Distributed attitude ultra-agile maneuvering control method of spacecraft based on saturation backstepping method
A spacecraft and distributed technology, applied in the direction of motor vehicles, aerospace vehicles, aerospace vehicle guidance devices, etc., can solve the problems of control torque and attitude angular velocity constraints, without considering the reduction of the burden on the actuator, etc., to achieve the goal of reducing the burden Effect
Active Publication Date: 2022-07-08
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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[0010] Obviously, the above research results have not really achieved ultra-agile maneuvering with an attitude angular velocity exceeding 10deg / s, and most of the research results have not constrained the control torque and attitude angular velocity, nor have they considered reducing the burden on the actuator
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[0048] The present invention will be further described in detail below in conjunction with the accompanying drawings.
[0049] The invention has five major benefits: ultra-agile maneuvering with saturation constraints, controllable segmented time, reducing the burden of attitude control actuators, distributed attitude maneuvering control, and model independence; figure 1 Medium (g) i Represents the i-th element of (g), i.e. the i-th channel, the AB segment is the acceleration stage, the BC segment is the uniform speed stage, and the CD segment is the deceleration stage; the super-agile maneuver with saturation constraints is: the spacecraft performs a large-angle maneuver When , the attitude angular velocity has a maximum value of 10-15deg / s; the segment time can be controlled as follows: when the spacecraft is maneuvering at a large angle, such as figure 1 As shown in (a), the acceleration torque and deceleration torque of the controller do not restrict each other, so that t...
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The invention relates to a distributed attitude super-agile maneuver control method of a spacecraft based on a saturated backstepping method, and belongs to the technical field of satellite attitude control. The design of the ultra-agile maneuvering controller of the spacecraft of the present invention combines saturation control and backstepping control, introduces multi-level saturation to the virtual input function, and has five major benefits: ultra-agile maneuvering with saturation constraints, segmented time controllable, lightening Attitude control actuator burden, distributed attitude maneuver control, and model independence. The invention introduces saturation constraints for the backstepping method for the first time, designs a super-agile maneuver control law for the attitude of the spacecraft, realizes the ultra-agile maneuver and distributed attitude control with an attitude angular velocity of 10-15deg / s, and effectively solves the mutual interaction between the acceleration phase and the deceleration phase. The restriction problem limits the maximum control torque and the maximum attitude angular velocity, reduces the burden of the attitude control actuator, and is suitable for spacecraft with unknown rotational inertia.
Description
technical field [0001] The invention relates to a distributed attitude super-agile maneuver control method of a spacecraft based on a saturation backstepping method, and belongs to the technical field of satellite attitude control. Background technique [0002] The agile maneuvering of spacecraft is still a research hotspot because the fast maneuverability of the spacecraft can make it better to complete the task. The maximum attitude angular velocity of traditional spacecraft agile maneuvering is about 5deg / s. There are a lot of research results, but the research on ultra-agile maneuvering of spacecraft with a maximum attitude angular velocity exceeding 10deg / s is still blank, especially considering the reduction of attitude. A spacecraft ultra-agile maneuvering control method for controlling actuator burden. [0003] At present, the research related to the rapid maneuvering of spacecraft is still limited to ordinary agile maneuvering control, including PD / PID (proportiona...
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IPC IPC(8): B64G1/24
CPCB64G1/24B64G1/245
Inventor 吴云华郑墨泓何梦婕陈志明华冰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS