The mission specification for this first order study of an Orbital Transfer Vehicle (OTV) was the capability to transport a two ton satellite (based on the Intelsat 4 design) between geostationary orbit and low Earth orbit. The OTV would rendezvous with the Space Transportation System (or equivalent) and with the Space Station. To minimize the mission cost, a low fuel requirement was a priority. Thus, orbital transfer was planned via the Hohmann minimum energy transfer ellipse, with an 'aerobraking maneuver' assist on the return journey. This was found to be the most fuel efficient. Apart from the new technologies involved with aerobreaking, design policy was conservative, using tried and tested materials and systems. The results outline a suggested format for an OTV and identify some of the main design problems faced, namely the saving of weight to reduce fuel requirements and the simulation of the complex flowfield during aerobraking.
Space Tug: An Orbital Transfer Vehicle
1990
73 pages
Report
No indication
English
Understanding the Orbital Transfer Vehicle Trade Space
AIAA | 2003
|Understanding the Orbital Transfer Vehicle Trade Space
British Library Conference Proceedings | 2003
|