CN111099041B - Space station multi-cabin solar wing autonomous identification control system and control method thereof - Google Patents
Space station multi-cabin solar wing autonomous identification control system and control method thereof Download PDFInfo
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- CN111099041B CN111099041B CN201911251057.8A CN201911251057A CN111099041B CN 111099041 B CN111099041 B CN 111099041B CN 201911251057 A CN201911251057 A CN 201911251057A CN 111099041 B CN111099041 B CN 111099041B
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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
- B64G1/443—Photovoltaic cell arrays
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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
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
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Abstract
The invention provides a space station multi-cabin solar wing autonomous identification control system and a control method thereof, wherein the system comprises: the first solar wing, the second solar wing, the first driving controller and the second driving controller are connected with the solar wings sequentially through the motor bodies and the output shafts of the motors; a bus command system issuing a motion command to the first drive controller and the second drive controller; the first driving controller and the second driving controller receive the motion command of the bus command system and respectively control the motion of the first solar wing and the second solar wing. The advantages are that: the system adopts the first drive controller and the second drive controller as the core of automatic identification and control, automatically identifies the solar wings of different cabins by collecting the first solar wing hard line identification signal and the second solar wing hard line identification signal, and automatically determines to adopt different solar wing rotation control strategies, thereby realizing the control of the sun-facing directional and equidirectional motion of the solar wings.
Description
Technical Field
The invention relates to the field of autonomous identification control of multiple solar wings of a space system, in particular to an autonomous identification control system of a space station multiple-cabin solar wing and a control method thereof.
Background
In the current aerospace system, no matter airship or satellite, the main power for maintaining the normal operation of the aerospace system in orbit is electric energy, and the solar wing is an important energy source for converting solar energy into electric energy. The solar wings are usually distributed on the satellite or the flying boat in a bilateral symmetry mode, the solar wings are of single-degree-of-freedom structures and rotate around the axis perpendicular to the cabin body respectively, and the two solar wings do not need to move in the same direction in a sun-oriented mode, so that different solar wings do not need to be identified for control.
However, in some working environments, for example, when the demand of the space station for electric energy is huge, a large solar wing (with a span of about 30 meters) is generally adopted to collect solar energy, and a two-degree-of-freedom large solar wing (with a span of about 30 meters) is adopted to realize the sun-oriented control of two-cabin solar wings (namely, a two-degree-of-freedom solar wing is respectively installed in the experimental cabin I and the experimental cabin II), but at present, no more complete system and method are available to solve the problem of autonomous identification control faced by the space station multi-cabin solar wing.
Disclosure of Invention
The invention aims to provide a space station multi-cabin solar wing automatic identification control system and a control method thereof.
In order to achieve the purpose, the invention is realized by the following technical scheme:
a space station multi-cabin solar wing autonomous identification control system comprises:
the first solar wing and the second solar wing are symmetrically distributed outside the space station cabin;
the first driving controller is connected with the first solar wing sequentially through a motor body and an output shaft of the first motor;
the second driving controller is connected with the second solar wing sequentially through the motor body and the output shaft of the second motor;
a bus command system that issues a motion command to the first drive controller and the second drive controller;
the first driving controller and the second driving controller automatically acquire a first solar wing hard wire identification signal and a second solar wing hard wire identification signal and automatically identify solar wings of different cabin sections, so that rotation control strategies of the first solar wing and the second solar wing are determined; the first driving controller and the second driving controller receive the motion command of the bus command system and respectively control the motion of the first solar wing and the second solar wing.
Preferably, a control method using the space station multi-cabin solar wing autonomous identification control system comprises the following steps:
s1, after the first drive controller and the second drive controller are powered on, the first drive controller and the second drive controller automatically acquire a first solar wing hard line identification signal and a second solar wing hard line identification signal and automatically identify solar wings of different cabin sections, so that rotation control strategies of the first solar wing and the second solar wing are determined;
and S2, after receiving the same motion command issued by the bus command system, the first drive controller and the second drive controller autonomously execute respective rotation control strategies to realize the sun-facing directional and same-direction motion of the first solar wing and the second solar wing.
Preferably, the first solar wing hard wire identification signal and the second solar wing hard wire identification signal are high-level electric signals or low-level electric signals.
Preferably, when the first solar wing hard line identification signal or the second solar wing hard line identification signal is a high-level electrical signal, the first drive controller or the second drive controller controls the first solar wing or the second solar wing to rotate according to a first rotation control strategy.
Preferably, the first rotation control strategy is:
when the motion command is a forward rotation command, the first sun wing or the second sun wing rotates anticlockwise around the output shaft of the first motor or the output shaft of the second motor;
when the motion command is a reverse rotation command, the first sun wing or the second sun wing rotates clockwise around the output shaft of the first motor or the output shaft of the second motor.
Preferably, when the first solar wing hard line identification signal or the second solar wing hard line identification signal is a low-level electrical signal, the first drive controller or the second drive controller controls the first solar wing or the second solar wing to rotate according to a second rotation control strategy.
Preferably, the second rotation control strategy is:
when the motion command is a forward rotation command, the first sun wing or the second sun wing rotates clockwise around the output shaft of the first motor or the output shaft of the second motor;
when the motion command is a reverse rotation command, the first sun wing or the second sun wing rotates counterclockwise around the output shaft of the first motor or the output shaft of the second motor.
Compared with the prior art, the invention has the following advantages:
according to the space station multi-cabin solar wing automatic identification control system, the first drive controller and the second drive controller are used as the cores of automatic identification and control, different cabin solar wings (the first solar wing or the second solar wing) are automatically identified by collecting the first solar wing hard line identification signal and the second solar wing hard line identification signal, different solar wing rotation control strategies are automatically determined to be adopted, and the automatic identification control function of the multi-cabin solar wings and the control of sun-facing directional and same-directional movement of the multi-cabin solar wings can be realized.
Drawings
Fig. 1 is a schematic diagram of an autonomous identification control system for a space station multi-cabin solar wing.
Detailed Description
The present invention will now be further described by way of the following detailed description of a preferred embodiment thereof, taken in conjunction with the accompanying drawings.
As shown in fig. 1, the present invention is an autonomous identification control system for a space station multi-bay solar wing, the system includes: the solar control system comprises a first cabin solar wing 1, a second cabin solar wing 2, a first cabin driving controller 3, a second cabin driving controller 4 and a bus instruction system 5. The cabin I driving controller 3 and the cabin II driving controller 4 have the same functions.
The solar wing 1 of the cabin I and the solar wing 2 of the cabin II are symmetrically distributed outside the space station cabin; the cabin I driving controller 3 is connected with the cabin I solar wing 1 sequentially through a motor body and an output shaft of a cabin I motor 6; the cabin II driving controller 4 is connected with the cabin II solar wing 2 through a motor body and an output shaft of a cabin II motor 7; the bus instruction system 5 issues motion instructions (the solar wings and the driving motors of the two cabins are symmetrically distributed with the vertical line of the axes of the two cabins) to the cabin I driving controller 3 and the cabin II driving controller 4.
The cabin I driving controller 3 and the cabin II driving controller 4 automatically acquire a cabin I solar wing hard line identification signal and a cabin II solar wing hard line identification signal and automatically identify solar wings of different cabin sections, so that rotation control strategies of a cabin I solar wing 1 and a cabin II solar wing 2 are determined; the cabin I driving controller 3 and the cabin II driving controller 4 receive the motion instruction of the bus instruction system 5 and respectively control the motion of the cabin I solar wing 1 and the cabin II solar wing 2.
The cabin I solar wing hard wire identification signal and the cabin II solar wing hard wire identification signal are high-level electric signals or low-level electric signals, are basis for judging different solar wings, and are fixed high-level signals or low-level signals after being electrified.
