CMG manipulation method and system based on adaptive adjustment of frame angle
An adaptive adjustment and control system technology, applied in the direction of adaptive control, control/adjustment system, general control system, etc., can solve the problems that affect the realization of aircraft performance indicators, satellites cannot output expected control torque, etc., and achieve a stable Effect
Active Publication Date: 2020-05-15
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. Although 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 for more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.
[0024] method embodiment
[0025] figure 1 It is a flowchart of a CMG manipulation method based on frame angle adaptive adjustment provided by an embodiment...
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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 aircraft automatic control, and in particular relates to a CMG manipulation method and system based on frame angle self-adaptive adjustment. Background technique [0002] As the mission of aircraft becomes more and more complex, the application of control moment gyroscope (CMG) is more and more extensive. 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 its accurate output of the desired control torque, and cannot track and plan the attitude trajectory, and even affect the realization of performance indicators such as rapid maneuvering and rapid stability of the aircraft. The solution to the singularity Mainly...
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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 袁利王新民何海锋姚宁
Owner BEIJING INST OF CONTROL ENG