STRUCTURAL-INTEGRATED THERMAL CONTROL SYSTEM FOR AEROSPACE AIRCRAFTS Russian patent published in 2020 - IPC G05D1/08 

FIELD: heat engineering; cosmonautics.

SUBSTANCE: present invention generally relates to systems for removing heat generated by electrically powered subsystems and components, such as electromechanical drives, on board of aerospace vehicles. Aerospace vehicle comprises heat bus and thermally active element. At the same time heat bus comprises structural element of aerospace aircraft. Thermally active element has thermal contact with thermal bus for heat dissipation from thermally active element to heat bus. At that, structural element represents aircraft wing or aircraft wing rib, and the thermally active element is an electrical device configured to operate with the aircraft wing. At that, electric device rests on heat conducting ledge, installed on said structural element, and has thermal contact with said heat conducting ledge. Aircraft-spacecraft also comprises a heat dissipating element having thermal contact with the thermal bus and comprising a heat-conducting element comprising a heat-conducting material, containing hydrogel, and heat distributor attached to heat-conducting element. Group of inventions also relates to a method of cooling an aerospace aircraft and a temperature control system for an aerospace aircraft.

EFFECT: group of inventions provides an improved cooling system for controlling thermal loads generated by electrical components onboard aerospace aircrafts.

14 cl, 9 dwg