CN104536113A - High-specific stiffness supporting structure of space optical remote sensor - Google Patents
High-specific stiffness supporting structure of space optical remote sensor Download PDFInfo
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- CN104536113A CN104536113A CN201410840011.0A CN201410840011A CN104536113A CN 104536113 A CN104536113 A CN 104536113A CN 201410840011 A CN201410840011 A CN 201410840011A CN 104536113 A CN104536113 A CN 104536113A
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- carbon fiber
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- remote sensor
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B7/00—Mountings, adjusting means, or light-tight connections, for optical elements
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B7/00—Mountings, adjusting means, or light-tight connections, for optical elements
- G02B7/18—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors
- G02B7/182—Mountings, adjusting means, or light-tight connections, for optical elements for prisms; for mirrors for mirrors
Abstract
The invention discloses a high-specific stiffness supporting structure of a space optical remote sensor, and belongs to the technical field of space optics. The supporting structure solves the problems that in the prior art, a supporting structure of the space optical remote sensor is heavy, poor in stability and low in inherent frequency. The supporting structure comprises a carbon fiber front cylinder, a carbon fiber rear cylinder, a secondary mirror embedded part, a carbon fiber secondary mirror support, a carbon fiber supporting ring, a plurality of supporting ring embedded parts, truss rod connectors, a plurality of carbon fiber truss rods, truss embedded parts, a carbon fiber matrix, primary mirror assembly embedded parts, a three-mirror embedded part and a carbon fiber rear cover. The carbon fiber front cylinder is connected to the carbon fiber rear cylinder, the secondary mirror embedded part adheres to the middle of the carbon fiber secondary mirror support, the supporting ring embedded parts are circumferentially and uniformly distributed on the carbon fiber supporting ring, the front ends of the carbon fiber truss rods are connected to the back surface of the carbon fiber supporting ring, the rear ends of the carbon fiber truss rods are connected to the truss embedded parts of a main backboard assembly, and the carbon fiber rear cover, the truss assembly embedded parts, the three-mirror assembly embedded part and the primary mirror assembly embedded parts are connected to the carbon fiber matrix.
Description
Technical field
The invention belongs to space optics technical field, be specifically related to a kind of high specific stiffness space optical remote sensor supporting construction.
Background technology
Space optical remote sensor is widely used in multiple field such as earth resources detailed survey and generaI investigation, topographic mapping, ocean research, urban construction, agricultural development, weather forecast, military surveillance.Space optical remote sensor, at ground development, test and launching phase, can be subjected to the test of the extraneous load such as multiple vibration, impact and noise and environmental baseline.Wherein, dynamics environment having the greatest impact to remote sensor.The dynamics load that remote sensor is subject to mainly be included in debug with test, ground transport, fairing of launch vehicle are separated, rocket propulsion cabin and carry the Flight Vehicle Stage Separation of camera, Flight Vehicle Structure launches the accidental impact that pose adjustment etc. brings, quick-fried de-impact, transient state and steady-state vibration, vibration, rocket and lifts up and shake and vibration etc. that large-scale flexible deployable structure causes.If the rigidity of remote sensor can cause great space flight accident not.
With the PhD dissertation that the immediate prior art of the present invention is Changchun Institute of Optics, Fine Mechanics and Physics, CAS Li Wei, the Space Remote Sensors structure in this paper has been applied to certain High Resolution Space Camera scientific research project.This Space Remote Sensors supporting construction comprises placket, secondary mirror support bar, connecting cylinder, camera support, cone cylinder and rear cylinder; Placket is connected to the front of connecting cylinder, connecting cylinder secondary mirror support bar, and camera support is connected with connecting cylinder, and cone cylinder is connected on connecting cylinder, and rear cylinder is connected on cone cylinder; The installation base surface of camera support is connected with aircraft.Placket is used for the light limited beyond visual field and enters optical system, and connecting cylinder is mainly used to support secondary mirror support bar, and connecting cylinder ensures the stability of relative position relation between the position of secondary mirror in optical system and primary and secondary mirror by the connection of camera support; Cone cylinder is the main support structure of remote sensor, and rear cylinder is used for the assemblies such as support the 3rd catoptron, and camera support is connected with cone cylinder and connecting cylinder respectively, realizes the support to whole remote sensor.
