METHOD OF THERMOCONTROL OF SPACECRAFT AND DEVICE FOR IMPLEMENTATION OF THIS METHOD Russian patent published in 2008 - IPC B64G1/50 B64G1/22 

FIELD: heating.

SUBSTANCE: invention refers to thermal control, chiefly to thermal control of automatic spacecrafts. The suggested method includes excessive heat removal from apparatus installed on a heat conductive cellular panel of an instrumentation container. The latter is formed by a combination of two U-shaped cellular panel blocks. L-shaped regulated heating pipes (HP) are installed into a middle instrument cellular panel. Evaporators of these HPs are longitudinally and in pairs connected to each other, while condensers are placed into side cellular panels which operate as radiators-emitters. For additional heat removal built-in HPs are incorporated, the evaporators of which are connected to evaporators of L-shaped HPs, while condensers are built into additional disclosed radiators-emitters. Evaporators and condensers of incorporated HPs are interconnected to each other by means of flexible silphon portions. Additional radiators-emitters are disclosed by means of electric drives into various angular positions depending on the removed heat space; the said angular positions are determined by a control unit with temperature sensors. The suggested system of a thermo regulation can contain two instrument containers of the said U-shaped blocks. These containers are connected to each other along the planes of the corresponding middle cellular panels so that the side cellular panels (radiators-emitters) of containers are located in orthogonal planes to each other.

EFFECT: upgraded accuracy and reliability of a thermoregulation of spacecraft and expanding of its application field.

6 cl, 3 dwg