CN110963087A - Multi-mode complex-process control method for space station solar wing - Google Patents
Multi-mode complex-process control method for space station solar wing Download PDFInfo
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- CN110963087A CN110963087A CN201911094942.XA CN201911094942A CN110963087A CN 110963087 A CN110963087 A CN 110963087A CN 201911094942 A CN201911094942 A CN 201911094942A CN 110963087 A CN110963087 A CN 110963087A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
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Abstract
The invention discloses a multi-mode complex-flow control method for a space station solar wing, which is used for configuring working modes of the space station solar wing, wherein the working modes comprise five working modes of stopping, starting, tracking, servo and zeroing; and the switching among a plurality of modes of stopping to starting, stopping to servo, stopping to return to zero, starting to servo, starting to return to zero, tracking to servo, tracking to return to zero, servo to return to zero and the like can be realized. The solar wing of the space station experimental cabin can flexibly switch various control modes during the sun capturing, so that the solar wing of the space station can capture solar energy more effectively, and meanwhile, the space station cabin body is not greatly interfered.
Description
Technical Field
The invention relates to the solar wing control technology in the field of space, in particular to a multi-mode complex-process control method for a solar wing of a space station.
Background
The space station is a large-scale space science project, the solar wings of the space station, especially the solar wings of two experimental cabins, the single wing span is about 30m long, and the space station has the characteristics of large size, large inertia, large flexibility and the like, the control of the solar wings of the experimental cabins of the space station is different from the control of the solar wings of the traditional satellites and other spacecrafts, the rotating mode and the control flow are very complex, the solar wings of the experimental cabins rotate around the α direction which takes the cabin body as a central shaft, the real-time sun-oriented capture of sunlight by the solar wings is required to be completed, the control precision and speed requirements are not met during the capture, too large interference cannot be generated on the cabin body of the space station, and the types, the switching mode, the speed, the acceleration control and the like of the working modes during the sun-oriented, are different from the control of the solar wings of the spacecrafts in the space station, therefore, the stable control technology of.
Disclosure of Invention
The invention aims to provide a multi-mode complex-process control method for a space station solar wing, which is used for realizing stable control of the multi-mode complex processes of starting, tracking, servo, zeroing, stopping and the like of the space station solar wing on the day.
In order to achieve the purpose, the invention provides a multi-mode complex-process control method for a space station solar wing, which comprises the following steps:
configuring the working modes of the solar wing of the space station, wherein the working modes comprise five working modes of stopping, starting, tracking, servo and zeroing; in the stalling mode, the solar wing is in an uncontrolled stalling state; in the starting mode, the solar wing is in an acceleration starting process; in the tracking mode, the solar wing is in a tracking state on the sun; in the servo mode, the solar wing reaches any angle position of 0-360 degrees according to the designated angle; in the return-to-zero mode, the solar wing reaches a return-to-zero state of 0 degree or 90 degrees;
when the solar wing is in a stalling mode, the solar wing can receive a starting instruction, a zeroing instruction and a servo instruction and can respectively enter the starting mode, the zeroing mode and the servo mode according to a preset program;
when the solar wing is in a starting mode, a stalling instruction, a tracking instruction, a zeroing instruction and a servo instruction can be received, and the stalling mode, the tracking mode, the zeroing mode and the servo mode can be respectively entered according to a preset program;
when the solar wing is in the tracking mode, the solar wing can receive a stalling instruction, a return-to-zero instruction and a servo instruction, and can respectively enter the stalling mode, the return-to-zero mode and the servo mode according to a preset program;
when the solar wing is in the servo mode, the control system can receive a stalling instruction and a zeroing instruction and can respectively enter the stalling mode and the zeroing mode according to a preset program;
when the sun wing is in the return-to-zero mode, the stall command and the servo command can be received, and the stall mode and the servo mode can be respectively entered according to a preset program.
