Critical Design Review
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1 Critical Design Review University of Illinois at Urbana-Champaign NASA Student Launch Illinois Space Society 1
2 Overview Illinois Space Society 2
3 Launch Vehicle Summary Javier Brown Illinois Space Society 3
4 Flight Profile Illinois Space Society 4
5 Current Launch Vehicle Design Nose cone 1) Ejection charge at apogee 3) Nose cone separation and parachute deployment at 1000 feet Upper body tube 2) Drogue deployment at apogee Coupler 4) Main parachute deployment at 800 feet Booster tube Illinois Space Society 5
6 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
7 Launch Vehicle Materials Upper Airframe and Booster Frame: High Strength Proven benefits based on past usage Blue Tube Bulkheads: Adequate structure support 0.25 thick Aircraft Plywood Centering Rings: Desired additional support due to thrust considerations Aircraft Plywood Fins and Nosecone: High Strength Proven benefits based on past usage Fiberglass Illinois Space Society 7
8 Static Stability Margin liftoff: 2.42 calibers Current CP location: Static CG location: Illinois Space Society 8
9 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
10 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 Motor Subsystem Illinois Space Society 10
11 Housing for the Motor Subsystem fiberglass fins 3 16 Booster Subsystem 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
12 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
13 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
14 Upper Airframe Houses Payload Hardware and Electronics Contains main parachute Shock cord Illinois Space Society 14
15 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
16 Custom MATLAB Flight Simulator User Interface OpenRocket simulation tools were also utilized and verified with MATLAB. Illinois Space Society 16
17 Flight Simulations Illinois Space Society 17
18 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
19 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 Simulation Results Future work will be conducted to narrow the discrepancies between the custom MATLAB simulator and OpenRocket, using higher fidelity models. Illinois Space Society 19
20 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. Section Drift in 0 mph winds (ft) Drift in 5 mph winds (ft) Drift in 10 mph winds (ft) Drift in 15 mph winds (ft) Drift in 20 mph winds (ft) Booster and Upper Airframe Nosecone Illinois Space Society 20
21 Predictions determined using OpenRocket. Terminal Velocities Nosecone ft/s Upper Airframe and Booster Frame 1 st separation: Drogue ft/s Main ft/s Kinetic Energies Booster Frame ft lbf Avionics Coupler ft lbf Upper Airframe ft lbf Nosecone ft lbf All kinetic energies are with specified threshold of 75 ft lbf Kinetic Energy Illinois Space Society 21
22 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
23 ~ 1/2 scale model of full-scale launch vehicle Material - Exact to that of the full-scale vehicle Stability margin 2.27 calibers Subscale Vehicle Data from test launch was used to address the possible performance issues that may arise in the full scale model Illinois Space Society 23
24 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
25 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
26 Comparison between Flight Data and Simulation Illinois Space Society 26
27 Deployable Rover Payload Destiny Fawley and Ryan Noe Illinois Space Society 27
28 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
29 Payload Overview Two systems: - Lazy Susan Orientation Mechanism - Deployable Rover Deployable Rover Lazy Susan Orientation Mechanism Illinois Space Society 29
30 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
31 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
32 Wheel Orientation and Rover Mobility Segmented body provides mobility Similar to RHex robot Bio-inspired Six wheels provide redundancy Will be updated with grip pads Rhex Robot Image from makezine.com MORRTE Wheel Configuration Path of Travel Illinois Space Society 32
33 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
34 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
35 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 Panel Deployment Servo Solar Cells 3D Printed Hinge Illinois Space Society 35
36 System Dimensions/Mass Rover x 3.94 x 4.35 Platform x 4.5 x 4.25 Total Mass: 3.75 lbm Illinois Space Society 36
37 Questions? Illinois Space Society 37
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