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公开(公告)号：US4869071A
公开(公告)日：1989-09-26
申请号：US172420
申请日：1988-03-24
CPC分类号： B64D13/00 , F25B1/10 , B64D2013/0614
摘要： 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. A valve (46), which is coupled to the ram air supply and to the loop blocks the supply of ram air to the loop in response to the aircraft being in the first portion of the flight envelope and supplies ram air to the loop when the aircraft is outside the first portion of the flight envelope. A controller (38), responsive to a temperature sensor (52) sensing air temperature of air supplied to the pod controls the activation of the cooling apparatus in response to the sensing of a temperature above a predetermined temperature when the aircraft is operating in the first portion of the flight envelope.
摘要翻译： 公开了用于飞机的舱（20）的冷却系统。 冷却系统包括用于将冷却的空气供应到舱的空气输入端（32）的空气循环回路（28），用于冷却设置在舱内的负载，并用于接收从空气排放口（34,35）排放到舱 这已经从荚中吸收了热量。 冷却装置（30）设置在环中，其被激活以在施加到荚之前冷却在环中流动的空气。 风扇（48）位于冷却装置和空气排放口（35）之间的空气循环回路中，当飞行器在飞行信封的第一部分中操作时，该空气循环被致动以将排出的空气吹向冷却装置。 冲压空气供应（44）为飞机的飞行提供冲压空气。 联接到冲压空气供应器和回路的阀门（46）响应于飞行器处于飞行包线的第一部分中而阻塞向环路供应的冲压空气，并且当冲程空气供应到空气环 飞机在飞行信封的第一部分之外。 响应于感测供应到舱的空气温度的温度传感器（52）的控制器（38）响应于当飞行器在第一个操作时响应于高于预定温度的温度的感测来控制冷却设备的启动 飞行信封的一部分。
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公开(公告)号：US4785639A
公开(公告)日：1988-11-22
申请号：US178874
申请日：1988-04-04
申请人： Guido Biagini
发明人： Guido Biagini
摘要： 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.
摘要翻译： 通过在系统中设置一个或多个加热器62,64,66来避免间歇运行的蒸发冷却系统中的低温环境的启动问题。 通常，系统将包括蒸发器10，压缩机24，冷凝器42，接收器62和膨胀阀56.当低环境温度将系统内部的内部压力降低到低于该值时，可以通过压缩机的操作开始 如图24所示，加热器62,64,66可以通电以使制冷剂蒸发，从而产生足够大的压力以允许启动。
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公开(公告)号：US4830096A
公开(公告)日：1989-05-16
申请号：US872871
申请日：1986-06-11
申请人： Guido Biagini
发明人： Guido Biagini
CPC分类号： B64D13/00 , F25D19/00 , B64D2013/0614 , Y10T403/1608
摘要： 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.
摘要翻译： 一种环境控制系统，用于相对于飞行器舱或其它类似的车辆子结构快速附接和断开热控单元。 在热控制单元和飞行器舱之间提供了互补的相互接合机构，用于相对于荚适当地定位控制单元。 在热控制单元和飞行器舱之间提供互补的相互接合的锁定机构，用于当定位时将控制单元锁定到舱。 热控制单元和飞机舱上的互补流体连接和电气连接被定位为响应于将控制单元定位并将其锁定到舱而自动进行互连。
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公开(公告)号：US4763859A
公开(公告)日：1988-08-16
申请号：US877231
申请日：1986-06-23
申请人： Guido Biagini
发明人： Guido Biagini
IPC分类号： B64D13/08
CPC分类号： B64D13/08
摘要： 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.
摘要翻译： 一种环境控制系统，用于相对于飞行器机身快速附接和断开热控单元。 机身包括与飞机外部通信的隔间，用于接收温度控制单元。 控制单元通过互补的相互接合的引导件支撑在可在隔室中定位的抽屉式机构，其提供支撑的控制单元进出隔室的推拉运动。 响应于将控制单元推入机身舱中的位置，互补液体连接和热控制单元和飞行器机身上的电气连接被自动地互连以进行互连。
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公开(公告)号：US4700549A
公开(公告)日：1987-10-20
申请号：US872872
申请日：1986-06-11
申请人： Guido Biagini
发明人： Guido Biagini
IPC分类号： F25B45/00
CPC分类号： F25B45/00 , F25B2345/001 , F25B2345/004
摘要： 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.
摘要翻译： 一种用于飞行器等中的蒸汽循环环境控制系统的车载制冷剂充注系统。 一对蓄积室用于容纳两个不同的制冷剂组分，每个室包括出口。 选择性操作的阀可操作地与每个室出口相关联。 入口被提供给蒸汽循环环境控制系统。 一体式双层泵与阀门和环境控制系统的入口流体连通。 控制器感测制冷剂损失和控制系统中的组分混合物，并且致动泵以代替制冷剂损失并根据所需的组分混合物进行操作。
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公开(公告)号：US4312191A
公开(公告)日：1982-01-26
申请号：US122148
申请日：1980-02-15
申请人： Guido Biagini
发明人： Guido Biagini
摘要： 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. In the final portion of the system, the expansion cooling turbine has an output coupled to the cabin to deliver conditioned air, which has been cooled, to the cabin. The system heating cycle relies on heated bleed air mixed with cooled air from the expansion turbine to heat the cabin.
摘要翻译： 本发明涉及一种为飞机机舱或座舱提供环境控制的空调系统。 系统冷却循环包括：旋转电源和涡轮机，其包括固定到用于提供压缩空气的动力轴的动力压缩机。 旋转电源驱动地联接到动力轴以以给定的速度运行。 膨胀冷却涡轮安装在与动力轴同心的轴上。 提供动力驱动的风扇，用于将环境空气源引导并通过热交换器。 动力压缩机分别连接到机舱并且通过热交换器连接到膨胀冷却涡轮机的输入端，从而从舱室抽出空气并将压缩空气输送到膨胀冷却涡轮。 膨胀冷却涡轮设计成以与动力轴的给定速度不同的速度运行。 在系统的最后部分中，膨胀冷却涡轮具有联接到舱室的输出，以将经冷却的调节空气输送到舱室。 系统加热循环依赖于与来自膨胀涡轮机的冷却空气混合的加热放气，以加热舱室。
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