CN104071355B - A kind of satellite attitude stabilization control method and device - Google Patents
A kind of satellite attitude stabilization control method and device Download PDFInfo
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Abstract
A kind of satellite attitude stabilization control method and device, method comprises: 1) obtain satellite attitude current steady pattern, and wherein, described current steady pattern is one of them of zero momentum stable mode or bias momentum stable mode; 2) receive the switching command that sends according to mission requirements of ground, described switching command comprises the handover information of the stable mode that need perform, and the described stable mode that need perform is one of them of zero momentum stable mode or bias momentum stable mode; 3) judge that whether the described stable mode that need perform is identical with described current steady pattern, if difference, performs step 4); 4) described current steady pattern is switched to the described stable mode that need perform, carry out satellite attitude stabilization control.The present invention, by introducing ground intervening surface, sends instruction according to ground, realizes bias momentum and stablizes and freely switch between zero momentum stable mode, improve control system alerting ability.
Description
Technical field
The present invention relates to aerospace measurement and control technology field, specifically, is a kind of satellite attitude stabilization control method having bias momentum and zero momentum stable mode concurrently and device of being applicable to microsatellite.
Background technology
At present, satellite attitude stabilization mode mainly contains the stable and zero momentum of bias momentum and stablizes two kinds of ripe modes.Bias momentum stable mode has orientation stability in one direction, thus possesses stronger interference rejection capability, and meanwhile, bias momentum stable mode has the advantages that configuration is simple, reliability is high; Zero momentum stable mode does not have gyroscopic intertia, is generally used for three axis stabilization and controls the stage, have the advantages that control accuracy is high.
The existing satellite attitude stabilization mode of flying in-orbit is single stable mode, or be bias momentum stable mode or be zero momentum stable mode, does not have the function of switching mutually between different stable mode.If only use bias momentum stable mode, large angle maneuver and high precision control overflow during cannot task observation being realized; If only use zero momentum stable mode, not there is antijamming capability, under the large disturbed condition of burst, easily lose attitude reference.Therefore, prior art does not have stationary mode flexibly, is no longer applicable to the mission requirements of nowadays satellite complexity.
Summary of the invention
The object of the invention is to, provide a kind of satellite attitude stabilization control method and device, it can have bias stabilization ability and zero momentum stabilizing power concurrently, and freely can switch between bias stabilization and zero momentum are stablized.
For achieving the above object, the invention provides satellite attitude stabilization control method, comprise the following steps: (1) obtains satellite attitude current steady pattern, wherein, described current steady pattern is one of them of zero momentum stable mode or bias momentum stable mode; (2) receive the switching command that sends according to mission requirements of ground, described switching command comprises the handover information of the stable mode that need perform, and the described stable mode that need perform is one of them of zero momentum stable mode or bias momentum stable mode; (3) judge that whether the described stable mode that need perform is identical with described current steady pattern, if difference, perform step (4); (4) described current steady pattern is switched to the described stable mode that need perform, carry out satellite attitude stabilization control.
Step (2) comprises further: (21) are analyzed current task demand and generated the switching command comprising the handover information of the stable mode that need perform; (22) send switching command, wherein, if desired the convergence of wide-angle attitude is carried out to satellite and control, then send the switching command switching to bias momentum stable mode; If desired carry out control accuracy to satellite and point to degree of stability controlling, then send the switching command switching to zero momentum stable mode.
Further, described bias momentum stable mode comprises: make satellite obtain the gyroscopic intertia of pitch orientation, possess interference rejection capability simultaneously at rolling jaw channel, controls to carry out the convergence of wide-angle attitude to satellite.
Further, described zero momentum stable mode comprises: introduce star sensor, fiber optic gyro as attitude sensor, introduces counteraction flyback as execution unit, to control satellite precision and to point to degree of stability.
To achieve these goals, present invention also offers a kind of satellite attitude stabilization control setup, comprising: an acquisition module, for obtaining satellite attitude current steady pattern, wherein, described current steady pattern is one of them of zero momentum stable mode or bias momentum stable mode; One receiver module, for receiving the switching command that ground sends according to mission requirements, described switching command comprises the handover information of the stable mode that need perform, and the described stable mode that need perform is one of them of zero momentum stable mode or bias momentum stable mode; One judge module is connected with described acquisition module, receiver module and a handover module respectively, whether identical with the current steady pattern that described acquisition module obtains for judging the stable mode that the need that described receiver module receives perform, if difference, call described handover module; Described handover module, for described current steady pattern is switched to the described stable mode that need perform, carries out satellite attitude stabilization control.
