CN111912548A - Non-contact measuring device for surface heat flow of spacecraft vacuum thermal test - Google Patents
Non-contact measuring device for surface heat flow of spacecraft vacuum thermal test Download PDFInfo
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- CN111912548A CN111912548A CN202010799476.1A CN202010799476A CN111912548A CN 111912548 A CN111912548 A CN 111912548A CN 202010799476 A CN202010799476 A CN 202010799476A CN 111912548 A CN111912548 A CN 111912548A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K17/00—Measuring quantity of heat
- G01K17/06—Measuring quantity of heat conveyed by flowing media, e.g. in heating systems e.g. the quantity of heat in a transporting medium, delivered to or consumed in an expenditure device
- G01K17/08—Measuring quantity of heat conveyed by flowing media, e.g. in heating systems e.g. the quantity of heat in a transporting medium, delivered to or consumed in an expenditure device based upon measurement of temperature difference or of a temperature
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Abstract
The application discloses spacecraft vacuum heat test surface heat flow non-contact measuring device, including support and black piece heat flow meter, the support includes screw rod and mounting panel, and mounting panel one end sets up black piece heat flow meter, and the screw rod is connected to the other end, and the screw rod is connected with the skeleton of infrared heating cage or infrared lamp battle array, hangs black piece heat flow meter near spacecraft surface and carries out the heat flow and measure, neither depends on spacecraft surface state and does not influence the heat flow meter again and use.
Description
Technical Field
The invention relates to the technical field of spacecraft environment tests, in particular to a non-contact measuring device for surface heat flow of a spacecraft vacuum thermal test.
Background
When the domestic spacecraft is used for vacuum heat test, an infrared heating cage, an infrared lamp array and the like are mostly used for on-orbit heat flow simulation, and a heat flow meter is used for measuring the heat flow actually reaching the surface of the spacecraft. Before each heat flow meter is installed, a positioning line for fixing the heat flow meter is drawn out from the star surface, the positioning line is fixed at a fixing point on the edge of or near the heat flow meter installation cabin plate, and the fixing point is a pin or a star surface protrusion. And connecting a fixing line at the bottom of the heat flow meter to a heat flow meter positioning line by adopting a direct binding method, and tensioning and fixing the fixing line along the mounting surface. For some special surfaces, such as pins or star surface protrusions which are large in heat dissipation surface and cannot find a positioning line of a fixed heat flow meter, or under the conditions that a heat flow meter is required to measure a heat flow value but cannot find a fixed point of the heat flow meter for a spacecraft normal load, or the heat flow meter cannot be fixed in parallel with a measurement surface, how to not depend on the surface state of the spacecraft and not influence the use of the heat flow meter is a problem to be solved.
Disclosure of Invention
In view of the above-mentioned drawbacks and deficiencies of the prior art, it would be desirable to provide a non-contact measurement device for measuring heat flow on a vacuum thermal test surface of a spacecraft.
In order to overcome the defects of the prior art, the technical scheme provided by the invention is as follows:
the invention provides a non-contact measuring device for heat flow on the surface of a spacecraft vacuum heat test, which comprises a support and a black sheet heat flow meter, wherein the support comprises a screw and a mounting plate, one end of the mounting plate is provided with the black sheet heat flow meter, the other end of the mounting plate is connected with one end of the screw, and the other end of the screw is used for being connected with a framework of an infrared heating cage or an infrared lamp array.
In one embodiment, the mounting plate is made of polyimide material, and the screw is made of stainless steel material.
In one embodiment, the screw and the mounting plate are coated with aluminized polyester film.
In one embodiment, the length of the mounting plate is 120mm, the middle position of the mounting plate is recessed by 10mm from two sides, and the recessed position is coated with aluminized polyester film.
In one embodiment, the screw has a diameter of 8mm and a length of not less than 100mm, and is coated with an aluminized polyester film except for a portion for contacting the mounting plate and the heating cage or the infrared lamp array.
In one embodiment, the distance from the axis of the screw to the center of the stepped hole is 100 mm.
In one embodiment, be equipped with the heat insulating mattress between mounting panel and the black piece heat flow meter, the heat insulating mattress with mounting panel fixed connection, the black piece heat flow meter with heat insulating mattress fixed connection.
In one embodiment, a stepped hole is formed in the end face, away from the mounting plate, of the heat insulation pad, a bolt penetrates through the stepped hole, a nut is accommodated in the stepped hole, and the black sheet heat flow meter is bonded to the heat insulation pad.
