CN102588716A - Satellite-remote sensor flexible heat sinking joint - Google Patents
Satellite-remote sensor flexible heat sinking joint Download PDFInfo
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- CN102588716A CN102588716A CN2012100576587A CN201210057658A CN102588716A CN 102588716 A CN102588716 A CN 102588716A CN 2012100576587 A CN2012100576587 A CN 2012100576587A CN 201210057658 A CN201210057658 A CN 201210057658A CN 102588716 A CN102588716 A CN 102588716A
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- supporting rod
- unloading groove
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Abstract
The invention discloses a satellite-remote sensor flexible heat sinking joint, which belongs to the field of spatial remote sensor optical instruments using a satellite as a carrier. The satellite-remote sensor flexible heat sinking joint comprises a first supporting rod, a second supporting rod and a plurality of unloading grooves such as an unloading groove a, an unloading groove b and the like. The unloading groove a and an unloading groove d are positioned on the first supporting rod and are mutually parallel; the unloading groove b and an unloading groove c are positioned on the first supporting rod, are mutually parallel, and are mutually perpendicular to the unloading groove a and the unloading groove d; an unloading groove e and an unloading groove h are positioned on the first supporting rod and are mutually parallel; an unloading groove f and an unloading groove g are positioned on the first supporting rod, are mutually parallel, and are mutually perpendicular to the unloading groove e and the unloading groove h; the first supporting rod and the second supporting rod are arranged triangularly; and the unloading grooves on the second supporting rod are fully symmetrical with the unloading grooves on the first supporting rod. When a large spatial remote sensor is assembled and positioned, the system stability is optimal, and the satellite-remote sensor flexible heat sinking joint has higher vibration resistance. A stress environment in a working process is improved, so that the remote sensor is in a favorable working condition, and the imaging quality is guaranteed.
Description
Technical field
The invention belongs to the satellite is the Space Remote Sensors class optical instrument field of carrier, specially refers to the technical field of the flexible interface aspect of remote sensor.
Background technique
Remote sensor is a kind of optical instrument of routine, and Space Remote Sensors is to be the optical instrument of the specific type of carrier with the satellite.The environment of the very special more common optical instrument work of its working environment wants much abominable.It operates mainly in weightlessness of space, vacuum and directly is exposed in the environment of solar particle radiation.Satellite is when trackwork; Its whole star is under the environment of temperature alternating; Celestial body is from the thermal distortion that under the effect of alternating temperature-changing, generation is difficult to predict; And the thermal stress that this thermal distortion produces will directly be transmitted to space optical remote sensor, causes each optical component optical surface quality and the requirement of positional accuracy out-of-size of participating in imaging, finally causes the reduction of image quality.
Be to guarantee the proper functioning of remote sensor, the Thermal structures design that between remote sensor and satellite, need disappear is to reduce or to eliminate the influence of satellite to the thermal stress of remote sensor.Traditional heat structure that disappears has forms such as spherical linkage mechanism, bearing iron hinge mechanism, though can play the heat effect that disappears to a great extent, these forms exist that assembling repeatability is low, part is more and shortcomings such as complex forms, vibration resistance difference.Be badly in need of a kind of Space Remote Sensors that the influence that can eliminate thermal distortion has pinpoint accuracy simultaneously again that has in the existing technology.
Summary of the invention
In order effectively to solve the deficiency that exists in the existing technology, the present invention has designed a kind of the disappear satellite of hot interface of flexibility that has that can effectively subdue thermal stress deformation and has used Space Remote Sensors.
Satellite-remote sensor flexibility hot interface that disappears is characterized in that: comprise strut first, strut second, spron a, spron b, spron c, spron d, spron e, spron f, spron g, spron h,
Described spron a and spron d are positioned on the strut first and are parallel to each other;
Described spron b and spron c are positioned on the strut first and are parallel to each other, and vertical each other with spron d with spron a;
Described spron e and spron h are positioned on the strut first and are parallel to each other;
Described spron f and spron g are positioned on the strut first and are parallel to each other; And it is vertical each other with spron h with spron e;
Described strut first, strut second triangularity is arranged, and the spron on spron on the strut second and the strut first is symmetrical fully.
The described flexibility hot interface that disappears adopts titanium alloy material.
The invention has the beneficial effects as follows: 1, between the attachment face of remote sensor and satellite, be provided with, therefore simultaneously angled three flexibilities heat structure that disappears that is provided with in the heat effect that realizes disappearing, can play location, supporting effect to remote sensor.
