CN107226220B - Stablize the magnetic suspension support device of rotation for satellite load - Google Patents
Stablize the magnetic suspension support device of rotation for satellite load Download PDFInfo
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- CN107226220B CN107226220B CN201710324140.8A CN201710324140A CN107226220B CN 107226220 B CN107226220 B CN 107226220B CN 201710324140 A CN201710324140 A CN 201710324140A CN 107226220 B CN107226220 B CN 107226220B
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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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02N—ELECTRIC MACHINES NOT OTHERWISE PROVIDED FOR
- H02N15/00—Holding or levitation devices using magnetic attraction or repulsion, not otherwise provided for
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The embodiment of the invention discloses a kind of magnetic suspension support devices for stablizing rotation for satellite load, including satellite platform, rotating mechanism, driving mechanism and satellite load placed side: the rotating mechanism, including stator, magnetic rotor and magnetic bearing；The stator is fixedly connected with the satellite platform；The magnetic rotor is fixedly connected with the satellite load placed side；The magnetic rotor can rotate under the driving of the driving mechanism relative to the stator；The stator includes first hollow；The magnetic rotor includes armature spindle, and can generate the first magnetic force；It is hollow interior that the magnetic bearing is mounted on described first, and can generate the second magnetic force；The magnetic bearing includes second hollow；It is hollow interior that the armature spindle is mounted on described second；The satellite load placed side is for carrying satellite load, wherein at least when the magnetic rotor rotates, first magnetic force and second magnetic force repulsion each other.
Description
Technical field
The present invention relates to space flight and machinery field more particularly to a kind of magnetic suspension supports for stablizing rotation for satellite load
Device.
Background technique
The magnetic suspension support device for stablizing rotation for satellite load includes a satellite load placed side, by satellite load
It is placed into after satellite load placed side, the magnetic suspension support device for stablizing rotation for satellite load can be by itself rotation
Turn band dynamic loading to rotate.Under normal conditions, load needs to be placed on the predetermined position of satellite load placed side, if deviateing pre-determined bit
It sets, then there may be the deviation of gravity center rotation axis of load, so as to cause the magnetic suspension support for stablizing rotation for satellite load
There is mass eccentricity or rotating eccentricity in device.Load itself is exactly that Density Distribution is uneven in some cases, and load is placed into
After satellite load placed side, it is difficult to ensure that the rotary shaft of load and the magnetic suspension support device for stablizing rotation for satellite load
Line alignment.
After there is rotating eccentricity or mass eccentricity, the unbalance of rotation will lead to, and then cause due to caused by unbalance
More violent collision or friction are generated between the internal structure of rotating mechanism；Especially when the quality of load is very big, thus
Lead to the rapid damage for stablizing the magnetic suspension support device of rotation for satellite load, and then causes to stablize rotation for satellite load
The magnetic suspension support device reduced service life turned.
Summary of the invention
In view of this, an embodiment of the present invention is intended to provide a kind of magnetic suspension for stablizing rotation for satellite load to support dress
It sets, expects that the magnetic suspension support device rate of decay for solving to be currently used for the stable rotation of satellite load is fast and service life is short and ask
Topic.
In order to achieve the above objectives, the technical scheme of the present invention is realized as follows:
The embodiment of the present invention provides a kind of magnetic suspension support device for stablizing rotation for satellite load, including satellite is put down
Platform, rotating mechanism, driving mechanism and satellite load placed side:
The rotating mechanism, including stator, magnetic rotor and magnetic bearing；
The stator is fixedly connected with the satellite platform；
The magnetic rotor is fixedly connected with the satellite load placed side；
The magnetic rotor can rotate under the driving of the driving mechanism relative to the stator；
The stator includes first hollow；
The magnetic rotor includes armature spindle, and can generate the first magnetic force；
It is hollow interior that the magnetic bearing is mounted on described first, and can generate the second magnetic force；
The magnetic bearing includes second hollow；It is hollow interior that the armature spindle is mounted on described second；
The satellite load placed side is for carrying satellite load, wherein described at least when the magnetic rotor rotates
First magnetic force and second magnetic force repulsion each other.
