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Attitude control method

A technology of attitude control and control method, applied in attitude control, space navigation equipment, space navigation equipment, etc., can solve problems such as increasing the cost of satellite hardware development

Active Publication Date: 2017-07-04
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Abstract
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  • Application Information

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Problems solved by technology

This puts high demands on the design of attitude sensors and actuators, and greatly increases the development cost of satellite hardware.

Method used

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Embodiment Construction

[0097] The present invention will be further elaborated below by describing a preferred specific embodiment in detail in conjunction with the accompanying drawings.

[0098] Such as figure 1 Shown, a kind of posture control method of the present invention comprises the following process:

[0099] Step 1. Use the second pulse signal to align the on-board time that affects the satellite attitude accuracy; that is, figure 2 As shown, the control computer receives the high-precision second pulse signal periodically generated by the time calibration center, and performs validity judgment and error correction on the local reference time. The flywheel speed command sending time, the thruster air injection command sending time and the thruster orbit parameter calculation time are corrected to ensure the time synchronization used for attitude control and reduce the attitude determination error and attitude control error caused by time asynchrony. Taking the correction of the exposur...

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Abstract

The invention discloses an attitude control method. The attitude control method comprises the following procedures that the on-satellite time influencing the satellite attitude precision is aligned through a second pulse signal; a satellite sensor error used for satellite attitude measurement is corrected in real time; the gravity gradient disturbance torque of an oblique flying satellite is compensated through a dynamics coupling relationship; the satellite flexibility is restrained through an input forming control method in the attitude controlling process; the attitude control law of an angular velocity feedforward instruction is increased through position and speed double loops and a position correcting loop to achieve high-precision and high-stability attitude guidance control; and quick attitude maneuver of the large-inertia satellite is achieved through a saturated sliding mold structural control algorithm. The attitude control method has the advantages that the computing method is simple, control is flexible, the attitude control method can be applied to attitude control of the large-inertia large-flexible oblique flying satellite, the property of the satellite is greatly improved, and researching and manufacturing cost of satellite hardware is reduced.

Description

technical field [0001] The invention relates to the field of satellite attitude control, in particular to a method for rapid attitude maneuvering and high-precision and high-stability attitude control of a large-inertia and large-flexibility tilt-flying satellite. Background technique [0002] In order to meet the imaging requirements of high-resolution satellites, it is necessary to realize high-precision and high-stability attitude control of satellites; in order to improve the efficiency of satellite use, it is necessary to realize rapid attitude maneuvers of satellites. Taking the synthetic aperture radar imaging satellite as an example, due to its characteristics of large solar cell array, large antenna and oblique flight of the satellite, the satellite has large inertia, large flexibility, and large gravity gradient interference moment. This has brought great difficulties to the rapid attitude maneuvering and high-precision and high-stability attitude control of the sa...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G1/36G06F19/00G05D1/08
CPCB64G1/24B64G1/244B64G1/361B64G1/245
Inventor 吴敬玉范季夏王文妍王新钟超
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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