Control method for reducing grand gesture perturbation under interative guidance

A control method and iterative technology, applied in the field of guidance, can solve problems such as system instability

Active Publication Date: 2010-06-09
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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Problems solved by technology

After adopting iterative guidance, a set of program angles will be regenerated in each iteration cycle, and there may be angle jumps between the newly generated program angles and the previous program an

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  • Control method for reducing grand gesture perturbation under interative guidance
  • Control method for reducing grand gesture perturbation under interative guidance
  • Control method for reducing grand gesture perturbation under interative guidance

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Embodiment Construction

[0042] Taking 5-period rolling accumulation as an example, the process of reducing attitude disturbance in the present invention is specifically described.

[0043] 1. Collect data

[0044] The aircraft body coordinate system O in the jth sampling period is measured by the accelerometer of the aircraft inertial measurement equipment 1 x 1 Y 1 Z 1 The pulse value of the lower positive and negative channels, P x+ j , P x- j , P y+ j , P y- j , P z+ j , P z- j , where X 1 The direction from the center of mass of the aircraft to the head is the positive direction, Y 1 with X 1 Vertical, pointing upward from the center of mass of the aircraft in its longitudinal symmetry plane is the positive direction, Z 1 with the longitudinal plane of symmetry X 1 o 1 Y 1 Vertical, pointing right from the center of mass of the aircraft is the positive direction, O 1 is the center of mass of the aircraft, and j is a natural number.

[0045] 2. Calculate apparent velocity in...

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Abstract

The invention discloses a control method for reducing grand gesture perturbation under interative guidance, comprising the following steps of: acquiring data, calculating apparent velocity increment; smoothly processing axial apparent acceleration; substituting the smoothed complete combustion time Tauin into an aircraft interative guidance formula to obtain the smoothed iterative program angle Psicxn; and finally carrying out amplitude limiting processing on iterative program angle increment delta Psicx at the current moment to obtain a stable iterative program angle output value at the current moment. In the invention, smooth and amplitude limiting measures are taken in the whole process of generating iterative program angle so as to reduce the grand gesture perturbation and ensure thatthe input quantity adopted by subsequent interative calculation and the smooth transition output by the iterative program angle cannot generate jumping, thereby ensuring that the input of a gesture control system cannot generate jumping and being greatly beneficial to improving the reliability of an aircraft control system and reducing the interference and influence in the flying; the grand gesture perturbation under interative guidance can be reduced by adopting the method without improving the sampling resolution of hardware, i.e without modifying an aircraft device; and the invention is simple and rapid, and has remarkable effect for reducing the gesture perturbation.

Description

technical field [0001] The invention relates to a method for reducing attitude disturbance under iterative guidance based on smoothing technology, belongs to the field of guidance technology, and can be applied to various aircrafts using iterative guidance as a guidance mode to reduce the large attitude disturbance of the aircraft under iterative guidance. Background technique [0002] Iterative guidance is an optimal guidance method developed on the basis of modern optimal control principles and computer application technology. It puts forward certain performance index requirements for the guidance law, and performs real-time calculations according to the initial value and terminal constraints to form an adaptive mission. control instructions. Since it is difficult to adjust the thrust of conventional liquid engines, the control means of guidance is mainly to change the direction of the thrust vector and control the shutdown time of the engine. Iterative guidance is to mak...

Claims

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Application Information

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IPC IPC(8): B64G1/24
Inventor 巩庆海吕新广李新明冯昊刘茜筠肖利红宋征宇孙友王丹晔
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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