The technical feasibility of a rendezvous and docking concept, (RVD) on geostationary transfer orbit (GTO) between a communication satellite as target, and a dedicated propulsion module as chaser, both launched by Ariane 3, is investigated. For an assumed layout of the 2000 kg satellite, a 2600 kg medium energetic, bipropellant chaser design is conceived including all its subsystems. The corresponding mission profile, including the guided phase underground station command, homing, final approach and docking under on board guidance, as well as the subsequent ground guided insertion into GEO, is established. Each mission phase is analyzed as to its content and problematics and appropriate system or hardware solutions are defined. Thus the RVD concept builds upon an S-band far range guidance sensor, a camera system as short range guidance sensor, 4 x 400 N thrusters supplemented by 10 N reaction control system (RCS) thrusters and an active soft impact docking adapter. The RVD functions sharing between the two 3-axis stabilized spacecraft is so that primarily the chaser is burdened with the active systems, while the target is carrying only the supplementary equipment.
System Feasibility Study on Rendezvous and Docking in Transfer Orbit, Volume 1
1982
160 pages
Report
Keine Angabe
Englisch
Astronautics , Manned Spacecraft , Communication satellites , Orbit transfer vehicles , Orbital rendezvous , Spacecraft control , Spacecraft docking , Transfer orbits , Feasibility analysis , Ariane launch vehicle , Ground based control , Liquid propellant rocket engines , Rendezvous guidance , Rendezvous spacecraft , Rendezvous trajectories , Spacecraft design , Target acquisition , Foreign technology