Described device comprises further: an analysis module, for analyzing current task demand and generating the switching command comprising the handover information of the stable mode that need perform; One sending module is connected with described analysis module and described receiver module, for sending switching command, wherein, if desired carrying out the convergence of wide-angle attitude to satellite and controlling, then sending the switching command switching to bias momentum stable mode; If desired carry out control accuracy to satellite and point to degree of stability controlling, then send the switching command switching to zero momentum stable mode.
Further, described bias momentum stable mode comprises: make satellite obtain the gyroscopic intertia of pitch orientation, possess interference rejection capability simultaneously at rolling jaw channel, controls to carry out the convergence of wide-angle attitude to satellite.
Further, described zero momentum stable mode comprises: introduce star sensor, fiber optic gyro as attitude sensor, introduces counteraction flyback as execution unit, to control satellite precision and to point to degree of stability.
The invention has the advantages that: send instruction according to ground, realize bias momentum to stablize and freely switch between zero momentum stable mode, by introducing ground intervening surface, use different stable modes in different situations, improve control system alerting ability, save whole star resource, give full play to the advantage of different stationary mode, make posture control system be more applicable for nowadays complicated control task requirement, therefore, have good future in engineering applications and promotional value.
Accompanying drawing explanation
Fig. 1, the diagram of circuit of a kind of satellite attitude stabilization control method of the present invention;
Fig. 2, the Organization Chart of a kind of satellite attitude stabilization control setup of the present invention.
Detailed description of the invention
Elaborate below in conjunction with the detailed description of the invention of accompanying drawing to a kind of satellite attitude stabilization control method provided by the invention and device.
Shown in Figure 1, a kind of satellite attitude stabilization control method, comprises the following steps: S10: obtain satellite attitude current steady pattern; S12: receive the switching command that ground sends according to mission requirements, described switching command comprises the handover information of the stable mode that need perform; S14: judge that whether the described stable mode that need perform is identical with described current steady pattern, if difference, performs step S16; S16: described current steady pattern is switched to the described stable mode that need perform, carries out satellite attitude stabilization control.
Step S10: obtain satellite attitude current steady pattern.
Described current steady pattern is one of them of zero momentum stable mode or bias momentum stable mode.If entering the orbit under initial stage and safety mode, then current steady pattern is being bias momentum stable mode, and Guarantee control system has higher antijamming capability; If in observation stage and large angle maneuver segmental arc, then current steady pattern is for use zero momentum stable mode, and Guarantee control system has higher control accuracy and degree of stability.
S12: receive the switching command that ground sends according to mission requirements, described switching command comprises the handover information of the stable mode that need perform.
The satellite of existing single stable mode is no longer applicable to nowadays complicated satellite platform appearance control task, needs to realize freely switching between zero momentum is stablized and bias momentum is stable according to different mission requirements, thus reaches control system alerting ability.Be specially: 1) analyze current task demand and generate the switching command comprising the handover information of the stable mode that need perform; 2) switching command is sent.Wherein, if desired the convergence of wide-angle attitude is carried out to satellite and control, then send the switching command switching to bias momentum stable mode; If desired carry out control accuracy to satellite and point to degree of stability controlling, then send the switching command switching to zero momentum stable mode.By surface instruction, freely switching can realizing from a kind of stationary mode to another stationary mode, thus reach control system alerting ability.
Described bias momentum stable mode comprises: make satellite obtain the gyroscopic intertia of pitch orientation, possess interference rejection capability simultaneously at rolling jaw channel, controls to carry out the convergence of wide-angle attitude to satellite.Enter the orbit the stages such as initial stage, rate damping, safety mode, need to carry out the convergence of wide-angle attitude to satellite to control, adopt bias momentum stable mode, make satellite obtain the gyroscopic intertia of pitch orientation, possess certain interference rejection capability at rolling jaw channel simultaneously.This pattern stand-alone configuration is simple, to attitude sensor and counteraction flyback less demanding, reliability is high.
