Transverse lateral guidance law design method

A design method and guide technology, applied in the field of control law design, can solve the problems of landing failure, the aircraft easily deviates from the glide path, and the landing accuracy is reduced.

Active Publication Date: 2014-08-20
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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AI Technical Summary

Problems solved by technology

The existence of disturbance will cause the aircraft to easily deviate from the predetermined glide

Method used

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  • Transverse lateral guidance law design method
  • Transverse lateral guidance law design method
  • Transverse lateral guidance law design method

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Experimental program
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Embodiment Construction

[0028] 1) The lateral deviation signal formed by the difference between the aircraft height measured by the radar and the ideal glide path is combined with the deck motion compensation lateral deviation to form the final lateral deviation signal H er ;

[0029] the y er =y er1 +y dmc

[0030] Among them, the lateral position deviation of the aircraft from the ideal glideslope is y er1 =y 理想下滑道 -y 飞机 Generally measured by the measuring device, no design work is required; the compensation lateral deviation of the deck motion compensation output is y dmc , obtained from the output of the lateral deck motion compensator, here simply consider y dmc = 1.5 sin(0.5t). but

[0031] the y er =y er1 +y dmc =y 理想下滑道 -y 飞机 +1.5sin(0.5t)

[0032] 2) For the deviation signal y er The α-β filter is used to suppress the electronic noise in the radar measurement information and improve the measurement accuracy. Among them, the α filter is used to filter out the height error y ...

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Abstract

The invention provides a transverse lateral guidance law design method, and belongs to the technical field of the full-automatic airplane landing control law design. The guidance law design method is targeted for the full-automatic airplane landing process, and belongs to the specific step of the full-automatic airplane landing; a control instruction is calculated according to a motion platform and airplane movement and posture states, thereby providing a command signal for a flight control system; and the guidance law design is a key step for realizing closed loop. According to the guidance law design method, lateral deviation information of an airplane is utilized; and calculation is carried out through a designated algorithm, thereby providing a roll angle command signal for the airplane, and realizing lateral control in the full-automatic airplane landing process. Compared with the conventional PID control, in order to improve the maneuverability of a system, the guidance law design method introduces double differential signals to form a PIDDD controller. The main advantages of the guidance law design method are that the measurement information can be rapidly and effectively converted into the command signal needed in the airplane flight control system; the guidance of the precise airplane landing is achieved; and the closed-loop cooperation control is realized.

Description

technical field [0001] The invention relates to a method for designing a lateral guidance law and belongs to the technical field of control law design. Background technique [0002] When an aircraft lands on a moving platform, it will be subject to complex external disturbances, including wake turbulence, gusts of wind, and platform movement, etc., and its landing environment is far worse than that of land-based aircraft. The existence of disturbance will cause the aircraft to easily deviate from the predetermined glide path during landing, reduce its landing accuracy, and even lead to landing failure in severe cases. Guidance control law is the key and core to ensure that the aircraft can quickly and accurately track the predetermined glide path and achieve a safe landing under the severe motion of the motion platform caused by wake turbulence, gusts of wind, and adverse sea conditions. [0003] The guidance law algorithm is bound in the landing guidance computer and consi...

Claims

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Application Information

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IPC IPC(8): G05B13/04G05D1/10
Inventor 王志刚桂敬玲丁岩连莉莉
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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