CN110104220A - A kind of fluid-type reaction device - Google Patents
A kind of fluid-type reaction device Download PDFInfo
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- CN110104220A CN110104220A CN201910380728.4A CN201910380728A CN110104220A CN 110104220 A CN110104220 A CN 110104220A CN 201910380728 A CN201910380728 A CN 201910380728A CN 110104220 A CN110104220 A CN 110104220A
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- 238000006243 chemical reaction Methods 0.000 title claims abstract description 43
- 239000012530 fluid Substances 0.000 claims abstract description 39
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 14
- 238000007789 sealing Methods 0.000 claims description 7
- 239000000919 ceramic Substances 0.000 claims description 6
- 238000005485 electric heating Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 5
- 230000000694 effects Effects 0.000 claims description 4
- 238000005259 measurement Methods 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 3
- 229910052751 metal Inorganic materials 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 3
- 239000011796 hollow space material Substances 0.000 claims description 2
- 229910001338 liquidmetal Inorganic materials 0.000 claims description 2
- QSHDDOUJBYECFT-UHFFFAOYSA-N mercury Chemical compound [Hg] QSHDDOUJBYECFT-UHFFFAOYSA-N 0.000 claims description 2
- 229910052753 mercury Inorganic materials 0.000 claims description 2
- 238000012806 monitoring device Methods 0.000 claims description 2
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 claims 1
- 239000010931 gold Substances 0.000 claims 1
- 229910052737 gold Inorganic materials 0.000 claims 1
- 239000000126 substance Substances 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 5
- 239000011553 magnetic fluid Substances 0.000 abstract 2
- 238000010586 diagram Methods 0.000 description 10
- 230000006698 induction Effects 0.000 description 7
- 239000004020 conductor Substances 0.000 description 4
- 230000006641 stabilisation Effects 0.000 description 4
- 238000011105 stabilization Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000009411 base construction Methods 0.000 description 2
- JJWKPURADFRFRB-UHFFFAOYSA-N carbonyl sulfide Chemical compound O=C=S JJWKPURADFRFRB-UHFFFAOYSA-N 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- 210000003813 thumb Anatomy 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000005674 electromagnetic induction Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 210000003811 finger Anatomy 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000003384 imaging method Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
-
- 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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
-
- 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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
- B64G1/245—Attitude control algorithms for spacecraft attitude control
-
- 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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
- B64G1/366—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors using magnetometers
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The present invention relates to a kind of fluid-type reaction devices to belong to field of aerospace technology for the actuator of spacecraft attitude adjustment.Gesture stability and adjustment of the device for spacecraft；The fluid-type reaction device includes executing agency, control unit and mounting bracket；The executing agency includes pedestal, hollow ring and permanent magnet, and hollow ring is fixed on the base by anchor ear, and permanent magnet is mounted on base central and is fixed with blind flange；The hollow ring outer surface is wound by resistance wire, and hollow ring is intracavitary to be full of conductive fluid, and hollow ring is inside and outside and is uniformly distributed four groups of positive and negative electrodes.The gesture stability of spacecraft is realized in the present invention using the rotation of magnetic fluid, quality is small, and at low cost, simple and reliable for structure, the friction between magnetic fluid and hollow ring is small, and loss is low, and it is without friction, it is high-efficient.
Description
Technical field
The present invention relates to a kind of fluid-type reaction devices to belong to aviation boat for the actuator of spacecraft attitude adjustment
Its technical field.
Background technique
The appearance of spacecraft makes the scope of activities of the mankind be expanded to unmeasured vastness cosmic space, realizes human knowledge certainly
Right and nature remodeling ability leap.In-orbit spacecraft has directly taken on the tasks such as detection, development and utilization to cosmic space,
This generic task proposes the demand of attitude stabilization or attitude maneuver to Spacecraft Attitude Control.Spacecraft attitude stabilization and motor-driven
Executing agency is widely noticed always as a key technology of Spacecraft Attitude Control, the momentum based on conservation of angular momentum principle
Wheel apparatus is a kind of common technical solution.Existing mature technology is mechanical ball bearing momenttum wheel, mechanical ball bearing momentum
There are biggish mechanical friction loss, quality for wheel greatly, structure is complicated, at high cost.The magnetic suspension bearing newly risen connects without machinery
Touching, but magnetic suspension bearing is a kind of auxiliary bearing device, needs that other mechanical bearings is cooperated to use, still remains no small
Frictional dissipation, and structure is more complicated, it is with high costs.
