CN106218925A - Suction ripple Orbital heat flux analog systems for large-scale microwave flat antenna vacuum thermal test - Google Patents
Suction ripple Orbital heat flux analog systems for large-scale microwave flat antenna vacuum thermal test Download PDFInfo
- Publication number
- CN106218925A CN106218925A CN201610565163.3A CN201610565163A CN106218925A CN 106218925 A CN106218925 A CN 106218925A CN 201610565163 A CN201610565163 A CN 201610565163A CN 106218925 A CN106218925 A CN 106218925A
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- test
- heat flux
- vacuum thermal
- microwave antenna
- analog systems
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/002—Thermal testing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/08—Measuring electromagnetic field characteristics
- G01R29/10—Radiation diagrams of antennas
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
- B64G2007/005—Space simulation vacuum chambers
Abstract
The invention discloses the suction ripple Orbital heat flux analog systems carrying out antenna performance test in a kind of Large Spacecraft microwave antenna vacuum thermal test in environmental space chamber, mainly include inhaling wave apparatus, aerial mounting structure, heating system, cold plate system, test bracket and infrared heating cage.Absorbing material utilizes notch to be fixed on installing plate, and paste to strengthen heat-conducting effect with silica gel in bottom surface, absorbing material installing plate is fixed on installation frame, installing plate outer surface installs heating system according to uniformity result of calculation, inhale and be mounted with that cold plate system, aerial mounting structure possess horizontal adjustment function below wave apparatus.The present invention solves wireless test and the technical problem of Orbital heat flux simulation when spacecraft whole device vacuum thermal test participated in by large-scale microwave antenna, it is applicable to large-scale microwave antenna vacuum thermal test, improve experimental test effectiveness and spreadability, it is possible to be applicable to be equipped with the spacecraft thermal vacuum test of large-scale microwave antenna.
Description
Technical field
The invention belongs to spacecraft large-scale microwave antenna ground vacuum heat test field, in particular it relates to one
Plant and carry out the suction ripple Orbital heat flux thermal simulation system used by vacuum thermal test on ground, for mould for the large-scale microwave antenna of spacecraft
Intend Microwave emission power absorption when antenna Orbital heat flux in-orbit and antenna power test.
Background technology
Spacecraft thermal vacuum test is in the vacuum of regulation and the checking various performance of spacecraft and function under thermal cycle conditions
Test.It is one of important tests in the multinomial environmental simulation test of spacecraft positive sample development stage.The main purpose of test
It is to make spacecraft expose material and the manufacturing process defect of spacecraft under vacuum with thermal cycle conditions, get rid of initial failure, from
And substantially increase spacecraft reliability in orbit.
In spacecraft thermal vacuum test, except vacuum to be simulated, cryogenic conditions, and the temperature of assembly on spacecraft is entered
Row control outside, in addition it is also necessary to carry out spacecraft performance synthesis test, the spreadability of test event for improve spacecraft development quality,
Guarantee that Mission Success is the most necessary.
Along with the development of China's spacecraft technology, in spacecraft thermal vacuum test, massive phased array antenna, satellite are dissipated
The wireless test demand penetrating the microwave load systems such as meter, radiometer gets more and more, and carries out inhaling ripple Orbital heat flux simulation analysis work
Making, for abundant spacecraft ground research technique, improving spacecraft parts ground vacuum heat test test coverage has important
Meaning.
Wireless test refers to use absorbing material to substitute load, and compared with wired test, wireless test has more advantage.
Test mode is true, when test, absorbs the radiation of microwave loaded antennas front by can be used for the absorbing material of thermal vacuum test
The electromagnetic wave sent, is not required to destroy the cable connection state of microwave loaded antennas, more consistent with state in-orbit；Test relevant equipment
Simply, when test, it is no longer necessary to plug the cable of thousands of bundle, it is only necessary to supporting suction wave apparatus；Highly versatile, inhales ripple material
Expect modular mentality of designing, be suitable for the test of various microwave load, it is not necessary to do extra cable auxiliary work.
