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single-phase loops, controlled by a pump; two-phase loops, composed of heat pipes (HP), loop heat pipes (LHP) or capillary pumped loops (CPL). Louvers (which change the heat rejection capability to space as a function of temperature). Thermoelectric coolers.
The International Space Station (ISS) External Active Thermal Control System (EATCS) [1] maintains an equilibrium when the ISS environment or heat loads exceed the capabilities of the Passive Thermal Control System (PTCS). Note Elements of the PTCS are external surface materials, insulation such as Multi-Layer Insulation (MLI), or Heat Pipes.
The second figure shows a typical grooved aluminium/ammonia variable conductance heat pipe (VCHP) for spacecraft thermal control. The heat pipe is an aluminium extrusion, similar to that shown in the first figure. The bottom flanged area is the evaporator. Above the evaporator, the flange is machined off to allow the adiabatic section to be bent.
Such space systems require advanced high-temperature thermal control systems. Liquid metal heat pipes with conventional radiators are considered ideally suited for such applications. [5] However, the required radiator surface area is huge, hence, the system mass is very large. The liquid droplet radiator (LDR) has an advantage in terms of the ...
A loop heat pipe (LHP) is a two-phase heat transfer device that uses capillary action to remove heat from a source and passively move it to a condenser or radiator.LHPs are similar to heat pipes but have the advantage of being able to provide reliable operation over long distance and the ability to operate against gravity.
The fuel pump delivered 15,471 US gallons (58,560 litres) of RP-1 per minute while the oxidizer pump delivered 24,811 US gal (93,920 L) of liquid oxygen per minute. Environmentally, the turbopump was required to withstand temperatures ranging from input gas at 1,500 °F (820 °C) to liquid oxygen at −300 °F (−184 °C).
Raptor 1 and 2 engines require a heat shroud to protect pipes and wiring from the heat of high-velocity atmospheric re-entry, [31] while Raptor 3 is designed so that it does not require an external heat shield. [53]
Waste heat rejection was intended to be accomplished using low-mass heat pipe technology. Safety was intended to be assured by a rugged design. [citation needed] Project Prometheus was an early 2000s NASA study on nuclear electric spacecraft. [citation needed] Kilopower is the latest NASA reactor development program, but is intended for surface ...