CN103674591B - Satellite dynamic angle adjusting mechanism in low-temperature vacuum environment - Google Patents
Satellite dynamic angle adjusting mechanism in low-temperature vacuum environment Download PDFInfo
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- CN103674591B CN103674591B CN201310560100.5A CN201310560100A CN103674591B CN 103674591 B CN103674591 B CN 103674591B CN 201310560100 A CN201310560100 A CN 201310560100A CN 103674591 B CN103674591 B CN 103674591B
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- square frame
- rood beam
- satellite
- spiral lift
- axle
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Abstract
The invention relates to a satellite dynamic angle adjusting mechanism in a low-temperature vacuum environment. The mechanism contains a satellite coupling square frame and a crossbeam positioned below the coupling square frame. A bracket vehicle used for supporting is arranged below the crossbeam. The coupling square frame is connected to the crossbeam through rotating shafts at two ends of the square frame and a spiral elevator. Lifting motion of a lead screw of the spiral elevator drives the coupling square frame to rotate along the axis. The crossbeam is connected to the bracket vehicle through a rotating shaft positioned on a short arm and a spiral elevator positioned at one side of the rotating shaft. Elevation angle of the coupling square frame is realized when the spiral elevator pushes a long arm of the crossbeam. Angle adjustment of a satellite in two directions is realized, mutual interference during motions in the two directions is eliminated, and an adaptive design is performed in allusion to the vacuum low-temperature operating environment so as to make the mechanism meet the requirement of being used in vacuum at low temperature.
Description
Technical field
The invention belongs to the heat test technical field of low-temperature vacuum environment, in particular it relates to a kind of satellite is true
Empty heat test special tooling, more particularly to a kind of satellite dynamic camber adjustment mechanism being exclusively used in low-temperature vacuum environment.
Background technology
The satellite dynamic camber adjustment mechanism being exclusively used in low-temperature vacuum environment, is satellite vacuum thermal test special tooling.
It is arranged in middle-size and small-size space simulator, is worked under the low-temperature vacuum environment during satellite vacuum thermal test, is used
The angle with pitching is rolled in dynamic adjustment satellite.Survey of deep space series of satellites, the especially space flight for the purpose of walking of landing
Device, after landing, spacecraft can experience the various workings such as static, walking, climbing, under every kind of operating mode, spacecraft on celestial body surface
The thermal control loop of itself is affected difference by gravity.In ground level heat process of the test, need to spacecraft under various working
The working environment in thermal control loop is simulated.
In ground level heat process of the test, by making the angle that satellite is rolled or pitching is certain, heat pipe is set to be under certain angle
Work, come analog satellite thermal control loop is affected by celestial body gravity, in ground level heat process of the test, needs to be adjusted according to different operating modes
The inclination angle of rolling or the pitching of whole satellite, it is therefore desirable to it is a set of can be during satellite heat test, vacuum low-temperature environment
Lower on-line tuning satellite rolls the governor motion with luffing angle.
Existing satellite heat test frock is based on static support, it is ensured that stability of the satellite during heat test, no
The demand of online real-time adjustment satellite rolling and luffing angle can be met.
The content of the invention
It is an object of the invention to provide a kind of mechanism for regulating satellite dynamic horizontal degree in low-temperature vacuum environment, realizes
To satellite inclination angle degree real-time regulation in Satellite Experiment.
The purpose of the present invention can be completed by technical scheme below：
A kind of satellite dynamic inclination governor motion in low-temperature vacuum environment, including docking square frame, spiral lift
First, rood beam, spiral lift two and stent car, dock the bearing block that square frame is arranged on rood beam centrally through setting axle
On, bearing block is arranged on the long-armed two ends of rood beam, and spiral lift one is arranged on rood beam galianconism, positioned at docking square frame axle
The side of line, the upper end of spiral lift one is fixed in the chute below docking square frame using cylinder bolt axle, rood beam with
Stent car connected mode is identical with docking square frame and rood beam, and it is in " ten " font that the rood beam is whole beam, by cross
The galianconism two ends of beam arrange axle, and long-armed upper two ends arrange bearing block, assemble with the axle for docking square frame two ends, the galianconism two of rood beam
The axle at end coordinates with the bearing block on stent car, and chute is fixed with below the long-armed one end of rood beam, and chute is propped up with being installed on
Spiral lift two connects in unwheeling, by the stretching motion of spiral lift leading screw, realizes the angle of rood beam and docking square frame
Degree adjustment.
