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899,924. Hot gas engines. GENERAL MOTORS CORPORATION. Nov. 16, 1960 [Nov. 17, 1959], No. 39319/60. Class 7(1). [Also in Groups XIII and XXI] Apparatus for providing continuous operation of a Sterling cycle engine from an intermittently effective heat source comprises several connected enclosures containing a heat transfer fluid and means for circulating the heat transfer fluid between the several enclosures, the several enclosures including a heat absorption enclosure wherein heat in excess of that required for normal operation of the engine may be intermittently supplied to the heat transfer fluid from the heat source, an engine heater enclosure wherein heat may be continually supplied to the working medium of the engine from the heat transfer fluid and a heat storage enclosure including separate container means immersed in the heat transfer fluid and having a heat storage substance therein characterized by a high heat of fusion and a melting point above 800‹F. and less than the normal operating temperature of the engine so that heat in excess of that required for normal operation of the engine may be acquired from the heat transfer fluid by the heat storage substance by the melting thereof when the heat source is effective and so that the acquired excess heat may be returned to the heat transfer fluid from the heat storage substance by the solidification thereof for continued operation of the engine when the 'heat source is ineffective. The heat storage substance may be a metal compound selected from the group consisting of lithium hydride, lithium fluoride and lithium hydroxide. The heat transfer fluid may be a liquid metal or it may be an alloy of sodium and potassium. In Fig. 1 the satellite power plant includes a Sterling cycle engine 10 which operates a pair of alternators 11. The engine is mounted on the last stage fuel tank 12 of the rocket which puts the power plant in orbit and serves as a radiator or heat sink for the engine. A heat absorber and accumulator 13 is mounted on the head of the engine 10 and in turn carries an inflated solar energy reflector 14. The reflector 14 is deflated prior to orbit and comprises a plurality of inflatable struts 15 carrying a balloon 16 which has a reflective coating on the interior of the outermost wall 17 while the innermost wall 18 is transparent. The struts 15 and back wall 17 may be made rigid if desired by the injection of plastic foam-forming materials after inflation. The heat absorber and accumulator 13 Fig. 3 consists of a hollow sphere having an aperture 19 through which the concentrated solar rays are directed on to the upper surface of the casing 20. The engine working fluid may be helium at an average pressure of 1250 1bs./sq. inch.
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