A method for smooth control of trajectory end position and attitude of unpowered aircraft

A terminal position, smooth control technology, applied in attitude control, three-dimensional position/course control, adaptive control and other directions, can solve the problem of only considering the flight trajectory speed inclination angle, the terminal attitude only considers the angle of attack, etc., to achieve accurate control, Solve the problem of comprehensive control of position and attitude, and the effect of simple principle

Active Publication Date: 2019-09-17
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

This type of method has clear theoretical thinking and good control performance, but most of them only consider the control of the flight trajectory velocity inclination angle, and the terminal attitude usually only considers the situation of the angle of attack.

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  • A method for smooth control of trajectory end position and attitude of unpowered aircraft
  • A method for smooth control of trajectory end position and attitude of unpowered aircraft
  • A method for smooth control of trajectory end position and attitude of unpowered aircraft

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Embodiment Construction

[0026] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0027] Such as figure 1 Shown, a kind of non-powered vehicle ballistic terminal position and attitude smooth control method of the present invention, its steps are:

[0028] S1: According to the accuracy requirements for the terminal control of the aircraft, design the position control loop and attitude control loop of the three channels respectively according to the existing methods in this field;

[0029] In a specific application example, the position control loop of three channels can be designed according to the accuracy requirements of the end position of the unpowered aircraft. For example, the overload plus angular rate feedback control loop can be used to ensure that the designed aircraft can accurately reach the target point.

[0030] Consider the atmospheric environment parameters near the target point, and design the thre...

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Abstract

The invention discloses an unpowered aircraft trajectory tail end position and attitude smoothing control method comprising the following steps: in step S1, according to precision requirements for aircraft tail end, a position control loop circuit and an attitude control loop circuit of three passageways are respectively designed; in step S2, needed smoothing time is calculated; in step S3, for rudder instruction output of the position control loop circuit and the attitude control loop circuit, linear smoothing operation is conducted according to the smoothing time and smoothing distance, and rudder instructions that needs to be executed are output. The method disclosed in the invention is advantaged by simple principles, easy-to-implement property, high control precision and the like.

Description

technical field [0001] The invention mainly relates to the field of control of aircraft, in particular to a method for smooth control of ballistic end position and attitude of an unpowered aircraft. Background technique [0002] In order to realize the control of the terminal position of the aircraft, the traditional method is to establish the relative relationship between the aircraft and the target point, design the guidance law to generate guidance commands related to the position (such as overload commands), and the control system receives the guidance commands and adjusts the body attitude to generate corresponding The overload to realize the tracking of the guidance order. Among them, the use of aerodynamics to control the space position by controlling the attitude of the projectile is the control method adopted by most aircrafts at present. This control method mainly uses the aerodynamic rudder surface to control the attitude of the projectile. Low, widely used in va...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04G05D1/08G05D1/10
Inventor 郭鸿武刘建斌曾宇航张佳辉
Owner NAT UNIV OF DEFENSE TECH
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