preliminary design...

Illinois Space Society 1

Preliminary Design ReviewUniversity of Illinois at Urbana-Champaign

NASA Student Launch 2017-2018

Illinois Space Society 2

Team Composition

Structures & Recovery:Javier Brown

Payload:Destiny Fawley

Safety Officer:Courtney Leverenz

Project Manager:Andrew Koehler

Illinois Space Society 3

Launch Vehicle Summary

Javier Brown

Illinois Space Society 4

Flight Profile

Illinois Space Society 5

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

Illinois Space Society 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): 10’’

Illinois Space Society 7

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

Illinois Space Society 8

Static Stability Margin

Stability @ liftoff: 2.33 calibers

Current CP location: 97.985’’

Static CG location: 83.3’’

Illinois Space Society 9

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

Illinois Space Society 10

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

Illinois Space Society 11

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

Illinois Space Society 12

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)

Illinois Space Society 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

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

Illinois Space Society 14

Upper Airframe

Houses Payload

– Hardware and Electronics

Contains main parachute

– Shock cords

Illinois Space Society 15

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

Illinois Space Society 16

Custom MATLAB Flight Simulator User Interface

OpenRocket simulation tools were also utilized and verified with MATLAB.

Illinois Space Society 17

Flight Simulations

Illinois Space Society 18

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.

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.

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

Illinois Space Society 20

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

Illinois Space Society 21

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

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 – 2.05 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.

Illinois Space Society 23

Deployable Rover Payload

Destiny Fawley

Illinois Space Society 24

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

Illinois Space Society 25

Payload Overview

Lazy Susan Orientation Mechanism

Deployable Rover

Two systems:

- Lazy Susan Orientation Mechanism

- Deployable Rover

Illinois Space Society 26

Lazy Susan Orientation Mechanism

Screw bulkhead into body tube

Bulkhead gear attached to bulkhead

Servomotor rotates platform

Threaded Holes

Bulkhead Gear

Platform Servomotor

Illinois Space Society 27

Lazy Susan Orientation Mechanism

Lazy Susan controlled by Arduino

Input from accelerometer

9V Battery (not shown)

Arduino

Accelerometer

Illinois Space Society 28

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

Illinois Space Society 29

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.

Illinois Space Society 30

Latching Mechanism

Locking Arm

Servo

Illinois Space Society 31

Solar Panel Deployment

Spring-loaded hinges

– Open solar panels easier

– Hold cells together

Servo facilitates opening and closing

Servo

Spring-loaded hinge

Illinois Space Society 32

Questions?