CN102981242B - Flexible supporting mechanism for reflector of spatial optical remote sensor - Google Patents
Flexible supporting mechanism for reflector of spatial optical remote sensor Download PDFInfo
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- CN102981242B CN102981242B CN201210536371.2A CN201210536371A CN102981242B CN 102981242 B CN102981242 B CN 102981242B CN 201210536371 A CN201210536371 A CN 201210536371A CN 102981242 B CN102981242 B CN 102981242B
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- outer shroud
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- 230000003287 optical effect Effects 0.000 title claims abstract description 17
- 230000005489 elastic deformation Effects 0.000 claims abstract description 8
- 239000000463 material Substances 0.000 claims description 9
- 229910000831 Steel Inorganic materials 0.000 claims description 7
- 229910052738 indium Inorganic materials 0.000 claims description 7
- APFVFJFRJDLVQX-UHFFFAOYSA-N indium atom Chemical compound [In] APFVFJFRJDLVQX-UHFFFAOYSA-N 0.000 claims description 7
- 239000010959 steel Substances 0.000 claims description 7
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 6
- 238000009827 uniform distribution Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 9
- 230000000694 effects Effects 0.000 abstract description 4
- 230000005484 gravity Effects 0.000 abstract description 3
- 230000007613 environmental effect Effects 0.000 abstract description 2
- 239000003292 glue Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 239000004809 Teflon Substances 0.000 description 1
- 229920006362 Teflon® Polymers 0.000 description 1
- 239000007767 bonding agent Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 239000005350 fused silica glass Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
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Abstract
The invention relates to a flexible supporting mechanism for a reflector of a spatial optical remote sensor. The supporting mechanism comprises a reflector frame, and a plurality of external ring bosses B that are circumferentially and uniformly distributed and connected with an external ring of the reflector frame; wherein the remote sensor is connected with the reflector frame through the external ring bosses B; radial flexible ring knots and axial flexible ring knots are arranged on the external ring bosses; each radial flexible ring knot comprises two radial flexible knots; each axial flexible ring knot comprises two axial flexible knots; the radial flexible knots can offset a radial force suffered by the reflector through elastic deformation; and the axial flexible knots can offset an axial force suffered by the reflector through the elastic deformation. With the adoption of the flexible supporting mechanism for the reflector of the spatial optical remote sensor, effects of stress and deformation of a remote sensor body on the reflector can be effectively eliminated; the difficulty of installing and adjusting of the reflector is reduced; the rigidity of the mechanism is ensured, effects of environmental factors such as temperature fluctuation and gravity on a surface shape of the reflector can be effectively reduced; and the supporting mechanism has the advantages that the supporting mechanism is high in rigidity, good in temperature adaptability, and easy to process and assemble.
Description
Technical field
The invention belongs to space remote sensing technical field, particularly relate to a kind of space optical remote sensor catoptron flexible support mechanism.
Background technology
The mechanical environment that space optical remote sensor can experience a shock, vibrate in rocket launching process and overload etc. is complicated and the variation of space temperature, and must guarantee face shape and the stability of its optical system simultaneously.Therefore must reasonably design the supporting mechanism of space optical remote sensor catoptron, can there is good rigidity and thermal adaptability, can effectively reduce the impact because external environment changes or its link distortion opposite shape produces.Therefore need to provide that a kind of rigidity is high, thermal adaptability good, easy processing, the easy new spatial optical sensor catoptron flexible support mechanism of assembling.