Inhale ripple Orbital heat flux analog systems and extend in the test of all microwave class load tests, before there is wide application
Scape, for improving spacecraft thermal vacuum test technical merit, improves the comprehensive and covering of whole star and subsystem heat test test
Property is significant.
Summary of the invention
The goal of the invention of the present invention is to provide and a kind of carries out wireless test on ground for the large-scale microwave antenna of spacecraft
The suction ripple Orbital heat flux analog systems of vacuum thermal test.This system can carry out antenna under vacuum, low temperature environment and arrive exterior-heat
Flow control, can absorb Microwave emission energy during antenna power test, it is ensured that antenna modeling operation on orbit state, improves spacecraft whole
Device and the verity of antenna wireless test.
The present invention seeks to be achieved through the following technical solutions:
For the suction ripple Orbital heat flux analog systems of large-scale microwave antenna vacuum thermal test, mainly include being installed on below antenna
Suction wave apparatus, heater, test cold drawing, test bracket and aerial mounting structure, wherein, inhale wave apparatus by absorbing material,
Aluminium alloy mounting base and stainless steel frame composition, the mode that absorbing material utilizes draw-in groove and silica gel to paste is fixed on aluminium alloy peace
On dress base plate, aluminium alloy mounting base is screwed in stainless steel frame；Heater is pasted on aluminium alloy mounting base
Outer surface, its size and heating power precalculate and determine, paste, at every piece according to the uniformity requirement distribution of Orbital heat flux simulation
Paste a temperature measuring point on the absorbing material that aluminium alloy mounting base is corresponding, utilize programmable power supply to power and carry out Temperature Feedback control
System；Inhaling, bottom wave apparatus, test cold drawing is set, to ensure to inhale the cooling-down effect of wave apparatus, the feed flow inlet/outlet pipe of test cold drawing
Road layout type determines according to Flow Field Calculation result；Inhale wave apparatus and test cold drawing is mounted on test bracket, Liang Zhefen
It is not provided with the mounting interface of correspondence；The aerial mounting structure being arranged on test bracket by some indium steel matter install column and
Heat insulation and controlling temperature structure forms, and single column is provided with horizontal adjustment function, is better than 1mm/1000mm, inhales after the regulation of integral level degree
Wave apparatus and test cold drawing all carry out perforate process corresponding to aerial mounting structure distributing position, in order to single column passes perforate
Supporting the interface of large-scale microwave antenna, aerial mounting structure surface is first with the heat insulation multilayer coating structure of metallized film, then uses suction ripple
Multilayer material is covered by material.
Wherein, using screw fastening to install between aluminium alloy mounting base and stainless steel frame, stainless steel frame is divided into four
Segmentation structure, each several part uses locating pin structure splicing to install.
Wherein, heater uses thin film heater or resistance heating rod, right at it for each aluminium alloy mounting base
Answer absorbing material surface mount thermocouple, test carries out temperature feedback control, by adjusting absorbing material temperature and then control
Antenna surface arrives hot-fluid.
Wherein, inhaling installation test cold drawing bottom wave apparatus, testing cold drawing during test and participate in space environment simulation container
Liquid nitrogen circulates, and maintains and stablizes low temperature boundary temperature.
Wherein, heat insulation and controlling temperature structure to mounting structure surface and the temperature tracing control installed between column to compensate leakage
Heat.
Wherein, absorbing material is made up of carborundum Wedge structure.
Wherein, test cold drawing is the test cold drawing of the swollen plate structure with liquid nitrogen cooling.
Wherein, inhale ripple Orbital heat flux analog systems and also include being arranged on the infrared heating cage inhaling wave apparatus upper surface of antenna,
Simulate for upper antenna surface Orbital heat flux.