Wherein, the docking square frame is the rectangular frame being welded with bar section of stainless steel, framework upper surface be designed with
The perforate of satellites coupling, at the two ends of framework axle is provided with, on the same axis, this axis and the long-armed diameter parallel of rood beam.
Chute is being fixed with below one lateral edges of docking, the straight pin at the top of spiral upgrading machine one can do a spacing in chute
From slip.
The rood beam is the overall beam assembly in " ten " word-lifting formula, is divided into long-armed and galianconism, sets at the two ends of galianconism
Axle is equipped with, is connected with stent car by axle sleeve；Long-armed two ends are provided with bearing block, by axle sleeve and the two ends for docking square frame
Axle connects, and the rotation to docking square frame plays a supportive role.On the galianconism of rood beam side, the peace of spiral lift two is provided with
Dress hole, hole position is corresponding with the chute of docking square frame bottom.
The spiral lift is that have stepper motor driven spiral lifting mechanism, drives worm screw to rotate by motor, Jing
The elevating movement that spiral lift is converted into leading screw is crossed, in the joint that the top of leading screw is a bolt-type, is inserted using column type
Pin is fixed in chute.The base of spiral lift one uses bolt connection with supporting construction.
The stent car, is welded by bar section of stainless steel, and in the both sides of stent car bearing block is provided with, bearing block with
The galianconism end axle of rood beam coordinates；The installation of spiral lift one is provided with corresponding stent car under the long-armed chute of rood beam
Hole, is fixed on the bolt-type joint at the top of upgrading machine in the chute of the long-armed lower section of rood beam using straight pin.Stent car bottom
4 wheels are provided with, guide rail that can be in container is rolled, realize the turnover container of this upset frock.
Wherein, the docking square frame is designed with heat insulation with satellite junction；
Wherein, heating plate and thermometric thermocouple are posted in the elevator and motor outside, during satellite heat test
Using temperature control measures.
Wherein, whole support coats multilayer insulation component during heat test, reduces thermal test support itself to defending
The heat affecting of star.
The beneficial effects of the present invention is：
A. by the framework using a rood beam, the angular adjustment of the orthogonal both direction of satellite is separated, with rood beam
An arm be axle, drive another arm to move up and down using spiral lift, rood beam and framework above is rotated along axle, it is real
Show the angle adjustment of the direction and do not affect another direction.The angle in another direction can be adjusted using same method,
The angle of both direction can also simultaneously be adjusted.The design of rood beam is solved in process of the test of satellite under different operating modes
The demand of the angle adjustment of both direction.
B. by the way that using chute-type connected mode, in the case where corner requirement is met, structure is simpler, reduce and rotate secondary
Design, reducing mechanism is because deforming the probability for causing mechanism blockage under low temperature environment.
C. using spiral lift drive rood beam rotate, spiral lift itself with it is stable, with self-locking energy
Power, can reduce impact when satellite is rotated, and ensure that satellite to turn over that remain after certain angle the angle constant.Pass through
The stroke of increase spiral lift, it is possible to achieve the rotation of satellite wide-angle.Motor motion is accurate, convenient accurate to angle
Control.
D. temperature control measures are adopted, prevents drive mechanism low-temperature deformation from causing stuck.Paste in motor and elevator outer surface
Heating plate and temperature thermocouple, outside cladding multilayer insulation component, carry out temperature control, it is ensured that motor and liter in process of the test to mechanism
Drop machine is operated under rated temperature.
E. foreign material component assembly is adopted in kinematic pair, prevents same material from producing under vacuum low-temperature environment cold
Weldering.