Because this remote sensor agent structure adopts metal material in a large number, although through height light-weight design, remote sensor overall weight is still higher, and stability is general, and natural frequency is low.
Summary of the invention
The object of this invention is to provide a kind of high specific stiffness space optical remote sensor supporting construction, solve the technical matters that prior art space optical remote sensor supporting construction weight is high, stability is general and natural frequency is low.
A kind of high specific stiffness space optical remote sensor of the present invention supporting construction comprises outer light shield group, component truss and eutergum assembly;
Outer light shield assembly comprises cylinder after carbon fiber placket and carbon fiber, and carbon fiber placket to be connected by screw after carbon fiber on cylinder;
Component truss comprises secondary mirror built-in fitting, carbon fiber time mirror support, carbon fiber sustained ring, multiple sustained ring built-in fitting, many carbon fiber truss rods and multiple truss rod joint; Secondary mirror built-in fitting is pasted onto the middle part of carbon fiber time mirror support, secondary mirror support is connected by screw on sustained ring built-in fitting, multiple sustained ring built-in fitting circumference uniform distribution is on carbon fiber sustained ring, every two adjacent carbons fiber truss rods share a truss rod joint, and carbon fiber truss rod front end is connected to the back side of carbon fiber sustained ring by truss rod joint;
Back board module comprises multiple truss built-in fitting, carbon fiber substrate, multiple primary mirror group built-in fitting, three mirror built-in fittings and carbon fiber bonnet; After carbon fiber, cylinder is connected by screw in carbon fiber substrate, carbon fiber bonnet is connected by screw in carbon fiber substrate, multiple truss built-in fitting circumference uniform distribution is in carbon fiber substrate, the rear end of carbon fiber truss rod is connected on truss built-in fitting by truss rod joint, every two adjacent carbons fiber truss rods share a truss rod joint, three mirror assembly built-in fittings are fixedly connected in carbon fiber substrate by glue and screw, and multiple primary mirror assembly built-in fitting is fixedly connected in carbon fiber substrate by glue and screw.
Described multiple sustained ring built-in fitting is 3.
Described many carbon fiber truss rods are 6.
Described multiple truss built-in fitting is 3.
Described multiple truss rod joint is 6.
Advantageous Effects of the present invention: the present invention adopts triangle secondary mirror supporting structure, utilizes leg-of-mutton stability, thus ensures the stability of this supporting construction; Adopt truss-like secondary mirror supporting structure, effectively make use of material and bear the ability of Tensile or Compressive Loading much larger than the characteristic of bearing bending load, the rigidity of this supporting construction is improved greatly; Material of main part of the present invention is carbon fibre composite, this material has the advantage of high specific strength, high specific stiffness, electrical isolation or electric conductivity, shock resistance, high damping characteristic, zero thermal expansion coefficient or negative thermal expansion coefficient, dimensional stability and antifatigue, thus ensure that supporting construction of the present invention has the advantage that weight is low, rigidity is high and stability is high.
Accompanying drawing explanation
Fig. 1 is the three-dimensional view of a kind of high specific stiffness space optical remote sensor of the present invention supporting construction;
Fig. 2 is the front view of a kind of high specific stiffness space optical remote sensor of the present invention supporting construction;
Fig. 3 is the left view of a kind of high specific stiffness space optical remote sensor of the present invention supporting construction;
Wherein, 1, carbon fiber placket, 2, sustained ring built-in fitting, 3, truss rod joint, 4, carbon fiber truss rod, 5, cylinder after carbon fiber, 6, truss built-in fitting, 7, carbon fiber substrate, 8, three mirror assembly built-in fittings, 9, carbon fiber bonnet, 10, carbon fiber sustained ring, 11, primary mirror assembly built-in fitting, 12, secondary mirror built-in fitting, 13, carbon fiber time mirror support.
Embodiment
Below in conjunction with accompanying drawing, the present invention is further elaborated.
