Optimization of Power Capabilities and Trajectory Parameters for Transportable Launch Space Systems

Yu. S.Solomonov

Moscow Institute for Heat Technology

10/1, Beryozovaya alleya, Moscow, 127276, Russia

 

This paper concerns one profitable way to develop a space launch vehicle (SLV) to be used for injection of satellites with mass of 50 to 1000 kg into low earth orbits (200-1200 km altitude) with wide range of inclinations (0-98°) and launch paths. Technical feasibility study of several alternative variants indicated that the most optimal variant is modification of battle solid-propellant missiles on the alert due to their service life expiration and the use of this missile as the base for the development of SLV with four (or five) boost stages. High accuracy of satellite injection into the prescribed orbit is achieved by a number of interconnected theoretical and engineering approaches such as: 1) using a post-boost stage which compensates kinematic parameter errors accumulated during operation of boost motors;  2) developing onboard instruments and programs ensuring controllability of four- and five-stage launch vehicles, which lengths exceed essentially analogous parameters of basic battle missiles;  3) using gas-reaction attitude control system operating in coast mode after third stage separation as well as after post boost stage motor burnout;  4) optimizing ballistic tasks and SLV launch paths taking into account safety requirements for spent stages impact areas;  5) equipping the additional measuring stations to receive trajectory data from onboard radio-telemetry system SKUT for SLV launches from Svobodny cosmodrome.

Launch Vehicle is maintained in the transport-and-launch canister (TLC) and launched from this canister after erection in vertical position.  The TLC is placed on mobile launcher.  Launch Vehicle is ejected from the TLC by autonomous solid-propellant hot-gas generator.

Space Launch vehicles of Start family, developed in such a way, were used for launch of the Russian scientific satellite ‘Zeya’ into sun-synchronous orbit as well as for launches of some communication satellites.