In one embodiment, the heat insulation pad is an I-shaped structure, the maximum diameter of the I-shaped structure is 40.5mm, the height of the I-shaped structure is 10mm, and the heat insulation pad is made of polyimide materials.
In one embodiment, the heat flow meter comprises a thermocouple, and a fixing line of the heat flow meter is led out from the bottom of the heat flow meter along the mounting plate through an extension line of the thermocouple, is routed from the back of the mounting plate, and is led out of a heating cage or an infrared lamp array along the screw rod.
Compared with the prior art, the invention has the beneficial effects that:
the non-contact measuring device for the heat flow on the surface of the spacecraft vacuum heat test comprises a support and a black sheet heat flow meter, wherein the support comprises a screw rod and a mounting plate, the black sheet heat flow meter is arranged at one end of the mounting plate, the other end of the mounting plate is connected with the screw rod, the screw rod is connected with a framework of a heating cage or an infrared lamp array, the black sheet heat flow meter is suspended near the surface of the spacecraft to measure the heat flow, and the device does not depend on the surface state of the spacecraft and does not influence the use of the heat flow meter.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
FIG. 1 is a perspective view of a non-contact measuring device for heat flow on a vacuum thermal test surface of a spacecraft, provided by an embodiment of the invention;
FIG. 2 is a perspective view of a cylindrical insulation mat and mounting plate assembly according to an embodiment of the present invention;
fig. 3 is a cross-sectional view of fig. 1.
In the figure: 1-mounting plate, 2-screw, 3-heat insulation pad and 4-bolt.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
As mentioned in the background, for some special surfaces, such as pins or star surface protrusions with large heat dissipation surfaces, which can not find the positioning lines of the heat flow meter, or the positive load of the spacecraft needs to measure the heat flow value but can not find the fixing points of the heat flow meter, or the heat flow meter can not be fixed in parallel with the measuring surface.
It is therefore an improvement of the present application how to not rely on the spacecraft surface conditions and not affect the use of the heat flux meter. The embodiment of the application provides a non-contact measuring device for heat flow on the surface of a spacecraft vacuum thermal test to effectively solve the problems.
Referring to fig. 1 to 3, fig. 1 to 3 show a non-contact measuring device for heat flow of a vacuum thermal test surface of a spacecraft.
This non-contact measuring device includes support and black piece heat flow meter, the support includes screw rod 2 and mounting panel 1, 1 one end of mounting panel sets up black piece heat flow meter, the other end is connected 2 one end of screw rod, 2 other ends of screw rod are used for being connected with the skeleton of infrared heating cage or infrared lamp battle array.
The screw rod 2 is connected with a framework of a heating cage or an infrared lamp array, the black sheet heat flow meter is suspended near the surface of the spacecraft for heat flow measurement, the fixed position of the black sheet heat flow meter is not required to be searched by depending on the surface state of the spacecraft, and the use of the black sheet heat flow meter is not influenced.
This device has utilized frame or skeleton of infrared heating cage or infrared lamp battle array for fixed heat flow meter support, place the heat flow meter in the parallel position on spacecraft surface through the heat flow meter support, but the heat flow meter support must control the deflection, require that the sensitive face of heat flow meter and star table contained angle are not more than 5, also need control the sheltering from of heat flow meter support to the thermal current, avoid secondary infrared interference, reduce heat flow measuring error, it does not exceed +/-5 to require the thermal current deviation.
Wherein, be equipped with heat insulating mattress 3 between mounting panel 1 and the black piece heat flow meter, heat insulating mattress 3 with 1 fixed connection of mounting panel, the black piece heat flow meter with 3 fixed connection of heat insulating mattress.
Specifically, a stepped hole is formed in the end face, away from the mounting plate 1, of the heat insulation pad 3, a bolt 4 penetrates through the stepped hole, a nut is accommodated in the stepped hole, and the black sheet heat flow meter is bonded to the heat insulation pad 3.
Above-mentioned solved and directly fixed the problem on the spacecraft surface with black piece heat flow meter, further for improving black piece heat flow meter measuring accuracy, reduce the infrared interference of secondary and measuring error, further optimize above-mentioned non-contact measuring device.
The error in the heat flow measurement is the difference between the heat flow received by the black patch heat flow meter and the heat flow that the spacecraft surface should actually receive in the thermal test. The error source mainly comprises two parts, namely, a radiation angle coefficient error caused by the change of the parallel position of a black sheet heat flow meter and a star surface due to the deformation of a heat flow meter support; and secondly, measuring errors caused by shielding of the heat flow meter support to heat flow.
