The Lake Zurich Rocketry Team and Responsibilities • Eric P • Team Leader • Payload Manager • Documentation Manager • Michael B • Building Team Manager • Safety Manager • Sean K • Outreach • Materials Manager • Jacob E • Launch Manager • Budget Manager • Mike P • Technology Manager • Equipment and Facility Manager • Michael G • Recovery Manager • Communications Manager • Brian G • Technical Manager • MSDS Manager
Vehicle dimensions, materials, and justifications – cont. • Carbon Fiber airframe was selected due to weight concerns of the total rocket, and • the required durability to reduce damage and ‘zippers’. • Special epoxy will be used wherever a bond to the carbon fiber airframe is required.
Static Stability Margin Static Stability Margin The team has used RockSim to arrive at a safe Stability Margin, and will also use physical Measurements to verify these results.
Vehicle Safety Verification and Testing • Systems and Subsystems to be tested and verified: • Airframe Structural Strength – Flight testing and analysis • Fins – Flight testing and analysis • Rocket Stability – RockSim and physical measurements • Motor Selection – RockSim, and manufacturer specs. • Ejection System – low pressure ground testing and flight testing • Recovery System – (chutes and shock cords) stress testing and flight testing • Payload – analysis, weather balloon testing, and flight testing • Test Dates: • Ejection and Recovery Systems: 1/17/2012, 2/25/2012, 3/3/2012, 3/17/2012 • Test Flights – Sub-scale: 1/17/2012 • Test Flights – Full-scale: 3/17/2012, 4/07/2012 • Payload testing: in December and January – as weather permits • Team Safety Managers will be briefing the team every other week on safety issues • and training. They will also be responsible for executing the team safety plan, and • maintaining a safe environment.
Motor Selection and Justification • Motor Selected: Aerotech K1050W • Total Impulse = 2522.038 Ns • Size= 54mm diameter x 62.7 cm length • Total Weight = 2203 g • Prop Weight = 1265 g • Maximum Thrust = 2172 N • Average Thrust = 1132.9 N • Burn Time = 2.1 sec
Thrust to Weight Ratio and Rail Exit Velocity • Thrust to Weight Ratio • Rocket weight = 10.9999 kg • Thrust = 2522.038 Ns • Ratio = 23.378 to 1 • Rail Exit Velocity • Launch Rail Length = 120” • Exit Velocity = 83.8321 ft/s
Launch Vehicle Verification and Test Plan PDR Requirements and Launch Vehicle Verification and Testing to Meet these Criteria Team Safety Managers will be briefing the team every other week on safety issues and training. They will also be responsible for executing the team safety plan, and maintaining a safe environment
Launch Vehicle Verification and Test Plan – cont. PDR Requirements and Launch Vehicle Verification and Testing to Meet these Criteria Team Safety Managers will be briefing the team every other week on safety issues and training. They will also be responsible for executing the team safety plan, and maintaining a safe environment
Major Components and Subsystems Launch Vehicle Systems • Launch System – the system to ignite the motor, the launch buttons, and the launch rail must all operate according to safe launch procedures. • Launch checklist – all team members must complete their assigned tasks as outlined in the Launch Checklist. • Motor System – the motor must operate as designed, and the structural system holding ht motor in the rocket must be secure and durable. • Ejection System – the altimeters and ejection charges must fire as planned in order to ensure a safe deployment of the recovery system. This is a critical subsystem in our project, and impacts not only the mission outcome, but also the safety of the team and bystanders. • Recovery System – the parachutes and shock cords must deploy correctly, and work to slow the LV to a safe velocity during descent. • Recovery Checklist – each team member must perform their assigned checklist duties to ensure safe and reliable recovery of the rocket, components, and data.
Major Components and Subsystems – cont. Recovery System • Avionics Bay Assembly Forward and Aft Bulkplates Electronics Sled housed in the Avionics Bay
Major Components and Subsystems – cont. Recovery System • Ejection Charges • Payload – Drogue Chute • Free volume = 622.04 ci • Charge size = 3 grams • Booster – Main Chute • Free volume = 235.62 ci • Charge size = 3 grams • Parachutes • Drogue Chute • Weight = .6 oz. • Diameter = 18” • Descent Velocity = 115.34 ft/sec • Main Chute • Weight = 11 oz. • Diameter = 78” • Descent Velocity = 17.83 ft/sec Recovery Note – The Launch Vehicle will descend without the payload and nose cone. This required a separate RockSim simulation to calculate for this different weight.
Payload Design Payload System
Payload Verification and Testing Payload Verification
Payload Verification and Testing – cont. Payload Testing
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