Optionally, the end of the armature spindle is provided with card and structure, and it is hollow that the armature spindle extends to described second
The outer diameter of end, the card and structure is greater than the described second hollow aperture；
The magnetic rotor arrives pre-determined distance under the action of first magnetic force and second magnetic force axially movable
Later, the card and structure and magnetic bearing interaction are to prevent the magnetic rotor from continuing axially movable.
Optionally, the magnetic suspension support device for stablizing rotation for satellite load, further includes:
Retaining mechanism, one end are fixed on the stator, and the other end is fixed with the magnetic rotor in the locked condition；When
When in non-locking state, the magnetic rotor is under the action of first magnetic force and second magnetic force, axially movable
It is separated in the axial direction with the stator.
Optionally, the magnetic suspension support device for stablizing rotation for satellite load further include:
Magnetic force control system is connect, for controlling at least one of the magnetic bearing and/or the magnetic rotor
The magnetic force between the magnetic bearing and the magnetic rotor is made, to provide anti-radial deflection ability.
Optionally, to be provided with third in the magnetic rotor hollow；
The first communication equipment is provided in the third is hollow；
It is hollow that the 4th is provided in the stator or the satellite platform；
The described 4th it is hollow in be provided with the second communication equipment；
Wherein, first communication equipment can carry out information exchange with second communication equipment.
Optionally, first communication equipment and second communication equipment are wireless telecom equipment, and described first is logical
Believe equipment and second communication equipment by wireless communication；
Alternatively,
The armature spindle is hollow shaft, by being located across between first communication equipment and second communication equipment
Conducting wire connection inside the armature spindle.
Optionally, the third it is hollow in be additionally provided with the first powering device；
And/or
Described 4th it is hollow in be additionally provided with the second powering device；
Wherein, first powering device and/or the second powering device, for be located at satellite load placed side satellite
Load is energized.
Optionally, the armature spindle is hollow shaft；
The satellite load placed side shows to be provided with the opening being connected to the armature spindle；
First powering device and/or the second powering device, by by inside the armature spindle and the opening
It is directed to the satellite load energy supply.
Optionally, the satellite load includes data processing equipment.
Optionally, the magnetic suspension support device for stablizing rotation for satellite load further include:
Magnetic force control system is connect, for controlling at least one of the magnetic bearing and/or the magnetic rotor
The magnetic force between the magnetic bearing and the magnetic rotor is made, to provide the magnetic rotor in anti-radial deflection energy
Power.
In the magnetic suspension support device provided in an embodiment of the present invention for stablizing rotation for satellite load, rotor is that can produce
The magnetic rotor of raw first magnetic force, bearing is the bearing that can generate the second magnetic force；First magnetic force and the second magnetic force repulsion each other,
In this way during magnetic rotor rotates, due to the interaction of the first magnetic force and the second magnetic force, it is possible to reduce magnetic rotor
It direct active force or avoids direct contact between stator and magnetic bearing, is led so as to reduce relative friction in rotary course
The damage of cause prolongs the service life so as to slow down damage rate, and especially when there is mass eccentricity, effect is especially aobvious
It writes.
Detailed description of the invention
Fig. 1 is the knot of the first magnetic suspension support device rotated for satellite load stabilization provided in an embodiment of the present invention
Structure schematic diagram；
Fig. 2 is the knot of the second provided in an embodiment of the present invention magnetic suspension support device for stablizing rotation for satellite load
Structure schematic diagram；
Fig. 3 is the survey of the first magnetic suspension support device rotated for satellite load stabilization provided in an embodiment of the present invention
Try flow diagram；
Fig. 4 is the survey of the second provided in an embodiment of the present invention magnetic suspension support device for stablizing rotation for satellite load
Try flow diagram.