In addition, the invention also discloses a control method adopting the space station multi-cabin solar wing autonomous identification control system, which comprises the following steps:
and S1, after the cabin I drive controller 3 and the cabin II drive controller 4 are powered on, the cabin I drive controller 3 and the cabin II drive controller 4 automatically acquire cabin I solar wing hard line identification signals and cabin II solar wing hard line identification signals (the signals are generated by a superior hard line instruction system), and automatically identify different cabin sections of solar wings (cabin I solar wing 1 or cabin II solar wing 2), so that the rotation control strategies of the cabin I solar wing 1 and the cabin II solar wing 2 are determined.
And S2, after receiving the same motion command issued by the bus command system 5, the cabin I drive controller 3 and the cabin II drive controller 4 autonomously execute respective rotation control strategies to realize the sun-facing directional homodromous of the cabin I solar wing 1 and the cabin II solar wing 2.
When I cabin I sun wing hard wire identification signal or II cabin sun wing hard wire identification signal are the high level signal of electricity, I cabin drive controller 3 is with first rotation control strategy control I cabin sun wing 1 rotates, or II cabin drive controller 4 is with first rotation control strategy control II cabin sun wing 2 rotates.
The first rotation control strategy is: when the motion command is a forward rotation command, the first cabin solar wing 1 rotates anticlockwise around the output shaft of the first cabin motor 6 (when viewed from the output shaft of the first cabin motor 7 to the motor body), and the second cabin solar wing 2 rotates anticlockwise around the output shaft of the second cabin motor 7 (when viewed from the output shaft of the second cabin motor 7 to the motor body).
When the motion instruction is a reverse rotation instruction, the first solar wing 1 of the cabin rotates clockwise around the output shaft of the first motor 6 of the cabin (seen from the output shaft of the first motor 7 of the cabin to the motor body), and the second solar wing 2 of the cabin rotates clockwise around the output shaft of the second motor 7 of the cabin (seen from the output shaft of the second motor 7 of the cabin to the motor body).
In addition, when the hard line identification signal of the first solar wing of the cabin or the hard line identification signal of the second solar wing of the cabin is a low-level electric signal, the first driving controller 3 of the cabin controls the first solar wing 1 to rotate by a second rotation control strategy, or the second driving controller 4 of the cabin controls the second solar wing 2 to rotate by the second rotation control strategy.
The second rotation control strategy is: when the motion command is a forward rotation command, the first cabin solar wing 1 rotates clockwise around the output shaft of the first cabin motor 6 (when viewed from the output shaft of the first cabin motor 7 to the motor body), and the second cabin solar wing 2 rotates clockwise around the output shaft of the second cabin motor 7 (when viewed from the output shaft of the second cabin motor 7 to the motor body);
when the motion instruction is a reverse rotation instruction, the first cabin solar wing 1 rotates anticlockwise around the output shaft of the first cabin motor 6 (when viewed from the output shaft of the first cabin motor 7 to the motor body), and the second cabin solar wing 2 rotates anticlockwise around the output shaft of the second cabin motor 7 (when viewed from the output shaft of the second cabin motor 7 to the motor body).
In summary, the invention provides an autonomous identification control system and a control method for a space station multi-cabin solar wing, the system adopts a first drive controller and a second drive controller as cores of autonomous identification and control, different cabin solar wings (a first solar wing or a second solar wing) are autonomously identified by collecting a first solar wing hard line identification signal and a second solar wing hard line identification signal, and the sun-facing directional and equidirectional motion control of the first solar wing and the second solar wing can be realized by autonomously determining to adopt different solar wing rotation control strategies.
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 (7)
1. A space station multi-cabin solar wing autonomous identification control system is characterized by comprising:
the first solar wing and the second solar wing are symmetrically distributed outside the space station cabin;
the first driving controller is connected with the first solar wing sequentially through a motor body and an output shaft of the first motor;
the second driving controller is connected with the second solar wing sequentially through the motor body and the output shaft of the second motor;
a bus command system that issues a motion command to the first drive controller and the second drive controller;
the first driving controller and the second driving controller automatically acquire a first solar wing hard wire identification signal and a second solar wing hard wire identification signal and automatically identify solar wings of different cabin sections, so that rotation control strategies of the first solar wing and the second solar wing are determined; the first driving controller and the second driving controller receive the motion command of the bus command system, autonomously execute respective rotation control strategies, and respectively control the motion of the first solar wing and the second solar wing.
