CN204043697U - Space optical remote sensor heat test Orbital heat flux simulation system - Google Patents
Space optical remote sensor heat test Orbital heat flux simulation system Download PDFInfo
- Publication number
- CN204043697U CN204043697U CN201420448250.7U CN201420448250U CN204043697U CN 204043697 U CN204043697 U CN 204043697U CN 201420448250 U CN201420448250 U CN 201420448250U CN 204043697 U CN204043697 U CN 204043697U
- Authority
- CN
- China
- Prior art keywords
- remote sensor
- optical remote
- space optical
- heat flux
- space
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The utility model discloses a kind of space optical remote sensor heat test Orbital heat flux simulation system, belong to space optical remote sensor environmental test technical field.Solve the problem that existing contact space optical remote sensor Orbital heat flux simulation system destroys the time of day on remote sensor surface.This system comprises space simulator, multilayer insulation assembly, electric heater, one side aluminized mylar, space optical remote sensor, cable and programmable power supply, multilayer insulation assembly is coated on the surface of space optical remote sensor, the space optical remote sensor of coated multilayer insulation assembly is positioned in space simulator, electric heater and one side aluminized mylar are fixed on the outside surface of multilayer insulation assembly outermost layer aluminized mylar from the inside to the outside successively, face of the aluminizing oriented multilayer insulating assembly outermost layer of one side aluminized mylar, electric heater is connected with programmable power supply by cable.This system ensures that space optical remote sensor surface keeps time of day.
Description
Technical field
The utility model belongs to space optical remote sensor environmental test technical field, is specifically related to a kind of space optical remote sensor heat test Orbital heat flux simulation system.
Background technology
Space optical remote sensor is a kind of widely used spacecraft, period needs the test facing harsh space environment in orbit for it, the acute variation of space heat flux can cause the fluctuation of remote sensor temperature and uneven, so need rationally effective Evolution of Thermal Control Technique, be in all the time within suitable temperature range during ensureing remote sensor operation on orbit.
In the development process of Space Remote Sensors, sufficient ground environment verification experimental verification is very necessary action, the environmental test on ground must simulate space orbit environment in-orbit, comprise the Orbital heat flux condition etc. of cold black background, high vacuum and space environment complexity, wherein Orbital heat flux simulation is the key link of heat test, the accuracy of its simulation has material impact to the reliability of heat test result and validity, and the complexity of simulated assembly also has very large association with the cost of heat test and cycle simultaneously.
In prior art, the simulation system of space optical remote sensor Orbital heat flux can be divided into the contactless and large class of direct contact type two, contactlessly comprise solar simulator, infrared lamp arrays, infrared heating cage etc., wherein solar simulator, infrared lamp arrays system relative complex is simultaneously also relatively high to the requirement of testing equipment; Infrared heating cage is easy to realize, but for the remote sensor of surface configuration complexity, is difficult to realize good shape adaptability, and is also difficult to realize accurate heat flux simulation; Direct contact type take Electric heating as representative, comprise electric heater, heat tape etc., specifically heating arrangement is pasted on remote sensor surface, directly confession electrical heating is carried out to heating arrangement, it is very little that the error that this kind of mode is simulated can control, precision is higher, but can destroy the surperficial time of day of remote sensor, is not suitable for the development of qualification or positive sample product.
Utility model content
The purpose of this utility model is to solve the technical matters that existing contact space optical remote sensor Orbital heat flux simulation system destroys the surperficial time of day of remote sensor, provides a kind of space optical remote sensor heat test Orbital heat flux simulation system.
For solving the problems of the technologies described above, the technical solution of the utility model is as follows.
Space optical remote sensor heat test Orbital heat flux simulation system, comprise electric heater, multilayer insulation assembly, space simulator, space optical remote sensor, cable and programmable power supply, described multilayer insulation assembly is coated on the surface of space optical remote sensor, the space optical remote sensor of described coated multilayer insulation assembly is placed in space simulator, described electric heater is connected with programmable power supply by cable, also comprise, one side aluminized mylar, described electric heater and one side aluminized mylar are fixed on the outside surface of multilayer insulation assembly outermost layer aluminized mylar from the inside to the outside successively, the face of aluminizing of one side aluminized mylar contacts with multilayer insulation assembly outermost layer.