See accompanying drawing 1, accompanying drawing 2 and accompanying drawing 3, a kind of high specific stiffness space optical remote sensor of the present invention supporting construction comprises outer light shield group, component truss and eutergum assembly;
Outer light shield assembly comprises cylinder 5 after carbon fiber placket 1 and carbon fiber, and carbon fiber placket 1 to be connected by screw after carbon fiber on cylinder 5;
Component truss comprises secondary mirror built-in fitting 12, carbon fiber time mirror support 13, carbon fiber sustained ring 10, multiple sustained ring built-in fitting 2, multiple truss rod joint 3 and Duo Gen carbon fiber truss rod 4; Secondary mirror built-in fitting 12 is pasted onto the middle part of carbon fiber time mirror support 13, secondary mirror support 13 is connected by screw on sustained ring built-in fitting 2, multiple sustained ring built-in fitting 2 circumference uniform distribution is on carbon fiber sustained ring, every two adjacent carbons fiber truss rods 4 share a truss rod joint 3, and carbon fiber truss rod 4 front end is connected to the back side of carbon fiber sustained ring by truss rod joint 3;
Back board module comprises multiple truss built-in fitting 6, carbon fiber substrate 7, multiple primary mirror group built-in fitting 11, three mirror assembly built-in fitting 8 and carbon fiber bonnet 9; Carbon fiber bonnet 9 is connected by screw in carbon fiber substrate 7, multiple truss built-in fitting 6 circumference uniform distribution is in carbon fiber substrate 7, the rear end of carbon fiber truss rod 4 is connected on the truss built-in fitting 6 of eutergum assembly by truss rod joint 3, every two adjacent carbons fiber truss rods 4 share a truss rod joint 3, three mirror assembly built-in fittings 8 are connected by screw in carbon fiber substrate 7, and multiple primary mirror assembly built-in fitting 11 is connected by screw in carbon fiber substrate 7.
Described multiple sustained ring built-in fitting 2 is 3.
Described many carbon fiber truss rods 4 are 6.
Described multiple truss built-in fitting 6 is 3.
Described multiple truss rod joint 3 is 6.
For guaranteeing that secondary mirror built-in fitting 12 end face in component truss and truss end surface are less than or equal to 0.01mm, truss rod joint 3 end face that secondary mirror built-in fitting 12 end face in lappingout component truss and component truss are connected with eutergum assembly, for guaranteeing that the coplane degree of 3 primary mirror assemblies is less than or equal to 0.005mm, on three truss built-in fittings 6, the coplane degree of lower surface is less than or equal to 0.005mm, and on three truss built-in fittings 6, the depth of parallelism of lower surface and primary mirror assembly built-in fitting 11 end face is less than or equal to 0.01mm, the end face plane degree of three mirror assembly built-in fittings 8 is less than or equal to 0.003mm, the end face of three mirror assembly built-in fittings 8 and the verticality of primary mirror assembly built-in fitting 11 end face are less than or equal to 0.01mm, truss built-in fitting 6 upper and lower end face in lappingout eutergum assembly, primary mirror assembly built-in fitting 11 end face, three mirror assembly built-in fitting 8 end faces,
The physical dimension of supporting construction of the present invention is Ф 870mm × 1540mm, and weight is 38kg, and the natural frequency of supporting construction is more than 120Hz.
Component truss adopts 6 carbon fiber truss rods 4, adjacent two truss rods and eutergum and support ring form triangle, make use of triangle stability principle, be conducive to integrally-built stability, remote sensor adopts leg-of-mutton eutergum, reduce eutergum size and quality, leg-of-mutton eutergum is the installation base plate of whole remote sensor, comprises carbon fiber substrate 7 and titanium alloy built-in fitting; Carbon fiber substrate 7 plays main load effect, and during eutergum global formation, metal embedded part reinforcement is embedded in carbon fiber substrate 7, has both improve the rigidity that reliability in turn ensure that eutergum assembly.