The prior art the most approaching with the present invention is that the people such as the Zhang Lei of Changchun Inst. of Optics and Fine Mechanics, Chinese Academy of Sciences are in the flexible support mechanism of the disclosed a kind of Space Remote Sensors catoptron of the patent No. 201110218847.0, as depicted in figs. 1 and 2.This mechanism comprises: interior ring 101, outer shroud 102, flexible link 103, inner and outer ring space 104, outer ring flange 105, outer shroud space 106, the protruding pad 107 of interior ring, flexible picture frame 108, pad 109, flexible compressing tablet 110, trip bolt 111, catoptron 112 etc.Wherein, on flexible picture frame 108 with interior ring 101, outer shroud 102 and flexible link 103, between interior ring 101 and outer shroud 102, there are three to be 120 ° of uniform concentric inner and outer ring spaces 104, flexible position between concentric inner and outer ring space 104 is flexible link 106 between two, on interior ring 101 with three protruding pads 107 of uniform interior ring, on outer shroud 102 with three uniform outer ring flanges 105, catoptron 112 sides are bonded in three and encircle on protruding pad 107, on the flexible picture frame 108 of catoptron 112 convex surface one sides, be fixed with flexible compressing tablet 110, the convex surface edge that flexible compressing tablet 110 presses to catoptron 112 is to provide axial pretightening.
The shortcoming of this catoptron flexible support mechanism is: this flexible support mechanism is by flexible compressing tablet, to eliminate the axially loaded of catoptron, and catoptron and reflection picture frame are bonding by tackifier, therefore the axial deformation that is delivered to reflection picture frame from remote sensor fuselage may be delivered to catoptron, has the risk that affects reflecting mirror surface shape; Due to by 3 independently flexible compressing tablet realize axial pretightening, mechanism's axial rigidity is difficult to ensure card.
Summary of the invention
The defect existing in order to overcome prior art, the object of the invention is to improve rigidity and the thermal adaptability of space optical remote sensor catoptron, and then more effectively guaranteeing the face shape of catoptron, a kind of rigidity of ad hoc meter is high, thermal adaptability good, the space optical remote sensor catoptron flexible support mechanism of easy processing.
In order to solve the problems of the technologies described above, technical scheme of the present invention is specific as follows:
A space optical remote sensor catoptron flexible support mechanism, comprising:
Reflection picture frame;
Be connected with reflection picture frame outer shroud a plurality of outer shroud boss B of circumference uniform distribution, remote sensor by this outer shroud boss B with reflect picture frame and be connected; On each outer shroud boss B, be provided with radial compliance link and axial elasticity link;
Each radial compliance link comprises the radially soft joint in two places, and each axial elasticity link comprises the two axial soft joints in place; Described radially soft joint can be offset the suffered radial force of catoptron by elastic deformation, and described axial soft joint can be offset the suffered axial force of catoptron by elastic deformation.
In technique scheme, the radially soft joint in two places on each outer shroud boss B is specially, the radial compliance groove with certain inclination angle that the outer shroud boss B left and right sides is arranged symmetrically with;
The two axial soft joints in place on each outer shroud boss B are specially, the axial elasticity groove with certain inclination angle that the upper and lower both ends of the surface of outer shroud boss B are arranged symmetrically with.
In technique scheme, be provided with altogether three described outer shroud boss B.
In technique scheme, described outer shroud boss B outer end is provided with the square hole of opening towards interior.
In technique scheme, the material of described reflection picture frame is titanium alloy or indium steel.
In technique scheme, be also provided with one and match and fix the annular preform of catoptron with described reflection picture frame.
In technique scheme, the material of described annular preform be titanium alloy or with indium steel.
Good effect of the present invention: space optical remote sensor catoptron flexible support mechanism of the present invention, can effectively eliminate the impact of remote sensor fuselage force and deformation on catoptron, reduce the difficulty that catoptron is debug, when guaranteeing mechanism's rigidity, can effectively reduce the impacts of environmental factor on reflecting mirror surface shape such as temperature variation, gravity, there is the advantages such as rigidity is high, thermal adaptability good, easy process and assemble.