Specific embodiment
Technical solution of the present invention is further described in detail with reference to the accompanying drawings and specific embodiments of the specification.
As shown in Figures 1 and 2, stablize the magnetic suspension support device rotated for satellite load the present embodiment provides a kind of,
Including satellite platform 110, rotating mechanism 120, satellite load placed side 130 and driving mechanism 140.
The rotating mechanism 120, including stator 121, magnetic rotor 122 and magnetic bearing 123；
The stator 121 is fixedly connected with the satellite platform 110；
The magnetic rotor 122 is fixedly connected with the satellite load placed side 130；
The magnetic bearing 123 is mounted between the stator 121 and the magnetic rotor 122；
The magnetic rotor 122 can rotate under the driving of the driving mechanism 140 relative to the stator 121；
The stator 121 includes first hollow；
The magnetic rotor 122 includes armature spindle 1221, and can generate the first magnetic force；
It is hollow interior that the magnetic bearing 123 is mounted on described first, and can generate the second magnetic force；
The magnetic bearing 123 includes second hollow；It is hollow interior that the armature spindle 1221 is mounted on described second；
The satellite load placed side 130 is for carrying satellite load, wherein at least rotates in the magnetic rotor 122
When, first magnetic force and second magnetic force repulsion each other.
It is provided with satellite load installation position on the satellite load placed side 130 in the present embodiment, can be used for fixing
Or satellite load is placed, satellite load here can be the various objects being placed on 130 platform of satellite load placed side.
The driving mechanism 140 may include various types of driving devices in the present embodiment, and driving device here can
It include: electric driver, fluid pressure drive device and pneumatic actuating device etc..The electric driver may include various types of drives
Dynamic motor, for example, drive motor etc..
The driving mechanism 140 is sequentially connected with the magnetic rotor 122, the fortune that the driving mechanism 140 passes through itself
Magnetic rotor 122 described in trend provides rotary force, and the magnetic rotor 122 is under the driving of driving mechanism 140, relative to described
Stator 121 rotates.
The stator 121 in the present embodiment can include: the first circular conical surface being recessed to first direction；The magnetic rotor
122 include the second circular conical surface to first direction protrusion；The circular cone amplitude phase of first circular conical surface and second circular conical surface
Adaptation.First circular conical surface and second circular conical surface cooperate, and constitute between stator 121 and magnetic rotor 122
The surfaces of revolution.
The bearing for providing slew buffer between stator 121 and magnetic rotor 122 in the present embodiment is magnetic bearing 123,
The second magnetic force that magnetic bearing 123 generates and the first magnetic force that magnetic rotor 122 provides are mutually exclusive, in 122 phase of magnetic rotor
When rotating for stator 121, the gap between magnetic rotor 122 and stator 121 is formed, avoids magnetic rotor 122 and described fixed
Son 121 directly contacts and direct friction with magnetic bearing 123, alternatively, can at least reduce magnetic rotor 122 and stator
Interaction force between 121 or magnetic bearing 123, so that the abrasion and damage in rotary course are avoided or reduced, to prolong
The service life of the long magnetic suspension support device for stablizing rotation for satellite load.In short, the first magnetic force described in the present embodiment
With the interaction force of the second magnetic force, it is equivalent to and provides for the magnetic rotor 122 relative to magnetic bearing 123 and stator
121 buoyancy.
In some embodiments, the magnetic rotor 122 and the magnetic bearing 123 permanent magnetism that may include magnetic force opposite
Iron；The permanent magnet can with permanent magnetic, so that the magnetic rotor 122 and magnetic bearing 123 be by opposite magnetic force,
Reduce or offset the frictional force between in rotary course.