The structure after the non-contact measuring device is optimized reduces the deformation of the bracket in the use state as much as possible, reduces the shielding of the bracket to heat flow, reduces the interference of secondary infrared and reduces the measuring error. The support is used for suspending the black sheet heat flow meter near the surface of the spacecraft to measure heat flow, and the measurement error can be controlled within an allowable measurement error range.
The deformation of the screws 2 of different materials was compared. The stress state of the screw rod 2 can be regarded as a cantilever beam structure, one end of the cantilever beam structure is fixed, and the other end of the cantilever beam structure is intensively stressed. According to the analysis of the cantilever beam stress, the bending deformation of the screw rod 2 is as follows:
wherein f ismax: maximum deformation of the screw;
p: converting the concentrated force to the tail end of the screw;
l: the length of the screw;
e: the modulus of elasticity of the screw material;
i: axial moment of inertia of the screw section;
the screw has a diameter of 8mm, a length greater than the distance between the infrared heating surface and the surface of the spacecraft, specifically not less than 100mm, and an I of 2.011 × 10-10m4And calculating the deformation of the screw and the mounting plate 1 made of different materials of stainless steel and polyimide, as shown in table 1.
TABLE 1 amount of deformation of screw and mounting plate using different materials of stainless steel and polyimide
It can be seen that the amount of deformation of the bracket is minimal when the screw 2 is stainless steel and the mounting plate 1 is a polyimide material. Therefore, the mounting plate 1 is made of polyimide material, and the screw rod 2 is made of stainless steel material.
The deformation amounts of the mounting plates 1 of different shapes were compared. Assuming that the mounting plate 1 is made of polyimide, the gravity direction is different depending on the mounting manner. The screw 2 is fixed and supported at the installation position and is subjected to the self gravity and the gravity of the heat insulation pad 3, and the heat insulation pad 3 is 0.1N. When gravity is vertical to the mounting plate 1, under the stress mode, the deformation of the concave shape in the middle of the mounting plate 1 is 0.29mm, and the deformation of the mounting plate 1 without the concave shape is 0.18 mm. When gravity is parallel to the mounting plate 1, under the stress mode, the deformation of the concave shape in the middle of the mounting plate 1 is 0.008mm, and the deformation of the mounting plate 1 without the concave shape is 0.003 mm. In general use, the situation is 2, and the deformation of the heat flow meter mounting plate 1 has little influence on the measurement of the black sheet heat flow meter.
The heat insulation pad 3 adopts a columnar structure. The diameter of the heat insulation pad 3 is 40.5mm, the height of the heat insulation pad is 10mm, and the heat insulation pad 3 is made of polyimide materials. The deformation amount of the heat insulating mats 3 of different shapes is compared. The calculation was performed according to the two shapes of the cylindrical heat insulating mat 3 and the i-shaped heat insulating mat 3, which were calculated only by its own weight because the black sheet heat flow meter was light. The deformation of the I-shaped heat insulation pad 3 is 10-5mm, the deformation is negligible, and the cylindrical deformation is smaller.
It should be noted that, when the screw rod 2 and the heat insulation pad 3 are used, the distance from the axis of the screw rod 2 to the installation center of the heat flow meter is 100 mm.
The deviation of the heat flow of the screw 2 painted with the black paint and coated with the aluminum film was compared. According to the calculation of the black sheet heat flow meter temperature 339.9K, the temperature measured by the heat flow meter when the screw 2 is painted with black paint is 339.1K, the heat flow deviation is 0.95 percent, the temperature measured by the heat flow meter when the screw 2 is coated with an aluminum plating film is 339.3K, and the heat flow deviation is 0.71 percent. In combination with the above analysis, the surface of the screw 2 is coated with an aluminized polyester film, specifically, the portions of the screw 2 except for the portions contacting the mounting plate 1 and the heating cage or the infrared lamp array are coated with the aluminized polyester film.
The heat flow deviations of the two concave and flat shapes of the mounting plate 1 were compared. The calculated heat flow when the mounting plate 1 was flat measured temperature of 339.0K and the heat flow deviation was 1.07%, calculated as black patch heat flow temperature 339.9K, and the calculated heat flow when the mounting plate 1 was recessed measured temperature of 339.3K and the heat flow deviation was 0.71%. The deviation of the heat flow of the mounting plate 1 painted with the black paint and the aluminum-plated film was compared. According to the calculation of the black sheet heat flow meter temperature 339.9K, the temperature measured by the heat flow meter when the mounting plate 1 is painted with black paint is 339.2K, the heat flow deviation is 0.83%, the temperature measured by the heat flow meter when the mounting plate 1 is coated with an aluminum plating film is 339.3K, and the heat flow deviation is 0.71%. In combination with the above analysis, the length of the mounting plate 1 was set to 120mm, the middle position of the mounting plate 1 was recessed by 10mm from each side, and the recess was coated with an aluminized polyester film.
