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SUPERSONIC AIRCRAFT WITH ACTIVE LIFT DISTRIBUTION CONTROL FOR REDUCING SONIC BOOM
SUPERSONIC AIRCRAFT WITH ACTIVE LIFT DISTRIBUTION CONTROL FOR REDUCING SONIC BOOM
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机译:具有主动升降分配控制的超音速飞机,可减少声振
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摘要
Methods and systems for actively reducing sonic boom in commercial supersonic aircraft and other supersonic aircraft (300) are described herein. A method for operating an aircraft in accordance with one aspect of the invention includes configuring at least one lift control device (324) to produce a first streamwise lift distribution, and flying the aircraft at a subsonic speed while the lift control device (324) is configured to produce the first streamwise lift distribution (304a) . The method can further include configuring the lift control device (324) to produce a second streamwise lift distribution (304b) , and flying the aircraft at a supersonic speed while the lift control device (324) is configured to produce the second streamwise lift distribution (304b) . The first streamwise lift distribution (304a) produces an N-shaped ground pressure signature (110) and a corresponding first sonic boom at the supersonic speed. The second streamwise lift distribution (304b) , however, produces a 'shaped' ground pressure signature (210) and a corresponding second sonic boom that is less than the first sonic boom at the supersonic speed.
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