In some embodiments, at least one of the magnetic rotor 122 and the magnetic bearing 123 can be charging magnetic
Power structure makes it generate magnetic force, finally makes magnetic by an energization into magnetic rotor 122 and/or magnetic bearing 123
Mutually exclusive the first magnetic force and the second magnetic force are generated between power rotor 122 and magnetic bearing 123.
The magnetic bearing 123 may include three parts, first part and 122 phase of magnetic rotor in the present embodiment
To effect, second part and the stator 121 are fixed；Part III can wrap between the first part and second part
It includes: the various structures for making first part and second part relative motion such as ball.The magnetic bearing 123 in the present embodiment
At least partly structure can generate magnetic force.
The magnetic rotor 122 may include armature spindle 1221 in the present embodiment, and be connected with the armature spindle 1221
At least part of rotor body, rotor body and armature spindle 1221 may include magnetic force body, which can be used for generating first
Magnetic force.
The magnetic bearing 123 can be used for the generation suspending power of magnetic rotor 122 in the present embodiment, therefore in the present embodiment
The magnetic bearing 123 can be referred to as magnetic suspension bearing again.It is flat in x-axis and y-axis to provide magnetic rotor 122 for the magnetic suspension bearing
Translation and rotation in face only allow the magnetic rotor 122 small distance in the rotation in y-axis direction and y-axis direction to be translatable.
Therefore magnetic bearing 123 provides at least the restriction of 4 freedom degrees, rotation and translation on y-axis direction.Here y-axis can be flat
The capable axis with magnetic rotor 122, x-axis is perpendicular to y-axis.
The magnetic rotor 122 constitutes the component part of the intrinsic articulation of the rotating mechanism in the present embodiment；It is described
Stator 121 constitutes the extrinsic articulation of rotating mechanism.
Since rotor is magnetic rotor 122, bearing is magnetic bearing 123 in the present embodiment, pass through what is generated between each other
Repulsive magnetic force, it is possible to reduce the frictional force in rotary course, even if there is bias in satellite load on satellite load placed side
It is not in the friction compared with great dynamics, to reduce abrasion.The magnetcisuspension provided in this embodiment for stablizing rotation for satellite load
The precision for stablizing rotation of over draft support arrangement can reach 0.005 °/s.
The magnetic suspension support device for stablizing rotation for satellite load further include:
Magnetic force control system is connect at least one of the magnetic bearing 123 and/or the magnetic rotor 122,
For controlling the magnetic force between the magnetic bearing 123 and the magnetic rotor 122, to provide anti-radial deflection ability.
The magnetic force control system in the present embodiment, it may include Xiang Tong electricity magnet provides the system of electric energy, passes through control
Size of current etc. controls the magnetic force size between magnetic bearing 123 and magnetic rotor 122, so as in the quality of satellite load
When eccentric larger, biggish repulsive magnetic force is provided, when mass eccentricity is smaller, provides lesser repulsive magnetic force, thus reduce or
Prevent the direct friction of the direct friction or large force between magnetic rotor and magnetic bearing 123.
The magnetic force control system in the present embodiment can include: sensor can be used for detecting the magnetic force of satellite load
Bias may also include various controllers, and the magnetic force which can control between magnetic bearing 123 and magnetic rotor 122 is big
It is small.
Here radial direction can be the direction of the plane of the rotary shaft perpendicular to the magnetic rotor 122.It is axial to turn for magnetic force
The direction of plane where the rotary shaft of axis.
Optionally, the end of the armature spindle 1221 is provided with card and structure 1222, and the armature spindle 1221 extends to institute
The second hollow end is stated, the card and the outer diameter of structure 1222 are greater than the described second hollow aperture；
The magnetic rotor 122 arrives default axially movable under the action of first magnetic force and second magnetic force
After distance, the card and structure 1222 and the magnetic bearing 123 interaction are to prevent the magnetic rotor 122 from continuing
Axially movable.