On the other hand, perturbed force can be generated when the work of traditional flywheel, seriously affects the pointing accuracy of satellite.Perturbed force is drawn
Spacecraft structure micro-vibration is played, this micro-vibration can travel on Satellite Camera along flywheel structure, cause the micro- of Satellite Camera
Vibration, destroys the imaging precision of camera.It is mainly three kinds following that flywheel disturbs Producing reason: flywheel is uneven, bearing disturbance,
Motor disturbance.Flywheel imbalance is the main reason for flywheel generates perturbed force, due to the error of flywheel production technology, leads to rotor
There are quality unevenness, although present manufacturing process progress is rapid, the Mass Distribution for reducing flywheel is uneven, can not be complete
It eliminates.Therefore the out-of-balance force and torque generated when flywheel work not can avoid, this is one of the main reason of flywheel perturbed force.
With flywheel high-speed rotation, then two groups of imbalances can generate perturbed force and disturbing moment respectively.Bearing disturbance is due to bearing work
Caused by skill error, when the rotor is turning, bearing fabrication error causes rotor the shake of low frequency or high frequency occur.In addition, flying
Perturbed force can be generated when wheel speed zero passage, the torque ripple of direct current generator can also generate perturbed force.
Summary of the invention
The purpose of the present invention is to solve existing device for adjusting posture, there are the pointing accuracies that serious vibration influences satellite
The problem of, a kind of fluid-type reaction device is provided, which provides the moment of momentum by the rotation of charged fluid for spacecraft, real
Now to the pose adjustment of spacecraft.
The purpose of the present invention is achieved through the following technical solutions.
A kind of fluid-type reaction device, comprising: executing agency, control unit and cabinet；Executing agency and control unit
It is placed in cabinet；Heat release hole is provided on the case box；Described control unit effect, for handling each sensor measurement data
And the direction of current loop and size in feedback control executing agency, including hollow ring positive and negative electrode, electric heating system and
Each detection device；
Executing agency includes: hollow ring, pedestal, permanent magnet, resistance wire and electrode；
The pedestal is for placing hollow ring；Permanent magnet is installed on the base, at upper cover or pedestal and upper cover；Then
Realize that sealing is fixed by upper cover；Full conductive fluid is filled in the hollow ring；In the inner side and outer side of the hollow ring
Process through-hole, the coaxial same aperture of inside and outside side through hole, for installing positive and negative electrode；The positive and negative electrode is contacted with fluid；Resistance
Silk is wrapped on hollow ring, electric heating is used for, to guarantee that fluid-type reaction device is in normal working temperature, from low temperature
Environmental disturbances；Thermometer is installed, so as to real-time monitoring device temperature on hollow ring.
Ampere force is generated when fluid is powered in hollow ring, the direction of Ampere force is judged by left hand rule.
The pedestal is cannular boss structure, and permanent magnet is placed in boss hollow space, and hollow ring is fixed on outside boss
Then side realizes that sealing is fixed by upper cover；
In the case where number of electrodes uses less, moreover it is possible to which the effect got well, the pedestal are to use with groove structure
In the placement pole N or the pole S permanent magnet；Hollow ring is fixed on the base, then realizes that sealing is fixed by upper cover；
The conductive fluid includes mercury, crystal liquid metal or other conductive fluid media；
Hollow ring is using nonmetallic materials such as ceramics；
Positive and negative electrode contacts with fluid in hollow ring and uses thread seal and O-ring seal, or using ceramics with
The welding technique of metal, electrode and nonmetallic circular ring are welded together.
The material of the cabinet is aluminium alloy；
It further include mounting bracket, fluid-type reaction device is fixed on the mounting bracket；
A kind of fluid-type reaction device disclosed by the invention quotes electromagnetic theory, by closed annulus in magnetic field
Interior conductive fluid is powered, and fluid rotates in annulus under ampere power drive, and rotation direction is determined by left hand rule, the present apparatus
The positive and negative rotation of fluid can be controlled by changing current direction.Then by Space Vehicle System conservation of angular momentum, overcome disturbance torque,
Realize the gesture stability to spacecraft.Fluid-type reaction device attached thermal control system, keep the temperature range of device controlled
System guarantees the normal work of system at ± 45 degrees Celsius, installs fluid speed measurement device, accurate to provide required angular momentum.Magnetic is provided
The devices such as strong meter, facilitate the size and Orientation in measurement magnetic field, eliminate interference magnetic field to place magnetic torquer.Finally it is fixed on peace
Couple on dress bracket with spacecraft.
