Abstract: A valve actuator having a drive shaft, which, in use, is configured to adjust a valve between an open position and a closed position, an AC induction motor for driving the drive shaft a contactless position sensor configured to, in use, output a signal representing an angular position of the drive shaft or the valve, and a controller configured to control the AC motor in accordance with the signal output by position sensor.
Abstract: An on board inert gas generation system for an aircraft receives air from a relatively low pressure source such as low pressure engine bleed air or ram air and passes it to a positive displacement compressor to increase the pressure thereof to be suitable for supply to an air separation module. All or a portion of the compressed air from the positive displacement compressor may be supplied by operation of a valve to one or more other aircraft components to provide at least one of power, heat or pressure thereto.
Abstract: An on board inert gas generation system receives cabin air, or air from another relatively low pressure source, passing a portion thereof through an energy recovery turbine to ambient to extract power which is used to provide all, or part of the energy required to drive a positive displacement compressor to co press another portion of cabin air to increase the pressure thereof to be suitable for supply to an air separation module.
Abstract: An on board inert gas generation system for an aircraft receives air from a relatively low pressure source such as low pressure engine bleed air or ram air and passes it to a positive displacement rotary compressor to increase the pressure thereof to be suitable for supply to an air separation module. The speed of the positive displacement compressor may be adjusted across a wide range in order to provide efficient operation in cruise and descent phases of aircraft flight.
Abstract: An inerting system for an aircraft fuel tank (10) uses an air separation device (12) to produce a supply of nitrogen-enriched air to replenish the fuel tank on consumption of fuel and to maintain the pressure difference across the walls of the tank (10) below design limits. The air separation device (12) provides substantially the whole of the mass of the gas required and so there is substantially no inward venting. This provides a substantially homogenous nitrogen content in the air in the tank (10).
Abstract: Operation of a power-by-light valve (15) by a source (11) along an optical fibre (13) is monitored by means of optical sensors (14) from which light passes back along fibre (13) to monitoring and processing units (16, 17). The sensors (14) include fibre bragg gratings (41, 43) for detecting differential pressure across diaphragms (42) and for detecting temperature. At the input end, an optical coupler (12) supplies sensor signals to units (16, 17) which can control source (11) via a signal (32).
Type:
Grant
Filed:
August 23, 2001
Date of Patent:
January 2, 2007
Assignee:
Eaton Aerospace Limited
Inventors:
Jirapong Lim, Qingping Yang, Phillip Richard Jackson, Barry Edward Jones
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