CN104002979A - Thermal deformation automatic adjusting supporting device for supporting structure - Google Patents
Thermal deformation automatic adjusting supporting device for supporting structure Download PDFInfo
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- CN104002979A CN104002979A CN201410227877.4A CN201410227877A CN104002979A CN 104002979 A CN104002979 A CN 104002979A CN 201410227877 A CN201410227877 A CN 201410227877A CN 104002979 A CN104002979 A CN 104002979A
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- thermal deformation
- cylinder
- automatic adjusting
- supporting
- composition fiber
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Abstract
The invention provides a thermal deformation automatic adjusting supporting device for a supporting structure, and belongs to the field of thermal deformation of the supporting structures. The device comprises a cylinder-wall base, piezoelectric complex fiber drivers and optical fiber strain transducers; the cylinder-wall base is manufactured through fiber reinforced resin based composite materials; a plurality of piezoelectric complex fiber drivers are uniformly distributed and adhered on the outer surface of the cylinder-wall base, and adhesive used is epoxy resin adhesive; a plurality of optical fiber strain transducers are uniformly distributed and adhered on the inner surface of the cylinder-wall base, respectively corresponding to the piezoelectric complex fiber drivers; the piezoelectric complex fiber drivers are driven by an external independent power supply to be deformed. With the adoption of the thermal deformation automatic adjusting supporting device of the supporting structure, the thermal deformation range of the cylinder-wall structure can be adjusted and expanded, and the adjusting precision is high; the thermal deformation automatic adjusting supporting device for the supporting structure is high in automatic adjusting capacity, and can be widely applied to the supporting structures of various high-precision observing platforms.
Description
Technical field
The invention belongs to supporting construction thermal deformation field, particularly a kind of thermal deformation self aligning bracing or strutting arrangement of supporting construction.
Background technology
Camera space and ground camera are very different, after the flight of entering the orbit, because solar light irradiation is inhomogeneous, camera supporting construction can be subject to the such environmental effects of the huge temperature difference, the effect of expanding with heat and contract with cold can cause supporting construction to deform, thereby affected imaging effect, particularly, when wide-long shot, very little drift angle will produce very large imaging error.So guarantee that the heat stability of the supporting construction of camera on satellite, naval vessel has important practical significance and engineering using value.
In recent years, scholars more both domestic and external have obtained certain achievement on the material development of aerial camera supporting construction, the light material of the high rigidity of low thermal expansion is undoubtedly the ideal chose of camera supporting construction, but the relation due to the mutual containing of these attributes, manufacture that this Master Cost is high, difficulty is large, and this passive to realize the effect that the heat-staple method of supporting construction obtains not very good.
Summary of the invention
The object of the invention is the problem existing in order to solve above-mentioned prior art, invent a kind of thermal deformation self aligning bracing or strutting arrangement, adopt the thermal deformation signal of fibre optic strain sensor Real-Time Monitoring barrel pedestal, and be transferred to computer control unit, controller calculates the required driving voltage value of each piezoelectricity composition fiber actuator and sends control command, make each piezoelectricity composition fiber actuator produce convergent force or produce stretching force, carry out the deformation of balance barrel pedestal, the heat stability that keeps supporting construction, adjusts precision high.
The technical solution used in the present invention is a kind of thermal deformation self aligning bracing or strutting arrangement of supporting construction, it is characterized in that, this device comprises barrel pedestal 1, piezoelectricity composition fiber actuator 2 and fibre optic strain sensor 3, barrel pedestal 1 adopts fiber-reinforced resin matrix compound material to make, several piezoelectricity composition fiber actuators 2 are uniformly distributed and stick on barrel pedestal 1 outside face, and alite paste used is epoxide-resin glue; Several fibre optic strain sensors 3 are uniformly distributed and stick on barrel pedestal 1 inside face, and form one-to-one relationship with several piezoelectricity composition fiber actuators 2, and alite paste used is epoxide-resin glue; Each piezoelectricity composition fiber actuator 2 is driven and is produced deformation by external-500～+ 1500V independent current source 4.
Beneficial effect of the present invention is: composite material Cylinder wall structure, piezoelectricity composition fiber actuator and fibre optic strain sensor that (1) the present invention adopts all have light weight, the feature that added mass is little; (2) the piezoelectricity composition fiber actuator adopting, has good compliance and machining property, and power-handling capability is strong, is specially adapted to curved-surface structure; (3) fibre optic strain sensor adopting is highly sensitive, affected by external environment factor little; (4) capable of regulating Cylinder wall structure thermal deformation scope of the present invention is large, adjusts precision high; (5) self aligning ability of the present invention is strong, and can be widely used in the supporting construction of all kinds of High Accuracy Observation platforms.
Accompanying drawing explanation
Fig. 1 is the structural representation of thermal deformation self-adjusting apparatus of the present invention.
Fig. 2 is the birds-eye view of Fig. 1.
Fig. 3 is thermal deformation self aligning schematic diagram in the embodiment of the present invention.
In figure: 1-barrel pedestal, 2-piezoelectricity composition fiber actuator, 3-fibre optic strain sensor, 4-power supply, 5-infrared source.
The specific embodiment
Below in conjunction with accompanying drawing and technical scheme, the present invention is specifically implemented and is described in further detail.
