Aircraft stall protection system

A technology for aircraft and flight control, applied in the direction of control/regulation systems, instruments, aircraft parts, etc.

Active Publication Date: 2017-03-08
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, although existing stall protection systems prevent the aircraft from drifting into areas of uncontrolled flight, they do not necessarily maximize aircraft performance, and pilot input can actually cause the aircraft to deplete energy faster than expected

Method used

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  • Aircraft stall protection system
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Embodiment Construction

[0022] While a detailed description of numerous different embodiments is set forth below, it should be understood that the legal scope of the present invention is defined by the words of the claims appended to this patent. The detailed description should be construed as exemplary only and does not describe every possible embodiment, since describing every possible embodiment would also be impractical. Numerous alternative embodiments could be implemented, using either current technology or technology developed after the filing date of this patent, which would still fall within the scope of the claims.

[0023] Unless a term is expressly defined in this patent using the phrase "As used herein, the term '____' is hereby defined to mean..." or similar, there is no intent, either expressly or by implication, to limit the meaning of that term beyond its ordinary or ordinary meaning, and such terms should not be construed as limiting in scope based on any statement made in any part ...

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Abstract

The invention discloses an aircraft stall protection system and a method thereof. The aircraft stall protection system include calculating a first angle of attack and a second angle of attack based on aircraft configuration and environmental conditions, the first angle of attack being greater than the second angle of attack. The system and method limit the actual aircraft angle of attack to the first angle of attack for a predetermined period of time and thereafter the system and method limit the actual aircraft angle of attack to the second angle of attack. The system and method allow the aircraft operator or pilot to extract maximum performance from the aircraft for any given set of flight conditions, without the risk of stalling or remaining in a high drag state for a prolonged period of time. This system and method are suitable for use in conjunction with a stall warning system.

Description

technical field [0001] The present invention relates to aircraft stall protection systems, and more particularly, to aircraft stall protection systems that calculate two different maximum angles of attack and limit the aircraft angle of attack to said at least two different maximum angles of attack at different times. Background technique [0002] Typically, an aircraft has an attached flow or non-stall flight region and a detached flow or stalled flight region. [0003] In the region of attached flow flight, the fluid (air) flowing over the flight control surfaces behaves in a predictable and predictable manner, and thus the control surfaces can be manipulated to control the flight path and orientation of the aircraft as it is airborne. In fixed-wing aircraft, the region of clinging flow flight includes the wing below the stall angle of attack and the angle of attack of the horizontal stabilizer (which is the angle of incidence formed between the chord line of the airfoil a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D45/00B64C9/00B64C19/02
CPCB64C9/00B64C19/02B64D45/00G05D1/0833B64D43/02G05D1/0825B64C13/16B64D31/06G05D1/0816
Inventor D·D·利奥波德D·L·威尔逊N·D·米尔斯
Owner THE BOEING CO
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