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System and method for coupling aircraft membrane nitrogen making oil tank inerting and cockpit environment control

A coupling system and fuel tank technology, applied in the field of aviation systems, can solve problems such as reducing the available power for flight, and achieve the effects of reducing the weight of the cabin structure, increasing the internal and external pressure difference, and reducing the exhaust pressure.

Active Publication Date: 2020-04-28
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0005] However, both the inerting system and the air circulation system need to provide engine bleed air, which reduces the available power for flight

Method used

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  • System and method for coupling aircraft membrane nitrogen making oil tank inerting and cockpit environment control

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Embodiment Construction

[0028]The present invention will be further described below in conjunction with embodiment. The following descriptions are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0029] Such as figure 1 As shown, a schematic diagram of a coupling system of aircraft membrane nitrogen fuel tank inerting and cockpit environment control of the present invention, the system of the present invention includes engine bleed air, first control valve 1, filter 2, dryer 3, heater 4 , humidity regulator 5, ozone converter 6, second control valve 7, first electric pressure regulating valve (8), first manual pressure regulating valve 9, first pressure sensor 10, first temperature sensor 11, first flow rate Sensor 12, humidity sensor 13, ozone concentration sensor 14, particle size de...

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Abstract

The invention discloses a g system for coupling aircraft membrane nitrogen making oil tank inerting and cockpit environment control, and belongs to the technical field of aviation systems. The systemis formed by coupling an aircraft fuel tank hollow fiber membrane nitrogen production inerting system with a cockpit environment control system, that is exhaust gas with high oxygen concentration in the inerting system is injected by an injection pump and is mixed with low-temperature gas at an outlet of a turbine cooler in an environmental control system, then the obtained mixture is sent to thecockpit, the temperature, the pressure, the oxygen concentration and the air cleanliness in the cockpit are adjusted, and the health and physiological needs of drivers and passengers are guaranteed. The engine air entraining amount of the cockpit environmental control system is effectively reduced, and the fuel oil compensation loss is reduced; the oxygen concentration level of the cockpit is increased, the pressure height of the cockpit is increased, and the structural weight of the cockpit is reduced; and exhaust pressure of a membrane nitrogen making device is reduced, internal and externalpressure difference of a separation membrane is increased, and separation efficiency of a membrane device is improved.

Description

technical field [0001] The invention belongs to the technical field of aviation systems, and relates to the coupling of an aircraft fuel tank inerting system and an environmental control system, in particular to an aircraft cockpit diffused oxygen supply system, in particular to a coupling of an aircraft membrane nitrogen-making fuel tank inerting and cockpit environment control systems and methods. Background technique [0002] In the past 50 years, there have been 18 fuel tank explosion accidents of transport aircraft worldwide, killing a total of 542 people, which has become one of the main threats to civil aviation safety. In 1996, the combustible vapor of the TWA800 central wing fuel tank of Boeing 747 aircraft was ignited and caused an explosion, and all crew members were killed. This prompted the US Federal Aviation Administration to issue a series of amendments, advisory notices and airworthiness regulations, mandating that effective measures be taken to reduce ignit...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D37/32B64D13/06B64D13/08
CPCB64D13/06B64D13/08B64D37/32B64D2013/0651B64D2013/0662B64D2013/0681
Inventor 刘卫华彭孝天张瑞华
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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