Preliminary Design Review University of Illinois at Urbana-Champaign - PowerPoint PPT Presentation

Preliminary Design Review University of Illinois at Urbana-Champaign NASA Student Launch 2017-2018 Illinois Space Society 1

Team Composition Project Manager: Andrew Koehler Structures & Recovery: Payload: Safety Officer: Javier Brown Destiny Fawley Courtney Leverenz Illinois Space Society 2

Launch Vehicle Summary Javier Brown Illinois Space Society 3

Flight Profile Illinois Space Society 4

Current Launch Vehicle Design 3) Nose cone separation and parachute deployment at 1000 feet 1) Separation at apogee Nose cone Upper body tube 2) Drogue deploy approximately 2 seconds after apogee 4) Main parachute deployment at 800 feet Coupler Booster tube Illinois Space Society 5

Vehicle Major Dimensions Total Length: 130’’  Total Mass: 43.5 lb.  Nosecone: 30’’   Upper Airframe: 48’’  Payload Bay: 14’’  Avionics Coupler: 16’’  Booster Frame: 48’’  Outer Diameter: 6’’  Root Chord (Fins): 10’’ Illinois Space Society 6

Launch Vehicle Materials  Upper Airframe and Booster Frame: Blue Tube – High Strength – Proven benefits seen from past usage  Bulkheads: Aircraft Plywood – Adequate structure support Layered to 0.25’’ thickness –  Centering Rings: Aircraft Plywood – Desired additional support due to thrust considerations  Fins and Nosecone: Fiberglass – High Strength – Proven benefits seen from past usage Illinois Space Society 7

Static Stability Margin  Stability @ liftoff: 2.33 calibers  Current CP location: 97.985’’  Static CG location: 83.3’’ Illinois Space Society 8

Motor Selection Motor: L1300R-P  Diameter: 3.86’’  Max thrust: 349 lbf ･ s  Total impulse: 1024 lbf  Burn time: 3.44s  T/W ratio: 7.87  Off-rail speed: 68.5 ft/s Illinois Space Society 9

Motor Subsystem  RMS 98/5120 Motor Casing ‘ – Constructed from high strength aluminum  Motor Mount Tube – 22’’ Blue tube (Vulcanized, high density) – Center rings permanently fixed  Plywood centering rings – Utilized 3 rings for assurance  Aero pack 98 mm Retainer Illinois Space Society 10

Booster Subsystem  Housing for the Motor Subsystem ′′ fiberglass fins 3 16  Τ – Slotted between centering rings and filleted for absolute support  Integrated 1515 rail buttons (x2)  Houses drogue parachute – (deploys approx. 2s after apogee) Drogue parachute Rail button Illinois Space Society 11

Avionics Coupler Section  Parachute connections via U-bolts 1 4 ’’ threaded rods to support sled  Τ  Contains recovery electronics and ejection charges  4 ’’ Switch Band – Rotary Switches (x2) Illinois Space Society 12

Avionics Bay Recovery Hardware  Parachutes – Main: Iris Ultra 96’’ – Drogue: Fruity Chutes Elliptical 18’’ – Nosecone: SkyAngle 36’’  Black powder ejection charges – Ignited by e-matches 1 2 ’’ tubular Kevlar shock cord  Τ  Redundant altimeters – 1 Telemetrum altimeter for altitude and tracking – 1 Stratologger altimeter for altitude • Will be official competition altimeter Illinois Space Society 13

Upper Airframe  Houses Payload – Hardware and Electronics  Contains main parachute – Shock cords Illinois Space Society 14

Nosecone  6’’ Ogive 5:1 (shape)  Material: Fiberglass  Houses nosecone electronics and hardware – Parachute and shock cord – Redundant Altimeters (x2) • Telemetrum • Stratelogger – Official competition altimeter Illinois Space Society 15

Custom MATLAB Flight Simulator User Interface  OpenRocket simulation tools were also utilized and verified with MATLAB. Illinois Space Society 16