According to the control method of the solar wing of the multi-mode complex-flow space station, when the solar wing is in the stall mode, the tracking command can be received, the solar wing enters the start mode before the stall mode is switched to the tracking mode, and when the speed of the solar wing is enabled to reach the speed required by the tracking mode through the start mode, the solar wing enters the tracking mode.
Compared with the prior art, the invention has the following beneficial effects:
based on the control method provided by the invention, the solar wing of the experimental cabin of the space station can autonomously complete the functions of sun-to-day trajectory planning, starting, tracking, servo, zeroing, stalling and the like according to the current position, speed and received control instructions, and the switching among various modes is strictly limited. Further, in order to realize stable control of sun orientation, the solar wing of the space station experiment cabin can call different control modes according to instructions at different positions and different speeds, and the solar wing can be switched among multiple modes of stopping to start, stopping to servo, stopping to zero, starting to servo, starting to zero, tracking to servo, tracking to zero, servo to zero and the like. The solar wing of the space station experimental cabin can be flexibly switched among a plurality of control modes when the sun is oriented, so that the solar wing of the space station can capture solar energy more effectively, and meanwhile, the space station cabin body is not greatly interfered.
Drawings
Fig. 1 is a schematic diagram of a control method of a space station solar wing with a multi-mode complex process according to the invention.
Detailed Description
The invention will be further described by the following specific examples in conjunction with the drawings, which are provided for illustration only and are not intended to limit the scope of the invention.
The control method of the solar wing of the multi-mode complex process space station is mainly characterized in that the solar wing is configured with 5 working modes as shown in figure 1, and strict conversion relations exist among the various modes. The solar wing of the space station is provided with five working modes of stopping, starting, tracking, servo and zeroing. Wherein, in the stalling mode, the solar wing is in an uncontrolled stalling state; in the starting mode, the solar wing is in an acceleration starting process and belongs to a capturing stage of the sun; in the tracking mode, the solar wing is in a tracking state on the sun; in the servo mode, the solar wing can reach any angle position of 0-360 degrees according to the designated angle; in the return-to-zero mode, the solar wing can reach a return-to-zero state of 0 degrees or 90 degrees.
When the solar wing is in the stalling mode, the starting command, the zeroing command and the servo command can be received, and the starting mode, the zeroing mode and the servo mode can be respectively entered according to a preset program. Meanwhile, the solar wing can also receive a tracking instruction when in the stall mode, the solar wing needs to enter the start mode before the stall mode is switched to the tracking mode, when the speed of the solar wing reaches the speed required by the tracking mode through the start mode, a stable start mark is received, then the solar wing enters the working process of the tracking mode, and then the solar wing is in the tracking state of the sun.
When the solar wing is in the startup mode, a stall command, a tracking command, a return-to-zero command, and a servo command may be received. After receiving the instruction, the solar wing can respectively enter a stop mode, a tracking mode, a zero-returning mode and a servo mode from a starting mode according to a preset program.
When the sun wing is in the tracking mode, stall commands, return to zero commands, and servo commands may be received. After receiving the instruction, the solar wing can enter a stalling mode, a return-to-zero mode and a servo mode from a tracking mode according to a preset program.
When the sun wing is in the servo mode, a stall command and a return to zero command may be received. After receiving the instruction, the solar wing can respectively enter a stalling mode and a return-to-zero mode from a servo mode according to a preset program.
When the sun wing is in the return-to-zero mode, stall commands and servo commands may be received. After receiving the instruction, the solar wing can respectively enter a stalling mode and a servo mode from a zeroing mode according to a preset program.
In conclusion, the control method provided by the invention can realize flexible switching of a plurality of control modes when the solar wing of the experimental cabin of the space station orients the sun, so that the solar wing of the space station can capture solar energy more effectively, and meanwhile, the space station cabin body is not interfered too much.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.
