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An aircraft aerodynamic characteristic and control design method with relaxation of yaw static stability

A technology of aerodynamic characteristics and design methods, applied in non-electric variable control, vehicle position/route/altitude control, attitude control, etc., can solve problems such as shape damage, bring stability control, and change aircraft characteristics, and improve flight reliability. The effect of reducing the design pressure and simplifying the lateral layout design

Active Publication Date: 2018-05-22
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When this type of aircraft flies for a long time, the long-term heating of the side parts will put a greater pressure on the heat insulation. Under the current technical capabilities, ablation problems are prone to occur, resulting in damage to the shape, which in turn leads to changes in the characteristics of the aircraft, bringing stability control problem

Method used

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  • An aircraft aerodynamic characteristic and control design method with relaxation of yaw static stability
  • An aircraft aerodynamic characteristic and control design method with relaxation of yaw static stability
  • An aircraft aerodynamic characteristic and control design method with relaxation of yaw static stability

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Embodiment Construction

[0023] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0024] In order to simplify the lateral layout design of the aircraft and improve flight reliability, such as Figure 5 As shown, the present invention proposes an aircraft aerodynamic layout and control strategy design method that relaxes the yaw static stability, which can achieve stable control of the lateral passage of the aircraft while reducing the requirements for the yaw static stability characteristics.

[0025] Realization principle of the present invention is as follows:

[0026] (1) Establish the open-loop state equation of the lateral channel of the aircraft as follows:

[0027]

[0028] In the formula,

[0029] c 1β = sinα,c 2β =cosα,c 1γ =cosα,c 2γ =-sinα

[0030]

[0031]

[0032] β: sideslip angle

[0033] ω x1 : roll angular velocity

[0034] ω y1 : Yaw rate

[0035] gamma v : roll angle

[0036] δ γ : r...

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Abstract

The invention discloses aerodynamic characteristics of an aircraft with widening and static yawing stability and a control design method, pertaining to the control field of high-speed plane symmetry aircrafts. By integrated design of aerodynamic characteristics and control strategies of aircrafts, the requirement for static yawing stability is lowered and stability control of transverse lateral channels of the aircraft is achieved. The aerodynamic characteristics of an aircraft with widening and static yawing stability and the control design method have following beneficial effects: the requirement for static yawing stability is lowered; a lateral layout of the aircraft is simplified; design pressure of anti-thermal insulation is lowered; and stability of flight is improved.

Description

technical field [0001] The invention relates to an aircraft aerodynamic characteristic and control design method for relaxing yaw static stability, and belongs to the field of high-speed plane symmetrical aircraft control. Background technique [0002] For high-speed plane-symmetrical aircraft, it generally relies on strong yaw static stability to achieve stable control of lateral channels, and strong yaw static stability needs to be realized through complex lateral layout. When this type of aircraft is flying for a long time, the long-term heating of the lateral parts will put a greater pressure on the anti-heat insulation. Under the current technical capabilities, ablation problems are prone to occur, resulting in damage to the shape, which in turn leads to changes in the characteristics of the aircraft, bringing Stability control issues. Contents of the invention [0003] The technical problem of the present invention is: to overcome the deficiencies of the prior art, ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/00G05D1/08
CPCB64F5/00G05D1/0825
Inventor 王颖陈敏闵昌万王毓栋黄兴李肖振陈安宏刘全军刘秀明周禹孙超逸姜智超闫颖鑫李欣肖文陈瞳王少慧
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST