LANDING LUNAR MODULE INSTRUMENT COMPARTMENT THERMAL CONTROL SYSTEM Russian patent published in 2013 - IPC B64G1/50 

FIELD: aircraft engineering.

SUBSTANCE: in compliance with first version, proposed system comprises radioisotope heat generator (HG), controlled contour heat tube (HT), radiative heat exchanger and three-way valve. HT condenser is built in radiative heat exchange disconnected by three-way valve with the help of bypass line at platform temperature dropped below preset magnitude. Platform is mounted parallel with lunar gravitation field vector. HTs are built in said platform so that their bottom zones have thermal contact with HG at platform bottom. Top zones of HTs have thermal contact with evaporator of controlled contour HT at platform top. In compliance with second version, built-in HTs are arranged also parallel with lunar gravitation field vector. Note here that, additionally, incorporated is uncontrolled contour HT with its evaporator having direct teat contact with HG while condenser stays in contact with bottom zones of built-in HTs. Top zones of said HTs are interconnected by, at least, one collector pipeline and with controlled contour HT evaporator.

EFFECT: maintenance of preset thermal mode without suing electric drives and extra electric power.

16 cl, 9 dwg