A TRADE STUDY BETWEEN PROPULSION METHODS FOR A SMALL SATELLITE ORBITAL TRANSFER VEHICLE

摘要

By developing an orbital transfer vehicle for small satellites, the launch costs could be reduced considerably compared with a dedicated launch. The satellite could be launched cheaply as a secondary payload, while obtaining the desired orbit using the Transfer Module. The transfer module should be able to perform transfers within Low Earth Orbit (LEO) and from Geostationary transfer orbit (GTO) to LEO, including inclination changes.rnThere are many propulsion options available for such a transfer module. A trade study is made for Verhaert Design and Development (Belgium). Propulsion selection is done depending on the type of transfer based on cost, reliability, complexity, flexibility, transfer duration, technology status, mass and volume.rnFor orbit changes within LEO with a delta-V up to 375 m/s (no inclination changes), a hybrid propulsion system is preferred. All electric propulsion options and bipropellant systems are too expensive. Solid rocket engines are cheaper, but are not restartable or have no throttle capability, making them impractical. For transfers from GTO to LEO or transfers with inclination changes from 10° upwards, electric propulsion options are preferred because other classical chemical options are too heavy. Electrodynamic tethers could offer interesting opportunities for an orbital transfer vehicle when the technology is more mature.