1. Preliminary Design Review NASA University Student Launch Initiative University of Nebraska–Lincoln 2012-2013

2. 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

4. Preliminary Design Discussion

5. Vehicle Overview Length:113” Diameter:6” Nose cone:34.6”Von Karman (LD-Haack), 5.5:1 Fin span:15”(3-fin configuration) Weight:35.9(With motor and payload) Motor Mount:98mm31” long

6. Kinetic Energy Section Kinetic Energy (ft-lbs) 153.459 219.498 344.604 47.06 Section Kinetic Energy (ft-lbs) 11101.7 2354.94 3811.99 4N/A Landing Velocity Terminal Velocity Wind Speed (mph)Time (s)Distance From Launchpad (ft) No Wind137.99.02776 5137.21629.4 10138.161274.7 15137.701982.6 20136.902,761.6 Wind Speed (mph)Time (s)Distance From Launchpad (ft) 20121.532,206.5 Ejection Charge is set for 1500ft Ejection Charge is set for 1000ft

7. Stability Characteristics OpenRocket Model Will need to be verified Mass (with motor): 35.9 lbs CG: 66.9 inches CP: 77 inches

8. Flight Simulation

9. Plans for Vehicle Safety RiskConsequencePrecautionary Measures Misuse of Power Tools Bodily Injury: Cuts, Abrasions, and Bruises Work stoppage Instructions will be given prior to student use of equipment. Experienced technicians or upper classmen must be present for all machining. Unintentional Ignition of Igniters or Electric Matches Bodily Injury: Minor Burns Fire Lose of critical supplies All electric matches will be shorted together at their ends. Proper storage in secure grounded case

10. Plans for Vehicle Safety RiskConsequencePrecautionary Measures Unintentional Detonation of Black Powder Bodily Injury: Serious Burns, and hearing loss Ejection charges will be filled last with flight computers deactivated. Handlers will wear work gloves and Ear Plugs. Unintentional Ignition of Motor Bodily Injury: Serious Burns, Bruises, Loss of Life Cancellation of Flight Property Damage All motors stored unloaded without igniters. Prepared motors will not be loaded with igniters until mounted on pad. Loading must be supervised or performed by Certified personnel.

11. Plans for Vehicle Safety RiskConsequencePrecautionary Measures Component Damage Through Testing Increased costs Project Delays Redesigns Grounded equipment used when handling sensitive electronics. Wearing necessary and precautionary safety equipment. Only required personnel allowed in proximity to components during testing. Checklists utilized to ensure proper procedures during operation Contact with Hazardous Chemicals and Materials Bodily Injury: Irritation, burns, and allergic reaction Work stoppage Material Safety Data Sheets of all hazardous chemicals and materials will be available to and reviewed by all members. Facilities with fume hoods will be used for caustic materials. Protective equipment including, but not limited to, gloves, safety glasses, and filtered face masks.

12. Plans for Vehicle Safety RiskConsequencePrecautionary Measures Launch and Recovery Problems Loss of Vehicle Loss of Payload Serious Bodily Injury or Death Property Damage Following TRA/NAR Safety Code Use of checklists Cancellation of Launch in event of adverse weather conditions. All personnel must be at safe distance before ignition system is armed.

13. Launch Characteristics Candidate Motors –75mm diameter –Aerotech L1520T-P Simulation Parameters –10 foot guide rail Rail velocity: 43.32 feet/sec Thrust-to-weight ratio: 10.72

14. Launch Vehicle Verification SubsystemTest PlanVerification MetricTarget Date Altimeter Accuracy Subscale Test flights Agreement between altimeters December 2012 Recovery System Deployment Ground Simulation Test flights Components ejected forcefully Visually confirm deployment Vehicle recovered intact January 2013 Tracking Equipment Ground distance test Test flights Line of sight transmission at least 1 mile Successful tracking after launch December 2012 Motor integration Test fit Fit adapter if needed No shifting of motor Motor housed internally January 2013 Altitude Full scale test flight for both candidate motors Add ballast as needed Compare recorded altitudes with that of simulations February – March 2013

15. System Overview

16. Assembly

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

18. 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”

19. 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

20. Recovery Mounting –Nosecone Tethered to Transition –Transition Tethered to Booster –Forged U-Bolts Concept of Operations –Drogue @ Apogee –Main @ 1,500-Feet ComponentCharacteristic DimensionComment Main Parachute108”16” Spill hole Drogue24”X-form Shock Cord52’1” Tubular Nylon Nomex Wadding24”

21. Booster Assembly Components –98mm MMT + Retaining Ring –Fins x 3 –Coupler Material –Carbon Fiber –Fiberglass (8oz) Dimensions –Length 50 inches

22. Fins Material –1/8-inch G10 fiberglass –Fiberglass –Vinyl Ester Resin Construction –Laser cutting –Hand sanding –Vacuum Bagging Assembly –Mounting to MMT –Bond to booster –Tip to tip

23. 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

24. 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

25. Baseline Payload Design

26. SubsystemPre-Flight Test PlanVerification MetricTarget Date Payload Canister Mechanical Ejection Test Degree of separationFebruary 2013 Plane Component deployment Wings unfold Airspeed/resonance relationship Degree of MovementJanuary 2012 Sensors and transmitter Compare sensor data to know values Transmit data Sensor output values (received data ) w/in 1% of known values (transmitted data) February 2013

27. Activity Plans

28. Schedule

29. Budget

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