Preliminary Design...
Transcript of Preliminary Design...
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Illinois Space Society 1
Preliminary Design ReviewUniversity of Illinois at Urbana-Champaign
NASA Student Launch 2017-2018
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Team Composition
Structures & Recovery:Javier Brown
Payload:Destiny Fawley
Safety Officer:Courtney Leverenz
Project Manager:Andrew Koehler
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Launch Vehicle Summary
Javier Brown
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Flight Profile
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Current Launch Vehicle Design
1) Separation at apogee
2) Drogue deploy approximately 2 secondsafter apogee
4) Main parachute deployment at 800 feet
3) Nose cone separation and parachute deployment at 1000 feet
Nose cone
Upper body tube
Coupler
Booster tube
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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’’
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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
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Static Stability Margin
Stability @ liftoff: 2.33 calibers
Current CP location: 97.985’’
Static CG location: 83.3’’
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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
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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
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Booster Subsystem
Housing for the Motor Subsystem
Τ3 16′′
fiberglass fins
– 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
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Avionics Coupler Section
Parachute connections via U-bolts
Τ1 4’’ threaded rods to support sled
Contains recovery electronics and ejection charges
4’’ Switch Band
– Rotary Switches (x2)
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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
Τ1 2’’ tubular Kevlar shock cord
Redundant altimeters
– 1 Telemetrum altimeter for altitude and tracking
– 1 Stratologger altimeter for altitude
• Will be official competition altimeter
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Upper Airframe
Houses Payload
– Hardware and Electronics
Contains main parachute
– Shock cords
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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
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Custom MATLAB Flight Simulator User Interface
OpenRocket simulation tools were also utilized and verified with MATLAB.
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Flight Simulations
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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.
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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
Airframe9.125 380.5 750 1230 1775
Nosecone 9.125 303.5 671 1180 1765
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Kinetic Energy
Predictions determined using OpenRocket.
Terminal Velocities
– Nosecone – 23.9 ft/s
– Upper Airframe and Booster Frame 1st 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
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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
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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.
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Deployable Rover Payload
Destiny Fawley
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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
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Payload Overview
Lazy Susan Orientation Mechanism
Deployable Rover
Two systems:
- Lazy Susan Orientation Mechanism
- Deployable Rover
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Lazy Susan Orientation Mechanism
Screw bulkhead into body tube
Bulkhead gear attached to bulkhead
Servomotor rotates platform
Threaded Holes
Bulkhead Gear
Platform Servomotor
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Lazy Susan Orientation Mechanism
Lazy Susan controlled by Arduino
Input from accelerometer
9V Battery (not shown)
Arduino
Accelerometer
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Wheel Orientation and Rover Mobility
Wheel Configuration
Segmented body provides mobility.
– Similar to RHex robot
– Bio-inspired
– Six wheels provide redundancy
Wheels operate like legs and wheels.
– Will be updated with grip pads
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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.
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Latching Mechanism
Locking Arm
Servo
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Solar Panel Deployment
Spring-loaded hinges
– Open solar panels easier
– Hold cells together
Servo facilitates opening and closing
Servo
Spring-loaded hinge
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Questions?