HEAT SINK AND ION ACCELERATOR SYSTEM EQUIPPED THEREWITH Russian patent published in 2013 - IPC B64G1/50 F03H1/00 

FIELD: transport.

SUBSTANCE: invention relates to thermal control systems and its application in electric rocket engine. Proposed heat sink comprises radiating ribs SS made integral with casing SM, and heat transfer system TC. The latter is made, mainly, from hypereutectoid alloy At-Si and includes ring element LM and LP. Elements LP are connected to polar tips PR while elements LM are connected with permanent magnets MR. Heat conducting layers made of more magnetically soft material, for example, gold may be arranged at said connections. Thermal expansion factor of TC differs by 10%…30% from that of polar tips and permanent magnets. Surface of magnets MR facing chamber wall K.W has reflection coating RE reducing heat transfer from chamber wall to magnetic core. Said coating, for example of gold, in interrupted in lengthwise direction nearby polar tips PR. In operation of ion accelerator chamber wall KW is heated to emit heat outward toward magnetic system. Heat absorbed by magnetic system is carried via magnets MR, pole tips PR and TC (elements LP, PM) to casing SM and emitted by ribs SS in space.

EFFECT: higher efficiency of heat transfer and operation of ion accelerator.

23 cl, 2 dwg