The utility model has the advantages that
1, a kind of fluid-type reaction device disclosed by the invention, due to not having using mechanical bearing and motor, so dress
It is simple to set structure, Mass Distribution is uniform, is solved from the root because of factors such as rotary body is uneven, bearing disturbance, motor disturbances
The vibration of generation, the not contact and friction of key part, substantially increases the service life that spacecraft effectively works, reduces
Economic cost improves the reliability of spacecraft.
2, a kind of fluid-type reaction device disclosed by the invention, electromagnetism and conservation of angular momentum theory are combined, at
Function is applied to Spacecraft Attitude Control field, carries thermal control system, can effectively ensure that the device in the ring of outer space harshness
It is worked normally in border.
Detailed description of the invention:
Fig. 1 is fluid-type reaction device embodiment overall structure diagram provided by the invention.
Fig. 2 is that the reaction device of fluid-type reaction device provided by the invention executing agency implements exemplary diagram.
Fig. 3 is the hollow ring structural schematic diagram of fluid-type reaction device provided by the invention.
Fig. 4 is the base construction schematic diagram of fluid-type reaction device provided by the invention.
Fig. 5 is a kind of single electrode fluid-type reaction device embodiment schematic diagram provided by the invention.
In figure: 1- mounting bracket；2- executing agency；3- control unit；4- cabinet；5- pedestal；6- hollow ring；7- is embraced
Hoop；8- permanent magnet；9- blind flange；10- electrode；11- resistance wire；12- bolt.
Specific embodiment
Objects and advantages in order to better illustrate the present invention with reference to the accompanying drawing make a specific embodiment of the invention
Further details of explanation.
Embodiment 1
A kind of fluid-type reaction device disclosed by the invention, Fig. 1 are that fluid-type reaction device provided by the invention is real
An overall structure diagram is applied, fluid-type reaction device includes mounting bracket 1, executing agency 2 and control unit 3.Execution machine
Structure 2 and control unit 3 make cabinet 4 by aluminum alloy casing, and cabinet is with used in blinds in heat dissipation.Mechanism is consolidated by four bolt machinery
Surely mounting bracket 1 is arrived.
Fig. 2 is that the reaction device of fluid-type reaction device provided by the invention executing agency implements exemplary diagram.It executes
Mechanism includes hollow ring 6, pedestal 5, electromagnetic flowmeter, flux-gate magnetometer and connection mechanical part and conducting wire.Fig. 3 is invention
The hollow ring structural schematic diagram of the fluid-type reaction device of offer.Hollow ring 6 can be made using nonmetallic materials such as ceramics
With 3D printing processing technology, annulus is interior to fill full conductive fluid.The inner side and outer side of hollow ring 6 is processed logical by the quartering
Hole, the coaxial same aperture of inside and outside side through hole, for installing positive and negative electrode, four positive electrodes are mounted on the outside of annulus, four negative electrodes
It is mounted on the inside of annulus.Positive and negative electrode contacts with fluid in hollow ring and uses thread seal and O-ring seal, or uses
The welding technique of ceramics and metal, electrode and nonmetallic circular ring are welded together.Equidistant uniform winding resistance on hollow ring 6
Silk is used for electric heating, guarantees that fluid-type reaction device is in normal working temperature, interferes from low temperature environment, installs thermometer
Real-time monitoring system temperature.Hollow ring 6 is fixed to pedestal 5 by bolt and anchor ear.Fig. 4, which is that the fluid-type of invention offer is counter, to be made
With the base construction schematic diagram of device.NS permanent magnet is placed in the central channel of pedestal 5 to be used to provide required magnetic field, uses blind flange
Closing.Ampere force is generated when fluid is powered in hollow ring, the direction of Ampere force is judged by left hand rule.
The course of work:
When spacecraft is interfered and needs gesture stability, by the momentum motor for changing fluid-type reaction device
Amount, we can absorb the extra angular momentum vector of spacecraft rest part, to achieve the purpose that Spacecraft Attitude Control.
The aggregated momentum moment vector of spacecraft, which is equal to the first derivative of time, acts on the sum of external force moment vector on spacecraft,
This is the working principle that reaction device carries out attitude stabilization to spacecraft, the i.e. moment of momentum theorem.
Spacecraft dynamics equation is
There is time t integral at formula (1) both ends
In formula (1) and formula (2), J indicates that total inertia of spacecraft, I indicate the rotary inertia of reaction device, MdIt is space flight
The interference moment of face that device is subject to, θ are the attitude misalignments generated by interference moment of face, and Ω is reaction device relative to spacecraft
Angular speed, Ω0The initial speed of reaction device when for t=0.
