CN203550988U - Earth external thermal flux simulator for space optical remote sensor thermal vacuum test - Google Patents
Earth external thermal flux simulator for space optical remote sensor thermal vacuum test Download PDFInfo
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- CN203550988U CN203550988U CN201320673164.1U CN201320673164U CN203550988U CN 203550988 U CN203550988 U CN 203550988U CN 201320673164 U CN201320673164 U CN 201320673164U CN 203550988 U CN203550988 U CN 203550988U
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Abstract
The utility model provides an earth external thermal flux simulator for space optical remote sensor thermal vacuum test and belongs to the technical field of space optical remote sensor ground test, so as to solve the problem that synchronization of a thermal balance test and a thermal optical test in the prior art can not be met. The earth external thermal flux simulator for space optical remote sensor thermal vacuum test comprises a cylinder and a bracket; the cylinder has a hollow structure; the inner surface of the cylinder is coated with black paint with the emission rate no less than 0.85; a film-type electric heater is attached to the outer surface of the cylinder; the bracket comprises an upper bracket and a lower bracket; the upper bracket and the lower bracket are connected via n height-adjusting bolts; and the upper bracket is welded together with a supporting ring. According to the earth external thermal flux simulator for space optical remote sensor thermal vacuum test, the diameter of the front end surface of the cylinder is the same as the aperture of a light inlet of the space optical remote sensor, the diameter of the back end of the cylinder is no less than the projection diameter of the optical remote sensor viewing angle at the back end of the cylinder close to the end surface of a parallel light source, the thermal balance test and the thermal optical test can be planned together, operating conditions of the test can be carried out in an intersection mode, the test cycle is shortened, and the test cost is saved.
Description
Technical field
The utility model belongs to space optical remote sensor ground experiment technical field, is specifically related to the outer heat flux simulation device of a kind of space optical remote sensor vacuum thermal test earth.
Background technology
Space optical remote sensor is a kind of widely used space borne imagery useful load, can carry out territory prospecting, marine surveillance, the task such as scouting over the ground.In the process of the actual development of its product, need to carry out abundant, strict ground vacuum thermal test checking to complete machine, vacuum thermal test not only will be verified the thermal control design of remote sensor, also will indicate the image quality under simulation operation on orbit temperature environment condition.
Vacuum thermal test generally carries out in space simulator, while carrying out temperature environment simulation in-orbit, need the outer hot-fluid of virtual space, the device of outer heat flux simulation comprises solar simulator, infrared heating cage, infrared lamp arrays, electric heater etc., wherein the outer heat flux simulation of the earth at remote sensor light inlet place is take infrared heating cage as main, simple in structure because of it, be easy to realize, apply comparatively general, but infrared heating cage only can meet the heat balance test requirement of checking remote sensor thermal control design, and be not suitable for and indicate the thermal optical test of image quality in-orbit, because there is blocking of intermittent the heating tape of infrared cage to remote sensor light inlet, the source of parallel light incident energy of test is significantly decayed, to detecting indication result, can make a big impact, even cannot carry out optical detection.
Utility model content
The purpose of this utility model is to propose the outer heat flux simulation device of a kind of space optical remote sensor vacuum thermal test earth, and what solve that prior art exists can not meet the problem that optical sensor heat balance test and thermal optical test synchronously carry out.
For achieving the above object, the outer heat flux simulation device of the space optical remote sensor vacuum thermal test earth of the present utility model comprises cylindrical shell and support, described cylindrical shell is hollow structure, described cylinder inner surface scribbles the pitch-dark of emissivity >=0.85, described barrel outer surface is pasted with film type electrical heater, and described cylindrical shell is fixed on support.
Described cylindrical shell comprises barrel front end and cylinder back-end, and described barrel front end is taper, and cylinder back-end is cylindricality, and described barrel front end end face, middle part and cylinder back-end end face are respectively arranged with support annulus, and described cylindrical shell is fixed on support by supporting annulus.
