CN104210676A - Spacecraft active magnetic supplement system - Google Patents
Spacecraft active magnetic supplement system Download PDFInfo
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- CN104210676A CN104210676A CN201410439499.6A CN201410439499A CN104210676A CN 104210676 A CN104210676 A CN 104210676A CN 201410439499 A CN201410439499 A CN 201410439499A CN 104210676 A CN104210676 A CN 104210676A
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Abstract
The invention provides a spacecraft active magnetic supplement system. The spacecraft active magnetic supplement system comprises a coil, a power supply circuit and a control circuit; the power supply circuit is used for supplying current to the coil and comprises n ways of current outputs corresponding to the in-orbit working state of the spacecraft, and the n ways of current outputs respectively supply n different currents to the coil; the coil is electrified to generate a required magnetic field; the control unit is used for receiving instruction from the spacecraft and transmitting switch instructions to control the power supply circuit to generate corresponding currents for the coil. In the development of large spacecrafts, the spacecraft active magnetic supplement system provided by the invention is lighter than a commonly-used magnet block in weight, and the emission cost for the spacecraft is reduced. Besides, the spacecraft active magnetic supplement system can provide a controllable supplement magnetic field, so as to meet the remanence requirements of a large spacecraft in different working states.
Description
Technical field
The present invention relates to spacecraft application, particularly a kind of magnetic compensation system of spacecraft.
Background technology
In Space Vehicle System, after certain equipment or some device power, the magnetic field of generation causes spacecraft remanent magnetism excessive.But, spacecraft in orbit time, its remanent magnetism produced can not be excessive, otherwise can affect the stable of spacecraft attitude and control.The remanent magnetism of spacecraft can be measured by magnetic pilot system.If remanent magnetism is excessive, must be revised by magnetic compensation.Current spacecraft is mended magnetic and is adopted one or more permanent magnet (i.e. magnetic patch) to realize.
For large-scale spacecraft, its power consumption is large, and need the magnetic field of correction very large during operation on orbit, the magnetic patch of needs is just many, adds the weight of spacecraft, certainly will add launch cost.In addition, current magnetic patch mend magnetic optimumly can only revise a kind of mode of operation of spacecraft under magnetic field.Along with spacecraft development, its operation on orbit will have more mode of operation, and after state adjustment, spacecraft changes of magnetic field is obvious.Therefore, magnetic patch mends magnetic beach to meet the development of Large Spacecraft and later stage spacecraft.
summary of the invention
In order to solve in prior art the defect adopting permanent magnet cannot adapt to the change of spacecraft mode of operation, the invention provides a kind of system that remanent magnetism initiatively can be provided to compensate for spacecraft in-orbit, the mode of operation change of spacecraft can not only be adapted to, also reduce the weight of space flight.
In order to achieve the above object, this invention takes following technical scheme:
A kind of spacecraft initiatively mends magnetic system, it is characterized in that: this system comprises coil, feed circuit and control circuit; Described feed circuit connect spacecraft, and accept the power supply that spacecraft provides, the electric current that described feed circuit comprise n road corresponding with spacecraft operation on orbit state exports, and this n road electric current output is respectively coil and provides the individual different electric current of n; Described coil connects described feed circuit, produces magnetic field benefit magnetic needed for corresponding with spacecraft operation on orbit state after powering on; Control unit is for receiving spacecraft command signal, and output switch command signal is to feed circuit, the switch exported with the electric current corresponding with spacecraft mode of operation controlled in described feed circuit.
The principle of work that described spacecraft initiatively mends magnetic system is: when spacecraft mode of operation is adjusted to mode of operation 1, command signal is sent to the control circuit of spacecraft Active Compensation system by spacecraft, control circuit can send switching instruction signals and make feed circuit outgoing current I1, can produce the compensating field needed for mode of operation 1 in coil after electric current I 1.The same manner, spacecraft in working order n time, control circuit can send switching instruction signals and make feed circuit outgoing current I
n, through electric current I in coil
nafter can produce compensating field needed for mode of operation n.
The invention has the beneficial effects as follows: in Large Spacecraft development, the magnetic patch that the weight ratio that spacecraft provided by the present invention initiatively mends magnetic system is commonly used is much smaller, reduces the launch cost of spacecraft.In addition, spacecraft of the present invention initiatively mends magnetic system can provide controollable compensating field, meets the remanent magnetism requirement under Large Spacecraft different operating state.
