CubeSat De-Orbit Project

Transcription

1 CubeSat De-Orbit Project Brockton Baskette Sahil Dhali Michael Foch Nicholas Montana Kyle Wade MAE 434W April 30, 2013

2 Outline Background Project Goals Develop commercial cubesat de-orbit device Demonstrate viability using sounding rocket flight Develop sounding rocket prototype Design Planning Testing

3 Background Material CubeSat Cubic Satellite or nanosatellite that is 1000 cm 3 Approximately 1 kg Purpose Versatile in mission capability, limited only by size and weight Cheap and easy way to perform space system experiments

4 CubeSats Use Mainly used by universities for research experiments Previous experiments include testing system capability in space environment, solar power, earth remote systems Future use includes potential geo-climate sensor arrays using CubeSats.

5 Problem Statement Pending international agreement to remove spacecraft from orbit in less than 25 years Once in orbit, how is it removed? Orbit decays by aerodynamic drag which depends on cross-sectional area By increasing this drag force, slow the object enough to drop it out of orbit

6 ODU CubeSat Airbrake Method Inflation of onboard balloon will increase the drag force and reduce the orbit (to zero). Sounding Rocket Flight Constraints How to inflate a balloon in space on command? What sensor systems are required? Space Flight time of 300 seconds Deadline Launch date of July 2014

7 Work Breakdown Structure CubeSat Airbrake Project Develop Controlled Cubesat Airbrake System Mechanical Engineering Electrical Engineering Balloon Inflation Cubesat Construction Repair Antennae Sensor Systems Signal Systems Test Benzoic Acid Develop Balloon Deployment Create CubeSat Structure Create Deployment POD Sand and Paint Tower Replace Radio Equipment

8 Satellite Ground Station System SGS s operate mission specific transceivers, antennas, transmission lines, amplifiers, and digital signal processing equipment. The ODUSGS was mainly intended to target communication with orbiting weather satellites (NOAA satellites) and amateur radio satellites. Built in 2005, by ODU senior design team then, this antenna receives and transmits live weather updates. It has not been used in over 8+ years. Our team is responsible for salvaging and restoring the antenna to its best possible shape.

9 CONCERNS Transmission power of CubeSat and NOAA satellites are low and limited, thus reception is not easy. CubeSats, amateur radio satellites and NOAA satellites are low orbit satellites and have high velocities. Low orbit satellites make complete orbits several times a day, collecting high amounts of data. This requires several hours of decoding and organizing.

10 ODUSGS - Breakdown FM Transceiver Pre-Amplifiers Antennas Antenna Rotators Computer Control and Tracking System Transmission Cables Modems and Data Decoders

11 Our Team s Project The Frame of the Tower was sanded and primed and is ready to be painted. The 2 meter Yagi antenna needs replacement. The antennas are held by a pair of fiber glass members. One of them needs to be replaced. The rotators are being greased and recoiled. Brand new Transreceiver and pre-amplifiers..

12 More Pictures

13 Air Brake Inflatable Deorbiting Device

14 Objective Inflate Balloon Airbrake within the Sounding Rocket space flight time of 300 seconds. Determine system requirements Balloon material Inflation gas Inflatable deorbiting device, the housing and any other elements must meet the weight and size requirements. (under 150 grams)

15 Proposed Solutions Pillow Shaped inflatable will be constructed due to its simple design and allows for only seals on the edges to be made. (easy to build and stow) Mylar will be used as the material to construct the inflatable because of its proven reliability in space applications (resistant to atomic oxygen, thin and flexible) Benzoic Acid was chosen to inflate/expand the deorbiting device because it sublimates at a relatively low temperature and pressure.

16 Experimental Method Using a vacuum chamber we will determine the sublimation rate of the benzoic acid at pressure levels found at flight altitude Foodsaver vacuum sealing system will be used to create airtight test balloon for use in vacuum chamber

17 Results and Conclusions In order to fully sublimate the acid in our time constraint we have determined that a heating element will be required Method of removing all excess air from balloon yet to be determined Foodsaver was unsuccessful

18 Air Brake Gantt Chart

19 Cubesat Structure Objectives Aluminum TestSat Fabrication Test velocity with ODU-Picosatellite Orbital Deployer Compare results with previous testing trials Specifications 4in. x 4in. x 4in. Cube.187in. thick aluminum plate Wood core

20 O-POD

21 TestSat

22 Cubesat Structure Gantt Chart

23 Design Project Hindrances Lack of resources Scheduling conflicts Future Challenges Choosing and constructing a quick release mechanism Triggering the release from Earth

24 Cost thus far have been minimal. Airbrake Mylar - $14.00 Vacuum Bags $10.00 Total - $24.00 Antenna Maintenance Paint - $25.00 Steel brushes - $5.00 Total - $30.00 TestSat Aluminum Plating - $48.00 Wood - $10.00 Screws - $4.00 Total - $62.00 Total Cost - $ (RocksatX Flight - $24,000) Cost Estimates

25 Summary To conclude our project report we have, as of now, three tasks to complete: Design the airbrake Repair the HAM Radio tower Design the Cubesat Structure So far Airbrake and Radio tower repair are in progress Cubesat structure is designed, yet requires internal system plans Future tasks to complete before launch: Design balloon housing Including balloon deployment system Design sensor systems