CN105322750A - Integrated momentum wheel motor for spacecraft and manufacturing method thereof - Google Patents
Integrated momentum wheel motor for spacecraft and manufacturing method thereof Download PDFInfo
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- CN105322750A CN105322750A CN201410402241.9A CN201410402241A CN105322750A CN 105322750 A CN105322750 A CN 105322750A CN 201410402241 A CN201410402241 A CN 201410402241A CN 105322750 A CN105322750 A CN 105322750A
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Abstract
The invention discloses an integrated momentum wheel motor for a spacecraft and a manufacturing method thereof. During motor manufacturing, a momentum wheel for attitude control of the spacecraft and a motor rotor are manufactured into one body to form the motor rotor of the integrated momentum wheel motor, so that the momentum generated by the motor rotor of the integrated momentum wheel motor is equal to that generated by the required momentum wheel for attitude control of the spacecraft, the integrated momentum wheel motor is driven through a drive module integrated by the motor, and the miniaturization and light-weight requirements of the whole momentum wheel system are met. The integrated momentum wheel motor has the advantage that the miniaturization and light-weight requirements of the whole momentum wheel system are met, and also has the advantages of reliable working performance, high reaction speed, long service life, lower cost and the like.
Description
Technical field
the present invention relates to a kind of spacecraft integrated momenttum wheel motor and preparation method thereof, belong to specific type of electric machine manufacturing technology field.
Background technology
in space industry, the gesture stability of spacecraft generally adopts momenttum wheel to carry out, and utilizes the principle that system angle momentum value is constant, by changing the angular momentum of momenttum wheel, driving spacecraft reversion, thus realizing the gesture stability of spacecraft.Existing spacecraft momenttum wheel system is made up of momenttum wheel, motor and corresponding drive system and mechanical support system, and system bulk is large, Heavy Weight.
Summary of the invention
the object of the invention is to, a kind of spacecraft integrated momenttum wheel motor and preparation method thereof is provided, to reduce spacecraft attitude control system volume and weight, thus overcomes the deficiencies in the prior art.
technical scheme of the present invention is achieved in that
a kind of spacecraft of the present invention manufacture method of integrated momenttum wheel motor is, when making motor, Spacecraft Attitude Control momenttum wheel and rotor are made as the rotor being integrally formed integrated momenttum wheel motor, the momentum that the rotor self of this integrated momenttum wheel motor is produced equals the momentum that Spacecraft Attitude Control produces with required momenttum wheel, and driven by the driver module that motor is integrated, thus meet whole momenttum wheel system compact, light-weighted requirement.
the shape of the rotor of above-mentioned integrated momenttum wheel motor is pie, and its structure is the additional steel bushing of surface-mount type magnet steel; And by three-dimensional modeling as follows
calculate the moment of inertia of rotor, to meet the exact requirements of momenttum wheel system to moment of inertia.
according to the integrated momenttum wheel motor of of the present invention a kind of spacecraft that said method builds, comprise the end cap, the Stator and electrical machine rotor that form whole motor; The momentum that its rotor produces equals the momentum that Spacecraft Attitude Control produces with required momenttum wheel, and rotor is rotationally connected through bearing and stator and end cap, and the winding overhang of stator is provided with motor rotor position sensor, and end cap is provided with driver module.
said stator is the fractional-slot structure of 26 pole 24 grooves, adopts accurate electromagnetic-field simulation to design, reduces gullet positioning torque to greatest extent, to improve running precision.
above-mentioned motor rotor position sensor adopts hall device to be pasted onto stator winding end, feeds back the position signalling of rotor with the magnet steel position of direct-detection rotor.
above-mentioned driver module adopts the special driver module of thick-film design forming to be directly mounted on end cap end face, outside driver module, be provided with protective cover.
owing to have employed technique scheme, the integrated momenttum wheel motor of spacecraft of the present invention, by integrated to drive circuit, momenttum wheel and motor height, effectively reduces the volume and weight of whole momenttum wheel system.So compared with prior art, the present invention not only has the advantage that can meet whole momenttum wheel system compact, lightweight requirements in the present invention, but also there is the advantages such as reliable working performance, reaction speed is fast, long service life, cost are lower.
Accompanying drawing explanation
fig. 1 is structural representation of the present invention;
fig. 2 is the external view of driver module.
being labeled as in accompanying drawing: 1-driver module, 2-end cap, 3-motor rotor position sensor, 4-stator, 5-rotor, 6-bearing.
Embodiment
below in conjunction with drawings and Examples, the present invention is described in further detail, but not as any limitation of the invention.
when implementing the manufacture method of a kind of spacecraft of the present invention with integrated momenttum wheel motor, the mode of prior art can be adopted to carry out whole motor making, when making motor, Spacecraft Attitude Control momenttum wheel and rotor are made as the rotor being integrally formed integrated momenttum wheel motor, the momentum that the rotor self of this integrated momenttum wheel motor is produced equals the momentum that Spacecraft Attitude Control produces with required momenttum wheel, and driven by the driver module that motor is integrated, thus meet whole momenttum wheel system compact, light-weighted requirement; The shape of the rotor of integrated momenttum wheel motor is made as pie simultaneously, makes its structure be the additional steel bushing of surface-mount type magnet steel; And by three-dimensional modeling as follows
calculate the moment of inertia of rotor, to meet the exact requirements of momenttum wheel system to moment of inertia.
as depicted in figs. 1 and 2, this integrated momenttum wheel motor comprises the end cap 2, stator 4 and the rotor 5 that form whole motor to the of the present invention a kind of spacecraft structural representation of integrated momenttum wheel motor built according to said method; During enforcement, the momentum that rotor 5 is produced equals the momentum that Spacecraft Attitude Control produces with required momenttum wheel, and be rotationally connected through bearing 6 and stator 4 and end cap 2 by rotor 5, be provided with motor rotor position sensor 3 at the winding overhang of stator 4, end cap 2 is provided with driver module 1; Described stator 4 is the fractional-slot structure of 26 pole 24 grooves, adopts existing accurate electromagnetic-field simulation design to design, and to reduce gullet positioning torque to greatest extent, improves running precision; Its motor rotor position sensor 3 adopts existing hall device to be pasted onto stator winding end, feeds back the position signalling of rotor with the magnet steel position of direct-detection rotor; Described driver module 1 adopts the special driver module of existing thick-film design forming to be directly mounted on end cap end face, at a driver module 1 outer installation protective cover.
