CN108639394B - Semi-physical simulation system and method for simulating flywheel - Google Patents
Semi-physical simulation system and method for simulating flywheel Download PDFInfo
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- CN108639394B CN108639394B CN201810506123.0A CN201810506123A CN108639394B CN 108639394 B CN108639394 B CN 108639394B CN 201810506123 A CN201810506123 A CN 201810506123A CN 108639394 B CN108639394 B CN 108639394B
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Abstract
The invention discloses a simulated flywheel semi-physical simulation system which comprises a satellite-borne calculation module, a flywheel simulation module and a simulation calculation module; the satellite-borne computing module is used for acquiring satellite attitude information and processing the satellite attitude information to obtain instruction information input into the flywheel; the flywheel simulation module is used for receiving the instruction information and processing the instruction information to obtain motion information output by the flywheel; the invention also discloses a simulated flywheel semi-physical simulation method applying the system, which solves the problems of the loss and test precision of the flywheel device participating in semi-physical simulation and designs a simulated flywheel to realize the verification requirement on the attitude control system.
Description
Technical Field
The invention relates to the field of semi-physical simulation, in particular to a flywheel semi-physical simulation system and a flywheel semi-physical simulation method.
Background
Stable attitude control is an important prerequisite to ensure that the satellite completes the flight mission. The flywheel is used as an attitude control executing mechanism for adjusting the attitude of the satellite and matching with other subsystems to complete flight tasks. The semi-physical simulation is used as an efficient and economic technical means to realize the simulation of each part of interfaces and functions of the satellite, and the physical simulation is accessed in a simulation test system to verify the correctness and the matching of each system of the satellite.
However, in the satellite ground test semi-physical simulation test, the test state requirement is limited by physical, which also causes the problems of loss of the flywheel device, test precision and test efficiency.
Disclosure of Invention
The invention aims to provide a simulated flywheel semi-physical simulation system, which adopts a simulated flywheel to replace a real flywheel to participate in a semi-physical simulation test, solves the problems of the loss and the test precision of the flywheel device participating in the semi-physical simulation, and realizes the verification requirement on an attitude control system.
In order to achieve the purpose, the invention adopts the following technical scheme:
the invention discloses a simulated flywheel semi-physical simulation system which comprises a satellite-borne calculation module, a flywheel simulation module and a simulation calculation module;
the satellite-borne computing module is used for acquiring satellite attitude information and processing the satellite attitude information to obtain instruction information input into the flywheel;
the flywheel simulation module is used for receiving the instruction information and processing the instruction information to obtain motion information output by the flywheel;
and the simulation calculation module is used for calculating the attitude of the satellite according to the motion information.
Preferably, the flywheel simulation module comprises a command input module, a simulation output module and a flywheel calculation module;
the instruction input module is used for receiving instruction information provided by the satellite-borne computing module, processing the instruction information to obtain a rotating speed instruction and transmitting the rotating speed instruction to the analog output module;
the analog output module is used for generating corresponding pulse information according to the rotating speed instruction;
and the flywheel calculation module is used for carrying out internal calculation according to the pulse information to generate the motion information of the flywheel.
Preferably, the motion information is a rotational speed of the flywheel.
The invention also discloses a semi-physical simulation method for simulating the flywheel, which comprises the following steps:
s1: acquiring satellite attitude information and processing the satellite attitude information to obtain command information input into a flywheel;
s2: receiving the instruction information and processing to obtain the motion information output by the flywheel;
s3: and resolving the attitude of the satellite according to the motion information.
Preferably, the S2 includes:
s21: receiving instruction information provided by a satellite-borne calculation module, processing the instruction information to obtain a rotating speed instruction, and transmitting the rotating speed instruction to the analog output module;
s22: generating corresponding pulse information according to the rotating speed instruction;
s23: and performing internal calculation according to the pulse information to generate the motion information of the flywheel.
Preferably, the motion information is a rotational speed of the flywheel.