The cylinder back-end of described cylindricality contacts with the small end face of the barrel front end of taper, described barrel front end end face diameter is identical with space optical remote sensor light inlet bore, the diameter of described column-shaped barrel rear end is not less than the diameter projected of optical sensor field angle in nearly source of parallel light end, cylindricality rear end, the length of described cylinder back-end be cylinder back-end diameter 1-1.5 doubly, the subtended angle of described barrel front end is 30 °-60 °.
Described support comprises upper bracket and lower carriage, between described upper bracket and described lower carriage, by n height adjustment bolt, connects, and described upper bracket welds together with support annulus.
The value of described n is: n=4.
Described barrel outer surface electric heater outside and support are coated with heat insulator.
The beneficial effects of the utility model are: the outer heat flux simulation device of the space optical remote sensor vacuum thermal test earth of the present utility model applies power consumption by electric heater to cylindrical shell, by cylinder inner surface, optical sensor light inlet is carried out to infrared heating, barrel outer surface well heater is divided to multiple regions, control respectively, can realize the simulation needs of heat flow density on a large scale, cylindrical shell is carried out to multi-area control simultaneously, be convenient to hot-fluid outside fine adjustment light inlet place, by the provision for thermal insulation of barrel outer surface and support, thermal loss can be dropped to minimumly, when economizing on resources, can also effectively lower the impact of the outer heat flux simulation device of the earth on space simulator heat sink temperature, the tapered front end of the outer heat flux simulation device of the earth is near optical sensor light inlet, cylindricality rear end is near source of parallel light, the cylinder back-end of cylindricality contacts with the small end face of the barrel front end of taper, barrel front end is identical with space optical remote sensor light inlet bore near the end face diameter at space optical remote sensor light inlet place, the diameter of the cylinder back-end of cylindricality be not less than space optical remote sensor field angle in cylindricality rear end the diameter projected near the end of source of parallel light, the length of cylinder back-end be cylinder back-end diameter 1-1.5 doubly, the subtended angle of barrel front end or circular cone drift angle are 30 °-60 °, both the needs of the outer heat flux simulation of optical sensor heat balance test light inlet can have been met, do not block again light path simultaneously, can meet the needs of thermal optical test optical detection, under " cold black " environment providing at space simulator, can normally use, so while carrying out heat test, above-mentioned two tests can be planned in the lump, operating condition of test intersection is carried out, so both can shorten the test period, can save again experimentation cost.
Accompanying drawing explanation
Fig. 1 is the outer heat flux simulation device structural representation of the space optical remote sensor vacuum thermal test earth of the present utility model;
Fig. 2 is the outer heat flux simulation device fundamental diagram of the space optical remote sensor vacuum thermal test earth of the present utility model;
Fig. 3 is that the outer heat flux simulation device of the space optical remote sensor vacuum thermal test earth of the present utility model uses schematic diagram;
Fig. 4 is the outer heat flux simulation device working method schematic diagram of the space optical remote sensor vacuum thermal test earth of the present utility model;
Wherein: 1, barrel front end, 2, cylinder back-end, 3, support annulus, 4, upper bracket, 5, height adjustment bolt, 6, lower carriage, 7, space optical remote sensor, 8, light inlet, 9, the outer heat flux simulation device of the earth, 10, hear rate, 11, infrared heat flow, 12, heat flow meter; 13, space simulator, 14, objective table, 15, source of parallel light.
Embodiment
Below in conjunction with accompanying drawing, embodiment of the present utility model is described further.
Referring to accompanying drawing 1, the outer heat flux simulation device of the space optical remote sensor vacuum thermal test earth of the present utility model comprises cylindrical shell and support, described cylindrical shell is flaring hollow structure, cylinder material is the thick aluminium alloy plate of 2mm, described cylinder inner surface sprays the pitch-dark of emissivity >=0.85, the heat sink inside surface emissivity of pitch-dark emissivity and space simulator 13 is suitable, barrel front end 1 and four heating subregions of the each division of cylinder back-end 2, cylindrical shell is carried out to partition heating, if need, improving outer heat flux simulation precision can further segment heating zone, electric heater can adopt two heating circuit well heaters as required, when active and standby part of heating circuit all starts work, can promote one times by adding heat power consumption, to meet the demand of high heat flux.
