Abstract: A cooling system is disclosed for a pod (20) of an aircraft. The cooling system includes an air circulation loop (28) for supplying cooled air to an air input (32) of the pod to cool a load disposed in the pod and for receiving air discharged from an air discharge (34, 35) to the pod which has absorbed heat from the pod. A cooling apparatus (30) is disposed in the loop which is activated to cool air flowing in the loop prior to application to the pod. A fan (48) is located in the air circulation loop between the cooling apparatus and the air discharge (35) which is activated to blow discharged air toward the cooling apparatus when the aircraft is operated in a first portion of the flight envelope. A ram air supply (44) supplies ram air in response to flight of the aircraft.

Abstract: An environmental control system for affording quick attachment and disconnection of a thermal control unit with respect to an aircraft pod or other like vehicular substructure. A complementary interengaging mechanism is provided between the thermal control unit and the aircraft pod for properly positioning the control unit with respect to the pod. A complementary interengaging locking mechanism is provided between the thermal control unit and the aircraft pod for locking the control unit to the pod when so positioned. Complementary fluid connections and electrical connections on the thermal control unit and the aircraft pod are located for interconnection automatically in response to positioning and locking the control unit to the pod.

Abstract: Start-up problems in an intermittently operated evaporative cooling system to low temperature environments is avoided by the provision of one or more heaters 62, 64, 66 in the system. Typically the system will include an evaporator 10, a compressor 24, a condenser 42, a receiver 62 and an expansion valve 56. When low ambient temperatures reduce internal pressure within the system to a value below which it can be started through operation of the compressor 24, the heaters 62, 64, 66 may be energized to vaporize refrigerant and thus generate a pressure of sufficient magnitude so as to allow starting.

Abstract: An environmental control system for affording quick attachment and disconnection of a thermal control unit with respect to an aircraft fuselage. The fuselage includes a compartment communicating with the exterior of the aircraft for receiving the temperature control unit. The control unit is supported on a drawer-like mechanism positionable in the compartment by complementary interengaging guides which provide push-pull movement of the supported control unit into and out of the compartment. Complementary fluid connections and electrical connections on the thermal control unit and the aircraft fuselage are located for interconnection automatically in response to pushing the control unit into position in the fuselage compartment.

Abstract: An on-board refrigerant charging system for a vapor cycle environmental control system in an aircraft or the like. A pair of accumulation chambers are provided for holding two different refrigerant components, each chamber including an outlet. A selectively operable valve is operatively associated with each chamber outlet. An inlet is provided to the vapor cycle environmental control system. A unitary dual-vaned pump is in fluid communication with the valves and the inlet to the environmental control system. A control senses refrigerant loss and the component mixture in the control system, and actuates the pumps to replace the refrigerant loss and operates the valves according to the desired component mixture charge.

Abstract: This invention relates to an airconditioning system to provide environmental control for an aircraft's cabin or cockpit. The system cooling cycle includes in combination: a rotary power supply and a turbomachine which includes a power compressor secured to a power shaft for providing compressed air. The rotary power supply is drivingly coupled to the power shaft to operate at a given speed. An expansion cooling turbine is mounted on a shaft concentric to the power shaft. A power driven fan is provided for directing a source of ambient air to and through a heat exchanger. The power compressor is coupled respectively to the cabin and through the heat exchanger to an input of the expansion cooling turbine to thereby draw air from the cabin and deliver the compressed air to the expansion cooling turbine. The expansion cooling turbine is designed to operate at a different speed than the given speed of the power shaft.