As depicted in figs. 1 and 2, the thermal deformation self aligning bracing or strutting arrangement of a kind of supporting construction involved in the present invention, comprise barrel pedestal 1, piezoelectricity composition fiber actuator 2 and fibre optic strain sensor 3, piezoelectricity composition fiber actuator 2 and fibre optic strain sensor 3 stick on respectively on the outside and inner surface of barrel pedestal 1, and paste position is corresponding and be contraposition shape one by one.Barrel pedestal is made by complex fiber material, utilize the designability of composite material, by material parameters such as design fiber type, fiber and resin content, laying angles, guarantee that the thermal deformation of Cylinder wall structure 1 and the deformation under 2 drivings of piezoelectricity composition fiber actuator match.
The quantity of the size of barrel pedestal 1 and piezoelectricity composition fiber actuator 2 and fibre optic strain sensor 3 can be adjusted according to the actual requirements, to meet actual design needs.The thermal deformation signal of described fibre optic strain sensor 3 Real-Time Monitoring barrel pedestals 1, piezoelectricity composition fiber actuator 2, according to this signal, by corresponding control algorithm, produces suitable stretching force or convergent force and guarantees that on barrel pedestal 1, end face is in desired locations.
As shown in Figure 3, when a side of barrel pedestal 1 is subject to illumination or thermal radiation 5 and causes temperature to raise, due to the principle of expanding with heat and contract with cold, the side that temperature raises can produce tensile deformation, cause end face on pedestal to tilt to C-C ' plane from original A-A ' plane, now, fibre optic strain sensor receives deformation signal, and be transferred to computer control unit, controller calculates the required driving voltage value of each piezoelectricity composition fiber actuator 2 and sends control command, each piezoelectricity composition fiber actuator 2 or generation convergent force or generation stretching force, force end face on barrel pedestal 1 to get back to new B-B ' plane.Although new B-B ' plane has one section of micro-displacement with respect to original A-A ' plane, can't exert an influence to camera imaging, the impact bringing with respect to clinoplane C-C ' is negligible.
Claims (1)
1. a thermal deformation self aligning bracing or strutting arrangement for supporting construction, is characterized in that, this device comprises barrel pedestal (1), piezoelectricity composition fiber actuator (2) and fibre optic strain sensor (3); Barrel pedestal (1) adopts fiber-reinforced resin matrix compound material to make, and several piezoelectricity composition fiber actuators (2) are uniformly distributed and stick on barrel pedestal (1) outside face, and alite paste used is epoxide-resin glue; Several fibre optic strain sensors (3) are uniformly distributed and stick on barrel pedestal (1) inside face, and form one-to-one relationship with several piezoelectricity composition fiber actuators (2), and alite paste used is epoxide-resin glue; Each piezoelectricity composition fiber actuator (2) is driven and is produced deformation by external-500～+ 1500V independent current source (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410227877.4A CN104002979B (en) | 2014-05-27 | 2014-05-27 | A kind of thermal deformation self aligning bracing or strutting arrangement of supporting construction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410227877.4A CN104002979B (en) | 2014-05-27 | 2014-05-27 | A kind of thermal deformation self aligning bracing or strutting arrangement of supporting construction |
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| Publication Number | Publication Date |
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| CN104002979A true CN104002979A (en) | 2014-08-27 |
| CN104002979B CN104002979B (en) | 2016-03-02 |
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| CN201410227877.4A Active CN104002979B (en) | 2014-05-27 | 2014-05-27 | A kind of thermal deformation self aligning bracing or strutting arrangement of supporting construction |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112188038A (en) * | 2019-07-01 | 2021-01-05 | 格科微电子（上海）有限公司 | Method for improving assembling precision of camera module |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060054745A1 (en) * | 2004-08-30 | 2006-03-16 | Plotke Leonard A | Thermal deformation determination for payload pointing using space-based beacon |
| CN201136593Y (en) * | 2007-12-25 | 2008-10-22 | 上海复合材料科技有限公司 | Micro-deformation carrier barrel |
| CN101872904A (en) * | 2010-06-30 | 2010-10-27 | 哈尔滨工业大学 | Deformable antenna reflection surface |
| CN102682171A (en) * | 2012-05-15 | 2012-09-19 | 中国电子科技集团公司第五十四研究所 | Method for compensating thermal deformation of mold for high-precision composite material antenna reflector unit |
| US20130193303A1 (en) * | 2012-02-01 | 2013-08-01 | Matthew W. Smith | Multi-functional star tracker with precision focal plane position control for small cubesat-class satellites |
-
2014
- 2014-05-27 CN CN201410227877.4A patent/CN104002979B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060054745A1 (en) * | 2004-08-30 | 2006-03-16 | Plotke Leonard A | Thermal deformation determination for payload pointing using space-based beacon |
| CN201136593Y (en) * | 2007-12-25 | 2008-10-22 | 上海复合材料科技有限公司 | Micro-deformation carrier barrel |
| CN101872904A (en) * | 2010-06-30 | 2010-10-27 | 哈尔滨工业大学 | Deformable antenna reflection surface |
| US20130193303A1 (en) * | 2012-02-01 | 2013-08-01 | Matthew W. Smith | Multi-functional star tracker with precision focal plane position control for small cubesat-class satellites |
| CN102682171A (en) * | 2012-05-15 | 2012-09-19 | 中国电子科技集团公司第五十四研究所 | Method for compensating thermal deformation of mold for high-precision composite material antenna reflector unit |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112188038A (en) * | 2019-07-01 | 2021-01-05 | 格科微电子（上海）有限公司 | Method for improving assembling precision of camera module |
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| CN104002979B (en) | 2016-03-02 |
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