The invention has the following beneficial effects:
the semi-physical simulation scheme based on the simulated flywheel provided by the invention can reduce the flywheel loss, improve the precision and the simulation efficiency, realize the semi-physical simulation test of the flywheel in a non-parametric state, complete the semi-physical simulation test verification of the flywheel system in the satellite ground test process, and meet the requirements of the semi-physical simulation test.
Drawings
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
FIG. 1 shows a block diagram of a simulated flywheel semi-physical simulation system according to the present invention.
FIG. 2 is a flow chart of a semi-physical simulation method for simulating a flywheel according to the present invention.
Reference numerals:
1. the system comprises a satellite-borne calculation module 2, a flywheel simulation module 3, an instruction input module 4, a simulation output module 5, a flywheel calculation module 6 and a simulation calculation module.
Detailed Description
In order to more clearly illustrate the invention, the invention is further described below with reference to preferred embodiments and the accompanying drawings. Similar parts in the figures are denoted by the same reference numerals. It is to be understood by persons skilled in the art that the following detailed description is illustrative and not restrictive, and is not to be taken as limiting the scope of the invention.
As shown in FIG. 1, the invention discloses a simulated flywheel semi-physical simulation system on one hand, and the system comprises a satellite-borne calculation module 1, a flywheel simulation module 2 and a simulation calculation module 6.
The satellite-borne computing module 1 is used for acquiring satellite attitude information and processing the satellite attitude information to obtain instruction information input into the flywheel, and the instruction information, the flywheel and the satellite form a closed loop.
And the flywheel simulation module 2 is used for receiving the instruction information and processing the instruction information to obtain the motion information output by the flywheel.
The flywheel simulation module 2 may further include a command input module 3, a simulation output module 4, and a flywheel calculation module 5.
The instruction input module 3 can be used for receiving instruction information provided by the satellite-borne computing module 1 and processing the instruction information to obtain the rotating speed instruction; the analog output module 4 can be used for generating corresponding pulse information according to the rotating speed instruction; the flywheel calculation module 5 may be configured to perform internal calculation according to the pulse information to generate motion information of the flywheel. The motion information is information such as the rotating speed of the flywheel.
And the simulation calculation module 6 is used for calculating the attitude of the satellite according to the motion information. The simulation calculation module 6 takes information such as the rotating speed generated by the flywheel simulation module 2 as input, the calculation is completed through the internal calculation of the simulation calculation module 6, the satellite motion information is finally generated and sent to the satellite-borne calculation module 1, a closed loop is formed, and the verification of the satellite attitude control system by the semi-physical simulation is completed.
As shown in fig. 2, in another aspect, the present invention further discloses a simulated flywheel semi-physical simulation method using the system, where the method includes:
s1: and acquiring satellite attitude information and processing the satellite attitude information to obtain command information input into the flywheel.
S2: and receiving the instruction information and processing to obtain the motion information output by the flywheel. The S2 may further include:
s21: receiving instruction information provided by the satellite-borne computing module 1, processing the instruction information to obtain a rotating speed instruction, and transmitting the rotating speed instruction to the analog output module 4;
s22: generating corresponding pulse information according to the rotating speed instruction;
s23: and performing internal calculation according to the pulse information to generate the motion information of the flywheel.
S3: and resolving the attitude of the satellite according to the motion information. The simulation calculation module 6 takes information such as the rotating speed generated by the flywheel simulation module 2 as input, the calculation is completed through the internal calculation of the simulation calculation module 6, the satellite motion information is finally generated and sent to the satellite-borne calculation module 1, a closed loop is formed, and the verification of the satellite attitude control system by the semi-physical simulation is completed.
In the invention, the simulated flywheel is adopted to replace a physical flywheel, so that the semi-physical simulation test of the flywheel in a non-parametric state is realized, the test efficiency of the system ground simulation test is improved, the test range is expanded, the abrasion and the loss of the flywheel can be reduced, and the test accuracy and the test precision are improved.