Described zero momentum stable mode comprises: introduce star sensor, fiber optic gyro as attitude sensor, introduces counteraction flyback as execution unit, to control satellite precision and to point to degree of stability.Three axis stabilization controls, observe stage and large angle maneuver segmental arc, needs to carry out high precision to satellite and points to control, adopt zero momentum stable mode.This pattern introduces star sensor, fiber optic gyro as attitude sensor (controlling attitude angle, cireular frequency), introduces counteraction flyback as execution unit, can reach very high control accuracy and point to degree of stability, being applicable to the task observation stage.
S14: judge that whether the described stable mode that need perform is identical with described current steady pattern, if difference, performs step S16, do not perform switching, and return step S10 if identical.
If according to mission requirements, the described stable mode that need perform is zero momentum stable mode, and the current steady pattern obtained is bias momentum stable mode, and namely the described stable mode that need perform is not identical with described current steady pattern yet, then perform switching, vice versa.If according to mission requirements, the described stable mode that need perform is zero momentum stable mode, and the current steady pattern obtained is zero momentum stable mode, and also namely the described stable mode that need perform is identical with described current steady pattern, then do not perform switching.
S16: described current steady pattern is switched to the described stable mode that need perform, carries out satellite attitude stabilization control.
Such as, according to mission requirements, the described stable mode that need perform is zero momentum stable mode, and the current steady pattern obtained is bias momentum stable mode, then perform switching, described current steady pattern (i.e. bias momentum stable mode) is switched to the described stable mode (i.e. zero momentum stable mode) that need perform, carry out satellite attitude stabilization control by zero momentum stable mode.Vice versa.
Also be, instruction is sent according to ground, realizing bias momentum to stablize and freely switch between zero momentum stable mode, by introducing ground intervening surface, using different stable modes in different situations, improve control system alerting ability, save whole star resource, give full play to the advantage of different stationary mode, make posture control system be more applicable for nowadays complicated control task requirement, therefore, good future in engineering applications and promotional value is had.
See Fig. 2, satellite attitude stabilization control setup Organization Chart of the present invention.Described device comprises: acquisition module 20, receiver module 22, judge module 24 and a handover module 26.
Described acquisition module 20, for obtaining satellite attitude current steady pattern, wherein, described current steady pattern is one of them of zero momentum stable mode or bias momentum stable mode.
Described receiver module 22, for receiving the switching command that ground sends according to mission requirements, described switching command comprises the handover information of the stable mode that need perform, and the described stable mode that need perform is one of them of zero momentum stable mode or bias momentum stable mode.
The satellite of existing single stable mode is no longer applicable to nowadays complicated satellite platform appearance control task, needs to realize freely switching between zero momentum is stablized and bias momentum is stable according to different mission requirements, thus reaches control system alerting ability.
As preferred embodiment, described device comprises further: analysis module 27 and a sending module 29.Described analysis module 27, for analyzing current task demand and generating the switching command comprising the handover information of the stable mode that need perform.Described sending module 27 is connected with described analysis module 29 and described receiver module 22, for sending switching command, wherein, if desired carrying out the convergence of wide-angle attitude to satellite and controlling, then sending the switching command switching to bias momentum stable mode; If desired carry out control accuracy to satellite and point to degree of stability controlling, then send the switching command switching to zero momentum stable mode.
Described judge module 24 is connected with described acquisition module 20, receiver module 22 and handover module 26 respectively, whether identical for judging the current steady pattern that the stable mode of the need execution that described receiver module 22 receives and described acquisition module 20 obtain, if difference, call described handover module 26.
Described handover module 26, for described current steady pattern is switched to the described stable mode that need perform, carries out satellite attitude stabilization control.
Described bias momentum stable mode comprises: make satellite obtain the gyroscopic intertia of pitch orientation, possess interference rejection capability simultaneously at rolling jaw channel, controls to carry out the convergence of wide-angle attitude to satellite.