Compared with prior art, it is of the invention for the satellite dynamic inclination governor motion in low-temperature vacuum environment, success
Solve the impact of low temperature, vacuum environment to mechanism kinematic；Solve kinematic accuracy and motion self-locking and be accurately positioned and want
Problem between asking；Solve the problems, such as that mechanism, to the issuable electromagnetism of Satellite Experiment environment, heat and chemical contamination, reaches comprehensively
The use requirement of satellite environment test.
Description of the drawings
Figure 1A is the upper strata schematic diagram of four-point supporting hue angle mode, and wherein interface frame, mating frame point is rotated around B-D axles and adjusted.
Figure 1B is lower floor's schematic diagram of four-point supporting hue angle mode, and the wherein strong point of B, D two is rotated around A-C axles and adjusted.
Fig. 2 is the front view of the low-temperature vacuum environment Satellite incidence regulating mechanism of the present invention.
Fig. 3 is the side view of the satellite inclination governor motion in the low-temperature vacuum environment of the present invention.
Fig. 4 is the shaft end installation diagram in the satellite inclination governor motion in the low-temperature vacuum environment of the present invention.
Fig. 5 is the chute installation diagram in the satellite inclination governor motion in the low-temperature vacuum environment of the present invention.
Wherein, 1 is stent car；2 is spiral lift one；3 is rood beam；4 are docking square frame；5 is spiral lift two；
6 is axle sleeve；7 is spiral lift bolt-type joint；8 is latch；9 is chute；10 is fastening bolt；11 is nut；12 is to open
Mouth pin；13 is temperature thermocouple；14 is temperature control heating piece.
Specific embodiment
Introduced below is the specific embodiment as content of the present invention, below by specific embodiment to this
The content of invention is further illustrated.Certainly, it is only the not Tongfang for showing 0 present invention to describe following detailed description
The content in face, and should not be construed as limiting the invention scope.
With reference to the angle adjustment schematic diagram in Figure 1A and Figure 1B, Figure 1A being upper strata docking square frame, to dock the axis for putting frame 4
Centered on line O1, O1 axles are long-armed parallel with rood beam, and spiral lift is located on the galianconism of rood beam.When spiral lift height
Degree from e1 to e2 change when, dock square frame 4 turn over angle △ 1 along axle o1；Figure 1B be with the short axle of rood beam 3 as fulcrum,
When the height of spiral lift 1 is when e1 changes to e2, docking square frame 4 and the long-armed of rood beam 3 turn over an angle along axle o2
Degree △ 2, realizes upper angle adjustment of the satellite in another direction.Its axis o1 is mutually perpendicular to axle o2, and satellite is along two axles
It is non-interference in rotation process, angle interference problem when solving both direction adjustment angle.
With reference to Fig. 3 and Fig. 4, the tilt adjustment structure of satellite mainly includes docking square frame 4, spiral liter under vacuum low-temperature environment
Drop machine 1 and spiral lift 25, rood beam 3, stent car 1, docking square frame 4 has bar section of stainless steel to be welded, and docks square frame
On be designed with structure with satellites coupling as needed, the Center at the two ends of docking square frame has projecting shaft, and projecting shaft leads to
Cross axle sleeve 6 to coordinate with the bearing block being arranged on rood beam 3, bearing block adopts stainless steel material, axle sleeve to adopt H62 materials, axle
Set ensures in 0.5mm or so with bearing block gap, prevents because shrinkage deformation causes " stuck " phenomenon under material at low temperature, in docking side
Frame side envisaged underneath has chute 9, and chute 9 is fixed using bolt 10 and nut 11 with square frame is docked, and spiral lift 25 is installed
On the galianconism of rood beam 3, when spiral lift 25 works, the traction lower edge axle for docking square frame in elevator is rotated, elevator
The latch 8 at top can slide in chute 9, meet the displacement demand that elevator latch 8 is produced because of angle change.Latch 8 makes
On the bolt-type joint 7 being fixed at the top of spiral lifting with split pin 12.
