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Propulsion system for an aircraft, a nozzle for use with the propulsion system, and a method of manufacturing a propulsion system for an aircraft
Propulsion system for an aircraft, a nozzle for use with the propulsion system, and a method of manufacturing a propulsion system for an aircraft
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机译:用于飞机的推进系统,用于推进系统的喷嘴,以及用于为飞机制造推进系统的方法
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摘要
A propulsion system for an aircraft includes: (1) an engine configured to generate a mass flow, (2) a nozzle having a pathway having a throat and a trailing edge, the throat or the trailing edge being configured to enlarge and contract, (3) a deployable obstructer disposed in the nozzle, (4) a first pressure sensor to sense the static pressure of the mass flow at the nozzle exit, (5) a second pressure sensor to sense the ambient pressure proximate the aircraft, and a (6) controller. The controller is coupled with the first and second pressure sensors, the deployable obstructer, and the throat or the trailing edge (whichever is configured to enlarge and contract). The controller receives the static and ambient pressures and when there is a disparity, the controller controls at least one of the deployable obstructer, the throat, and the trailing edge in a manner that reduces the disparity.
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