2. A control method using the space station multi-cabin solar wing autonomous identification control system according to claim 1, characterized in that the method comprises:
s1, after the first drive controller and the second drive controller are powered on, the first drive controller and the second drive controller automatically acquire a first solar wing hard line identification signal and a second solar wing hard line identification signal and automatically identify solar wings of different cabin sections, so that rotation control strategies of the first solar wing and the second solar wing are determined;
and S2, after receiving the same motion command issued by the bus command system, the first drive controller and the second drive controller autonomously execute respective rotation control strategies to realize the sun-facing directional and same-direction motion of the first solar wing and the second solar wing.
3. The control method according to claim 2,
the first solar wing hard wire identification signal and the second solar wing hard wire identification signal are high-level electric signals or low-level electric signals.
4. The control method according to claim 3,
when the first solar wing hard wire identification signal or the second solar wing hard wire identification signal is a high-level electric signal, the first drive controller or the second drive controller controls the first solar wing or the second solar wing to rotate by a first rotation control strategy.
5. The control method of claim 4, wherein the first rotation control strategy is:
when the motion command is a forward rotation command, the first sun wing or the second sun wing rotates anticlockwise around the output shaft of the first motor or the output shaft of the second motor;
when the motion command is a reverse rotation command, the first sun wing or the second sun wing rotates clockwise around the output shaft of the first motor or the output shaft of the second motor.
6. The control method according to claim 3,
when the first solar wing hard wire identification signal or the second solar wing hard wire identification signal is a low-level electric signal, the first drive controller or the second drive controller controls the first solar wing or the second solar wing to rotate according to a second rotation control strategy.
7. The control method of claim 6, wherein the second rotational control strategy is:
when the motion command is a forward rotation command, the first sun wing or the second sun wing rotates clockwise around the output shaft of the first motor or the output shaft of the second motor;
when the motion command is a reverse rotation command, the first sun wing or the second sun wing rotates counterclockwise around the output shaft of the first motor or the output shaft of the second motor.
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| CN201911251057.8A CN111099041B (en) | 2019-12-09 | 2019-12-09 | Space station multi-cabin solar wing autonomous identification control system and control method thereof |
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| CN201911251057.8A CN111099041B (en) | 2019-12-09 | 2019-12-09 | Space station multi-cabin solar wing autonomous identification control system and control method thereof |
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| CN111099041B true CN111099041B (en) | 2021-06-29 |
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| CN112591152B (en) * | 2020-12-01 | 2023-01-31 | 上海航天控制技术研究所 | Space station solar wing control system |
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|---|---|---|---|---|
| EP0435708A2 (en) * | 1989-11-29 | 1991-07-03 | AEROSPATIALE Société Nationale Industrielle | Control method of the attitude with respect to the roll- and the gear axis for a 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 |
| CN108801127A (en) * | 2018-06-25 | 2018-11-13 | 上海卫星工程研究所 | Solar wing windsurfing rotation precision scaling method based on single Hall sensor |
| CN109050546A (en) * | 2018-08-21 | 2018-12-21 | 中车株洲电力机车有限公司 | A kind of urgent pulliung circuit, method and train based on rigid line control |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0435708A2 (en) * | 1989-11-29 | 1991-07-03 | AEROSPATIALE Société Nationale Industrielle | Control method of the attitude with respect to the roll- and the gear axis for a 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 |
| CN108801127A (en) * | 2018-06-25 | 2018-11-13 | 上海卫星工程研究所 | Solar wing windsurfing rotation precision scaling method based on single Hall sensor |
| CN109050546A (en) * | 2018-08-21 | 2018-12-21 | 中车株洲电力机车有限公司 | A kind of urgent pulliung circuit, method and train based on rigid line control |
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