preliminary design...

Illinois Space Society 1

Preliminary Design ReviewUniversity of Illinois at Urbana-Champaign

NASA Student Launch 2017-2018


Team Composition

Structures & Recovery:Javier Brown

Payload:Destiny Fawley

Safety Officer:Courtney Leverenz

Project Manager:Andrew Koehler


Launch Vehicle Summary

Javier Brown


Flight Profile


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


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’’


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


Static Stability Margin

Stability @ liftoff: 2.33 calibers

Current CP location: 97.985’’

Static CG location: 83.3’’


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


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


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


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)


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


Upper Airframe

Houses Payload

– Hardware and Electronics

Contains main parachute

– Shock cords


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


Custom MATLAB Flight Simulator User Interface

OpenRocket simulation tools were also utilized and verified with MATLAB.


Flight Simulations


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.


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


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


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


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.


Deployable Rover Payload

Destiny Fawley


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


Payload Overview

Lazy Susan Orientation Mechanism

Deployable Rover

Two systems:

- Lazy Susan Orientation Mechanism

- Deployable Rover



Screw bulkhead into body tube

Bulkhead gear attached to bulkhead

Servomotor rotates platform

Threaded Holes

Bulkhead Gear

Platform Servomotor



Lazy Susan controlled by Arduino

Input from accelerometer

9V Battery (not shown)

Arduino

Accelerometer


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


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.


Latching Mechanism

Locking Arm

Servo


Solar Panel Deployment

Spring-loaded hinges

– Open solar panels easier

– Hold cells together

Servo facilitates opening and closing

Servo

Spring-loaded hinge


Questions?

preliminary design...

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