The heat flow deviation of the cylindrical heat insulating mat and the I-shaped heat insulating mat was compared. The temperature measured by the heat flow meter when the cylindrical heat insulation pad is adopted is 339.1K and the heat flow deviation is 0.95 percent according to the calculation of 339.9K of the black sheet heat flow meter, and the temperature measured by the heat flow meter when the I-shaped heat insulation pad is adopted is 339.3K and the heat flow deviation is 0.71 percent.
And comparing the heat flow deviation of the front outgoing line and the back outgoing line of the heat flow meter. The temperature measured by the heat flow meter when the front face outgoing line is adopted is 338.1K and the heat flow deviation is 2.15 percent according to the calculation of the black sheet heat flow meter temperature 339.9K, and the temperature measured by the heat flow meter when the back face outgoing line is adopted is 339.3K and the heat flow deviation is 0.71 percent. The heat flow meter comprises a thermocouple, a fixed wire of the heat flow meter is routed from the back of the mounting plate 1, and a heating cage or an infrared lamp array is led out along the screw rod 2.
Through many optimizations, screw rod 2 adopts the stainless steel, mounting panel 1 adopts the polyimide material, screw rod 2 and the 1 surface cladding aluminized polyester film of mounting panel, and screw rod 2 is even to 1 one end of mounting panel, and black piece heat flow meter is placed to the other end, and mounting panel 1 is the concave design, and the heat flow meter lead wire back is qualified for the next round of competitions.
Wherein, the diameter of the screw rod 2 is 8mm, the length is 150mm, the length of the mounting plate 1 is 120mm, and the distance from the axis of the screw rod 2 to the center of the stepped hole is 100 mm. The diameter of the heat insulation pad 3 is 40.5mm, and the height of the heat insulation pad is 10 mm.
The temperature measured by the heat flow meter is calculated according to 339.9K of the black piece heat flow meter, the temperature measured by the heat flow meter before the optimization design is 337.8K, the heat flow deviation is 2.51%, the temperature measured by the heat flow meter after the optimization design is 339.3K, and the heat flow deviation is 0.71%.
The black piece heat flow meter is installed on heat insulating mattress 3, and screw rod 2 passes through the nut to be fixed on the bracing piece of infrared heating cage or the square pipe of infrared lamp battle array, and the heat flow meter is accomplished through adjusting screw 2 to the distance of heating surface, is close to the spacecraft surface as far as possible. The fixed line of heat flow meter passes through the extension line of thermocouple is followed the heat flow meter bottom is followed 1 of mounting panel is drawn forth, walks the line from 1 back of mounting panel, along screw rod 2 draws forth outside the heating surface of infrared heating cage or infrared lamp battle array, gathers the fixed line of all heat flow meters into a beam, welds to measuring plug, is measured by the heat flow of data acquisition system again.
The above description is only a preferred embodiment of the present application and an explanation of the technical principle used, and it should be understood by those skilled in the art that the scope of the present invention related to the present application is not limited to the technical solution of the specific combination of the above technical features, and also covers other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.
Claims (10)
1. The utility model provides a spacecraft vacuum heat test surface thermal current non-contact measuring device, a serial communication port, including support and black piece heat flow meter, the support includes screw rod and mounting panel, mounting panel one end sets up black piece heat flow meter, the other end is connected screw rod one end, the screw rod other end is used for being connected with the skeleton of infrared heating cage or infrared lamp battle array.
2. The non-contact measurement device for the heat flow on the vacuum thermal test surface of the spacecraft of claim 1, wherein the mounting plate is made of polyimide material, and the screw is made of stainless steel material.
3. The non-contact measuring device for measuring the heat flow on the vacuum thermal test surface of the spacecraft of claim 2, wherein the surfaces of the screw and the mounting plate are coated with aluminized polyester films.
4. The non-contact measurement device for the heat flow of the vacuum thermal test surface of the spacecraft of claim 3, wherein the length of the mounting plate is 120mm, the middle position of the mounting plate is recessed by 10mm from each of two sides, and the recessed position is coated with an aluminized polyester film.
5. The non-contact measuring device for the heat flow on the surface of the spacecraft vacuum thermal test according to claim 4, wherein the diameter of the screw is 8mm, the length of the screw is not less than 100mm, and the screw except for the part for contacting with the mounting plate and the heating cage or the infrared lamp array is coated with an aluminized polyester film.
