Integrated analyzing and setting method for control parameters of three-loop automatic pilot

A technology of autopilot and control parameters, applied in the field of aircraft control, which can solve problems such as phase lag system stability

Inactive Publication Date: 2013-05-01
BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE +1
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AI Technical Summary

Problems solved by technology

[0004] However, in practical engineering applications, the influence of the phase lag caused by the dynamic characteristics of autopilot-related components on system stability cannot be ignored

Method used

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  • Integrated analyzing and setting method for control parameters of three-loop automatic pilot
  • Integrated analyzing and setting method for control parameters of three-loop automatic pilot
  • Integrated analyzing and setting method for control parameters of three-loop automatic pilot

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Embodiment Construction

[0047] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

[0048] Such as figure 2 As shown, a three-loop autopilot control loop structure block diagram, n c is an overload instruction; n′ c is the overload command after correction; k 11 is the attitude angular velocity control parameter; k 01 is the attitude angle feedback control parameter; k c is the overload feedback control parameter; k a Calibrate parameters for overload commands; is the integral control link in the frequency domain; G R transfer function model for the actuator; G 1 is the pitch rate of the guided aircraft; that is, the transfer function model of the yaw rate relative to the control output of the actuator; G 2 Be the normal overload, that is, the transfer function model of lateral overload relative to the pitch rate (yaw rate) of the guided aircraft; G g is the transfer function model of the angular rate sens...

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Abstract

The invention relates to the technical field of spacecraft control and particularly discloses an integrated analyzing and setting method for control parameters of a three-loop automatic pilot. The integrated analyzing and setting method comprises the following steps of: firstly, establishing a control loop model of the three-loop automatic pilot; secondly, setting a pitching motion relative damping coefficient after compensating an attitude angular velocity feedback circuit to acquire an attitude angular velocity control parameter and the open-loop cross-over frequency of the attitude angular velocity feedback circuit; thirdly, acquiring an open-loop gain system of a control system according to an open-loop transmission function of the control system and acquiring a closed-loop transmission function which is inputted to a guidance spacecraft by an overload instruction after correction and is outputted in an overload manner; and fourthly, acquiring the attitude angular velocity control parameter, an overload feedback control parameter and an overload instruction correction parameter. According to the integrated analyzing and setting method, the solving of a nonlinear equation is avoided; in addition, attitude stability and attitude control precision of the guidance spacecraft can be maintained by the acquired parameter under various single deviations and combined deviation and the balancing state of the spacecraft required by the guidance instruction is quickly realized.

Description

technical field [0001] The invention belongs to the technical field of aircraft control, and in particular relates to an integrated analytical setting method for control parameters of a three-loop autopilot. Background technique [0002] With its high-precision, flexible and efficient combat performance, guided aircraft has become an important direction in the development of modern weapons. One of its key technologies is: under the premise of a certain control structure, quickly obtain high-performance stable control parameters to ensure that the aircraft Flight stability during flight to meet the guidance system's requirements for the aircraft's flight attitude. [0003] At present, many guided aircraft use a three-loop autopilot. Based on the structure of the two-loop overload pilot, it introduces attitude angle feedback information into the inner loop, which is equivalent to forming three feedback loops for overload, attitude angular velocity, and attitude angle. If the ...

Claims

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Application Information

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IPC IPC(8): G05D1/08G05B13/04
Inventor 郭洪波庄凌
Owner BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE
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