Described barrel outer surface is pasted with film type electrical heater, realizes simulator subregion is loaded to power consumption, and described cylindrical shell is fixed on support.
Described cylindrical shell comprises barrel front end 1 and cylinder back-end 2, described barrel front end 1 is taper, cylinder back-end 2 is cylindricality, described barrel front end 1 end face, middle part and cylinder back-end 2 end faces are respectively arranged with and support annulus 3, cylindrical shell is played to sizing and fixation, support ring and cylindrical shell are along being circumferentially welded as a whole, and material is the thick steel band of 2cm, and described cylindrical shell is fixed on support by supporting annulus 3.
The cylinder back-end 2 of described cylindricality contacts with the small end face of the barrel front end 1 of taper, described barrel front end 1 end face diameter is identical with space optical remote sensor light inlet 8 bores, the diameter of described column-shaped barrel rear end 2 is not less than the diameter projected of optical sensor field angle in nearly source of parallel light end, cylindricality rear end, not block light inlet light path as principle, the length of described cylinder back-end 2 be cylinder back-end 2 diameter 1-1.5 doubly, the subtended angle of described barrel front end 1 or circular cone drift angle are 30 °-60 °.
Described support comprises upper bracket 4 and lower carriage 6,
Described upper bracket 4 is steel angle structure, by six tie points, cylindrical shell is supported, each support annulus 3 arranges two tie points, upper bracket 4 is welded as a whole with support annulus 3, between described upper bracket 4 and described lower carriage 6, by four height adjustment bolt 5, connect, according to test, need to carry out height regulates, the outer heat flux simulation device of earth center is aimed at optical sensor light inlet center, height adjustment bolt 5 specifications need to be chosen according to test, height adjustment bolt 5 strokes must meet test needs, lower carriage 6 is steel angle structure, in test, the outer heat flux simulation device 9 of the earth is placed on the objective table 14 of space simulator 13.
Described barrel outer surface electric heater outside and support are coated with 15 unit multi-layer heat-barrier materials, effectively reduce by the radiation heat loss of barrel outer surface and support, and reduce the impact of the outer heat flux simulation device 9 of the earth on space simulator 13 heat sink temperatures.
Referring to accompanying drawing 2, outer heat flux simulation device 9 outside surfaces of the earth are applied to hear rate 10, barrel temperature rises, the infrared heat flow 11 of inside surface increases, light inlet 8 to space optical remote sensor 7 carries out infrared heating, by the heat flow meter 12 at light inlet 8 places, carries out hot-fluid monitoring, by adjust the outer heat flux simulation device 9 of the earth the each region of outside surface add heat power consumption, make heat flow meter 12 monitor values reach desired value, the heat flow density uniformity of each position.
Referring to accompanying drawing 3, during actual use, barrel front end 1 is just to space optical remote sensor 7 light inlets 8, cylindrical shell central axial alignment optical sensor light inlet 8 centers, according to use experience, barrel front end 1 is comparatively suitable apart from remaining on 10cm left and right with optical sensor light inlet 8.In test, optical sensor light inlet 8 centers, the outer heat flux simulation device 9 cylindrical shell centers of the earth and source of parallel light 15 center threes are coaxial.During heat test, the outer heat flux simulation device 9 of space optical remote sensor 7 and the earth is all placed on the objective table 14 of space simulator 13, between heat flux simulation device lower carriage 6 and objective table 14, install outside 20mm thick polyimide or teflon heat insulating mattress additional, to reduce the conductive heat loss to objective table 14 by simulator support.
Referring to accompanying drawing 4, while using the outer hot-fluid of outer heat flux simulation device 9 simulation of this earth, heat flow meter 12 is set at optical sensor light inlet 8 places and measures hot-fluid outside arrival, simulator pilot system is passed through programmable power supply, heat flow meter 12, temp measuring system and computer system composition control loop, by programmable power supply, outer heat flux simulation device 9 outside surfaces of the earth are applied to power consumption, simulator inside surface carries out infrared heating to optical sensor light inlet 8, by heat flow meter 12 and temperature acquisition system collecting temperature data, by computer system, temperature value is converted into heat flow density value, feed back to again programmable power supply adjustment and load power consumption, until light inlet 8 places reach target heat flow value.