The present invention designs by absorbing material is combined structure, and the method controlled in conjunction with high/low temperature solves large-scale
Microwave antenna carries out the technological difficulties of Orbital heat flux simulation and wireless test in vacuum thermal test simultaneously, have microwave antenna or
When the spacecraft of other type microwave load carries out vacuum thermal test, it is possible to meet microwave load wireless test demand, make space flight
Device and microwave load obtain comprehensive assessment.
Accompanying drawing explanation
Fig. 1 is that the structure inhaling ripple Orbital heat flux analog systems being applicable to large-scale microwave antenna vacuum thermal test of the present invention is shown
It is intended to.
Wherein, 1 for inhaling wave apparatus；2 is heater；3 is test cold drawing；4 is test bracket；5 is aerial mounting structure；
6 is infrared heating cage.
Fig. 2 is for being installed on suction wave apparatus to obtain heater schematic layout pattern.
Detailed description of the invention
Introduced below is the detailed description of the invention as content of the present invention, below by detailed description of the invention to this
The described content of invention further illustrates.Certainly, the not Tongfang that following detailed description is only the example present invention is described
The content in face, and should not be construed as limiting the invention scope.
The present invention is the Microwave emission power absorption when large-scale microwave antenna carries out vacuum thermal test and Orbital heat flux mould
The suction ripple Orbital heat flux analog systems intended, structure, as it is shown in figure 1, the suction ripple Orbital heat flux analog systems of the present invention, mainly includes inhaling ripple
Device 1, heater 2 (thin film heater or heating plate), with liquid nitrogen cooling the test cold drawing 3 of swollen plate structure, bottom arrange
Roll the test bracket 4 of opinion, aerial mounting structure 5 and infrared heating cage 6.Wherein, wave apparatus 1 is inhaled by absorbing material (carborundum
Wedge structure is constituted), aluminium alloy mounting base and stainless steel frame composition, inhale the shape phase of the shape of wave apparatus and antenna to be measured
It is suitable for, according to antenna envelope dimensional requirement design corresponding size and shape, when being designed as rectangular structure as shown in Figure 1, its end
Portion and sidepiece are all made up of absorbing material close-packed arrays and (for there being the position of construction opening, absorbing material need to be used notch part
Position is repaired, to reduce system leaky wave), the mode that absorbing material utilizes draw-in groove and silica gel to paste is fixed on aluminium alloy installs the end
On plate, aluminium alloy mounting base is screwed in stainless steel frame；Heater 2 is fixed on aluminium alloy mounting base appearance
Face, its size and heating power are determined by calculating, paste according to the uniformity requirement distribution of Orbital heat flux simulation, for ensureing temperature
Control effect, the absorbing material that every piece of mounting base is corresponding pasted a temperature measuring point, utilize programmable power supply power into
Trip temperature feedback control；Test cold drawing 3 is installed on bottom suction wave apparatus, to ensure to inhale the cooling-down effect of wave apparatus, cold drawing feed flow
Import and export pipeline layout type to determine according to Flow Field Calculation result；Inhale wave apparatus 1 and test cold drawing 3 is mounted on test bracket 4
On, the mounting interface of correspondence has been separately designed according to both interface requirements；Aerial mounting structure 5 is installed by 24 indium steel matter
Column and heat insulation and controlling temperature structure composition, single column is provided with horizontal adjustment function, can be better than 1mm/ after the regulation of integral level degree
1000mm, inhales wave apparatus 1 and test cold drawing 3 all carries out perforate process corresponding to aerial mounting structure 5 distributing position, and antenna is installed
Structure 5 surface is first with the heat insulation multilayer coating structure of metallized film, then uses absorbing material to cover multilayer material, it is possible to reduce
Column temperature controls the impact of effect to system temperature, and the system entirety avoiding metal surface to cause microwave reflection inhales ripple
Performance impact.Infrared heating cage 6 is installed on antenna and inhales wave apparatus 1 upper surface, is mainly used in the simulation of upper antenna surface Orbital heat flux, and
Heating arranges 2 outer surfaces being arranged on whole suction wave apparatus.
