Design and Development of a CubeSat De-Orbit Device

An Kim Cian Branco David Warner Edwin Billips Langston Lewis Thomas Work Mackenzie Webb Benjamin Cawrse (CS) Jason Harris (TCC)

Team Members

Thousands of man made objects in earth orbit (mostly junk).

Debris can be a serious hazard to satellites. A paint flake threatened the Space Shuttle;

a Russian Satellite disabled an Iridium satellite

Introduction

Debris in Earth’s Orbit

CubeSats are picosatellites used by universities and institutions for research in space.

Pending international treaty will require future launch stages and LEO satellites to deorbit within 25 years of mission completion.

Objective: design and test a de-orbit system to de-orbit CubeSats within 25 years of mission completion.

Introduction

Demonstrate commercial viability Prove it is a robust and viable system Achieve these objectives with a minimum

cost◦ Orbital demonstrator ◦ Suborbital flight◦ High altitude balloon flight

Objectives

Demonstrate commercial viability Prove it is a robust and viable system Achieve these objectives with a minimum

cost◦ Orbital demonstrator ◦ Suborbital flight◦ High altitude balloon flight

Objectives

Demonstrate commercial viability Prove it is a robust and viable system Achieve these objectives with a minimum

cost◦ Orbital demonstrator ◦ Suborbital flight◦ High altitude balloon flight

Objectives

Demonstrate commercial viability Prove it is a robust and viable system Achieve these objectives with a minimum

cost◦ Orbital demonstrator ◦ Suborbital flight◦ High altitude balloon flight

Objectives

The RockSat-X program out of Wallops Flight Facility is currently considered the best option for our test flight

RockSat-X utilizes the Terrier-Improved Malemute suborbital sounding rocket

The sounding rocket will reach apogee at approximately 160 km altitude from the Earth.

RockSat-X Program

300 seconds of microgravity flight Power and telemetry on deck provided for

timing devices, communication between ground and payload, and data storage

Direct access to orbital space after second stage burn-out when the skin of the sounding rocket is ejected.

Adequate space and weight capacity available to mount the deployment device and necessary telemetry for the mission of our CubeSat

Advantages of RockSat-X

ElectronicsLangston Lewis

Power Lithium-Ion batteries will be used to supply

power to the board and release mechanism. Can sustain high amounts of continuous

current discharge in order to run the camera and communications devices.

Mass of batteries is a concern

Arduino Board

•Stable operation between 6-20 volts•14 digital and 6 analog pins•Board has built in accelerometers

Strain Gauge•Mounted on aero brake support structure. •Voltage differences can be converted to strain and then used to calculate drag coefficient produced by balloon

Video Acquisition•160x120 resolution•Support capture JPEG from serial port•Default baud rate of serial port is 38400 but we will be transmitting at 19200•Works reliably with 5v power supply•Size 32X32mm•Consumes between 80-100 mA of current

Radio Communication•Low-power and weight in an equally small size•Provides adequate resolution and range

Objective:◦ Mylar Balloon

Test benzoic acid inflations under different temperature than the sublimating temperature

Calculate the correct benzoic acid mass to inflate the Mylar balloon within the vacuum chamber

Record time for the benzoic acid to fully inflate◦ Nitinol (SMA)

Aerodynamic Brake

Temperature for benzoic acid inflation◦ From Emerald Performance

Materials, estimated sublimation temp is C

◦ A thermistor will be use to vary temperature when testing benzoic acid inflation

Aerodynamic Brake

Mass of benzoic acid◦ The required amount of

benzoic acid will be less than 0.1 gram.

◦ The mass may vary to increase the rate of inflation

Aerodynamic Brake

http://social.rollins.edu/wpsites/chm220th/files/2011/09/photo-4.jpg

Time Limit◦ Must inflate in under

300 seconds◦ Goal of the

experiment is to have the Mylar Balloon to inflate in less than 200 seconds.

Aerodynamic Brake

David WarnerCian Branco

O-POD Design

ODU Picosatellite Orbital Deployer Bolted to Rocksat-X deck, “piggybacks” rocket Directly connected to RS-X Power Interface (1 A-

h) Stores, imparts ejection velocity to CubeSat

1.6 m/s from spring, lateral to deck Al-7075-T651 frame 1.477 kg total mass

O-POD Overview

O-POD SpecificationsMaterials

7mm thick Al-7075 plates

Holes can be cut for RS-X power interface & instruments

42 + 12 bolts (M4 x0.70 10mm)

ASTM-A228 “Music Wire” Spring

19.62cm length (entire)

7 turns coil

Held by crossbar on back plate

Supports pusher-plate

~1.5 kg total

Overall Dimensions

12.7cm x 12.7 cm x 19.62 cm

5 design iterations, still not space-rated Weak pusher-plate to spring connection Torsion in spring, friction issues on rails

CubeSat mockup “f” varies w/ humidity (cardboard) Aluminum mockup in the works Lubrication?

Quick Release Mechanism Options Vectran Line Cutter (ODU built) 2 Linear Solenoids

Center-of-Mass Must be inside 2” square at center

Design Concerns

Further PATRAN & FEA analysis (vibrations accountable)

Resume velocity measurements with new mockup

Choose quick release mechanism within budget Design a mounting plate to connect O-POD to

RockSat-X

Future Work

Gantt Chart

Most of our time so far has been allocated to gathering information, resources and planning

We will apply that information to create prototypes and perform the necessary experimental tests for the successful mission of our CubeSat

All tests and prototypes will be performed and created to interface with RockSat-X, but we will consider other options for test flights as well.

Conclusion

?Questions