Critical Design Review NASA University Student Launch Initiative University of Nebraska–Lincoln

Team Overview Mission –Build a launch vehicle to reach an 5,280 feet altitude –Use a dual-deployment recovery system –Deploy a payload at 1,500 feet –Recover all components in a relaunchable condition

Preliminary Design Discussion

Vehicle Overview Length: 111” Diameter: 5.5” Nose cone: 34.6” Von Karman (LD-Haack), 5.5:1 Fin span: 15” (3-fin configuration) Weight:32.8 lbs(With motor and payload) Motor Mount:98mm31” long

Stability Characteristics OpenRocket Model Will need to be verified Mass (with motor): 32.8 lbs CG: 68.3 inches CP: 78.7 inches

Launch Characteristics Candidate Motors –75mm diameter –AMW L900RR-P Simulation Parameters –10 foot guide rail Rail velocity: feet/sec Thrust-to-weight ratio: 8.33:1

Recovery Mounting –Nosecone Tethered to Transition –Transition Tethered to Booster –Forged U-Bolts Concept of Operations Apogee 1,500-Feet Main parachute 84” in diameter, 162” long Drogue shute36” in diameter, X-form 52” and 30” of shock chord, 1 inch tubular nylon Nomex wadding, 24” length

Drift analysis

Kinetic Energy

Test Structural test 150+ lbs man No bending

Subscale Launch

Subscale Actual results Apogee 1357’ Max Vel. 459 ft/s Weight 1.873

Final Payload Design In our mission, the desired direction will be a GPS transmitter on the ground with the receiver in the probe. The goal is to have the GPS guide the probe using the systems on board to “Home base” which will be the launch pad. The scientific significance of this UAV is to introduce a convenience factor into recovery of rocket parts that have implicated the same hardware as this UAV will have.

Assembly

Nosecone Characteristics –Von Kármán (LD- Haack) –5.5:1 Fineness Communications –BRB 900 GPS Transmitter –Antenna

Transition Assembly Components –2 6-inch bulkheads –One small step for man –One 6-inch diameter polycarbonate plate –One GoPro camera –Two eyebolts Material –Alumium case Dimensions –Length – 6”

Avionics Components –Perfectflite StrattoLogger –Featherweight Raven Concept of Operation –Activated by external key switches –Primary charge fired by both altimeters –Secondary charge fires 5 seconds later by Raven

Functional Requirements SystemSubsystemRequirement Nosecone with payload bay Primary System Reduce drag force Must not deform under flight loading Mount drogue parachute Couple with Sustainer Communications Array Transmit GPS location to Ground Station TransitionPrimary System House recovery and avionics bays Must not deform under flight loading Couple to payload bay Couple to Booster Recovery Systems Tethers the Nosecone and Booster together Avionics Bay House Flight Computers Mount Ejections Charges Allows space for video camera

Functional Requirements SystemSubsystemRequirement BoosterPrimary System House motor mount tube Fin Mounting Couple to Sustainer Must not deform under flight loading Transfer fin moment Fins Stabilize vehicle for flight Must not deform under flight loading Motor Mount Tube Transfer axial motor thrust load Mount Parachute to Engine Block Retain motor Allow quick installation of motor

Schedule

Outreach Previous Activities –Engineering Week –Astronomy Day –Lockheed Martin Space Day Current Collaboration –Water rocketry –Hosting Robotic Competition –Connect a Million minds