In one embodiment, absorbing material and the aluminium alloy mounting base of inhaling wave apparatus use draw-in groove and silica gel to paste phase
In conjunction with mounting means, between aluminium alloy mounting base and stainless steel frame use screw fastening install, stainless steel frame is divided into
Four-part form structure, each several part uses locating pin structure splicing to install.
In one embodiment, heater can use thin film heater or resistance heating rod, pacifies for each aluminium alloy
Dress base plate, at its corresponding absorbing material surface mount thermocouple, carries out temperature feedback control in test, by adjusting absorbing material
Temperature and then control antenna surface arrive hot-fluid.
In one embodiment, inhaling installation test cold drawing bottom wave apparatus, during test, cold plate system participates in spatial loop
Border simulation container liquid nitrogen circulation, maintains and stablizes low temperature boundary temperature.
In one embodiment, aerial mounting structure is installed column by indium steel matter and heat insulation and controlling temperature structure forms, and can enter
The levelness regulation in row integral installation face, and the temperature tracing control between mounting structure surface and installation column is to compensate leakage
Heat.
In one embodiment, infrared heating cage is installed on antenna and inhales wave apparatus upper surface, is mainly used in upper antenna surface
Orbital heat flux is simulated.
In specific implementation process, determine suction wave apparatus and test cold drawing size according to the size of antenna, according to sky
Line mounting interface position determines antenna mounting interface position, inhales wave apparatus and test cold drawing determines position of opening.According to outside antenna
The specific requirement design heating devices heat power of heat flux simulation, determines heater mounting arrangement according to uniformity result of calculation
See Fig. 2, Fig. 2 for being installed on suction wave apparatus to obtain heater schematic layout pattern.And infrared heating cage can be fixedly installed in suction
Wave apparatus framework, it is possible to be fixed on other correct position in environmental space chamber.
Test bracket design needs to consider the factors such as load-bearing, mounting interface and transhipment.Test bracket design should possess antenna,
Inhale wave apparatus and the respective independently installed interface of cold drawing.Relatively greatly and to deformation, strict test bracket is required for load-bearing, can press
It is designed as frame structure shown in Fig. 1, and carries out deformation analysis, under simple condition, test bracket form can be simplified.My god
Line mounting structure column design position should match with antenna mounting interface, meets the security requirement that antenna is installed, indium steel
Matter can at utmost avoid material temperature to change the deformation caused and then the change of the structure mounting plane degree caused, if adopted
With rustless steel or other material, column temperature is answered to be controlled, it is to avoid the mounting interface deformation that each column excessive temperature differentials causes
The antenna mounting interface being likely to result in damages.
During vacuum thermal test, according to absorbing material temperature control features, design the control journey corresponding to heater
Sequence, absorbing material temperature uses thermocouple measurement, controls absorbing material temperature by adjusting heater supply current, and then
Reach to control antenna surface and arrive the purpose of hot-fluid.
Although the detailed description of the invention to the present invention gives detailed description and illustrates above, but it should be noted that
Those skilled in the art can carry out various equivalence according to the spirit of the present invention to above-mentioned embodiment and change and amendment, its institute
Produce function contained without departing from description and accompanying drawing spiritual time, all should be within scope.
