METHOD OF THERMOSTATTING OF INSTRUMENT MODULE OF SPACE LAUNCH VEHICLE NOSE CONE AND ONBOARD SYSTEM FOR REALIZATION OF THIS METHOD (VERSIONS) Russian patent published in 2006 - IPC B64G1/50 G05D23/00 F24F5/00 

FIELD: methods of thermostatting instrument modules of launch vehicles.

SUBSTANCE: proposed method includes simultaneous injection of thermostatting medium into payload module and into cryogenic stage. Thermostatting medium is injected into cryogenic stage on side of its lateral surface symmetrically and at angle relative to vertical plane passing through plane of symmetry of instrument module in tangential direction relative to lateral surface of instrument module. Overflow of thermostatting medium from payload module to cryogenic stage is effected in way of thermostatting medium injected into cryogenic stage. Injection unit is made in form of subsonic diffuser with at least two bent branch pipes. Inlet section of diffuser is communicated with injection hole made in cryogenic stage envelope. Outlet sections of diffuser branch pipes are located in clearance between instrument module and cryogenic stage envelope symmetrically relative to space nose cone. Tangent to axis of each diffuser branch pipe in its outlet section is directed tangentially relative to surface of instrument module. According to first version, partition separating the payload module from cryogenic stage has holes for overflow of thermostatting medium. Valve articulated in these holes opens symmetrically relative to plane of symmetry of space nose cone. Valve articulations are secured in partition on side of injection hole in such way that axes of their turn coincide with radial direction. According to second version, at least central part of partition is made from lightened permeable material.

EFFECT: enhanced heat exchange on surface of instrument module; reduced mass of onboard thermostatting system.

4 cl, 9 dwg