The card and the outer diameter of structure 1222 are greater than aperture in the present embodiment, and card and the outer diameter of structure 1222 can not just be worn
Saturating described second hollow aperture, so that it may prevent the magnetic rotor 122 from further diverging from the magnetic bearing 123, so that
The magnetic rotor 122 is just upwardly separated from stator 121 more than pre-determined distance in axial (i.e. z-axis)；But turn magnetic force
Son 122 can be detached from stator 121 in z-axis in certain distance, so that gap is generated between stator 121 and magnetic rotor 122, from
Without being used in relative friction.
The pre-determined distance is equal to the length of the armature spindle 1221 and the difference of the second hollow depth in the present embodiment.
The length of the armature spindle 1221 is greater than the described second hollow depth.The card and structure 1222 can be the armature spindle 1221
Outwardly extending outer eaves.The outer diameter is the minimum diameter of the outer eaves of the armature spindle 1221.The armature spindle 1221 can be with institute
It states rotor body to be detachably connected, facilitates the assembling of the magnetic rotor 122.Certainly in some embodiments, the card and knot
Structure 1222 is not limited to the outer eaves that outer diameter is greater than space, may also include the structures such as hook.
Optionally, the magnetic suspension support device for stablizing rotation for satellite load, further includes:
Retaining mechanism 150, one end are fixed on the stator 121, the other end in the locked condition with the magnetic rotor
122 is fixed；When being in non-locking state, effect of the magnetic rotor 122 in first magnetic force and second magnetic force
Under, it is separated in the axial direction with the stator 121 axially movable.
The retaining mechanism 150 in the present embodiment can include: the structures such as manipulator or mechanical hook can pass through itself
Activity so that current rotating mechanism is in locking state and non-locking state.In the locked condition, the magnetic rotor 122
It is opposing stationary between the stator 121, it is unable to relative rotation；Under non-locking state, the magnetic rotor 122 with it is described fixed
It can relative rotation between son 121.
One end of retaining mechanism 150 is fixed on stator 121 in the present embodiment, and the other end can locked with automatic movable
It is fixed with the magnetic rotor 122 under tight state, the magnetic rotor 122 is unclamped under non-locking state.
Optionally, the armature spindle 1221 is arranged in the middle position of the magnetic rotor 122, and with magnetic rotor 122
Rotation overlapping of axles.
The armature spindle 1221 is arranged in the middle position of magnetic rotor 122, magnetic rotor 122 itself can be made not
There is the problem of rotating eccentricity, reduces the friction phenomenon in rotary course.
Optionally, to be provided with third in the magnetic rotor 122 hollow；The first communication is provided in the third is hollow
Equipment；It is hollow that the 4th is provided in the stator 121 or the satellite platform 110；The described 4th it is hollow in be provided with second
Communication equipment；Wherein, first communication equipment can carry out information exchange with second communication equipment.
The information of first communication equipment and second communication equipment interaction in the present embodiment, it may include: control
The rotation instruction of rotating mechanism rotation also includes the condition information of detection rotating mechanism rotary state.In some embodiments, institute
The first communication equipment and second communication equipment are stated, interactive information may also include the various information of satellite platform acquisition.
First communication equipment and the second communication equipment can be wire communication facility in the present embodiment, or nothing
Line communication equipment.Wire communication facility carries out information exchange by cable or optical cable.The wireless telecom equipment passes through wireless communication
Number carry out information exchange.
Preferably, first communication equipment and second communication equipment are wireless telecom equipment, and described first is logical
Believe equipment and second communication equipment by wireless communication.Here wireless telecom equipment can are as follows: bluetooth radio communication device,
WiFi communication equipment, infrared communication device, Ultraviolet Communication equipment or laser communication gear etc..
In some embodiments, the armature spindle 1221 is hollow shaft, first communication equipment and second communication
It is connected between equipment by being located across the conducting wire inside the armature spindle 1221.