Claims (10)
1., for the suction ripple Orbital heat flux analog systems of large-scale microwave antenna vacuum thermal test, mainly include being installed on below antenna
Inhale wave apparatus, heater, test cold drawing, test bracket and aerial mounting structure, wherein, inhale wave apparatus by absorbing material, aluminum
Alloy mounting base and stainless steel frame composition, the mode that absorbing material utilizes draw-in groove and silica gel to paste is fixed on aluminium alloy installs
On base plate, aluminium alloy mounting base is screwed in stainless steel frame；Heater is pasted on outside aluminium alloy mounting base
Surface, its size and heating power precalculate and determine, paste, at every block of aluminum according to the uniformity requirement distribution of Orbital heat flux simulation
Paste a temperature measuring point on the absorbing material that alloy mounting base is corresponding, utilize programmable power supply to power and carry out Temperature Feedback control
System；Inhaling, bottom wave apparatus, test cold drawing is set, to ensure to inhale the cooling-down effect of wave apparatus, the feed flow inlet/outlet pipe of test cold drawing
Road layout type determines according to Flow Field Calculation result；Inhale wave apparatus and test cold drawing is mounted on test bracket, Liang Zhefen
It is not provided with the mounting interface of correspondence；The aerial mounting structure being arranged on test bracket by some indium steel matter install column and
Heat insulation and controlling temperature structure forms, and single column is provided with horizontal adjustment function, higher than 1mm/1000mm after the regulation of integral level degree, inhales
Wave apparatus and test cold drawing all carry out perforate process corresponding to aerial mounting structure distributing position, in order to single column passes perforate
Supporting the interface of large-scale microwave antenna, aerial mounting structure surface is first with the heat insulation multilayer coating structure of metallized film, then uses suction ripple
Multilayer material is covered by material.
The suction ripple Orbital heat flux analog systems of large-scale microwave antenna vacuum thermal test the most as claimed in claim 1, wherein, aluminium alloy
Using screw fastening to install between mounting base and stainless steel frame, stainless steel frame is divided into four-part form structure, and each several part uses
Locating pin structure splicing is installed.
The suction ripple Orbital heat flux analog systems of large-scale microwave antenna vacuum thermal test the most as claimed in claim 1, wherein, adds hot charging
Put employing thin film heater or resistance heating rod, for each aluminium alloy mounting base in its corresponding absorbing material surface mount heat
Galvanic couple, carries out temperature feedback control in test, by adjusting absorbing material temperature and then controlling antenna surface arrival hot-fluid.
The suction ripple Orbital heat flux analog systems of large-scale microwave antenna vacuum thermal test the most as claimed in claim 1, wherein, is inhaling ripple
Bottom of device installation test cold drawing, tests cold drawing and participates in the circulation of space environment simulation container liquid nitrogen during test, maintenance is stablized low
Temperature boundary temperature.
5. the suction ripple Orbital heat flux analog systems of the large-scale microwave antenna vacuum thermal test as described in any one of claim 1-4, its
In, heat insulation and controlling temperature structure is hot to compensate leakage to mounting structure surface and the temperature tracing control installed between column.
6. the suction ripple Orbital heat flux analog systems of the large-scale microwave antenna vacuum thermal test as described in any one of claim 1-4, its
In, absorbing material is made up of carborundum Wedge structure.
7. the suction ripple Orbital heat flux analog systems of the large-scale microwave antenna vacuum thermal test as described in any one of claim 1-4, its
In, test cold drawing is the test cold drawing of the swollen plate structure with liquid nitrogen cooling.
8. the suction ripple Orbital heat flux analog systems of the large-scale microwave antenna vacuum thermal test as described in any one of claim 1-4, its
In, inhale ripple Orbital heat flux analog systems and also include being arranged on the infrared heating cage inhaling wave apparatus upper surface of antenna, for antenna
Surface Orbital heat flux simulation.
9. the suction ripple Orbital heat flux analog systems of the large-scale microwave antenna vacuum thermal test as described in any one of claim 1-4, its
In, test bracket is composite steel shelf structure.