6. The non-contact measurement device for heat flow of a spacecraft vacuum thermal test surface of claim 5, wherein the distance from the axis of the screw to the installation center of the heat flow meter is 100 mm.
7. The non-contact measuring device for the heat flow on the vacuum thermal test surface of the spacecraft of claim 1, wherein a heat insulation pad is arranged between the mounting plate and the black sheet heat flow meter, the heat insulation pad is fixedly connected with the mounting plate, and the black sheet heat flow meter is fixedly connected with the heat insulation pad.
8. The non-contact measurement device for the heat flow on the vacuum thermal test surface of the spacecraft of claim 7, wherein a stepped hole is formed in the end face, away from the mounting plate, of the heat insulation pad, a screw cap is received in the stepped hole through a bolt penetrating through the stepped hole, and the black sheet heat flow meter is bonded to the heat insulation pad.
9. The non-contact measuring device for the heat flow on the surface of the spacecraft vacuum thermal test according to claim 7, wherein the heat insulation pad is of an I-shaped structure, the maximum diameter position of the I-shaped structure is 40.5mm, the height of the I-shaped structure is 10mm, and the heat insulation pad is made of polyimide materials.
10. The non-contact measurement device for heat flow on a spacecraft vacuum thermal test surface of claim 1, wherein the heat flow meter comprises a thermocouple, a fixing line of the heat flow meter is led out from the bottom of the heat flow meter along the mounting plate through an extension line of the thermocouple, is routed from the back of the mounting plate, and is led out of a heating cage or an infrared lamp array along the screw rod.
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1035017A1 (en) * | 1999-03-11 | 2000-09-13 | Alcatel | Method for the simulation of the external thermal flows absorbed by spacecraft external radiator elements in flight and spacecraft for the application of said method |
| CN201293721Y (en) * | 2008-11-17 | 2009-08-19 | 北京卫星环境工程研究所 | Infrared heating cage for spacecraft vacuum heat test |
| CN102967623A (en) * | 2012-11-06 | 2013-03-13 | 上海卫星工程研究所 | Infrared lamp array heat-flow density calibration device and calibration method |
| CN103359298A (en) * | 2013-06-26 | 2013-10-23 | 上海卫星装备研究所 | Infrared heating cage heat flow density calibrating device |
| CN104062036A (en) * | 2014-06-11 | 2014-09-24 | 北京空间飞行器总体设计部 | Three-stage heat insulation type heat flow meter |
| CN104215659A (en) * | 2014-08-20 | 2014-12-17 | 上海卫星装备研究所 | Infrared lamp single-lamp radiation characteristic test system under vacuum thermal environment |
| CN109855752A (en) * | 2019-03-22 | 2019-06-07 | 华北电力大学 | A kind of contact temperature-measuring system of crimp type semiconductor device inside Temperature Distribution |
| CN110469760A (en) * | 2019-08-21 | 2019-11-19 | 北京卫星环境工程研究所 | Angle adjustable heat-flow meter mounting bracket |
-
2020
- 2020-08-11 CN CN202010799476.1A patent/CN111912548A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1035017A1 (en) * | 1999-03-11 | 2000-09-13 | Alcatel | Method for the simulation of the external thermal flows absorbed by spacecraft external radiator elements in flight and spacecraft for the application of said method |
| CN201293721Y (en) * | 2008-11-17 | 2009-08-19 | 北京卫星环境工程研究所 | Infrared heating cage for spacecraft vacuum heat test |
| CN102967623A (en) * | 2012-11-06 | 2013-03-13 | 上海卫星工程研究所 | Infrared lamp array heat-flow density calibration device and calibration method |
| CN103359298A (en) * | 2013-06-26 | 2013-10-23 | 上海卫星装备研究所 | Infrared heating cage heat flow density calibrating device |
| CN104062036A (en) * | 2014-06-11 | 2014-09-24 | 北京空间飞行器总体设计部 | Three-stage heat insulation type heat flow meter |
| CN104215659A (en) * | 2014-08-20 | 2014-12-17 | 上海卫星装备研究所 | Infrared lamp single-lamp radiation characteristic test system under vacuum thermal environment |
| CN109855752A (en) * | 2019-03-22 | 2019-06-07 | 华北电力大学 | A kind of contact temperature-measuring system of crimp type semiconductor device inside Temperature Distribution |
| CN110469760A (en) * | 2019-08-21 | 2019-11-19 | 北京卫星环境工程研究所 | Angle adjustable heat-flow meter mounting bracket |
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