Further, be provided with bracing frame in described space simulator, space optical remote sensor is placed on bracing frame.
Further, described electric heater and one side aluminized mylar are multiple, and one_to_one corresponding; Further, multiple electric heater is uniformly distributed on multilayer insulation assembly outermost layer aluminized mylar.
Further, described electric heater and one side aluminized mylar all adopt to paste and fix.
Compared with prior art, the beneficial effects of the utility model are:
Space optical remote sensor heat test Orbital heat flux simulation system of the present utility model directly applies power consumption by the electric heater of multilayer insulation assembly outermost layer aluminized mylar outside surface, combined high precision programmable power supply again, can absorb Orbital heat flux by accurate analog by controlling electric heater input current; And electric heater is pasted on multilayer insulation component internal, do not affect surface state and the heat-proof quality of multilayer insulation assembly, can adapt to test from space optical remote sensor thermal control model machine to the ground level heat in positive each stage of sample product; Orbital heat flux simulated assembly depends on multilayer insulation assembly, has extraordinary shape adaptability, is particularly useful for the spacecraft of surface configuration complexity.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of space optical remote sensor in space orbit work of the coated multilayer insulation assembly of the utility model;
Fig. 2 is the structural representation of the utility model space optical remote sensor heat test Orbital heat flux simulation system;
Fig. 3 is the structural representation of the Orbital heat flux simulated assembly of the utility model space optical remote sensor;
Fig. 4 is the fundamental diagram of the Orbital heat flux simulated assembly of the utility model space optical remote sensor;
In figure: 1, multilayer insulation assembly outermost layer, 2, electric heater, 3, one side aluminized mylar, 4, aluminized mylar, 5, space optical remote sensor surface, 6, terylene net, 7, arrive Orbital heat flux, 8, Orbital heat flux is absorbed, 9, heating power consumption, 10, space simulator, 101, bracing frame, 11, Orbital heat flux simulated assembly, 12, space optical remote sensor; 13, cable, 14, programmable power supply.
Embodiment
Below in conjunction with accompanying drawing 1-4, embodiment of the present utility model is described further.
Because space heat flux comprises solar irradiation, earth light, earth infrared radiation etc., if simulate each Space Heat Flux respectively, then need the analog machines such as special solar irradiation, infrared radiation, the complexity of testing equipment can improve greatly, cost also can improve greatly, so space heat flux of the present utility model is total Orbital heat flux of the Orbital heat flux synthesis such as solar irradiation, earth light, earth infrared radiation.In addition, the simulation strategy of space heat flux comprises the space heat flux value that simulation arrives remote sensor surface, is called for short and arrives Orbital heat flux, and simulation is by the Orbital heat flux value on Space Remote Sensors surface, i.e. absorbed Orbital heat flux value, is called for short and absorbs Orbital heat flux.The utility model is the virtual condition avoiding direct Contact Effect Space Remote Sensors surface, adopts contactless simulation, namely adopts the coated space optical remote sensor of multilayer insulation assembly to simulate.Specifically see accompanying drawing 1, space optical remote sensor is when space orbit runs, first space heat flux arrives the surface of multilayer insulation assembly outermost layer 1, hot-fluid outside this surface is the utility model indication and arrives Orbital heat flux 7, the part hot-fluid arriving Orbital heat flux 7 is reflected by multilayer insulation assembly outermost layer 1 or stops, but still have part hot-fluid can be absorbed by multilayer insulation assembly outermost layer 1, thus the surface of multilayer insulation assembly outermost layer aluminized mylar is arrived by multilayer insulation assembly outermost layer 1, but heat flow density has had and has largely weakened, the surface heat flow being arrived multilayer insulation assembly outermost layer aluminized mylar by multilayer insulation assembly outermost layer 1 is the utility model indication absorption Orbital heat flux 8.