Embodiment
as shown in Figure 1, the integrated momenttum wheel motor of this example, is designed by Rational structure, by momenttum wheel and the unified consideration of rotor, is designed to one, and the Integrate Design of motor own, meet whole momenttum wheel system compact, light-weighted requirement.
technical scheme and the course of work
angular momentum formula is
in formula, L is the angular momentum of rotor;
j is the moment of inertia of rotor;
ω is the angular speed of rotor.
moment of inertia formula:
in formula, m is the quality of rigid body i-th part;
r is the distance of rigid body i-th part relative to rigid body barycenter.
in order to improve motor reliability, be low speed, large rotating inertia type motor by design of electrical motor, be inner rotor core by design of electrical motor, rotor 5 is designed to pie, the additional steel sleeve structure of surface-mount type magnet steel, by the accurate Calculation to rotor moment of inertia, meet the exact requirements of momenttum wheel system to moment of inertia, design of electrical motor is the fractional-slot structure of 26 pole 24 grooves, design through accurate electromagnetic-field simulation, reduce gullet positioning torque to greatest extent, improve running precision, and the motor speed that accurate Calculation circuit and magnetic Field Coupling effect determine.
in order to realize Miniaturization Design, controller being carried out thick-film design, forming special driver module as shown in Figure 2, be mounted on motor end face.
Claims (6)
1. the spacecraft manufacture method of integrated momenttum wheel motor, it is characterized in that: when making motor, the momenttum wheel of Spacecraft Attitude Control and rotor are made as the rotor being integrally formed integrated momenttum wheel motor, the momentum that the rotor self of this integrated momenttum wheel motor is produced equals the momentum that Spacecraft Attitude Control produces with required momenttum wheel, and driven by the driver module that motor is integrated, thus meet whole momenttum wheel system compact, light-weighted requirement.
2. the spacecraft manufacture method of integrated momenttum wheel motor according to claim 1, it is characterized in that: the shape of the rotor of described integrated momenttum wheel motor is pie, its structure is the additional steel bushing of surface-mount type magnet steel; And by three-dimensional modeling as follows
calculate the moment of inertia of rotor, to meet the exact requirements of momenttum wheel system to moment of inertia.
3. the integrated momenttum wheel motor of spacecraft that method builds according to claim 1 or 2, comprises the end cap (2), stator (4) and the rotor (5) that form whole motor; It is characterized in that: the momentum that rotor (5) produces equals the momentum that Spacecraft Attitude Control produces with required momenttum wheel, and rotor (5) is rotationally connected through bearing (6) and stator (4) and end cap (2), the winding overhang of stator (4) is provided with motor rotor position sensor (3), and end cap (2) is provided with driver module (1).
4. the integrated momenttum wheel motor of spacecraft according to claim 3, is characterized in that: described stator (4) is the fractional-slot structure of 26 pole 24 grooves, adopts accurate electromagnetic-field simulation to design, reduces gullet positioning torque to greatest extent, improves running precision.
5. the integrated momenttum wheel motor of spacecraft according to claim 3, to it is characterized in that: described motor rotor position sensor (3) adopts hall device to be pasted onto stator winding end, feed back the position signalling of rotor with the magnet steel position of direct-detection rotor.
6. the integrated momenttum wheel motor of spacecraft according to claim 3, is characterized in that: described driver module (1) adopts the special driver module of thick-film design forming to be directly mounted on end cap end face, outside driver module (1), be provided with protective cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410402241.9A CN105322750A (en) | 2014-08-15 | 2014-08-15 | Integrated momentum wheel motor for spacecraft and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410402241.9A CN105322750A (en) | 2014-08-15 | 2014-08-15 | Integrated momentum wheel motor for spacecraft and manufacturing method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105322750A true CN105322750A (en) | 2016-02-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410402241.9A Pending CN105322750A (en) | 2014-08-15 | 2014-08-15 | Integrated momentum wheel motor for spacecraft and manufacturing method thereof |
Country Status (1)
| Country | Link |
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| CN (1) | CN105322750A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2035397A1 (en) * | 1969-07-16 | 1971-01-28 | Societe Nationale Industrielle Aerospatiale, Paris | Inertia flywheel for an art borrowed satellite |
| KR20110007816A (en) * | 2009-07-17 | 2011-01-25 | (주) 대화레이져 | Motor |
| CN102616387A (en) * | 2012-04-01 | 2012-08-01 | 洛阳轴研科技股份有限公司 | Momentum wheel |
-
2014
- 2014-08-15 CN CN201410402241.9A patent/CN105322750A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2035397A1 (en) * | 1969-07-16 | 1971-01-28 | Societe Nationale Industrielle Aerospatiale, Paris | Inertia flywheel for an art borrowed satellite |
| KR20110007816A (en) * | 2009-07-17 | 2011-01-25 | (주) 대화레이져 | Motor |
| CN102616387A (en) * | 2012-04-01 | 2012-08-01 | 洛阳轴研科技股份有限公司 | Momentum wheel |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160210 |