Described zero momentum stable mode comprises: introduce star sensor, fiber optic gyro as attitude sensor, introduces counteraction flyback as execution unit, to control satellite precision and to point to degree of stability.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (7)
1. a satellite attitude stabilization control method, is characterized in that, comprises the following steps:
(1) obtain satellite attitude current steady pattern, wherein, described current steady pattern is one of them of zero momentum stable mode or bias momentum stable mode;
(2) receive the switching command that sends according to mission requirements of ground, described switching command comprises the handover information of the stable mode that need perform, and the described stable mode that need perform is one of them of zero momentum stable mode or bias momentum stable mode;
(3) judge that whether the described stable mode that need perform is identical with described current steady pattern, if difference, perform step (4);
(4) described current steady pattern is switched to the described stable mode that need perform, carry out satellite attitude stabilization control;
Wherein, step (2) comprises further: (21) are analyzed current task demand and generated the switching command comprising the handover information of the stable mode that need perform; (22) send switching command, wherein, if desired the convergence of wide-angle attitude is carried out to satellite and control, then send the switching command switching to bias momentum stable mode; If desired carry out precision to satellite and point to degree of stability controlling, then send the switching command switching to zero momentum stable mode.
2. satellite attitude stabilization control method according to claim 1, it is characterized in that, described bias momentum stable mode comprises: make satellite obtain the gyroscopic intertia of pitch orientation, possess interference rejection capability simultaneously at rolling jaw channel, controls to carry out the convergence of wide-angle attitude to satellite.
3. satellite attitude stabilization control method according to claim 1, it is characterized in that, described zero momentum stable mode comprises: introduce star sensor, fiber optic gyro as attitude sensor, introduces counteraction flyback as execution unit, to control satellite precision and to point to degree of stability.
4. a satellite attitude stabilization control setup, is characterized in that, comprising:
One acquisition module, for obtaining satellite attitude current steady pattern, wherein, described current steady pattern is one of them of zero momentum stable mode or bias momentum stable mode;
One receiver module, for receiving the switching command that ground sends according to mission requirements, described switching command comprises the handover information of the stable mode that need perform, and the described stable mode that need perform is one of them of zero momentum stable mode or bias momentum stable mode;
One judge module is connected with described acquisition module, receiver module and a handover module respectively, whether identical with the current steady pattern that described acquisition module obtains for judging the stable mode that the need that described receiver module receives perform, if difference, call described handover module;
Described handover module, for described current steady pattern is switched to the described stable mode that need perform, carries out satellite attitude stabilization control.
5. satellite attitude stabilization control setup according to claim 4, it is characterized in that, described device comprises further: an analysis module, for analyzing current task demand and generating the switching command comprising the handover information of the stable mode that need perform; One sending module is connected with described analysis module and described receiver module, for sending switching command, wherein, if desired carrying out the convergence of wide-angle attitude to satellite and controlling, then sending the switching command switching to bias momentum stable mode; If desired carry out control accuracy to satellite and point to degree of stability controlling, then send the switching command switching to zero momentum stable mode.
6. satellite attitude stabilization control setup according to claim 4 or 5, it is characterized in that, described bias momentum stable mode comprises: make satellite obtain the gyroscopic intertia of pitch orientation, possess interference rejection capability simultaneously at rolling jaw channel, controls to carry out the convergence of wide-angle attitude to satellite.
7. satellite attitude stabilization control setup according to claim 4 or 5, it is characterized in that, described zero momentum stable mode comprises: introduce star sensor, fiber optic gyro as attitude sensor, introduces counteraction flyback as execution unit, to control satellite precision and to point to degree of stability.
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| CN104290925B (en) * | 2014-09-29 | 2016-06-29 | 北京控制工程研究所 | A kind of spacecraft angular momentum control method in inertial system |
| CN105180926B (en) * | 2015-09-21 | 2018-01-12 | 中国科学院国家天文台 | The decision method of geo-stationary orbit space object status stationary mode |
| CN105259905A (en) * | 2015-10-20 | 2016-01-20 | 中国人民解放军国防科学技术大学 | Networked man-in-the-loop satellite control system and control method thereof |
| CN107089348B (en) * | 2017-04-01 | 2019-04-30 | 中国空间技术研究院 | On-orbit fault game method based on more flexible accessory satellite dynamics optimized Control Modes |
| CN110712767B (en) * | 2019-10-29 | 2021-07-30 | 上海航天控制技术研究所 | Method for automatically reconstructing control moment gyro group in pentagonal pyramid configuration |
| CN111806727B (en) * | 2020-06-01 | 2022-01-04 | 上海航天控制技术研究所 | Operating system-based satellite attitude and orbit control application software architecture design method |
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