As Figure 2-3, space optical remote sensor heat test Orbital heat flux simulation system, comprises space simulator 10, Orbital heat flux simulated assembly 11, space optical remote sensor 12, cable 13 and programmable power supply 14.Wherein, outer space environment simulated by space simulator 10, is existing apparatus, and can be provided with bracing frame 101 in space simulator 10, space simulator 11 is placed on bracing frame 101, Orbital heat flux simulated assembly 11 comprises electric heater 2, one side aluminized mylar 3 and multilayer insulation assembly, electric heater 2 and one side aluminized mylar 3 are fixed on the outside surface of multilayer insulation assembly outermost layer aluminized mylar from the inside to the outside successively, the face of aluminizing of one side aluminized mylar 3 contacts with multilayer insulation assembly outermost layer, multilayer insulation assembly is coated on (namely Orbital heat flux simulated assembly 11 is coated on space optical remote sensor surface 5) on space optical remote sensor surface 5, the innermost layer of multilayer insulation assembly contacts with space optical remote sensor surface 5, multilayer insulation assembly outermost layer 1 is directly towards cold black space, the space optical remote sensor 12 of coated Orbital heat flux simulated assembly 11 is placed in space simulator 10, electric heater 2 is connected with program-controlled unit 14 by cable 13, and programmable power supply 14 controls the power input of electric heater 2, and programmable power supply 14 can be arranged on outside space optical remote sensor 12.
In present embodiment, multilayer insulation assembly is prior art, generally comprise wall and outermost layer successively from the inside to the outside, wall is made up of alternately laminated aluminized mylar 4 and terylene net 6, the outermost layer of wall and innermost layer are all aluminized mylar 4, outermost layer aluminized mylar 4 contacts with multilayer insulation assembly outermost layer 1, and innermost layer mylar 4 contacts with space optical remote sensor surface 5, and the material of multilayer insulation assembly outermost layer 1 is generally F46.
Orbital heat flux simulated assembly 11 depends on multilayer insulation assembly, and electric heater 2 is pasted and fixed on the outside surface of multilayer insulation assembly outermost layer aluminized mylar 4, and the general heat-conducting silicon rubber that adopts is pasted; Due to the surface properties of electric heater 2 and aluminized mylar 4 variant, so fix one side aluminized mylar 3 at the surface mount of electric heater 2, make the surface properties of the side of electric heater 2 oriented multilayer insulating assembly outermost layer 1 close with outermost layer aluminized mylar 4 surface properties, the simulation precision of Orbital heat flux is improved with this, general one side aluminized mylar 3 adopts heat-conducting silicon rubber to paste, and the extraction wire of electric heater 2 adopts one side aluminum polyester pressure sensitive adhesive tape to paste and fixes; Due to the size general satisfaction not large-sized space optical remote sensor requirement of electric heater single in prior art, electric heater 2 and one side aluminized mylar 3 can be all multiple, and one_to_one corresponding, preferred multiple electric heater is uniformly distributed on the outside surface of multilayer insulation assembly outermost layer aluminized mylar 4, concrete according to actual needs and determining, electric heater 2 is not particularly limited, and can be purchased, as copper constantan electric heater.