With reference to Fig. 2 and Fig. 3, projecting shaft is designed as at the galianconism two ends of rood beam 3, axle is by axle sleeve 6 and stent car 1
Bearing block is assembled, and material, axle sleeve is H62, and axle sleeve is 0.5mm with the gap of bearing block, is prevented stuck caused by low-temperature deformation
Phenomenon, foreign material avoids the appearance of vacuum cold welding phenomenon.The long-armed envisaged underneath of rood beam 3 has chute, and chute uses bolt
Fixed, spiral lift 1 is fixed on stent car 1, and the top latch 8 of spiral lift 1 is with the connected mode of chute 9 ibid.
Spiral lift 1 and spiral lift 25 adopt the leading screw of step motor drive, spiral lift one to have certainly
Lock ability, ensure that satellite turns over and be maintained at certain angle.Spiral lift 1 and spiral lift 25 and stepping electricity
Machine all can under vacuum conditions have extremely low volatile lubricant grease to substitute common lubricant grease using a kind of, together
When, on the surface of spiral lift and motor by patch heating plate 14 and temperature thermocouple 13, outer layer coats again multilayer insulation group
The mode of part carries out temperature control, it is ensured that spiral lift and motor can be in normal works under vacuum low-temperature environment.
Whole support all winds heating tape, external sheath multilayer insulation during heat test on non-movable member surface
Component, in process of the test, makes test bracket be generally held under normal temperature state by temperature control, reduces test bracket because temperature becomes
Change the deformation for producing, it is ensured that support can be moved normally.
Brand-new technical scheme is present invention employs, two dimension angular can during vacuum thermal test to be successfully realized satellite
Adjust, employ simple and reliable version, while demand under meeting vacuum low-temperature environment, reduce answering for later maintenance
Miscellaneous degree.
This programme is that both direction maximum adjustment angle is ± 5 °, and working environment is vacuum for the design of CE-3 rovers
Spend for 1 × 10-4Pa, temperature is 100K, and during first sample heat test, repeatedly adjustment rover rolls the angle with pitching, it
Afterwards after considerably long one section of storage period, through simple-to-maintain, during the positive sample heat test of rover is applied to again, realizes and patrol
The adjustment of the multiple angle of visual organ.Mechanism is that the real-time inclination angle of the satellite being exclusively used under vacuum low-temperature environment that the country develops first is adjusted
Section mechanism.And with higher reliability.With the development to survey of deep space, the adjustment angle during vacuum thermal test is needed
Satellite it is more and more, this technology is transplanted in new heat test frock, it has a extensive future.
Although above the specific embodiment of the present invention being described in detail and being illustrated, it should be noted that
We can make various changes and modifications to above-mentioned embodiment, but these are without departure from the spirit and appended power of the present invention
Profit requires described scope.
Claims (9)
1. a kind of satellite dynamic inclination governor motion in low-temperature vacuum environment, including docking square frame, spiral lift one,
Rood beam, spiral lift two and stent car, dock square frame and are arranged on the bearing block on rood beam centrally through setting axle, axle
Bearing is arranged on the long-armed two ends of rood beam, and spiral lift one is arranged on rood beam galianconism, positioned at docking square frame axis
Side, the upper end of spiral lift one is fixed in the chute below docking square frame using cylinder bolt axle, rood beam and support
Car connected mode is identical with docking square frame and rood beam, and it is in " ten " font that the rood beam is whole beam, by rood beam
Galianconism two ends arrange axle, and long-armed upper two ends arrange bearing block, assemble with the axle for docking square frame two ends, the galianconism two ends of rood beam
Bearing block on axle and stent car coordinates, and is fixed with chute below the long-armed one end of rood beam, chute be installed on stent car
Upper spiral lift two connects, and by the stretching motion of the leading screw of spiral lift one, realizes the angle of rood beam and docking square frame
Adjustment；On the galianconism of rood beam, the installing hole of spiral lift one, hole position and the chute pair for docking square frame bottom are provided with
Should.
2. satellite dynamic inclination governor motion as claimed in claim 1, wherein, the docking square frame is with bar section of stainless steel weldering
The rectangular frame for connecing, framework upper surface is provided with the perforate with satellites coupling, and the two ends of framework are provided with axle, axis with
The long-armed diameter parallel of rood beam.