Claims (2)
1. A control method of a multi-mode space station solar wing with a complex flow is characterized by comprising the following steps:
configuring the working modes of the solar wing of the space station, wherein the working modes comprise five working modes of stopping, starting, tracking, servo and zeroing; in the stalling mode, the solar wing is in an uncontrolled stalling state; in the starting mode, the solar wing is in an acceleration starting process; in the tracking mode, the solar wing is in a tracking state on the sun;
in the servo mode, the solar wing reaches any angle position of 0-360 degrees according to the designated angle; in the return-to-zero mode, the solar wing reaches a return-to-zero state of 0 degree or 90 degrees;
when the solar wing is in a stalling mode, the solar wing can receive a starting instruction, a zeroing instruction and a servo instruction and can respectively enter the starting mode, the zeroing mode and the servo mode according to a preset program;
when the solar wing is in a starting mode, a stalling instruction, a tracking instruction, a zeroing instruction and a servo instruction can be received, and the stalling mode, the tracking mode, the zeroing mode and the servo mode can be respectively entered according to a preset program;
when the solar wing is in the tracking mode, the solar wing can receive a stalling instruction, a return-to-zero instruction and a servo instruction, and can respectively enter the stalling mode, the return-to-zero mode and the servo mode according to a preset program;
when the solar wing is in the servo mode, the control system can receive a stalling instruction and a zeroing instruction and can respectively enter the stalling mode and the zeroing mode according to a preset program;
when the sun wing is in the return-to-zero mode, the stall command and the servo command can be received, and the stall mode and the servo mode can be respectively entered according to a preset program.
2. The method as claimed in claim 1, wherein the sun wing is in a stall mode, and further capable of receiving a tracking command, before the stall mode is switched to the tracking mode, the sun wing is first in a start mode, and when the sun wing is in the start mode, the sun wing reaches a speed required by the tracking mode, the sun wing enters the tracking mode.
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Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0436425A1 (en) * | 1989-12-29 | 1991-07-10 | AEROSPATIALE Société Nationale Industrielle | Attitude control system provided by solar sails for a satellite stabilized around three axes |
| US6021979A (en) * | 1993-07-19 | 2000-02-08 | Hughes Electronics Corporation | Sun-referenced safe-hold control for momentum biased satellites |
| US20080128559A1 (en) * | 2006-12-04 | 2008-06-05 | The Boeing Company | Optimal sun safe attitude for satellite ground tracking |
| CN101332874A (en) * | 2008-08-07 | 2008-12-31 | 航天东方红卫星有限公司 | Autonomous hierarchical process control guiding method for satellite system |
| CN101435704A (en) * | 2008-12-04 | 2009-05-20 | 哈尔滨工业大学 | Star tracking method of star sensor under high dynamic state |
| CN201698025U (en) * | 2010-07-02 | 2011-01-05 | 成都捷康特科技有限公司 | GPS antitheft tracking system for solar panel |
| CN102004492A (en) * | 2010-10-11 | 2011-04-06 | 北京控制工程研究所 | Non-sun-synchronous orbit satellite double-shaft sailboard control method |
| US7925426B2 (en) * | 2005-11-17 | 2011-04-12 | Motility Systems | Power management systems and devices |
