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Airplane attitude control method under influence of wind field

A technology of attitude control and wind field, applied in the field of flight control

Active Publication Date: 2015-12-23
北京创奇视界科技有限公司
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention mainly solves the control problem of the aircraft in the micro-downdraft airflow field

Method used

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  • Airplane attitude control method under influence of wind field
  • Airplane attitude control method under influence of wind field
  • Airplane attitude control method under influence of wind field

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Embodiment Construction

[0076] The method of the present invention will be specifically described below in conjunction with the accompanying drawings and embodiments.

[0077] like Figure 7 Shown, the wind field of the present invention influences a kind of aircraft attitude control method and can be finished according to the following steps:

[0078] Step 1: Establish the motion equation of the aircraft under the influence of the wind field.

[0079] Specifically include:

[0080] Step 1.1: Establish the dynamics and kinematics equations of the center of mass of the aircraft under wind field disturbance, and obtain the equations of airspeed, angle of attack, and sideslip angle:

[0081] In the body coordinate system, record the body axis velocity vector as V=(u, v, w) Τ , u, v, w are the components of V on the x, y, and z axes of the aircraft system, and the rotational angular velocity of the aircraft is Ω=(p, q, r) Τ , p, q, r are roll angular velocity, pitch angular velocity, yaw angular velo...

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Abstract

The present invention discloses an airplane attitude control method under the influence of a wind field. The method comprises the following steps of 1, establishing an airplane motion equation under the influence of the wind field; 2, establishing a micro-downburst wind field suitable for the flight real-time simulation based on the vortex ring principle; 3, designing a control loop based on a non-linear dynamic inversion theory; 4, establishing an overall simulation model containing the wind field and the control, and changing a gain coefficient in the model by a tracking result. According to the present invention, the micro-downburst wind field established based on the vortex ring principle can be embedded in a flight real-time simulation model to calculate the wind field at an airplane center of mass position real-timely, thereby improving the calculation precision, and being suitable for the aircraft motion and control simulation under the influence of the wind field.

Description

technical field [0001] The invention belongs to the technical field of flight control, in particular to an aircraft attitude control method under the influence of a wind field. Background technique [0002] The atmospheric environment, especially the wind field environment, has a significant impact on the dynamic characteristics of the aircraft. Some complex wind fields can also cause flight accidents such as stalls and control failures, which directly endanger flight safety. Micro-downdraft is an atmospheric movement that occurs below 1 kilometer, with an outflow radius of less than 4 kilometers, and sudden changes in wind speed or direction. It is the most dangerous form of atmospheric movement in low-altitude wind shear. The reason why the micro-downdraft airflow causes flight accidents is mainly due to two reasons. One is that it has the characteristics of short duration, small range and high intensity, which makes it difficult to detect and warn. The other reason is tha...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
Inventor 王江云陈姣李盖
Owner 北京创奇视界科技有限公司
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