Development of a Generic Inflatable de-Orbit Device for CUBESATS
- Paper number
IAC-07-A6.3.06
- Author
Mr. Daan Maessen, Delft University of Technology (TU Delft), The Netherlands
- Coauthor
Mr. Eddie van Breukelen, ISIS - Innovative Solutions In Space B.V., The Netherlands
- Coauthor
Mr. Barry Zandbergen, Delft University of Technology, The Netherlands
- Coauthor
Dr. Otto Bergsma, Delft University of Technology (TU Delft), The Netherlands
- Year
2007
- Abstract
New space debris mitigation guidelines require satellites in low Earth orbit to de-orbit within 25 years after end of life. This effectively limits the orbital altitude of conventional CubeSat satellites, with a ballistic coefficient in the range of 50-150 kg/m 2, to 400-700 km. For CubeSats employing the generic inflatable de-orbit device discussed here, this range is extended to 1000 km by reducing the ballistic coefficient by about a factor 100. This paper outlines the concept and preliminary design of a generic inflatable de-orbit device, which reduces the ballistic coefficient by increasing the frontal surface area of the satellite. The device essentially is of the attached ballute type and consists of a thin membrane covering an inflatable structure, which is chemically rigidized after deployment. Coatings are applied to the structure to provide protection against the hostile low Earth orbit environment and to manipulate the temperature of the inflatable. The inflation gas is stored in solid form inside a so-called Cool Gas Generator, developed by The Netherlands Organisation for Applied Scientific Research (TNO) in the Netherlands.
Three different geometrical concepts for the ballute are analyzed. A pyramid-like structure is selected as the best overall concept based on mass, stowed volume, flexibility, manufacturing, and deployment control. A preliminary design of the device is performed for a 1-unit CubeSat of 1 kg mass, with focus on ease of integration.
Initial results of the physical development of the structure are shown. A development model of a flexible connector piece is constructed to which five inflatable tubes, made from polyethylene foil, are attached at right angles in a leak-tight manner. The method used to bond the tubes to the connector piece as well as attachment of the membranes to the inflatable structure is outlined. Lastly, stowage and deployment of the inflatable structure are discussed. The results indicate that the mass and stowed volume of the complete de-orbit system remain within 10% of the CubeSats’ total mass and volume.
- Abstract document
- Manuscript document
IAC-07-A6.3.06.pdf (🔒 authorized access only).
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