CMG steering method and system based on frame angle self-adaptive adjustment
A technology for self-adaptive adjustment and control system, applied in the direction of self-adaptive control, control/regulation system, general control system, etc., it can solve the problems affecting the realization of aircraft performance indicators and the inability of satellites to output the desired control torque, and achieve a stable Effect
Active Publication Date: 2018-07-27
BEIJING INST OF CONTROL ENG
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Problems solved by technology
[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a CMG control method and system based on frame angle adaptive adjustment, and to solve the problem that the satellite cannot output the expected control torque due to the singularity of the CMG, and even affect the performance index of the aircraft implementation problem
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[0023] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that the present disclosure will be more thoroughly understood, and will fully convey the scope of the present disclosure to those skilled in the art. It should be noted that the embodiments of the present invention and the features of the embodiments may be combined with each other under the condition of no conflict. The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
[0024] Method embodiment
[0025] figure 1 It is a flowchart of the CMG manipulation method based on frame angle ad...
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The invention discloses a CMG steering method and system based on frame angle self-adaptive adjustment. The method comprises the following steps of 1, calculating the included angles of all CMG angular momentum direction unit vectors and flight vehicle expected control moment direction unit vectors in sequence to obtain an included angle vector theta including all included angles, wherein the flight vehicle expected control moment direction unit vectors are shown in the description, if the minimum included angle in the included angle vector theta is smaller than a threshold value allele, self-adaptive adjustment is needed, and the adjustment direction is calculated; 2, within the self-adaptive adjustment time, calculating the sinusoidal motion rotation speed and the corresponding moment ofa CMG frame corresponding to the minimum included angle in step 1, and then calculating follow-up compensation rotation speeds of other CMGs; 3, merging the sinusoidal motion rotation speed of the CMG frame corresponding to the minimum included angle in step 2 and the compensation rotation speeds of other CMGs with other steering laws of the CMGs to serve as CMG control instruction input. By means of the CMG steering method and system based on the frame angle self-adaptive adjustment, the problems that a satellite cannot output expected control moment, and the achievement of the performance index of the flight vehicle is even influenced due to CMG singular problems are solved.
Description
technical field [0001] The invention belongs to the technical field of automatic control of aircraft, and in particular relates to a CMG manipulation method and system based on frame angle adaptive adjustment. Background technique [0002] As aircraft missions have become more complex, the application of Control Moment Gyroscopes (CMGs) has become more widespread. CMG has excellent torque amplification ability and energy storage ability. In order to use CMG well, it is necessary to ensure its stability and reliability during operation, and it is very important to design an effective control law. The main problem of CMG is the singularity problem. Due to the existence of the singularity, it cannot guarantee the accurate output of the desired control torque, cannot follow the planned attitude trajectory, and even affects the realization of performance indicators such as rapid maneuvering and rapid stability of the aircraft. Mainly rely on the design of the manipulation law. ...
Claims
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Login to View More IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 袁利王新民何海锋姚宁
Owner BEIJING INST OF CONTROL ENG