The hollow shaft includes: axial wall and hollow in axial wall.Armature spindle 1221 is hollow shaft in the present embodiment,
Then have inside armature spindle 1221 hollow.In the present embodiment the first communication equipment and the second communication equipment at least one be cable modem
When believing equipment, the conducting wire of two communication equipments is connected, it can be by the hollow connection inside armature spindle 1221；Therefore armature spindle 1221
Also cabling space is provided for conducting wire.
In some embodiments, as shown in Fig. 2, being additionally provided with the first powering device in the third is hollow；And/or institute
State the 4th it is hollow in be additionally provided with the second powering device；Wherein, first powering device and/or the second powering device, are used for
It is energized to the satellite load for being located at satellite load placed side 130.
First powering device and the second powering device all can be power supply unit in the present embodiment, can be used for each
Kind current consuming apparatus provides electric energy.First powering device and the second powering device can be battery or can be by luminous energy or wind
The natural energies such as energy are converted to the energy conversion of electric energy, can provide electric energy to various current consuming apparatus.
Optionally, the armature spindle 1221 is hollow shaft；The surface of the satellite load placed side 130 be provided with it is described
The opening that armature spindle 1221 is connected to；First powering device and/or the second powering device, by passing through the armature spindle 1221
The internal and described opening is directed to the satellite load energy supply.
In some cases, at least one of first powering device and second powering device, can be with
Former power etc. is driven for providing to driving mechanism.
The satellite platform 110 can be satellite platform in some embodiments.
Optionally, the satellite load includes data processing equipment.The data processing equipment is for handling satellite load
Data and/or image and/or video information.Certainly in specific implementation, the acquisition equipment is not limited to this.
As shown in figure 3, the embodiment of the present invention also provides a kind of magnetic suspension support device for stablizing rotation for satellite load
Test method, comprising:
Step S1: retaining mechanism releases locking；
Step S2: after retaining mechanism releases locking, rotating mechanism is switched to magnetic bearing holding state from locking state；
Step S3: magnetic force control system controls the magneticaction between magnetic bearing and magnetic rotor, so that the magnetic force
Shaft moves in axial satellite load placed side direction, so that magnetic rotor is separated from each other with stator and magnetic bearing；
Step S4: after the magnetic rotor is separated with stator and magnetic bearing, driving force is provided to magnetic rotor, is driven
The magnetic rotor is moved relative to stator rotation；
Step S5: the magnetic rotor is detected relative to the rotary state in stator rotation, obtains test result parameter.
In some embodiments, as shown in 4 figures, the method also includes:
Step S6: according to the test result parameter, control parameter and/or the adjustment institute of the magnetic force control system are calibrated
State magnetic bearing and the magnetic rotor；The control parameter be preset for control the magnetic rotor and magnetic bearing it
Between the parameter that interacts.
Step S7: test terminates, by magnetic force control system gradually contact the magnetic bearing and the magnetic rotor it
Between magneticaction so that the magnetic rotor is slowly converted from rotation status according to pre-set velocity as the branch of the magnetic bearing
Support state suddenly falls to caused mutual expansion and the caused damage of friction on magnetic bearing to avoid the magnetic rotor and asks
Topic.
A specific example is provided below in conjunction with above-mentioned any embodiment:
Rotating mechanism uses hybrid magnetic suspension scheme in this example, realizes the magnetic confinement to 5 freedom degrees of rotating mechanism
It is designed with the motor-driven rotating mechanism of one degree of freedom.Utilize the permanent magnet passive stabilization and permanent magnet bias electromagnetism of rotor
Active control realizes that the magnetic suspension to 5 freedom degrees of rotating mechanism constrains, to translation radially of the axis of rotation carry out active control,
Passive stabilization is carried out to axial translation and radial deflection.The rotating mechanism has following characteristics:
Increase the independent passive axial magnetic bearing of permanent magnetism in the outer rim of rotating mechanism, to increase the anti-radial direction of magnetic rotor
Deflection capacity keeps system relatively easy reliable；
Radial magnetic force control system has been installed additional, it can be achieved that accurate control to magnetic suspension mechanism shaft position, improves magnetic
The rotor mechanism rigidity of suspension；
Perhaps it is exemplary in rail magnetic levitation and ground machine bearing branch to be suitable for this there are a small amount of translation displacements amounts axial
The conversion designs demand of support.