The suction ripple Orbital heat flux analog systems of large-scale microwave antenna vacuum thermal test the most as claimed in claim 9, wherein, test
The bottom of support arranges rolling opinion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201610565163.3A CN106218925B (en) | 2016-07-18 | 2016-07-18 | Suction wave Orbital heat flux simulation system for large-scale microwave flat antenna vacuum thermal test |
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| CN201610565163.3A CN106218925B (en) | 2016-07-18 | 2016-07-18 | Suction wave Orbital heat flux simulation system for large-scale microwave flat antenna vacuum thermal test |
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| CN106218925B CN106218925B (en) | 2018-09-18 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107121672A (en) * | 2017-05-16 | 2017-09-01 | 上海卫星工程研究所 | The radar satellite vacuum thermal test method of ripple cover is inhaled based on microwave |
| CN107390346A (en) * | 2017-09-19 | 2017-11-24 | 北京仿真中心 | A kind of infrared field lens device of Low emissivity |
| CN107985638A (en) * | 2017-11-27 | 2018-05-04 | 上海卫星装备研究所 | Free form surface Orbital heat flux simulator |
| CN108216694A (en) * | 2017-12-27 | 2018-06-29 | 中国科学院国家空间科学中心 | A kind of more equipment thermal vacuum test facilities |
| CN109398768A (en) * | 2018-10-23 | 2019-03-01 | 北京卫星环境工程研究所 | Super large infrared heat flow simulator suitable for space station bay section grade spacecraft |
| CN109625343A (en) * | 2018-12-10 | 2019-04-16 | 上海卫星装备研究所 | Edge compensation formula Orbital heat flux simulator |
| CN109682603A (en) * | 2017-10-18 | 2019-04-26 | 北京机电工程研究所 | The ground experiment of subsonic speed bay section grade thermal control design verifies system |
| CN111239502A (en) * | 2020-03-04 | 2020-06-05 | 湖南人文科技学院 | Distributed microwave radiometer system based on leaky-wave antenna |
| CN111338401A (en) * | 2020-03-06 | 2020-06-26 | 北京卫星环境工程研究所 | Multi-temperature-zone temperature control device based on large-temperature-difference environment |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107121672A (en) * | 2017-05-16 | 2017-09-01 | 上海卫星工程研究所 | The radar satellite vacuum thermal test method of ripple cover is inhaled based on microwave |
| CN107390346A (en) * | 2017-09-19 | 2017-11-24 | 北京仿真中心 | A kind of infrared field lens device of Low emissivity |
| CN109682603B (en) * | 2017-10-18 | 2020-07-21 | 北京机电工程研究所 | Ground test verification system for subsonic cabin stage thermal control design |
| CN109682603A (en) * | 2017-10-18 | 2019-04-26 | 北京机电工程研究所 | The ground experiment of subsonic speed bay section grade thermal control design verifies system |
| CN107985638A (en) * | 2017-11-27 | 2018-05-04 | 上海卫星装备研究所 | Free form surface Orbital heat flux simulator |
| CN108216694A (en) * | 2017-12-27 | 2018-06-29 | 中国科学院国家空间科学中心 | A kind of more equipment thermal vacuum test facilities |
| CN109398768A (en) * | 2018-10-23 | 2019-03-01 | 北京卫星环境工程研究所 | Super large infrared heat flow simulator suitable for space station bay section grade spacecraft |
| CN109625343A (en) * | 2018-12-10 | 2019-04-16 | 上海卫星装备研究所 | Edge compensation formula Orbital heat flux simulator |
| CN109625343B (en) * | 2018-12-10 | 2022-03-29 | 上海卫星装备研究所 | Edge compensation type external heat flow simulation device |
| CN111239502A (en) * | 2020-03-04 | 2020-06-05 | 湖南人文科技学院 | Distributed microwave radiometer system based on leaky-wave antenna |
| CN111239502B (en) * | 2020-03-04 | 2022-01-28 | 湖南人文科技学院 | Distributed microwave radiometer system based on leaky-wave antenna |
| CN111338401A (en) * | 2020-03-06 | 2020-06-26 | 北京卫星环境工程研究所 | Multi-temperature-zone temperature control device based on large-temperature-difference environment |
| CN111338401B (en) * | 2020-03-06 | 2022-02-11 | 北京卫星环境工程研究所 | Multi-temperature-zone temperature control device based on large-temperature-difference environment |
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|---|---|
| CN106218925B (en) | 2018-09-18 |
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