Accompanying drawing explanation
Fig. 1 is that spacecraft of the present invention initiatively mends magnetic system structure figure.
Detailed description of the invention
Illustrate below in conjunction with accompanying drawing and detailed description of the invention the present invention is further described.
The present invention proposes a kind of spacecraft and initiatively mend magnetic system, as shown in Figure 1, a kind of spacecraft initiatively mends magnetic system, and this system comprises coil, feed circuit and control circuit; Described feed circuit connect spacecraft, accept the power supply that spacecraft provides, and described feed circuit comprise a n road electric current corresponding with spacecraft operation on orbit state and export, and the electric current output of this n road is respectively coil and provides the individual different electric current of n; Described coil connects described feed circuit, produces magnetic field benefit magnetic needed for corresponding with spacecraft operation on orbit state after powering on; Control unit is for receiving spacecraft command signal, and output switch command signal is to feed circuit, the switch exported with the electric current corresponding with spacecraft mode of operation controlled in described feed circuit.
The principle of work that spacecraft of the present invention initiatively mends magnetic system is: suppose that spacecraft operation on orbit has n mode of operation, when spacecraft mode of operation is adjusted to mode of operation 1, send command signal to the control circuit of spacecraft Active Compensation system by spacecraft, control circuit can send switching instruction signals and make feed circuit outgoing current I
1, through electric current I in coil
1after can produce compensating field needed for mode of operation 1.The same manner, spacecraft in working order n time, control circuit can send switching instruction signals and make feed circuit outgoing current I
n, through electric current I in coil
nafter can produce compensating field needed for mode of operation n.So just according to spacecraft different operating state, controllable current can be provided.Coil produces required magnetic field after by electric current.
During spacecraft operation on orbit, the tasks such as spatial intersection, earth observation, data down transmission are needed.Every task starts, and by ground station by ground antenna emitting radio frequency signal, the control module of spacecraft is by the signal of its antenna satellite receiver.After control module receives signal, analyzed and transform and give Star Service module.Finally, need to provide switching on and shutting down instruction by Star Service module is unified, switching on and shutting down instruction will make the equipment of this task start working or close.
When spacecraft starts a certain task in-orbit, namely operation on orbit state changes.Star Service module, when providing switching on and shutting down instruction, is also initiatively mended magnetic system instruction simultaneously.Initiatively mend after magnetic system control circuit obtains instruction, control circuit regulates feed circuit to the outgoing current of coil, thus produces dynamic correction-compensation remanent magnetism.
When spacecraft operation on orbit, its mode of operation changes, when the remanent magnetism that equipment in spacecraft produces there occurs change, initiatively mend magnetic system and also receive the control command that the mode of operation from satellite receiver adjusts, the control circuit of initiatively mending magnetic system changed by its feed circuit the power module of spacecraft be supplied to feed circuit
i 0 ,
v 0 , revise required compensation remanent magnetism dynamically.
Above content is in conjunction with concrete preferred implementation further description made for the present invention, can not assert that specific embodiment of the invention is confined to these explanations.For general technical staff of the technical field of the invention, without departing from the inventive concept of the premise, some simple deduction or replace can also be made, all should be considered as belonging to protection scope of the present invention.
Claims (2)
1. spacecraft initiatively mends a magnetic system, it is characterized in that: this system comprises coil, feed circuit and control circuit; Described feed circuit connect spacecraft, and accept the power supply that spacecraft provides, the electric current that described feed circuit comprise n road corresponding with spacecraft operation on orbit state exports, and this n road electric current output is respectively coil and provides the individual different electric current of n; Described coil connects described feed circuit, produces magnetic field benefit magnetic needed for corresponding with spacecraft operation on orbit state after powering on; Control unit is for receiving spacecraft command signal, and output switch command signal is to feed circuit, the switch exported with the electric current corresponding with spacecraft mode of operation controlled in described feed circuit.
