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

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

Overview 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) Ejection charge at apogee Nose cone Upper body tube 2) Drogue deployment at 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): 12’’ Illinois Space Society 6

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

Static Stability Margin  Stability @ liftoff: 2.42 calibers  Current CP location : 97.064’’  Static CG location : 82.331’’ Illinois Space Society 8

Motor Selection Motor: L1420R-P  Diameter : 2.95’’  Max thrust: 374 lbf ･ s  Total impulse: 1038 lbf  Burn time: 3.18s  T/W ratio: 8.48  Off-rail speed: 60.1 ft/s Illinois Space Society 9

Motor Subsystem  RMS 75/5120 Motor Casing – Constructed from high strength aluminum  Motor Mount Tube – 24’’ Blue tube (Vulcanized, high density) – Center rings permanently fixed  Plywood centering rings – Utilized 3 rings for assurance  Aero pack 75 mm Retainer Illinois Space Society 10

Booster Subsystem  Housing for the Motor Subsystem ′′ fiberglass fins  3 16 – Slotted between centering rings and filleted for absolute support  Integrated 1515 rail buttons (x2)  Houses drogue parachute and tubular Kevlar shock cord – deploys at apogee Rail button Illinois Space Society 11

Avionics Coupler Section  Parachute connections via U-bolts 1 4 ’’ threaded rods to support sled   Contains recovery electronics and ejection charges  3’’ 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  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 cord 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 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

CFD Analysis  Pressure analysis conducted on the launch vehicle  Determine the reliability and safety of avionics in the nosecone  Pressure variations subside very quickly as curvature decreases Illinois Space Society 18

Simulation Results  Apogee: – OpenRocket – 5438 ft – MATLAB – 5010 ft  Offrail Velocity: – OpenRocket – 60.1 ft/s – MATLAB – 63.7 ft/s  Maximum velocity: – OpenRocket – 678 ft/s – MATLAB – 701 ft/s – Vertical Velocity (Avg) – 643 ft/s  Future work will be conducted to narrow the discrepancies between the custom MATLAB simulator and OpenRocket, using higher fidelity models. Illinois Space Society 19

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 (ft) winds (ft) winds (ft) winds (ft) winds (ft) Booster and 9.3 590 1041.4 1614.3 2335.32 Upper Airframe Nosecone 9.3 349.1 791.1 1430 2117 Illinois Space Society 20

Kinetic Energy  Predictions determined using OpenRocket.  Terminal Velocities – Nosecone – 20.67 ft/s – Upper Airframe and Booster Frame 1 st separation: • Drogue – 36.27 ft/s • Main – 11.95 ft/s  Kinetic Energies – Booster Frame – 26.25 ft ･ lbf – Avionics Coupler – 14.74 ft ･ lbf – Upper Airframe – 21.55 ft ･ lbf – Nosecone – 29.85 ft ･ lbf  All kinetic energies are with specified threshold of 75 ft ･ lbf Illinois Space Society 21

Vehicle Verification Plan  Detailed verification plan can be found in CDR 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 have been verified by subscale launch but other performance issues were observed and addressed as they occured. – Full-scale model will be verified during test launch Illinois Space Society 22

Subscale Vehicle  ~ 1/2 scale model of full-scale launch vehicle – Material - Exact to that of the full-scale vehicle – Stability margin – 2.27 calibers  Data from test launch was used to address the possible performance issues that may arise in the full scale model Illinois Space Society 23

Subscale Launch Vehicle  Test flight occurred on January 8 th , 2018 in Wisconsin  Team members were able to practice proper launch preparation techniques Illinois Space Society 24

Subscale Flight Results  Off rail launch procedure was precise and typical of any launch. All recovery systems worked without problems.  There was some deviation from the flight profile, which may have been the result of stability issues manifesting in the vehicle.  It is suspected that the fins were not suitable. Illinois Space Society 25

Comparison between Flight Data and Simulation Illinois Space Society 26

Deployable Rover Payload Destiny Fawley and Ryan Noe Illinois Space Society 27

Payload Requirements  Design a remotely activated custom rover that deploys 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 cells. - Solar panel deployment mechanism on rover  Internal Requirements - 5 lb. or less - 6” or smaller diameter rocket Illinois Space Society 28

Payload Overview  Two systems: - Lazy Susan Orientation Mechanism - Deployable Rover Deployable Rover Lazy Susan Orientation Mechanism Illinois Space Society 29

Lazy Susan Orientation Mechanism  Screw bulkhead into body tube  Axle gear bolted to bulkhead  Servomotor rotates platform  Rover secured with servo latches Illinois Space Society 30

Lazy Susan Orientation Mechanism  Lazy Susan controlled by Arduino Micro  Redundant Rotation Trigger – Detect launch/landing with accelerometer/gyro – Receive signal from Ground Station  Rotate platform with gyroscope input Illinois Space Society 31

Wheel Orientation and Rover Mobility  Segmented body provides mobility Rhex Robot – Similar to RHex robot – Bio-inspired – Six wheels provide redundancy – Will be updated with grip pads Image from makezine.com MORRTE Wheel Configuration Path of Travel Illinois Space Society 32

Rover Sensors and Power Systems  Redundant Drive Trigger – Time delay from ground station signal – Lazy Susan ‘Green’ signal  Drive forward  Deploy solar panel – Record solar power data Middle Segment Illinois Space Society 33

Latching Mechanism  Locking Mechanism – Controlled by Lazy Susan Arduino – Thicker hooks for strength – 0.2” hook clearance – 0.1” servo clearance Illinois Space Society 34

Solar Panel Deployment  3D printed non-spring loaded hinges – Shape to fit solar cells – Facilitate solar panel deployment – Hold cells together  Servo controls movement – Actively holds closed during launch – Opens hinge when commanded by Arduino Solar Cells 3D Printed Hinge Servo Illinois Space Society 35

System Dimensions/Mass  Rover – 12.77 x 3.94 x 4.35”  Platform – 14.12 x 4.5 x 4.25”  Total Mass: 3.75 lbm Illinois Space Society 36