Flight Simulations Illinois Space Society 17

Simulation Results  Apogee: – OpenRocket – 5295 ft – MATLAB – 4805 ft  Offrail Velocity: – OpenRocket – 68.5 ft/s – MATLAB - 66.1 ft/s  Maximum velocity: – OpenRocket – 640 ft/s – MATLAB – 602 ft/s – Vertical Velocity (Avg) – 621 ft/s  Future wok will be conducted to narrow the discrepancies between the custom MATLAB simulator and OpenRocket, using higher fidelity models. Illinois Space Society 18

Drift Predictions  Predictions determined using OpenRocket. Will be verified by MATLAB in future work.  All predictions are well within the stipulated threshold of 2640 ft. Drift in 0 mph Drift in 5 mph Drift in 10 mph Drift in 15 mph Drift in 20 mph Section winds winds winds winds winds (ft) (ft) (ft) (ft) (ft) Booster and Upper 9.125 380.5 750 1230 1775 Airframe Nosecone 9.125 303.5 671 1180 1765 Illinois Space Society 19

Kinetic Energy  Predictions determined using OpenRocket.  Terminal Velocities – Nosecone – 23.9 ft/s – Upper Airframe and Booster Frame 1 st separation: • Drogue – 110 ft/s • Main – 15.54 ft/s  Kinectic Energies – Booster Frame – 62.48 ft ･ lbf – Avionics Coupler – 18.54 ft ･ lbf – Upper Airframe – 36.78 ft ･ lbf – Nosecone – 56.82 ft ･ lbf  All kinectic energies are with specified threshold of 75 ft ･ lbf Illinois Space Society 20

Vehicle Verification Plan  Detailed verification plan can be found in PDR report  Focus on quantitative comparison – Scrutinize and catalog launch vehicle components as they arrive  Paramount milestones – Incremental testing of all components during the build process – Aerodynamics to be validated from subscale launch – Full-scale model verified during test launch Illinois Space Society 21

Subscale Vehicle  ~ 1/2 scale model of full-scale launch vehicle – Material - Exact to that of the full-scale vehicle – Stability margin – 2.05 calibers  Data from test launch will be used to refine the full-scale vehicle  Parts have been ordered and test launch to be conducted before winter break. Illinois Space Society 22

Deployable Rover Payload Destiny Fawley Illinois Space Society 23

Payload Requirements  Design a remotely activated custom rover that will deploy from the internal structure of the launch vehicle. - Must remain inside rocket until landed - On-board communication system - Correct orientation to exit after landing  The rover will autonomously move at least 5 ft. (in any direction) from the launch vehicle. - On-board program facilitates movement - Traverse field terrain  Once the rover has reached its final destination, it will deploy a set of foldable solar cell panels. - Solar panel deployment mechanism on rover  Internal Requirements - 5 lb. or less - 6 ” or smaller diameter rocket Illinois Space Society 24

Payload Overview  Two systems: - Lazy Susan Orientation Mechanism - Deployable Rover Lazy Susan Orientation Mechanism Deployable Rover Illinois Space Society 25

Lazy Susan Orientation Mechanism  Screw bulkhead into body tube  Bulkhead gear attached to bulkhead  Servomotor rotates platform Threaded Holes Platform Servomotor Bulkhead Gear Illinois Space Society 26

Lazy Susan Orientation Mechanism  Lazy Susan controlled by Arduino  Input from accelerometer  9V Battery (not shown) Arduino Accelerometer Illinois Space Society 27

Wheel Orientation and Rover Mobility  Segmented body provides mobility. – Similar to RHex robot – Bio-inspired – Six wheels provide redundancy Wheel Configuration  Wheels operate like legs and wheels. – Will be updated with grip pads Illinois Space Society 28

Sensors and Power Systems  Close-up of stationary Arduino – Uses gyroscope to rotate Lazy Susan mechanism. – Powered by 9V battery.  Close-up of rover Arduino – Uses gyroscope to detect when movement should be initiated – Powered by 9V battery as well, but may be LiPo later on. Illinois Space Society 29

Latching Mechanism Locking Arm Servo Illinois Space Society 30

Solar Panel Deployment  Spring-loaded hinges – Open solar panels easier – Hold cells together  Servo facilitates opening and closing Spring-loaded hinge Servo Illinois Space Society 31

Questions? Illinois Space Society 32