2, when satellite produces thermal distortion owing to temperature variation; With affecting the heat structure that disappears to produce linear displacement around three coordinate axes of rotation and edge of two coordinate axes of level; This degrees of freedom changes can't make remote sensor produce destructive rigid body displacement, but can realize the function of hinge, and the thermal distortion of satellite is unloaded; Realized the thermal distortion isolation between satellite and the remote sensor, thereby remote sensor is effectively protected.
3, owing to there is not the rocking link of micro parts, when remote sensor was debug, three flexibilities disappeared that heat structure is very close to each other, backlash, catching phenomenon, so the remote sensor stability of a system is higher.
4, simple mechanical cold working and electric machining process are adopted in the disappear processing of hot interface structure of flexibility, have avoided the complicated technology of hinge-like assembling, realize extremely easily.
5, through concrete analytical calculation, reasonably select concrete parameter, can guarantee that remote sensor has higher dynamic rate, under the operating conditions of whole star, have higher thermal adaptability again.
Description of drawings
Below in conjunction with accompanying drawing and embodiment the present invention is further specified.
Fig. 1 is the disappear structural representation of hot interface of remote sensor flexibility of the present invention.
Fig. 2 is the disappear left view of hot interface strut first of remote sensor flexibility of the present invention.
Fig. 3 is the disappear stereogram of hot interface of remote sensor flexibility of the present invention.
Fig. 4 is remote sensor flexibility of the present invention disappear hot interface and satellite annexation schematic representation.
Fig. 5 concerns schematic representation for disappear hot interface and satellite position of remote sensor flexibility of the present invention.
Among the figure: 1 is that strut first, 2 are that strut second, 3 is that spron a, 4 is that spron b, 5 is that spron c, 6 is that spron d, 7 is that spron e, 8 is that spron f, 9 is that spron g, 10 is spron h.
Embodiment
1) as shown in the figure is that the profile of strut first 1, strut second 2 is processed to flexibility two struts of hot interface that disappear at first; The flexibility of remote sensor and the satellite hot interface that disappears itself needs high stability; The disappear flexible spron of hot interface of flexibility will be on five degrees of freedom directions embodies respectively.The present invention carries out the rigidity reduction respectively according to the disappear basic principle of hot mechanism of hinge on two struts on single structure spare, promptly on five degrees of freedom, carry out limited release, has realized the flexibility hot merit ability that disappears.
2) the disappear structure and shape of two struts of hot interface of flexibility is heat-treated work.The flexibility hot interface that disappears adopts titanium alloy material, needs during sharp processing strictly to be undertaken by operation, guarantees that all geometric sense tolerances reach the requirement that designing institute needs, and through strict heat treatment process.
3) the flexibility hot interface form structure that disappears is carried out the operation of electric machining.Need strictness to be undertaken during this sharp processing, guarantee that all tolerances reach designing requirement by operation.
4) assembling of remote sensor and the flexible hot interface structure that disappears.For the large space remote sensor, adopt three flexibilities hot interface respective outer side edges that disappears to use, so that remote sensor stability of a system when assembling, location reaches optimum, and have higher vibration resistance.
5) three flexibilities installation coplanarity finishing of hot interface structure that disappears.The disappear layout of heat structure angle of three flexibilities need be passed through and carried out strict joint project analytical calculation with satellite and confirm.
6) integral installation of remote sensor and satellite.The flexibility of the present invention hot interface structure that disappears mainly comprises: remote sensor, flexibility disappear hot interface one, flexibility disappear hot interface two, flexibility disappear hot interface three, satellite celestial body and the screw of each connection part and pin etc.When three flexibilities being set disappearing the hot interface structure, in order to guarantee to have higher uninstall feature, when carrying out integral body debugging fitting operation, the flexible direction of the hot interface of must guaranteeing to disappear is pointed to the geometric centroid of satellite.The hot interface structure effectively absorbs because the reduction of interface rigidity, the thermal stress of satellite will be disappeared, and has improved the ambient stress of remote sensor when work, thereby has made remote sensor be in the good operation condition, guarantees image quality.
7) though the present invention is under the environment of temperature alternating the satellite in rail work; But can effectively offset thermal distortion and bring the deformation that each optical component caused of participating in imaging; And the optical surface quality of being brought thus and positional accuracy out-of-size situation about requiring, thereby the quality that has guaranteed imaging can not reduce.The present invention has abandoned traditional heat structure fit that disappears, and component function comparatively broadness has been avoided repeated assembling, and a large amount of minimizing number of spare parts makes mounting type no longer complicated and changeable, effectively raises vibration resistance, and is with the obvious advantage.