2. spacecraft according to claim 1 initiatively mends magnetic system, it is characterized in that: the principle of work that described spacecraft initiatively mends magnetic system is: when spacecraft mode of operation is adjusted to mode of operation 1, send command signal to the control circuit of spacecraft Active Compensation system by spacecraft, control circuit can send switching instruction signals and make feed circuit outgoing current I
1, through electric current I in coil
1after can produce compensating field needed for mode of operation 1; The same manner, spacecraft in working order n time, control circuit can send switching instruction signals and make feed circuit outgoing current I
n, through electric current I in coil
nafter can produce compensating field needed for mode of operation n.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410439499.6A CN104210676B (en) | 2014-09-01 | 2014-09-01 | A kind of spacecraft initiatively mends magnetic system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410439499.6A CN104210676B (en) | 2014-09-01 | 2014-09-01 | A kind of spacecraft initiatively mends magnetic system |
Publications (2)
| Publication Number | Publication Date |
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| CN104210676A true CN104210676A (en) | 2014-12-17 |
| CN104210676B CN104210676B (en) | 2016-06-01 |
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| CN201410439499.6A Active CN104210676B (en) | 2014-09-01 | 2014-09-01 | A kind of spacecraft initiatively mends magnetic system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104699072A (en) * | 2015-01-30 | 2015-06-10 | 航天东方红卫星有限公司 | Residual magnetism control expansion satellite solar wing and test verification method thereof |
| CN110562488A (en) * | 2019-08-16 | 2019-12-13 | 南京理工大学 | power supply and control circuit applied to cube star brake sail |
| CN113212811A (en) * | 2021-06-24 | 2021-08-06 | 中国科学院微小卫星创新研究院 | Thermal control system compatible with dynamic magnetic compensation |
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| DE10302717A1 (en) * | 2003-01-23 | 2004-08-05 | Astrium Gmbh | Optical receiver used in a spacecraft has the incident emission received measured by sensors to provide input to controller input |
| CN102901939A (en) * | 2012-10-16 | 2013-01-30 | 北京航空航天大学 | Precise control method of atom spin SERF (Self-Exchange Relaxation-Free) state for stabilizing atom spin device |
| CN103438877A (en) * | 2013-09-02 | 2013-12-11 | 北京航空航天大学 | Inertia and magnetic field integration measuring method based on SERF (spin-exchange-relaxation-free) atomic spin effect |
| CN103600853A (en) * | 2013-11-25 | 2014-02-26 | 北京卫星环境工程研究所 | Method for compensating magnetic moment of spacecraft |
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Patent Citations (4)
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| DE10302717A1 (en) * | 2003-01-23 | 2004-08-05 | Astrium Gmbh | Optical receiver used in a spacecraft has the incident emission received measured by sensors to provide input to controller input |
| CN102901939A (en) * | 2012-10-16 | 2013-01-30 | 北京航空航天大学 | Precise control method of atom spin SERF (Self-Exchange Relaxation-Free) state for stabilizing atom spin device |
| CN103438877A (en) * | 2013-09-02 | 2013-12-11 | 北京航空航天大学 | Inertia and magnetic field integration measuring method based on SERF (spin-exchange-relaxation-free) atomic spin effect |
| CN103600853A (en) * | 2013-11-25 | 2014-02-26 | 北京卫星环境工程研究所 | Method for compensating magnetic moment of spacecraft |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104699072A (en) * | 2015-01-30 | 2015-06-10 | 航天东方红卫星有限公司 | Residual magnetism control expansion satellite solar wing and test verification method thereof |
| CN104699072B (en) * | 2015-01-30 | 2017-04-19 | 航天东方红卫星有限公司 | Residual magnetism control expansion satellite solar wing and test verification method thereof |
| CN110562488A (en) * | 2019-08-16 | 2019-12-13 | 南京理工大学 | power supply and control circuit applied to cube star brake sail |
| CN110562488B (en) * | 2019-08-16 | 2021-05-04 | 南京理工大学 | Power supply and control circuit applied to cube star brake sail |
| CN113212811A (en) * | 2021-06-24 | 2021-08-06 | 中国科学院微小卫星创新研究院 | Thermal control system compatible with dynamic magnetic compensation |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104210676B (en) | 2016-06-01 |
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Address after: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee after: Shenzhen Aerospace Dongfanghong Satellite Co.,Ltd. Address before: 518057 room 910, block D, Shenzhen Institute of space technology innovation, South 10th Road, Science Park, Nanshan District, Shenzhen City, Guangdong Province Patentee before: AEROSPACE DONGFANGHONG DEVELOPMENT Ltd. |
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