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

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Critical Design Review

University of Illinois at Urbana-Champaign NASA Student Launch 2017-2018

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Overview

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Launch Vehicle Summary

Javier Brown

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Flight Profile

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Current Launch Vehicle Design

1) Ejection charge at apogee 2) Drogue deployment at 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): 12’’

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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

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Static Stability Margin

• Stability @ liftoff: 2.42 calibers
• Current CP location: 97.064’’
• Static CG location: 82.331’’

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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

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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

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Booster Subsystem

• Housing for the Motor Subsystem
• 3 16

′′ fiberglass fins

– 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

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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)

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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

• 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

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Upper Airframe

• Houses Payload

– Hardware and Electronics

• Contains main parachute

– Shock cord

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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

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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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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

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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.

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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 Airframe

9.3 590 1041.4 1614.3 2335.32

Nosecone

9.3 349.1 791.1 1430 2117

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Kinetic Energy

• Predictions determined using OpenRocket.
• Terminal Velocities

– Nosecone – 20.67 ft/s – Upper Airframe and Booster Frame 1st 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

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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

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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 – 2.27 calibers

• Data from test launch was used to address the possible performance

issues that may arise in the full scale model

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Subscale Launch Vehicle

• Test flight occurred on January 8th, 2018 in Wisconsin
• Team members were able to practice proper launch preparation techniques

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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.

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Comparison between Flight Data and Simulation

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Deployable Rover Payload

Destiny Fawley and Ryan Noe

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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

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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
• Axle gear bolted to bulkhead
• Servomotor rotates platform
• Rover secured with servo latches

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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

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Wheel Orientation and Rover Mobility

MORRTE Wheel Configuration

• Segmented body provides mobility

– Similar to RHex robot – Bio-inspired – Six wheels provide redundancy – Will be updated with grip pads

Path of Travel

Rhex Robot

Image from makezine.com

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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

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Latching Mechanism

• Locking Mechanism

– Controlled by Lazy Susan Arduino – Thicker hooks for strength – 0.2” hook clearance – 0.1” servo clearance

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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

Servo 3D Printed Hinge Solar Cells

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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

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Questions?