It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations or modifications may be made on the basis of the above description, and all embodiments may not be exhaustive, and all obvious variations or modifications may be included within the scope of the present invention.
Claims (4)
1. A simulated flywheel semi-physical simulation system is characterized by comprising a satellite-borne calculation module, a flywheel simulation module and a simulation calculation module;
the satellite-borne computing module is used for acquiring satellite attitude information and processing the satellite attitude information to obtain instruction information input into the flywheel;
the flywheel simulation module is used for receiving the instruction information and processing the instruction information to obtain motion information output by the flywheel;
the flywheel simulation module comprises a command input module, a simulation output module and a flywheel calculation module;
the instruction input module is used for receiving instruction information provided by the satellite-borne computing module, processing the instruction information to obtain a rotating speed instruction and transmitting the rotating speed instruction to the analog output module;
the analog output module is used for generating corresponding pulse information according to the rotating speed instruction;
the flywheel calculation module is used for carrying out internal calculation according to the pulse information to generate motion information of the flywheel;
and the simulation calculation module is used for calculating the attitude of the satellite according to the motion information.
2. The simulated flywheel semi-physical simulation system of claim 1 wherein the motion information is a rotational speed of the flywheel.
3. A simulated flywheel semi-physical simulation method using the simulated flywheel semi-physical simulation system according to any one of claims 1 to 2, comprising:
s1: acquiring satellite attitude information and processing the satellite attitude information to obtain command information input into a flywheel;
s2: receiving the instruction information and processing to obtain the motion information output by the flywheel;
the S2 includes:
s21: receiving instruction information provided by a satellite-borne calculation module, processing the instruction information to obtain a rotating speed instruction, and transmitting the rotating speed instruction to the analog output module;
s22: generating corresponding pulse information according to the rotating speed instruction;
s23: performing internal calculation according to the pulse information to generate motion information of the flywheel;
s3: and resolving the attitude of the satellite according to the motion information.
4. The method according to claim 3, wherein the motion information is a rotational speed of the flywheel.
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| CN109634139B (en) * | 2018-12-10 | 2021-12-07 | 中国航天空气动力技术研究院 | Semi-physical simulation system and method for navigation and control system of hypersonic aircraft |
| CN112784448A (en) * | 2021-03-12 | 2021-05-11 | 北京仿真中心 | Data storage simulation device, system and method |
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| CN104071361A (en) * | 2014-06-25 | 2014-10-01 | 南京航空航天大学 | Speed-up flywheel inertia simulator and method for realizing rotational inertia and translational inertia simulation of spacecraft by using speed-up flywheel inertia simulator |
| CN105259793A (en) * | 2015-11-19 | 2016-01-20 | 中国人民解放军国防科学技术大学 | AODV protocol wireless intelligent network-based satellite attitude control simulation system |
| CN107817697A (en) * | 2017-10-25 | 2018-03-20 | 北京仿真中心 | A kind of flywheel information collecting device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| KR100699673B1 (en) * | 2005-09-06 | 2007-03-23 | 현대모비스 주식회사 | A hardware in the loop simulator system for active geometry controlled suspension |
| CN102411313B (en) * | 2011-11-16 | 2013-06-05 | 清华大学 | Satellite flight control closed loop simulation system based on component simulator |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104071361A (en) * | 2014-06-25 | 2014-10-01 | 南京航空航天大学 | Speed-up flywheel inertia simulator and method for realizing rotational inertia and translational inertia simulation of spacecraft by using speed-up flywheel inertia simulator |
| CN105259793A (en) * | 2015-11-19 | 2016-01-20 | 中国人民解放军国防科学技术大学 | AODV protocol wireless intelligent network-based satellite attitude control simulation system |
| CN107817697A (en) * | 2017-10-25 | 2018-03-20 | 北京仿真中心 | A kind of flywheel information collecting device |
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