System of the present utility model in use, first calculates the absorption Orbital heat flux 8 of space optical remote sensor 12 at space orbit of coated multilayer insulation assembly by software;
The software that specifically NX or I-DEAS etc. can be adopted to have the hot computing power of space orbit calculates in-orbit: the 3 d structure model first obtaining the space optical remote sensor 12 of coated multilayer insulation assembly, then need to carry out Rational Simplification to 3 d structure model according to thermal analyses, comprise and remove screw, the assemblies such as rivet, delete tiny geometric properties, remove technique fillet etc., then the thermal analyses finite element model setting up the space optical remote sensor 12 of coated multilayer insulation assembly (namely carries out stress and strain model, space heat flux calculates only need set up finite element model for space optical remote sensor surface 5 and multilayer insulation assembly, trellis-type adopts shell unit), when calculating absorption Orbital heat flux 8, convenient disposal method is setting space optical sensor surface 5 and multilayer insulation component grid unit is ghost, like this without the need to designated space optical sensor surface 5 and the material of multilayer insulation component grid unit, the attributes such as thickness, namely the surface properties that only need set grid can calculate, guaranteeing can improve computing velocity under the prerequisite calculating accuracy, emissivity is given according to space optical remote sensor surface 5 and multilayer insulation assembly virtual condition, the surface properties such as absorptivity, the calculating absorbing Orbital heat flux 8 can be carried out after setting parameter, wherein the surface properties of multilayer insulation assembly outermost layer 1 (F46 film) will give special concern, because the attribute of F46 film can along with remote sensor time and progressively degenerating in orbit, solar absorptance is caused to rise, emissivity declines, thus absorption Orbital heat flux 8 is increased, so calculate the degeneration need considering F46 membrane material characteristic when absorbing Orbital heat flux 8, material properties when being divided into space optical remote sensor 12 operation on orbit initial and operation on orbit be about at the end of material properties, again in conjunction with other design condition conditions, period absorbs Orbital heat flux 8 maximal value that may occur and minimum value in orbit to calculate space optical remote sensor 12, remove according to the maximal value and minimum value that absorb Orbital heat flux 8 thermal control design examining camera again in heat test, the material properties reference value of F46 membrane material is as follows:
1) when space optical remote sensor 12 operation on orbit is initial, solar absorptance 0.18, emissivity 0.72;
2) during space optical remote sensor 12 operation on orbit latter stage, solar absorptance 0.28, emissivity 0.62;
Then be the heating power consumption 9 of electric heater 2 by absorption Orbital heat flux 8 equivalent simulation obtained, utilize programmable power supply 14 pairs of electric heaters 2 to apply to produce the input current of this heating power consumption 9, complete the simulation of space optical remote sensor heat test Orbital heat flux;
When electric heater 2 is multiple, multilayer insulation assembly outermost layer mylar 4 outside surface is segmented by region, and calculate in each region according to the absorption Orbital heat flux 8 obtained and absorb Orbital heat flux value, then by absorb in each region Orbital heat flux value respectively equivalent simulation be the heating power consumption 9 of electric heater 2 in this region, utilize programmable power supply 14 to apply to produce the input current of this region heating power consumption 9 respectively to the electric heater 2 in each region, complete the simulation of space optical remote sensor heat test Orbital heat flux;
When absorbing Orbital heat flux in zoning, first calculate heat flow density, its unit is W/m
2, the absorption Orbital heat flux value in each region, only need be multiplied by this region area by the heat flow density in this region.
Obviously, the explanation of above embodiment just understands core concept of the present utility model for helping.Should be understood that; for the those of ordinary skill of described technical field; under the prerequisite not departing from the utility model principle, can also carry out some improvement and modification to the utility model, these improve and modify and also fall in the protection domain of the utility model claim.
Claims (5)
1. space optical remote sensor heat test Orbital heat flux simulation system, comprise electric heater (2), multilayer insulation assembly, space simulator (10), space optical remote sensor (12), cable (13) and programmable power supply (14), described multilayer insulation assembly is coated on the surface (5) of space optical remote sensor (12), the space optical remote sensor (12) of described coated multilayer insulation assembly is positioned in space simulator (10), described electric heater (2) is connected with programmable power supply (14) by cable (13), it is characterized in that, also comprise, one side aluminized mylar (3), described electric heater (2) and one side aluminized mylar (3) are fixed on the outside surface of multilayer insulation assembly outermost layer aluminized mylar (4) from the inside to the outside successively, the face of aluminizing of one side aluminized mylar (3) contacts with multilayer insulation assembly outermost layer (1).
2. space optical remote sensor heat test Orbital heat flux simulation system according to claim 1, is characterized in that, described electric heater (2) and one side aluminized mylar (3) are multiple, and one_to_one corresponding.
3. space optical remote sensor heat test Orbital heat flux simulation system according to claim 2, is characterized in that, described multiple electric heater (2) is uniformly distributed on multilayer insulation assembly outermost layer aluminized mylar (4).
4. according to the space optical remote sensor heat test Orbital heat flux simulation system of claim 1-3 described in any one, it is characterized in that, be provided with bracing frame (101) in described space simulator (10), space optical remote sensor (12) is placed on bracing frame (101).
