METHOD FOR THERMOSTATTING PAY LOAD AND INSTRUMENTS OF CONTROL SYSTEM OF SPACE HEAD OF CARRIER ROCKET, AND AIRBORNE SYSTEM USED FOR METHOD REALISATION Russian patent published in 2009 - IPC B64G1/50 F24F13/06 B64G5/00 

FIELD: aircraft industry.

SUBSTANCE: inventions refer to thermostatting methods and means of space objects, and are mainly used during pre-launch procedure. According to invention, thermostatting medium is injected at one and the same time into head block and block DM with its subsequent flow at least out of block DM. The above medium is injected into head block and block DM above pay load and instruments of control system along fairings of the above blocks in longitudinal and circumferential directions. At that, one of vectors of longitudinal velocities of injected medium is forwarded in the direction of head block nose part, and the other one - in block DM direction. Velocity vector along block DM fairing is directed only to its front part. Vectors of circumferential velocities are directed in an equal manner relative to blocks symmetry axes; thus providing the medium swirling in space head part, with its flowing from head block to block DM. According to invention, airborne system injection devices of thermostatting medium into head block and block DM are made in the form of subsonic diffusers. Each of them is provided with one inlet hole and three outlet holes (for head block) and two outlet holes (for block DM) which are perpendicular thereto. Diffusers are installed above pay load and the specified instruments near fairings of head block and block DM so that medium swirling and overflow can be provided in circumferential direction relative to head part axis.

EFFECT: developing the airborne thermostatting system with improved performance and design and arrangement characteristics for the objects arranged in-series in space head part of carrier rocket.

2 cl, 9 dwg