| CN103135572A (en) * | 2011-11-30 | 2013-06-05 | 西安博昱新能源有限公司 | Sun tracking and control system |
| CN104181941A (en) * | 2014-09-02 | 2014-12-03 | 上海新跃仪表厂 | Double-direction solar panel control method applicable to inclined orbit satellite |
| CN105620794A (en) * | 2016-02-05 | 2016-06-01 | 上海微小卫星工程中心 | Reliable method for controlling solar panel to autonomously track sun |
| CN105819004A (en) * | 2016-04-21 | 2016-08-03 | 上海微小卫星工程中心 | Solar array control method and system of satellite and satellite |
| CN105899430A (en) * | 2013-11-25 | 2016-08-24 | 空中客车防务和空间公司 | Method and device for control of a sunlight acquisition phase of a spacecraft |
| CN106697334A (en) * | 2016-11-29 | 2017-05-24 | 上海卫星工程研究所 | Driving control method for satellite solar wing sailboard |
| CN106970573A (en) * | 2017-05-22 | 2017-07-21 | 上海航天控制技术研究所 | A kind of spacecraft solar wing drive control system of permanent magnet synchronous motor |
| EP3406532A1 (en) * | 2017-05-23 | 2018-11-28 | Space Systems/Loral, LLC | A method for orienting an earth-orbiting spacecraft |
-
2019
- 2019-11-11 CN CN201911094942.XA patent/CN110963087B/en active Active
Patent Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0436425A1 (en) * | 1989-12-29 | 1991-07-10 | AEROSPATIALE Société Nationale Industrielle | Attitude control system provided by solar sails for a satellite stabilized around three axes |
| US6021979A (en) * | 1993-07-19 | 2000-02-08 | Hughes Electronics Corporation | Sun-referenced safe-hold control for momentum biased satellites |
| US7925426B2 (en) * | 2005-11-17 | 2011-04-12 | Motility Systems | Power management systems and devices |
| US20080128559A1 (en) * | 2006-12-04 | 2008-06-05 | The Boeing Company | Optimal sun safe attitude for satellite ground tracking |
| CN101332874A (en) * | 2008-08-07 | 2008-12-31 | 航天东方红卫星有限公司 | Autonomous hierarchical process control guiding method for satellite system |
| CN101435704A (en) * | 2008-12-04 | 2009-05-20 | 哈尔滨工业大学 | Star tracking method of star sensor under high dynamic state |
| CN201698025U (en) * | 2010-07-02 | 2011-01-05 | 成都捷康特科技有限公司 | GPS antitheft tracking system for solar panel |
| CN102004492A (en) * | 2010-10-11 | 2011-04-06 | 北京控制工程研究所 | Non-sun-synchronous orbit satellite double-shaft sailboard control method |
| CN103135572A (en) * | 2011-11-30 | 2013-06-05 | 西安博昱新能源有限公司 | Sun tracking and control system |
| CN105899430A (en) * | 2013-11-25 | 2016-08-24 | 空中客车防务和空间公司 | Method and device for control of a sunlight acquisition phase of a spacecraft |
| CN104181941A (en) * | 2014-09-02 | 2014-12-03 | 上海新跃仪表厂 | Double-direction solar panel control method applicable to inclined orbit satellite |
| CN105620794A (en) * | 2016-02-05 | 2016-06-01 | 上海微小卫星工程中心 | Reliable method for controlling solar panel to autonomously track sun |
| CN105819004A (en) * | 2016-04-21 | 2016-08-03 | 上海微小卫星工程中心 | Solar array control method and system of satellite and satellite |
| CN106697334A (en) * | 2016-11-29 | 2017-05-24 | 上海卫星工程研究所 | Driving control method for satellite solar wing sailboard |
| CN106970573A (en) * | 2017-05-22 | 2017-07-21 | 上海航天控制技术研究所 | A kind of spacecraft solar wing drive control system of permanent magnet synchronous motor |
| EP3406532A1 (en) * | 2017-05-23 | 2018-11-28 | Space Systems/Loral, LLC | A method for orienting an earth-orbiting spacecraft |
Non-Patent Citations (3)
| Title |
|---|
| 孙丹峰; 申友涛，邵若薇，刘忠国，付培华: "基于FPGA的永磁同步电机控制系统设计与实现", 《国外电子测量技术》 * |
| 王颖，顾荃莹: "倾斜轨道航天器太阳翼对日跟踪方法探究", 《航天器工程》 * |
| 龚浙安: "卫星太阳翼驱动机构可靠性建模与分析", 《中国优秀硕士学位论文全文数据库工程科技II辑》 * |
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