5., according to the space optical remote sensor heat test Orbital heat flux simulation system of claim 1-3 described in any one, it is characterized in that, described electric heater (2) and one side aluminized mylar (3) all adopt paste fixing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420448250.7U CN204043697U (en) | 2014-08-08 | 2014-08-08 | Space optical remote sensor heat test Orbital heat flux simulation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420448250.7U CN204043697U (en) | 2014-08-08 | 2014-08-08 | Space optical remote sensor heat test Orbital heat flux simulation system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204043697U true CN204043697U (en) | 2014-12-24 |
Family
ID=52244350
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420448250.7U Expired - Fee Related CN204043697U (en) | 2014-08-08 | 2014-08-08 | Space optical remote sensor heat test Orbital heat flux simulation system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204043697U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104154943A (en) * | 2014-08-08 | 2014-11-19 | 中国科学院长春光学精密机械与物理研究所 | Thermal test outer heat flux simulation system and method for space optical remote sensor |
| CN106289318A (en) * | 2016-07-28 | 2017-01-04 | 北京空间机电研究所 | A kind of high rail large-aperture optical remote sensor light inlet Orbital heat flux analogy method |
-
2014
- 2014-08-08 CN CN201420448250.7U patent/CN204043697U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104154943A (en) * | 2014-08-08 | 2014-11-19 | 中国科学院长春光学精密机械与物理研究所 | Thermal test outer heat flux simulation system and method for space optical remote sensor |
| CN106289318A (en) * | 2016-07-28 | 2017-01-04 | 北京空间机电研究所 | A kind of high rail large-aperture optical remote sensor light inlet Orbital heat flux analogy method |
| CN106289318B (en) * | 2016-07-28 | 2019-02-15 | 北京空间机电研究所 | A kind of high rail large-aperture optical remote sensor light inlet Orbital heat flux analogy method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103662111B (en) | Suction ripple temperature control type Orbital heat flux analog machine under hot vacuum environment | |
| CN104154943A (en) | Thermal test outer heat flux simulation system and method for space optical remote sensor | |
| CN102967623B (en) | Infrared lamp array heat-flow density calibration device and calibration method | |
| Zhou et al. | Experimental and CFD investigation on temperature distribution of a serpentine tube type photovoltaic/thermal collector | |
| Karim et al. | Mathematical modelling of counter flow v-grove solar air collector | |
| CN102963545B (en) | Infrared lamp arrays heating system | |
| CN104925269B (en) | The assay device of a kind of high hypervelocity aircraft cabin section thermal environment and method | |
| CN106275496B (en) | A kind of heat balance test method of the more stars of a tank | |
| CN204043697U (en) | Space optical remote sensor heat test Orbital heat flux simulation system | |
| CN102539181A (en) | Method for testing ground surface heat of complex space mechanism | |
| CN205403951U (en) | Laser energy meter probe | |
| CN104535605A (en) | Heat flux density calibration system for vacuum wave-absorbing type external heat flux analog device | |
| JP2000281000A (en) | Simulation method of external heat-ray flux absorbed in flying by external radiating element of spacecraft and spacecraft for performing this method | |
| CN111498146A (en) | Thermal control system and method for detecting and verifying satellite by near-earth orbit gravitational wave | |
| CN105486711A (en) | Thermal infrared imager-based measuring system and method for emissivity of space material | |
| Fernández et al. | Low and medium temperature solar thermal collector based in innovative materials and improved heat exchange performance | |
| CN206540988U (en) | A kind of sleeve pipe paper oil insulation electric heating combines senile experiment device | |
| CN104597075A (en) | Heat flux simulation calibration system and calibration method for vacuum wave-absorbing type external heat flux simulation device | |
| CN109018456A (en) | A kind of thermal vacuum test Orbital heat flux analogy method of high rail remote sensing satellite platform | |
| CN104096667A (en) | Rubber drying equipment | |
| JP2634085B2 (en) | Satellite | |
| CN110757847B (en) | Repair device for composite part | |
| CN104732010B (en) | A kind of multilayer thermal protection struc ture fast Optimization | |
| CN108120369A (en) | The method and device of fixed foil gauge | |
| Lux et al. | Adhesive curing cycle time optimization in wind turbine blade manufacturing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141224 Termination date: 20170808 |