Claims (5)
1. a high specific stiffness space optical remote sensor supporting construction, is characterized in that, comprises outer light shield group, component truss and eutergum assembly;
Outer light shield assembly comprises cylinder (5) after carbon fiber placket (1) and carbon fiber, and carbon fiber placket (1) to be connected by screw after carbon fiber on cylinder (5);
Component truss comprises secondary mirror built-in fitting (12), carbon fiber time mirror support (13), carbon fiber sustained ring (10), multiple sustained ring built-in fitting (2), multiple truss rod joint (3), many carbon fiber truss rods (4); Secondary mirror built-in fitting (12) is pasted onto the middle part of carbon fiber time mirror support (13), secondary mirror support (13) is connected by screw on sustained ring built-in fitting (2), multiple sustained ring built-in fitting (2) circumference uniform distribution is on carbon fiber sustained ring, every two adjacent carbons fiber truss rods (4) share a truss rod joint (3), and carbon fiber truss rod (4) front end is connected to the back side of carbon fiber sustained ring by truss rod joint (3);
Back board module comprises multiple truss built-in fitting (6), carbon fiber substrate (7), multiple primary mirror group built-in fitting (11), three mirror assembly built-in fittings (8) and carbon fiber bonnet (9), carbon fiber bonnet (9) is connected by screw in carbon fiber substrate (7), carbon fiber bonnet 9 is connected by screw in carbon fiber substrate (7), multiple truss built-in fitting (6) circumference uniform distribution is in carbon fiber substrate (7), the rear end of carbon fiber truss rod (4) is connected on the truss built-in fitting (6) of eutergum assembly by truss rod joint (3), every two adjacent carbons fiber truss rods (4) share a truss rod joint (3), three mirror assembly built-in fittings (8) are connected by screw in carbon fiber substrate (7), multiple primary mirror assembly built-in fitting (11) is connected by screw in carbon fiber substrate (7).
2. a kind of high specific stiffness space optical remote sensor supporting construction according to claim 1, it is characterized in that, described multiple sustained ring built-in fitting (2) is 3.
3. a kind of high specific stiffness space optical remote sensor supporting construction according to claim 1, it is characterized in that, described many carbon fiber truss rods (4) are 6.
4. a kind of high specific stiffness space optical remote sensor supporting construction according to claim 1, it is characterized in that, described multiple truss built-in fitting (6) is 3.
5. a kind of high specific stiffness space optical remote sensor supporting construction according to claim 1, it is characterized in that, described multiple truss rod joint (3) is 6.
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| CN201410840011.0A CN104536113B (en) | 2014-12-30 | 2014-12-30 | High-specific stiffness supporting structure of space optical remote sensor |
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| CN201410840011.0A CN104536113B (en) | 2014-12-30 | 2014-12-30 | High-specific stiffness supporting structure of space optical remote sensor |
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| CN104536113B CN104536113B (en) | 2017-02-01 |
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Cited By (14)
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| CN105607216A (en) * | 2015-12-30 | 2016-05-25 | 中国科学院长春光学精密机械与物理研究所 | Large-size and high specific stiffness truss off-axis three-reflection optical system main support structure |
| CN106226042A (en) * | 2016-07-27 | 2016-12-14 | 中国科学院长春光学精密机械与物理研究所 | The Auto-Test System of space optical remote sensor carbon fiber structural stability and method |
| CN106287151A (en) * | 2016-09-07 | 2017-01-04 | 中国科学院长春光学精密机械与物理研究所 | Space optical remote sensor and support means thereof |
| CN106482770A (en) * | 2016-11-25 | 2017-03-08 | 中国科学院上海技术物理研究所 | A kind of outer light shield of metal for geostationary orbit space optical remote sensor |
| CN107144935A (en) * | 2017-06-16 | 2017-09-08 | 中国科学院西安光学精密机械研究所 | A kind of primary and secondary mirror support of the high resonant frequency of Light deformation |
| CN107991747A (en) * | 2017-09-15 | 2018-05-04 | 北京仿真中心 | A kind of optical system is without thermalization mechanical device |
| CN108254852A (en) * | 2018-03-23 | 2018-07-06 | 中国科学院光电研究院 | A kind of primary mirror mount structure for space camera |