The specific structure of this rotating mechanism can be as follows:
Magnetic rotor includes armature spindle, armature spindle at rotating mechanism intrinsic articulation.Intrinsic articulation extends to and payload
The connection of satellite load placed side, while the inner space of intrinsic articulation and structure should be able to adapt to the communication equipment of wireless data transmission
And the mounting arrangement and space requirement of the powering device of wireless energy transfer.
Stator forms the extrinsic articulation of rotating mechanism, and extrinsic articulation is connect with satellite platform, while installing accordingly on extrinsic articulation
Wireless data transmission communication equipment and wireless energy transfer powering device.
In an end face of rotating mechanism, intrinsic articulation is accordingly docked with satellite load placed side；Pair used when docking
Binding structure is the connection structure of the satellite load placed side of satellite launch stage satellite platform and payload, while being also used as and defending
The restraining structure of star launching phase rotating mechanism upper surface.
In another end face of rotating mechanism, it is similarly designed with the constraint mechanism of launching phase rotating mechanism.In addition it also sets
Set one group with magnetic bearing be main load component bearing support mechanism, for rotating mechanism the ground test stage movement
Test, can adapt to the rotary motion test request of payload under the influence of ground gravity.
For terra mechanics test mode, rotating mechanism is locked using the retaining mechanism of rotating mechanism, with satellite launch
The rotating mechanism locking state of state is consistent.
In this example, it takes the connection structure of rotating mechanism retaining mechanism and satellite platform and satellite load placed side
The scheme of integrated design is carried out with retaining mechanism, design feature is as follows:
The inner and outer eaves structure for designing the upper surface of rotating mechanism, undertakes being stressed directly between payload and satellite platform
Transmitting, and formed to the relative motion of rotating mechanism upper surface and the constraint of rotation；
Inside and outside joint end face design in the lower end surface of rotating mechanism has relative motion constraint mechanism, realizes to whirler
The relative motion of the lower end surface of structure constrains.
In order to meet the large bearing capacity locking of rotating mechanism simultaneously and the particular/special requirement slowly without impact release, by whirler
The retaining mechanism and synchronous release mechanism of structure are separately designed, and design feature is as follows:
The locking and coupling mechanism force of large bearing capacity are only undertaken positioned at the interior outer rim structure and retaining mechanism of rotating mechanism upper surface
Removing function, matched relieving mechanism only undertake shock-free synchronous slow release function.Pass through stepper motor, connecting rod machine
The driving of the components such as structure, substep are realized the releasing of big carrying coupling mechanism force and are slowly discharged without impact.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, can easily think of the change or the replacement, and should all contain
Lid is within protection scope of the present invention.Therefore, protection scope of the present invention should be based on the protection scope of the described claims.
Claims (10)
1. a kind of magnetic suspension support device for stablizing rotation for satellite load, which is characterized in that including satellite platform, whirler
Structure, driving mechanism and satellite load placed side:
The rotating mechanism, including stator, magnetic rotor and magnetic bearing；
The stator is fixedly connected with the satellite platform；
The magnetic rotor is fixedly connected with the satellite load placed side；
The magnetic rotor can rotate under the driving of the driving mechanism relative to the stator；
The stator includes first hollow；
The magnetic rotor includes armature spindle, and can generate the first magnetic force；
It is hollow interior that the magnetic bearing is mounted on described first, and can generate the second magnetic force；
The magnetic bearing includes second hollow；It is hollow interior that the armature spindle is mounted on described second；
The satellite load placed side is for carrying satellite load, wherein at least when the magnetic rotor rotates, described first
Magnetic force and second magnetic force repulsion each other.