WhenWhen, spacecraft attitude stabilization.I.e.
Formula (3) shows that the impulsive moment for acting on spacecraft is stored into fluid-type reaction device, the device output with
MdContrary torque equal in magnitude.
So that positive and negative electrode on hollow ring is powered by control unit, is generated after fluid conductive by permanent magnet in hollow ring
Magnetic field penetration be allowed to move in hollow ring at this point, Ampere force can be generated in magnetic field and act on charged fluid.Ampere
Power is switched on the active force that conductor is subject in magnetic field.In uniform magnetic field, Ampere force size is
F=BIL sin α (4)
In formula (2), F indicates Ampere force；B is magnetic induction intensity, measures size and Orientation by flux-gate magnetometer；I is electricity
The size of stream is measured by ampere meter in control unit；L is the length of conductor, i.e. open circles endless tube interior diameter；α is indicated in conductor
The angle of current direction and magnetic induction line.
The plane that the direction of Ampere force F is formed perpendicular to energization fluid and magnetic induction line, is determined by left hand rule.Left hand is fixed
Then: stretching out left hand, keep thumb vertical with other four fingers and in a plane, magnetic induction line is allowed to penetrate from the palm of the hand, four refer to and are directed toward electricity
Direction is flowed, what thumb was directed toward is exactly ampere force direction (i.e. conductor Impact direction).
It may determine that the direction of motion of fluid according to left hand rule, current direction can be changed by control unit 3 and realized
The direction of motion of fluid realizes the positive and negative rotation of moving fluid, the posture of spacecraft is then adjusted flexibly.
Fluid-type reaction device provided by the invention measures the stream of fluid in ring using the working principle of electromagnetic flowmeter
Speed.The size of induced electromotive force is determined by Faraday's electromagnetic induction law
E=BLV (5)
E indicates that the electromotive force that fluid motion cutting magnetic induction line generates, B indicate that the magnetic induction intensity in magnetic field, L are in formula (5)
The internal diameter of hollow ring, V are the flow velocitys of fluid.
It is obtained by formula (5)
Hollow ring obtains angular speed
After the angular speed for measuring fluid by electromagnetic flowmeter, the moment of momentum of fluid can be obtained
H=J ω (6)
Rotary inertia
In formula (6) formula (7), H is the moment of momentum of fluid, and J is the rotary inertia of fluid, and m, ρ, V respectively indicate the matter of fluid
Amount, density and volume, R are distance of the annulus mass center to the ring cross-section center of circle, and r is the radius of ring cross-section circle.
Formula (7) substitution formula (6) is had
H is exactly the moment of momentum caused by charged fluid in formula (8), anti-by spacecraft and the fluid-type in spacecraft
Momentum-exchange between acting device controls the posture of spacecraft.
Embodiment 2
Fig. 5 is one other fluid formula reaction device embodiment schematic diagram provided by the invention.The difference of the device
It is to contact only with a secondary positive and negative electrode with fluid, and NS permanent magnet is located at the surface and just of pipeline and electrode
Lower section.By formula (4) it is found that magnetic induction line generates at this time perpendicular to current direction when permanent magnet is located at electrode or more two sides
Ampere force is maximum value.Reduce the open amount on hollow ring in this way, improves fluency and the sealing of confined space
Grade reduces the friction of fluid and circle ring inner wall.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (7)
1. a kind of fluid-type reaction device, it is characterised in that: include: executing agency, control unit and cabinet；Executing agency and
Control unit is placed in cabinet；Heat release hole is provided on the case box；Described control unit effect, for handling each sensor
The direction of current loop and size in measurement data and feedback control executing agency, including hollow ring positive and negative electrode, electric heating
System and each detection device；
Executing agency includes: hollow ring, pedestal, permanent magnet, resistance wire and electrode；
The pedestal is for placing hollow ring；Permanent magnet is installed on the base, at upper cover or pedestal and upper cover；Then pass through
Upper cover realizes that sealing is fixed；Full conductive fluid is filled in the hollow ring；It is processed in the inner side and outer side of the hollow ring
Through-hole out, the coaxial same aperture of inside and outside side through hole, for installing positive and negative electrode；The positive and negative electrode is contacted with fluid；Resistance wire twines
It is wound on hollow ring, electric heating is used for, to guarantee that fluid-type reaction device is in normal working temperature, from low temperature environment
Interference；Thermometer is installed, so as to real-time monitoring device temperature on hollow ring；Ampere is generated when fluid is powered in hollow ring
The direction of power, Ampere force is judged by left hand rule.
