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Improved design features have made the pivoted-target thrust reverser concept most attractive for modern small turbofans with coaxial flow exhaust systems. These aerodynamic, mechanical and structural design improvements provide 40% or more reverse thrust effectiveness in a simple, light weight, low cost unit that has clean aerodynamic lines and minimum effect on engine performance. The pivoted-target thrust reverser system, under development at Grumman for the AiResearch TFE-731-2 and -3 engines, is described. Applications include the IAI Westwind 1124, the Gates Learjet 35/36 and the Dassault Falcon 10 aircraft.

During the period from Feb. 1984 to April 1985, test data have been obtained on several of the Space Constructible radiator (SCR) system components, such as the high capacity monogroove heat pipe, the contact heat exchanger, and the heat pipe disconnect. In light of both the performance data that are now available and the changes in Space Station requirements that have occurred since the inception of the SCR program in 1979, an optimization study of the entire SCR system is warranted. This paper reports the results of that study, which includes performance, weight, and reliability estimates.

This paper reports the proof of concept demonstration of a heat pipe quick disconnect being developed for the space constructible radiator system. The disconnect provides a maintainable coupling between the heat pipe evaporator, which is brazed to a mating heat exchanger, and the replaceable condenser section of a monogroove heat pipe radiator element. Test results, with pressurized nitrogen gas, confirm low leakage rates in both demated and mated configurations. Comparative thermal tests in a working 3 m (10 ft) test bed heat pipe using ammonia fluid revealed a 30% decrease in heat transport due to the additional minor pressure losses from the quick disconnect. The bulk of this loss is attributed to the transition section that joins the two adjacent heat pipe flow channels to the separated liquid and vapor passages within the disconnect coupling. It would be possible to decrease this overall loss in heat transport to under 10% with a redesigned transition section.