2. the magnetic suspension support device according to claim 1 for stablizing rotation for satellite load, which is characterized in that
The end of the armature spindle is provided with card and structure, and the armature spindle extends to the described second hollow end, the card
It is greater than the described second hollow aperture with the outer diameter of structure；
The magnetic rotor under the action of first magnetic force and second magnetic force, arrive axially movable pre-determined distance it
Afterwards, the card and structure and magnetic bearing interaction are to prevent the magnetic rotor from continuing axially movable.
3. the magnetic suspension support device according to claim 1 or 2 for stablizing rotation for satellite load, which is characterized in that
The magnetic suspension support device for stablizing rotation for satellite load, further includes:
Retaining mechanism, one end are fixed on the stator, and the other end is fixed with the magnetic rotor in the locked condition；When being in
When non-locking state, the magnetic rotor under the action of first magnetic force and second magnetic force, axially movable with institute
Stator is stated to separate in the axial direction.
4. the magnetic suspension support device according to claim 1 or 2 for stablizing rotation for satellite load, which is characterized in that
The magnetic suspension support device for stablizing rotation for satellite load further include:
Magnetic force control system is connect, for controlling at least one of the magnetic bearing and/or the magnetic rotor
The magnetic force between magnetic bearing and the magnetic rotor is stated, to provide anti-radial deflection ability.
5. the magnetic suspension support device according to claim 1 or 2 for stablizing rotation for satellite load, which is characterized in that
It is hollow that third is provided in the magnetic rotor；
The first communication equipment is provided in the third is hollow；
It is hollow that the 4th is provided in the stator or the satellite platform；
The described 4th it is hollow in be provided with the second communication equipment；
Wherein, first communication equipment can carry out information exchange with second communication equipment.
6. the magnetic suspension support device according to claim 5 for stablizing rotation for satellite load, which is characterized in that
First communication equipment and second communication equipment are wireless telecom equipment, first communication equipment and described
Second communication equipment is by wireless communication；
Alternatively,
The armature spindle is hollow shaft, by passing through the rotor between first communication equipment and second communication equipment
Conducting wire connection inside axis.
7. the magnetic suspension support device according to claim 5 for stablizing rotation for satellite load, which is characterized in that
The first powering device is additionally provided in the third is hollow；
And/or
Described 4th it is hollow in be additionally provided with the second powering device；
Wherein, first powering device and/or the second powering device, for be located at satellite load placed side satellite load
It is energized.
8. the magnetic suspension support device according to claim 7 for stablizing rotation for satellite load, which is characterized in that
The armature spindle is hollow shaft；
The surface of the satellite load placed side is provided with the opening being connected to the armature spindle；
First powering device and/or the second powering device pass through the conducting wire by the armature spindle inside and the opening
For satellite load energy supply.
9. the magnetic suspension support device according to claim 1 or 2 for stablizing rotation for satellite load, which is characterized in that
The satellite load includes acquisition equipment.
10. the magnetic suspension support device according to claim 1 or 2 for stablizing rotation for satellite load, which is characterized in that
The magnetic suspension support device for stablizing rotation for satellite load further include:
Magnetic force control system is connect, for controlling at least one of the magnetic bearing and/or the magnetic rotor
The magnetic force between magnetic bearing and the magnetic rotor is stated, to provide the magnetic rotor in anti-radial deflection capacity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710324140.8A CN107226220B (en) | 2017-05-09 | 2017-05-09 | Stablize the magnetic suspension support device of rotation for satellite load |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| JPH11257354A (en) * | 1998-03-16 | 1999-09-21 | Tdk Corp | Rotor for magnetic bearing and superconductive magnetic bearing |
| CN201045606Y (en) * | 2007-03-26 | 2008-04-09 | 北京智源博科技有限公司 | Uniaxle magnetic suspension free rotating floor |
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