2. a kind of fluid-type reaction device as described in claim 1, it is characterised in that: further include mounting bracket, fluid-type
Reaction device is fixed on the mounting bracket.
3. a kind of fluid-type reaction device as described in claim 1, it is characterised in that: the pedestal is cannular boss knot
Structure, permanent magnet are placed in boss hollow space, and hollow ring is fixed on outside the boss, then realize that sealing is fixed by upper cover.
4. a kind of fluid-type reaction device as described in claim 1, it is characterised in that: the pedestal is with groove structure
For placing the pole N or the pole S permanent magnet；Hollow ring is fixed on the base, then realizes that sealing is fixed by upper cover.
5. a kind of fluid-type reaction device as described in claim 1, it is characterised in that: the conductive fluid includes mercury, crystalline substance
Body liquid metal or other conductive fluid media.
6. a kind of fluid-type reaction device as described in claim 1, it is characterised in that: the hollow ring is using ceramics etc.
Nonmetallic materials；The material of the cabinet is aluminium alloy.
7. a kind of fluid-type reaction device as described in claim 1, it is characterised in that: the positive and negative electrode and hollow ring
Interior fluid contacts and uses thread seal and O-ring seal, or using the welding technique of ceramics and metal, by electrode and non-gold
Belong to annulus to weld together.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910380728.4A CN110104220B (en) | 2019-05-08 | 2019-05-08 | Fluid type reaction device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910380728.4A CN110104220B (en) | 2019-05-08 | 2019-05-08 | Fluid type reaction device |
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| Publication Number | Publication Date |
|---|---|
| CN110104220A true CN110104220A (en) | 2019-08-09 |
| CN110104220B CN110104220B (en) | 2021-04-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910380728.4A Active CN110104220B (en) | 2019-05-08 | 2019-05-08 | Fluid type reaction device |
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| Country | Link |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110435932A (en) * | 2019-08-12 | 2019-11-12 | 北京控制工程研究所 | A kind of magnetic fluid flywheel for spacecraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4732353A (en) * | 1985-11-07 | 1988-03-22 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Three axis attitude control system |
| JPS6483497A (en) * | 1987-09-24 | 1989-03-29 | Nec Corp | Nutation damper |
| CN1766647A (en) * | 2004-09-23 | 2006-05-03 | 伊纳拉伯斯技术公司 | Magnetofluidic accelerometer with partial filling of cavity with magnetic fluid |
| CN101633411A (en) * | 2009-08-24 | 2010-01-27 | 哈尔滨工业大学 | Actuating mechanism of spacecraft for integrating heat control and liquid momentum wheel |
| CN104483972A (en) * | 2014-10-31 | 2015-04-01 | 上海新跃仪表厂 | Spacecraft fluid ring reaction performing mechanism |
| CN109525092A (en) * | 2018-11-27 | 2019-03-26 | 上海交通大学 | SYMMETRIC ELECTROMAGNETIC structure based on magnetohydrodynamics satellite gravity anomaly executing agency |
-
2019
- 2019-05-08 CN CN201910380728.4A patent/CN110104220B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4732353A (en) * | 1985-11-07 | 1988-03-22 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Three axis attitude control system |
| JPS6483497A (en) * | 1987-09-24 | 1989-03-29 | Nec Corp | Nutation damper |
| CN1766647A (en) * | 2004-09-23 | 2006-05-03 | 伊纳拉伯斯技术公司 | Magnetofluidic accelerometer with partial filling of cavity with magnetic fluid |
| CN101633411A (en) * | 2009-08-24 | 2010-01-27 | 哈尔滨工业大学 | Actuating mechanism of spacecraft for integrating heat control and liquid momentum wheel |
| CN104483972A (en) * | 2014-10-31 | 2015-04-01 | 上海新跃仪表厂 | Spacecraft fluid ring reaction performing mechanism |
| CN109525092A (en) * | 2018-11-27 | 2019-03-26 | 上海交通大学 | SYMMETRIC ELECTROMAGNETIC structure based on magnetohydrodynamics satellite gravity anomaly executing agency |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110435932A (en) * | 2019-08-12 | 2019-11-12 | 北京控制工程研究所 | A kind of magnetic fluid flywheel for spacecraft |
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| CN110104220B (en) | 2021-04-23 |
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