Claims (2)
1. satellite-remote sensor flexibility hot interface that disappears; It is characterized in that: comprise strut first (1), strut second (2), spron a (3), spron b (4), spron c (5), spron d (6), spron e (7), spron f (8), spron g (9), spron h (10)
Described spron a (3) and spron d (6) are positioned on the strut first (1) and are parallel to each other;
Described spron b (4) and spron c (5) are positioned on the strut first (1) and are parallel to each other, and vertical each other with spron d (6) with spron a (3);
Described spron e (7) and spron h (10) are positioned on the strut first (1) and are parallel to each other;
Described spron f (8) and spron g (9) are positioned on the strut first (1) and are parallel to each other; And it is vertical each other with spron h (10) with spron e (7);
Described strut first (1), strut second (2) triangularity are arranged, and the spron on spron on the strut second (2) and the strut first (1) is symmetrical fully.
2. satellite according to claim 1-remote sensor flexibility hot interface that disappears is characterized in that: the flexibility hot interface that disappears adopts titanium alloy material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100576587A CN102588716A (en) | 2012-03-07 | 2012-03-07 | Satellite-remote sensor flexible heat sinking joint |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100576587A CN102588716A (en) | 2012-03-07 | 2012-03-07 | Satellite-remote sensor flexible heat sinking joint |
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| CN102588716A true CN102588716A (en) | 2012-07-18 |
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| CN2012100576587A Pending CN102588716A (en) | 2012-03-07 | 2012-03-07 | Satellite-remote sensor flexible heat sinking joint |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104536116A (en) * | 2014-12-25 | 2015-04-22 | 中国科学院长春光学精密机械与物理研究所 | Multi-directional flexible supporting structure of oversized-aperture optical reflector |
| CN105242370A (en) * | 2015-11-19 | 2016-01-13 | 中国工程物理研究院应用电子学研究所 | Stress isolator based on flexible structure |
| CN105508819A (en) * | 2015-12-18 | 2016-04-20 | 中国科学院西安光学精密机械研究所 | Optical instrument rigid-flexible support structure and optical instrument |
| CN105840677A (en) * | 2016-05-20 | 2016-08-10 | 北京空间飞行器总体设计部 | Six-freedom-degree self-adaptive flexible universal joint |
| CN109975830A (en) * | 2019-02-21 | 2019-07-05 | 上海卫星工程研究所 | The in-orbit thermal deformation suppressing system of GEO satellite optical remote sensing instrument |
| CN112113116A (en) * | 2020-08-10 | 2020-12-22 | 中国原子能科学研究院 | Novel bracket |
| CN114084382A (en) * | 2021-11-25 | 2022-02-25 | 北京微纳星空科技有限公司 | Flexible support and space remote sensing camera |
| CN115145095A (en) * | 2022-06-30 | 2022-10-04 | 中国科学院长春光学精密机械与物理研究所 | One-way labyrinth type composite flexible structure |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104536116A (en) * | 2014-12-25 | 2015-04-22 | 中国科学院长春光学精密机械与物理研究所 | Multi-directional flexible supporting structure of oversized-aperture optical reflector |
| CN105242370A (en) * | 2015-11-19 | 2016-01-13 | 中国工程物理研究院应用电子学研究所 | Stress isolator based on flexible structure |
| CN105508819A (en) * | 2015-12-18 | 2016-04-20 | 中国科学院西安光学精密机械研究所 | Optical instrument rigid-flexible support structure and optical instrument |
| CN105840677A (en) * | 2016-05-20 | 2016-08-10 | 北京空间飞行器总体设计部 | Six-freedom-degree self-adaptive flexible universal joint |
| CN105840677B (en) * | 2016-05-20 | 2018-05-04 | 北京空间飞行器总体设计部 | A kind of six degree of freedom self-adapting flexible universal joint |
| CN109975830A (en) * | 2019-02-21 | 2019-07-05 | 上海卫星工程研究所 | The in-orbit thermal deformation suppressing system of GEO satellite optical remote sensing instrument |
| CN109975830B (en) * | 2019-02-21 | 2021-09-03 | 上海卫星工程研究所 | In-orbit thermal deformation suppression system for GEO satellite optical remote sensing instrument |
| CN112113116A (en) * | 2020-08-10 | 2020-12-22 | 中国原子能科学研究院 | Novel bracket |
| CN112113116B (en) * | 2020-08-10 | 2021-07-16 | 中国原子能科学研究院 | Novel bracket |
| CN114084382A (en) * | 2021-11-25 | 2022-02-25 | 北京微纳星空科技有限公司 | Flexible support and space remote sensing camera |
| CN115145095A (en) * | 2022-06-30 | 2022-10-04 | 中国科学院长春光学精密机械与物理研究所 | One-way labyrinth type composite flexible structure |
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Application publication date: 20120718 |