Be more than embodiment of the present utility model, but absolutely not to restriction of the present utility model.
Claims (6)
1. the outer heat flux simulation device of the space optical remote sensor vacuum thermal test earth, it is characterized in that, comprise cylindrical shell and support, described cylindrical shell is hollow structure, described cylinder inner surface scribbles the pitch-dark of emissivity >=0.85, described barrel outer surface is pasted with film type electrical heater, and described cylindrical shell is fixed on support.
2. the outer heat flux simulation device of the space optical remote sensor vacuum thermal test earth according to claim 1, it is characterized in that, described cylindrical shell comprises barrel front end (1) and cylinder back-end (2), described barrel front end (1) is taper, cylinder back-end (2) is cylindricality, described barrel front end (1) end face, middle part and cylinder back-end (2) end face are respectively arranged with and support annulus (3), and described cylindrical shell is fixed on support by supporting annulus (3).
3. the outer heat flux simulation device of the space optical remote sensor vacuum thermal test earth according to claim 2, it is characterized in that, the cylinder back-end (2) of described cylindricality contacts with the small end face of the barrel front end (1) of taper, described barrel front end (1) end face diameter is identical with space optical remote sensor (7) light inlet bore, the diameter of described column-shaped barrel rear end (2) is not less than the diameter projected of field angle in nearly source of parallel light end, cylindricality rear end, the length of described cylinder back-end (2) be cylinder back-end (2) diameter 1-1.5 doubly, the subtended angle of described barrel front end (1) is 30 °-60 °.
4. the outer heat flux simulation device of the space optical remote sensor vacuum thermal test earth according to claim 2, it is characterized in that, described support comprises upper bracket (4) and lower carriage (6), between described upper bracket (4) and described lower carriage (6), by n height adjustment bolt (5), connect, described upper bracket (4) welds together with support annulus (3).
5. the outer heat flux simulation device of the space optical remote sensor vacuum thermal test earth according to claim 4, is characterized in that, the value of described n is: n=4.
6. the outer heat flux simulation device of the space optical remote sensor vacuum thermal test earth according to claim 1, is characterized in that, described barrel outer surface electric heater outside and support are coated with heat insulator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320673164.1U CN203550988U (en) | 2013-10-28 | 2013-10-28 | Earth external thermal flux simulator for space optical remote sensor thermal vacuum test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320673164.1U CN203550988U (en) | 2013-10-28 | 2013-10-28 | Earth external thermal flux simulator for space optical remote sensor thermal vacuum test |
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| CN203550988U true CN203550988U (en) | 2014-04-16 |
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| CN201320673164.1U Expired - Fee Related CN203550988U (en) | 2013-10-28 | 2013-10-28 | Earth external thermal flux simulator for space optical remote sensor thermal vacuum test |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103591974A (en) * | 2013-10-28 | 2014-02-19 | 中国科学院长春光学精密机械与物理研究所 | Extraterrestrial heat flow simulator for vacuum heat test of space optical remote sensor |
| CN111319804A (en) * | 2018-12-17 | 2020-06-23 | 中国科学院长春光学精密机械与物理研究所 | External heat flow simulator of optical remote sensor |
-
2013
- 2013-10-28 CN CN201320673164.1U patent/CN203550988U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103591974A (en) * | 2013-10-28 | 2014-02-19 | 中国科学院长春光学精密机械与物理研究所 | Extraterrestrial heat flow simulator for vacuum heat test of space optical remote sensor |
| CN103591974B (en) * | 2013-10-28 | 2015-11-25 | 中国科学院长春光学精密机械与物理研究所 | Extraterrestrial heat flow simulator for vacuum heat test of space optical remote sensor |
| CN111319804A (en) * | 2018-12-17 | 2020-06-23 | 中国科学院长春光学精密机械与物理研究所 | External heat flow simulator of optical remote sensor |
| CN111319804B (en) * | 2018-12-17 | 2021-10-26 | 中国科学院长春光学精密机械与物理研究所 | External heat flow simulator of optical remote sensor |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140416 Termination date: 20141028 |
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| EXPY | Termination of patent right or utility model |