METHOD OF TEMPERATURE CONTROL OF SPACECRAFT AND DEVICE FOR REALIZATION OF THIS METHOD Russian patent published in 2006 - IPC B64G1/50 B64G1/10 

FIELD: space engineering; temperature control systems of automatic spacecraft flying in near-earth orbits.

SUBSTANCE: proposed method includes removal of excessive heat from instruments through two first and two second evaporators interconnected in longitudinal direction; said evaporators are made in form of L-shaped adjustable thermal tubes. Removal of heat from condensers of these tubes is effected to first and to second radiators-emitters of U-shaped heat-conducting honeycomb unit located orthogonally relative to first ones. Inner surfaces of side radiators-emitters are provided with heat insulation and side radiators-emitters have edges projecting beyond boundaries of instrument container. Their inner surfaces are provided with heat-controlled coat. Temperature control system is provided with two instrument containers interconnected by their center honeycomb panels. Side radiators-emitters are located in parallel or orthogonal planes. Built in structure of each U-shaped honeycomb units are L-shaped thermal tubes in such position that their condensers are located in side radiators-emitters and evaporators are located in center honeycomb panel. System provides for narrow range of control of seats of instruments mounted on center honeycomb panels.

EFFECT: enhanced efficiency of temperature control; enhanced reliability of spacecraft; extended field of application.

6 cl, 6 dwg