Loop heat pipe for staged reentry spacecraft
AssigneeThe United States of America as represented by the Secretary of the Air Force
InventorJonathan Allison
Life of this patent
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Abstract
A frangible loop heat pipe provides a passive heat transfer system in a staged spacecraft having one or more separable modules. The frangible loop heat pipe is positioned within adjacent separable modules and is designed to separate such that a primary element remains with the command module of the spacecraft and a secondary element is jettisoned with an expendable module. The primary element operates as a flash evaporator that provides heat transfer to the module as heat pipe fluid is ejected from the heat pipe.
Claims19
A spacecraft system comprising:
- a spacecraft having a primary module and one or more separable modules connected thereto;
- a frangible loop heat pipe positioned within the primary module and the one or more separable modules;
- wherein the frangible loop heat pipe is separable into a primary element and a secondary element;
- wherein the primary element remains within the primary module and the secondary element of the frangible loop heat pipe breaks away with the one or more separable modules after post staging separation of the spacecraft;
- and
- wherein the frangible loop heat pipe includes at least one shaped charge configured to sever the loop heat pipe when the modules are separated.
A frangible loop heat pipe comprising:
- a hollow pipe forming a single loop path for a heat pipe fluid to flow therethrough;
- a pair of fill/drain valves connected to the loop path at opposing ends thereof;
- a first normally open squib valve coupled the loop heat pipe on one side;
- a second normally open squib valve coupled the loop heat pipe on an opposing side;
- first and second shaped charges coupled to the loop heat pipe proximate the first and second squib valves;
- first and second beam seal joints positioned in the loop heat pipe between the first and second squib valves, respectively;
- a first heat exchanger in thermal communication with the loop heat pipe proximate a first end;
- a compensation chamber connected with the loop heat pipe positioned to receive thermal input from the first heat exchanger;
- a condenser formed within the loop heat pipe proximate a second end opposite of the first end;
- an extension pipe in fluid communication with the loop heat pipe, the extension pipe projecting away from the loop heat pipe between the compensation chamber and the second squib valve;
- a normally closed third squib valve positioned proximate a connection point between the loop path and the extension pipe;
- a flow control valve positioned downstream of the first squib valve in the extension pipe;
- a second heat exchanger positioned downstream of the flow control valve in the extension pipe;
- a temperature sensor in a closed loop connection between the flow control valve and the second heat exchanger;
- and
- a dump vent formed in the extension pipe to permit heat pipe fluid to vent therefrom after the loop heat pipe has been severed by the shaped charges.
A spacecraft system comprising:
- a spacecraft having a primary module and one or more separable modules connected thereto;
- a frangible loop heat pipe positioned within the primary module and the one or more separable modules;
- wherein the frangible loop heat pipe is separable into a primary element and a secondary element;
- wherein the primary element remains within the primary module after post staging separation of the spacecraft;
- and
- wherein the frangible loop heat pipe includes at least two beam seal joints.
Dependencies are inferred from the claim text.