Abstract A flying launcher (airplane carrier) can generate initial errors in position and time of launch. In order to compensate for these errors, one should have two control parameters in addition to those that provide for a spacecraft's injection into a preset orbit. We suggest the concept of controlling the trajectory of injection by choosing thrust values (within allowable regions of control) of second-stage engines or/and of a space booster of the Polyot carrier launcher. As an example, a rendezvous of the spacecraft at the end of its boost phase with the International Space Station (ISS) is considered. The methodology of the suggested approach can be extended to other mobile systems of launch to rendezvous orbits.
A Concept of Guidance for an Air-Launch Vehicle with Compensation of Initial Downrange and Launch Time Errors at Direct Insertion into a Rendezvous Point in the Orbit
Cosmic Research ; 43 , 5
2005
Aufsatz (Zeitschrift)
Englisch
BKL: | 55.60 Raumfahrttechnik / 39.00 Astronomie: Allgemeines / 50.93 Weltraumforschung | |
Lokalklassifikation TIB: | 770/3520/8000 |
Navigation and guidance of hypersonic/rocket two-stage launch vehicle for rendezvous mission
Engineering Index Backfile | 1968
|Maximum rendezvous launch window characteristics
AIAA | 1964
|