3. satellite dynamic inclination governor motion as claimed in claim 2, wherein, positioned at the lower section of the docking lateral edges of square frame one
Chute is fixed with, the straight pin at the top of spiral lift one does the slip of certain distance in chute.
4. satellite dynamic inclination governor motion as claimed in claim 2, wherein, the rood beam sets for overall in " ten " font
The beam assembly of meter, is divided into long-armed and galianconism, and the two ends of galianconism are provided with axle, is connected with stent car by axle sleeve；Long-armed two
End is provided with bearing block, is connected with the axle at the two ends of docking square frame by axle sleeve, and the rotation to docking square frame plays a supportive role.
5. satellite dynamic inclination governor motion as claimed in claim 4, wherein, the spiral lift one is by motor
The spiral lifting mechanism of driving, drives worm screw to rotate by motor, and through spiral lift the elevating movement of leading screw is converted into,
The top of leading screw is the joint of a bolt-type, is fixed in chute using column type latch, and spiral lift one is tied with supporting
Structure uses bolt connection.
6. satellite dynamic inclination governor motion as claimed in claim 4, wherein, the stent car welded by bar section of stainless steel and
Into, bearing block is installed in the both sides of stent car, bearing block coordinates with the galianconism end axle of rood beam；Under the long-armed chute of rood beam
The installing hole of spiral lift one is provided with corresponding stent car, is connect the bolt-type at the top of spiral lift using straight pin
Head is fixed in the chute of the long-armed lower section of rood beam.
7. satellite dynamic inclination governor motion as claimed in claim 4, wherein, stent car bottom is provided with 4 wheels, described
Docking square frame is provided with heat insulation with satellite junction.
8. satellite dynamic inclination governor motion as claimed in claim 4, wherein, the spiral lift one and motor outside are
Heating plate and thermometric thermocouple are posted, temperature control measures are adopted during satellite heat test.
9. satellite dynamic inclination governor motion as claimed in claim 4, wherein, whole support is coated during heat test
Multilayer insulation component.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310560100.5A CN103674591B (en) | 2013-11-12 | 2013-11-12 | Satellite dynamic angle adjusting mechanism in low-temperature vacuum environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310560100.5A CN103674591B (en) | 2013-11-12 | 2013-11-12 | Satellite dynamic angle adjusting mechanism in low-temperature vacuum environment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103674591A CN103674591A (en) | 2014-03-26 |
| CN103674591B true CN103674591B (en) | 2017-05-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310560100.5A Expired - Fee Related CN103674591B (en) | 2013-11-12 | 2013-11-12 | Satellite dynamic angle adjusting mechanism in low-temperature vacuum environment |
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| CN (1) | CN103674591B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110751891B (en) * | 2019-11-08 | 2020-07-07 | 深圳翔成电子科技有限公司 | Satellite operation simulation device |
| CN111623956B (en) * | 2020-03-23 | 2021-12-07 | 北京空间机电研究所 | Triaxial angle adjustment frock |
| CN112122916B (en) * | 2020-09-07 | 2022-02-01 | 蓝箭航天空间科技股份有限公司 | Driving device for rocket assembly |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201149551Y (en) * | 2007-12-04 | 2008-11-12 | 北京卫星环境工程研究所 | Mechanism for regulating satellite dynamic horizontal degree for low temperature vacuum surroundings |
| CN102075117A (en) * | 2010-12-31 | 2011-05-25 | 刘建中 | Sunlight-tracking double-shaft device and control method thereof |
| WO2013056894A1 (en) * | 2011-10-21 | 2013-04-25 | Skf B.V. | Toe angle adjustor |
| CN102968125A (en) * | 2012-11-06 | 2013-03-13 | 刘建中 | Sunlight dual-shaft tracking support |
| CN203103512U (en) * | 2013-02-04 | 2013-07-31 | 四川九洲空管科技有限责任公司 | Miniature wide-angle pitching adjusting locking device for secondary radar antenna |
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- 2013-11-12 CN CN201310560100.5A patent/CN103674591B/en not_active Expired - Fee Related
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| CN103674591A (en) | 2014-03-26 |
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