Accompanying drawing explanation
Fig. 1 is that the general structure master of the flexible support mechanism of prior art Space Remote Sensors catoptron looks schematic diagram;
Fig. 2 is the dextrad cross-sectional schematic of Fig. 1;
Fig. 3 is structure cross-sectional schematic of the present invention;
Fig. 4 is the local enlarged diagram of I in Fig. 3;
Fig. 5 is the schematic side view such as just that reflects picture frame in the present invention;
Fig. 6 is the schematic top plan view that reflects picture frame in the present invention;
Fig. 7 is the elevational schematic view of annular preform in the present invention.
Reference numeral in figure is expressed as:
Ring in 101-; 102-outer shroud; The flexible link of 103-; 104-inner and outer ring space; 105-outer ring flange; 106-outer shroud space; The protruding pad of ring in 107-; The flexible picture frame of 108-; 109-pad; The flexible compressing tablet of 110-; 111-trip bolt; 112-catoptron;
1-catoptron; 2-pad; 3-screw; 4-annular preform; 5-reflects picture frame; Ring boss in 6-; 7-hole for injecting glue; 8-base ring boss; 9,11-radial compliance groove; The radially soft joint of 10-; 12,14-axial elasticity groove; The axial soft joint of 13-; 15,16-threaded hole; 17-square hole; The 18-boss that is threaded; The bonding boss of 19-pad.
Embodiment
As shown in Fig. 3-7, space optical remote sensor catoptron flexible support mechanism of the present invention comprises: catoptron 1, pad 2, screw 3, annular preform 4, reflection picture frame 5; Wherein, reflection picture frame 5 comprises: interior ring boss 6, hole for injecting glue 7, base ring boss 8, radial compliance groove 9, radial compliance groove 11, radially soft joint 10, axial elasticity groove 12, axial elasticity groove 14, axial soft joint 13, threaded hole 15, part shown in A in threaded hole 16, square hole 17, outer shroud boss A(Fig. 5) part shown in B and in outer shroud boss B(Fig. 5).On reflection picture frame 5, three are 120 ° of uniform outer shroud boss A and three and are 120 ° of uniform outer shroud boss B and are 60 ° and are staggeredly placed; There is threaded hole 15 outer shroud boss A upper surface, and annular preform 4 is connected with reflection picture frame 5 by three threaded holes 15; Outer shroud boss B is the rectangular structure being connected with reflection picture frame outer shroud, the outer shroud boss B left and right sides is arranged symmetrically with radial compliance groove 9 and the radial compliance groove 11 with certain inclination angle, the upper and lower both ends of the surface of outer shroud boss B are arranged symmetrically with axial elasticity groove 12 and the axial elasticity groove 14 with certain inclination angle, the inside opening square hole 17 in outer shroud boss B outer face, there is threaded hole 16 outer shroud boss B lower surface, and remote sensor fuselage can be connected with reflection picture frame 5 by threaded hole 16; On the interior ring of reflection picture frame 5, be 60 ° and be evenly equipped with and in six, encircle boss 6, interior ring boss 6 is positioned at 30 ° of positions in the middle of outer shroud boss A and outer shroud boss B, encircles boss 6 and be provided with a hole for injecting glue 7 in each; Above reflection picture frame 5 bottom annulus, be provided with three base ring boss 8 with interior ring boss A opposite position.In annular preform 4, have and be 120 ° of three uniform be threaded boss 18 and three bonding boss 19 of pad.Catoptron 1 bottom surface lies against on three base ring boss 8 of reflection picture frame 5, three pads 2 are bonded on the bonding boss 19 of three pads of annular preform 4, and be placed on the other end of catoptron 1, the light screw 3 stationary annular compressing tablets 4 of twisting are to picture frame, make it spacing to catoptron, after adjust position, by hole for injecting glue 7, inject bonding agent and realize the fixing of catoptron.