| CN108594396A (en) * | 2018-06-08 | 2018-09-28 | 中国科学院西安光学精密机械研究所 | A kind of quasi- zero thermal expansion space optical remote sensor support construction and method |
| CN109557633A (en) * | 2018-12-12 | 2019-04-02 | 中国科学院西安光学精密机械研究所 | A kind of space optical remote sensor carbon fiber sub-truss jointing and sub-truss |
| CN110231689A (en) * | 2019-06-11 | 2019-09-13 | 中国科学院长春光学精密机械与物理研究所 | Push away the ultralight carbon fiber lattice supporting framework of solidifying integrated high-resolution space optics load |
| CN112782832A (en) * | 2021-01-19 | 2021-05-11 | 长光卫星技术有限公司 | Carbon fiber honeycomb type main bearing plate |
| CN112965324A (en) * | 2021-03-24 | 2021-06-15 | 中国科学院西安光学精密机械研究所 | Carbon fiber truss body assembling and adjusting device and process based on gluing error compensation |
| CN113515002A (en) * | 2021-04-23 | 2021-10-19 | 上海卫星工程研究所 | External heat flow restrained satellite-borne shading system |
| CN114047594A (en) * | 2021-11-23 | 2022-02-15 | 长光卫星技术有限公司 | Foldable reflector supporting truss structure |
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Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105607216B (en) * | 2015-12-30 | 2018-09-14 | 中国科学院长春光学精密机械与物理研究所 | The off-axis three reflecting optical systems main supporting structure of large scale high specific stiffness truss-like |
| CN105607216A (en) * | 2015-12-30 | 2016-05-25 | 中国科学院长春光学精密机械与物理研究所 | Large-size and high specific stiffness truss off-axis three-reflection optical system main support structure |
| CN106226042A (en) * | 2016-07-27 | 2016-12-14 | 中国科学院长春光学精密机械与物理研究所 | The Auto-Test System of space optical remote sensor carbon fiber structural stability and method |
| CN106226042B (en) * | 2016-07-27 | 2018-06-15 | 中国科学院长春光学精密机械与物理研究所 | The Auto-Test System and method of space optical remote sensor carbon fiber structural stability |
| CN106287151A (en) * | 2016-09-07 | 2017-01-04 | 中国科学院长春光学精密机械与物理研究所 | Space optical remote sensor and support means thereof |
| CN106287151B (en) * | 2016-09-07 | 2018-05-15 | 中国科学院长春光学精密机械与物理研究所 | Space optical remote sensor and its support device |
| CN106482770A (en) * | 2016-11-25 | 2017-03-08 | 中国科学院上海技术物理研究所 | A kind of outer light shield of metal for geostationary orbit space optical remote sensor |
| CN107144935B (en) * | 2017-06-16 | 2022-12-23 | 中国科学院西安光学精密机械研究所 | Primary and secondary mirror support of high resonant frequency of micro-deformation |
| CN107144935A (en) * | 2017-06-16 | 2017-09-08 | 中国科学院西安光学精密机械研究所 | A kind of primary and secondary mirror support of the high resonant frequency of Light deformation |
| CN107991747A (en) * | 2017-09-15 | 2018-05-04 | 北京仿真中心 | A kind of optical system is without thermalization mechanical device |
| CN107991747B (en) * | 2017-09-15 | 2024-03-19 | 北京仿真中心 | Athermalization mechanical device of optical system |
| CN108254852A (en) * | 2018-03-23 | 2018-07-06 | 中国科学院光电研究院 | A kind of primary mirror mount structure for space camera |
| CN108594396A (en) * | 2018-06-08 | 2018-09-28 | 中国科学院西安光学精密机械研究所 | A kind of quasi- zero thermal expansion space optical remote sensor support construction and method |
| CN108594396B (en) * | 2018-06-08 | 2023-09-05 | 中国科学院西安光学精密机械研究所 | Supporting structure and method for quasi-zero expansion space optical remote sensor |
| CN109557633A (en) * | 2018-12-12 | 2019-04-02 | 中国科学院西安光学精密机械研究所 | A kind of space optical remote sensor carbon fiber sub-truss jointing and sub-truss |
| CN110231689A (en) * | 2019-06-11 | 2019-09-13 | 中国科学院长春光学精密机械与物理研究所 | Push away the ultralight carbon fiber lattice supporting framework of solidifying integrated high-resolution space optics load |
| CN112782832A (en) * | 2021-01-19 | 2021-05-11 | 长光卫星技术有限公司 | Carbon fiber honeycomb type main bearing plate |
| CN112965324A (en) * | 2021-03-24 | 2021-06-15 | 中国科学院西安光学精密机械研究所 | Carbon fiber truss body assembling and adjusting device and process based on gluing error compensation |
| CN112965324B (en) * | 2021-03-24 | 2022-02-18 | 中国科学院西安光学精密机械研究所 | Carbon fiber truss body assembling and adjusting device and process based on gluing error compensation |
| CN113515002A (en) * | 2021-04-23 | 2021-10-19 | 上海卫星工程研究所 | External heat flow restrained satellite-borne shading system |
| CN114047594A (en) * | 2021-11-23 | 2022-02-15 | 长光卫星技术有限公司 | Foldable reflector supporting truss structure |
| CN114047594B (en) * | 2021-11-23 | 2023-09-22 | 长光卫星技术股份有限公司 | Foldable reflector support truss structure |
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