METHOD FOR PLACING A PAYLOAD INTO ORBIT BY MEANS OF A HYBRID MULTIFUNCTION BOOSTER ROCKET EQUIPPED WITH A LIQUID-FUEL ROCKET PROPULSION SYSTEM (LRPS), HYBRID MULTIFUNCTION BOOSTER ROCKET WITH CRUISING LRPS AND DEVELOPMENT TEST THEREFOR

摘要

The invention relates to the field of rocket-space engineering and may find application during the development of rocket-space systems serving to place manned and unmanned space ships into a near-earth orbit.;The method includes forming a launch assembly of a launch vehicle in accordance with a launch program, including a lower multiunit assembly of rocket units (RU), firing cruise LRESs of a central and side RUs at the launch, and operating the LRESs in accordance with the launch program. Identical RUs with adjustable LRESs of identical thrust are used to form the lower multiunit assembly. At the launch of the launch vehicle, LRESs of the side RUs have a nominal thrust, while the LRES of the central RU - a thrust equal to 90-100% of the nominal value. When the launch vehicle reaches a longitudinal acceleration of 12.7-16.7 m/sec², the thrust of the LRES of the central RU is reduced to 0.3-0.5 of the nominal thrust until the LRESs of the side RUs are cut off. The reduction of the thrust of the LRESs of the side RUs is also presumed in order to adjust the inertial and aerodynamic loads on the launch vehicle.;The launch vehicle of a combined scheme comprises a lower multiunit assembly of RUs, composed of identical RUs, wherein the side RUs are mounted on the central RU symmetrically relative to its longitudinal axis in sectors formed by the swinging planes of the LRES of the central RU.;The method of refining the multifunctional launch vehicle presumes that during the selection of the characteristics of its RUs, identical size-mass characteristics and thrust of the LRESs of the lower multiunit assembly of RUs will be set, this ensuring use of the central RU in the makeup of a launch vehicle of a tandem scheme. The aforesaid RU is produced and its ground-based and flight-structural tests carried out, including in the makeup of a launch vehicle of a tandem scheme, and then it is used in the formation of a lower multiunit assembly of RUs of a launch vehicle of a combined scheme.;The main technical result from use of the invention is expansion of the range in which the payload being placed into orbit may change.