СПОСОБ ТЕРМОСТАТИРОВАНИЯ ПРИБОРНОГО ОТСЕКА РАЗГОННОГО БЛОКА КОСМИЧЕСКОЙ ГОЛОВНОЙ ЧАСТИ РАКЕТЫ-НОСИТЕЛЯ И БОРТОВАЯ СИСТЕМА ДЛЯ ЕГО РЕАЛИЗАЦИИ

摘要

FIELD: thermostatting of instrument bays of launch vehicles. ^ SUBSTANCE: thermostatting medium is injected into payload module and into cryogenic stage simultaneously. Injection of thermostatting medium into cryogenic stage is carried out on side of its lateral surface at angle to plane of its cross section and at shift relative to axis of symmetry, thus ensuring twisting of thermostatting medium relative to said axis. Overflow of thermostatting medium from payload module to cryogenic stage is effected in direction similar to that of twisting of thermostatting medium injected into cryogenic stage. Proposed system has holes for injection, overflow and efflux of thermostatting medium provided with single-acting valves and injection unit. Device for injection of thermostatting medium into cryogenic stage is made in form of subsonic diffuser which is mounted in clearance between instrument bay and cryogenic stage envelope. Inlet hole of diffuser is communicated with injection hole in cryogenic stage envelope and outlet hole is located in such way that tangent to diffuser axle in its outlet section is directed at angle to plane of cryogenic stage cross section and at shift relative to its axis of symmetry. Articulations of overflow valves mounted in partition separating the payload module and cryogenic stage are secured in such way that projections of axes of turn on plane of cryogenic stage cross section coincide with radial direction relative to axis of symmetry. ^ EFFECT: enhanced heat exchange on instrument bay surface; reduction of mass of onboard thermostatting system. ^ 3 cl, 4 dwg