Space optical remote sensor catoptron flexible support mechanism of the present invention, there are uniform three radial compliance links and uniform three axial elasticity links corresponding one by one with the connecting thread hole 16 of remote sensor fuselage, to eliminate the impact of remote sensor fuselage force and deformation on catoptron; Inclination angle and the size of radial compliance groove 9, radial compliance groove 11 and axial elasticity groove 12, axial elasticity groove 14, and the size of radially soft joint 10 and axial soft joint 13 can design according to the reflection size of picture frame 5 and the optimization of structure calculating; Catoptron 1 material that adopts is fused quartz glass; Pad 2 material that adopts is teflon; Annular preform 4 material that adopts be titanium alloy or with indium steel; Reflection picture frame 5 material that adopts is titanium alloy or indium steel.
Principle of work explanation: the space optical remote sensor catoptron flexible support mechanism described in the present invention has three radial compliance links and three axial elasticity links, each radial compliance link comprises again two radially soft joints 10, and each axial elasticity link also comprises two axial soft joints 13.Radially soft joint 10 is offset the suffered radial force of catoptron by elastic deformation, and axial soft joint 13 is offset the suffered axial force of catoptron by elastic deformation.The acting force that remote sensor fuselage is subject to and distortion are just eliminated by radially soft joint 10 and axial soft joint 13, and can not be delivered on catoptron after being delivered on reflection picture frame 5 by threaded hole 16; Catoptron also can effectively be eliminated by radially soft joint 10 and axial soft joint 13 owing to being subject to acting force that the impact of the factor such as temperature gravity produces.In the violent environment of temperature variation, reflection picture frame 5 can be adopted to the indium Steel material consistent with catoptron 1 coefficient of thermal expansion, to reach the effect of better elimination temperature deformation.
Obviously, above-described embodiment is only for example is clearly described, and the not restriction to embodiment.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here exhaustive without also giving all embodiments.And the apparent variation of being extended out thus or change are still among the protection domain in the invention.
Claims (7)
1. a space optical remote sensor catoptron flexible support mechanism, comprising:
Reflection picture frame;
Be connected with reflection picture frame outer shroud a plurality of outer shroud boss B of circumference uniform distribution, remote sensor by this outer shroud boss B with reflect picture frame and be connected;
It is characterized in that,
On each outer shroud boss B, be provided with radial compliance link and axial elasticity link;
Each radial compliance link comprises the radially soft joint in two places, and each axial elasticity link comprises the two axial soft joints in place; Described radially soft joint can be offset the suffered radial force of catoptron by elastic deformation, and described axial soft joint can be offset the suffered axial force of catoptron by elastic deformation.
2. flexible support mechanism according to claim 1, is characterized in that,
The radially soft joint in two places on each outer shroud boss B is specially, the radial compliance groove with certain inclination angle that the outer shroud boss B left and right sides is arranged symmetrically with;
The two axial soft joints in place on each outer shroud boss B are specially, the axial elasticity groove with certain inclination angle that the upper and lower both ends of the surface of outer shroud boss B are arranged symmetrically with.
3. flexible support mechanism according to claim 1, is characterized in that, is provided with altogether three described outer shroud boss B.
4. flexible support mechanism according to claim 1, is characterized in that, described outer shroud boss B outer end is provided with the square hole of opening towards interior.
5. according to the flexible support mechanism described in claim 1-4 any one, it is characterized in that, the material of described reflection picture frame is titanium alloy or indium steel.
6. according to the flexible support mechanism described in claim 1-4 any one, it is characterized in that, be also provided with one and match and fix the annular preform of catoptron with described reflection picture frame.
7. flexible support mechanism according to claim 6, is characterized in that, the material of described annular preform is titanium alloy or indium steel.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210536371.2A CN102981242B (en) | 2012-12-12 | 2012-12-12 | Flexible supporting mechanism for reflector of spatial optical remote sensor |
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| CN201210536371.2A CN102981242B (en) | 2012-12-12 | 2012-12-12 | Flexible supporting mechanism for reflector of spatial optical remote sensor |
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| CN102981242A CN102981242A (en) | 2013-03-20 |
| CN102981242B true CN102981242B (en) | 2014-10-15 |
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