rate - 24.97 fps

Test Plans & Procedures Ground test (vacuum jar) of complete avionics sled (4 altimeters). Launch prep and sequence will be reviewed and finalized during ground tests. Verification of reliability in both data collection and recovery deployment during ground tests. Ejection charge ground tests will be performed. Our launch and safety procedures will follow NAR guidelines.

Scale Model Flight Test Rocket design performed well Powerful, straight flights in windy conditions Successful recovery deployment Initial altitude readings: 1,100 and 1,800 feet

Scale Model Flight Test Electronics Issues Second flight data stream incomplete due to poorly charged battery Data examination revealed severe pressure spike at ejection Additional experience needed with data retrieval and manipulation

Dual Deployment Avionics Test Our final ground test plans will merge the pre-flight procedures from both brands of altimeters. Simple “vacuum jar” tests will be performed. Both simple circuit tests (LED) and charge tests will be performed.

Ejection Charge Amount Test Ejection charge testing will be conducted. Current estimates for black powder charge For a 6” airframe, 5.3 psi is desirable (150 lbs force) C * D * D * L = grams of BP .002 * 6*6*12 = .86 g Main .002 * 6*6*8 = .58 g Drogue

Payload Integration Feasibility The payload is essentially a double-redundant dual deployment system employing high-rate altitude and G-force data recording Integration appears to be no more complex than a standard dual-deploy avionics configuration

Questions?