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 to 400-700 km. For CubeSats employing the generic inflatable de-orbit device discussed here, this range is extended to at least 900 km. This paper outlines the concept and preliminary design of a generic inflatable de-orbit device, which reduces the ballistic coefficient of the satellite by increasing its frontal surface area. The device is of the attached ballute type and consists of a thin membrane covering an inflatable structure, which is chemically rigidized after deployment. 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 are attached. Construction as well as 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 9.4% and 10.3% of the CubeSat's total mass and volume.
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