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Three axis directional controlling method for stabilizing posture in deep space based on behavior mode

A three-axis stable and directional control technology, applied in the direction of aerospace vehicle guidance devices, etc., can solve the problems of not introducing the general calculation method of attitude motion parameters, and not disclosing the top-level command algorithm and structure of three-axis attitude control, so as to reduce the amount of calculation , clear logical effect

Inactive Publication Date: 2007-11-28
HARBIN INST OF TECH
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AI Technical Summary

Problems solved by technology

However, the public literature only mentions the special calculation steps in the simplest case, and does not introduce the general calculation method of the attitude motion parameters, so there is no public three-axis attitude control top-level command algorithm and architecture with complete practical significance

Method used

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  • Three axis directional controlling method for stabilizing posture in deep space based on behavior mode
  • Three axis directional controlling method for stabilizing posture in deep space based on behavior mode
  • Three axis directional controlling method for stabilizing posture in deep space based on behavior mode

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specific Embodiment approach 1

[0022] Specific embodiment 1: This embodiment requires the support of the on-board navigation system and the solar system ephemeris. The orbital motion of the target celestial body obtained by interpolation of the aircraft orbit provided by the navigation system and the ephemeris file includes the position of the aircraft and the celestial body at the same time. , velocity vector. According to the master and slave body orientation axes and the corresponding target vector of the reference coordinate system, the coordinate transformation matrix from the reference coordinate system to the body coordinate system is calculated, that is, the attitude matrix of the star. Considering the aberration caused by relative motion, the light speed correction is made to the orientation vector. The whole process is shown in Figure 1.

[0023]The block diagram of the attitude control system of the deep space probe is shown in Figure 2. The core of the system is two sets of computers: the fligh...

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Abstract

The invention discloses a deep-space three-axle stable attitude directional control method, based on operation mode, belonging to an attitude control method of space aircraft, wherein said method comprises: the space aircraft with automatic navigation function, via flying computer, receives the reference directional mission and auxiliary directional mission; the flying computer, according to the aircraft track supported by navigation system and the track of target heavenly body obtained by astronomical ephemeris interpolation, finds the attitude operation process meet the demand of said mission, as the reference attitude track; and uses attitude track control rule, via the attitude interface unit, to drive the attitude executer of aircraft, to realize needed attitude. The invention can improve the automatic degree.

Description

technical field [0001] The invention relates to an attitude control method of a space vehicle, in particular to a three-axis attitude orientation method of artificial satellites and interstellar spacecraft. Background technique [0002] Modern deep space probes generally adopt a long-term three-axis stable attitude control scheme. During scientific exploration, three-axis stabilization can achieve high orientation accuracy; in addition, most tasks require the orientation of more than two vectors, and three-axis stable orientation is an inevitable solution. [0003] Different from earth-oriented earth satellites, a single reference coordinate system such as the local orbital coordinate system cannot adapt to the attitude control of various three-axis orientation modes in deep space missions; Unknown and complex, the selection of attitude sensitive components and actuators is less than that of earth satellites. Currently, it mainly relies on inertial sensors such as star sens...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
Inventor 崔平远崔祜涛张泽旭徐敏强仲维国史雪岩
Owner HARBIN INST OF TECH
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