Joshua Laub Jake Tynis Lindsey Andrews Advisor: Dr. Robert Ash Small, lightweight satellites Size = 10 cm cube (1 U up to 3U) Total Mass < 1 kg Orbital altitudes as great as 900 km (ISS is about 350 km) CubeSat lifetime: ≈ 500 years ( 1000 yrs @ 900 km) Velocities ≈ 7.4 km/s NASA/IADC Guideline: Orbital lifetime of 25 years or less Develop a prototype inflatable device to deorbit CubeSats Increase frontal area >> Increase drag >> Decrease orbital lifetime Current Challenges: Folding/Packaging Inflation Initiation Material Procurement US Air Force Plug and Play prototype system LabVIEW to trigger the inflation sequence: Boolean program outputs about 1 Volt +1 Volt output is sent to relay Relay amplifies signal up to 30 Volts, if desired Amplified signal sent to Micro Solenoid valve to start air flow (inflation) Mylar Kapton Resistant to punctures Low cost Vulnerable to radiation over long periods of time Good mechanical properties External chemical coating necessary to prevent atomic oxygen degradation Both will be utilized in the prototype development Space-Qualified Design Prototype Material 2 Mil Mylar Contact Cement Gas Cylinder (from lab) Lab air Aluminum (from stock) Valve (Clippard) Circuit board Misc. Net cost: Cost $33 $10 $0 $0 $0 $48 $2 $15 $108 Material Cost Mass (g) Upilex-S polyimide film (50µm) $75 126 Elastosil S $15 0.004 Aluminum 6061-T6 $15 2.13 SUVA-236fa refrigerant unknown 1.77 Aluminum 6061-T6 (from stock) $0 2.13 Upilex-S polyimide film (50µm) included above 0.74 Dyneema $3 0.075 Clippard ≥ $70 Around 11 g Misc. $15 Cost Net mass (g) $193 143.849 We have begun integration, headed towards full system testing! Investigated different folding methods in the lab Folding affects speed and ease of inflation Must consider decreased frontal area due to bulges Found that this is an area requiring further refinement STK software used for drag analysis Inputs: Orbital characteristics, frontal area Outputs: Predicted orbital decay, orbital lifetime EXAMPLE: Plausible CubeSat orbit and frontal area: Eccentricity (0 to 0.004) Time Elapsed (Years 2004 – 2021) Yellow: Height of Apogee Red: Height of Perigee Blue: Eccentricity Acquired Materials: Mylar Adhesive Micro Solenoid Valve Gas cylinder Micro Solenoid Valve Relay Aluminum Deorbit Casing Steel “Cubesat” Above: Deorbit Casing Below: Mock CubeSat Have now acquired all parts; ready for lab simulation. Goal: Create deorbiting device for CubeSat Complete Lab simulation using: LabVIEW Remote Communication Challenges: Weight Packaging Folding Signaling Bate, Roger R, Donald D Mueller and Jerry E White. Fundamentals of Astrodynamics. New York: Dover Publications, Inc., 1971. Bradford Engineering. "Sold Propellant Cool Gas Generator." 2006. <http://www.bradfordspace.com/pdf/be_datasheet_spcgg_sep2006.pdf>. California Polytechnic, State University. "CubeSat Design Specification Rev.12." Clippard Instrument Laboratory, Inc. www.Clippard.com. 2011. D.C. Maessen, E.D. van Breukelen, B.T.C. Zandbergen, O.K. Bergsma. "Development of a Generic Inflatable De-Orbit Device for CubeSats." (n.d.). DuPont. "Summary of Properties for Kapton Polymide Films." <http://www2.dupont.com/Kapton/en_US/assets/downloads/pdf/summaryofprop.pdf>. IADC. "Space Debris Mitigation Guidelines." Standard. 2007. Lokcu, Eser. "Design Considerations for CubeSat Inflatable Deorbit Devices in Low Earth Orbit." Old Dominion University (2010). McMaster Carr. 27 November 2010 <http://www.mcmaster.com/#aluminum/=a2cdo0>. Office for Outer Space Affairs. "Space Debris Mitigation Guidelines of the Committee on the Peaceful Uses of Outer Space." Vienna: United Nations, 2010. Pumpkin, Inc. CubeSat Kit. 2008. <http://www.cubesatkit.com/>. R. Janovsky, M. Kassebom, H. Lubberstedt, O. Romberg. END-OF-LIFE DE-ORBITING Strategies for Satellites. Bremen: OHB System AG, 2002. RobotShop. 30 November 2010 <http://www.robotshop.com/>. Wacker Chemie AG. 1 December 2010 <http://www.wacker.com/cms/en/productsmarkets/trademarks/elastosil/elastosil.jsp>. Questions?