CN113050456A - Ground simulation test system for near space aerostat - Google Patents
Ground simulation test system for near space aerostat Download PDFInfo
- Publication number
- CN113050456A CN113050456A CN202110331999.8A CN202110331999A CN113050456A CN 113050456 A CN113050456 A CN 113050456A CN 202110331999 A CN202110331999 A CN 202110331999A CN 113050456 A CN113050456 A CN 113050456A
- Authority
- CN
- China
- Prior art keywords
- sealed cabin
- simulator
- test
- cabin
- environment
- 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.)
- Pending
Links
- 238000004088 simulation Methods 0.000 title claims abstract description 35
- 230000005855 radiation Effects 0.000 claims abstract description 22
- 230000001105 regulatory effect Effects 0.000 claims description 10
- 230000008602 contraction Effects 0.000 claims description 7
- 230000000694 effects Effects 0.000 claims description 5
- 238000009413 insulation Methods 0.000 claims description 5
- 230000000087 stabilizing effect Effects 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 4
- 238000003825 pressing Methods 0.000 claims description 3
- 229910052724 xenon Inorganic materials 0.000 claims description 3
- FHNFHKCVQCLJFQ-UHFFFAOYSA-N xenon atom Chemical compound [Xe] FHNFHKCVQCLJFQ-UHFFFAOYSA-N 0.000 claims description 3
- RNFJDJUURJAICM-UHFFFAOYSA-N 2,2,4,4,6,6-hexaphenoxy-1,3,5-triaza-2$l^{5},4$l^{5},6$l^{5}-triphosphacyclohexa-1,3,5-triene Chemical compound N=1P(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP=1(OC=1C=CC=CC=1)OC1=CC=CC=C1 RNFJDJUURJAICM-UHFFFAOYSA-N 0.000 claims description 2
- 230000005494 condensation Effects 0.000 claims description 2
- 238000009833 condensation Methods 0.000 claims description 2
- 238000013016 damping Methods 0.000 claims description 2
- 238000005265 energy consumption Methods 0.000 claims description 2
- 239000003063 flame retardant Substances 0.000 claims description 2
- 230000003068 static effect Effects 0.000 claims description 2
- 230000007613 environmental effect Effects 0.000 abstract description 3
- 238000001514 detection method Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000003466 welding Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B17/00—Systems involving the use of models or simulators of said systems
- G05B17/02—Systems involving the use of models or simulators of said systems electric
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention relates to the technical field of near space aerostats, and provides a ground simulation test system for a near space aerostat. The sealed cabin provides a sealed test environment for the aerostat; the temperature control device realizes the control of the temperature of the sealed cabin and simulates the temperatures at different heights; the solar irradiation simulator is positioned right above the sealed cabin and provides a solar irradiation environment for a test target; the earth simulator is characterized in that ground radiation simulation equipment is positioned at the lower end of the sealed cabin, background infrared radiation and earth albedo solar radiation are simulated, and ground radiation characteristics of different orbit heights and different earth areas are realized; the pressure simulator provides a low-pressure environment for the sealed cabin; the wind field simulator provides wind field environments with different wind speeds for the sealed cabin; the attitude adjusting mechanism is used for simulating multiple horizontal, pitching and rotating attitudes. The invention constructs a set of test box which is close to the high-altitude environment characteristic of a zero-wind layer, and successfully realizes the simulation of various environmental factors such as solar irradiation, ground radiation, high-altitude wind, low-temperature and low-pressure environment and the like.
Description
Technical Field
The invention relates to the technical field of near space aerostats, in particular to a ground simulation test system of a near space aerostat.
Background
Most of the near space aerostats operate in an stratospheric environment (a zero wind layer with the height of about 20 km), are influenced by various factors such as solar irradiation, ground radiation, high-altitude airflow and the like in the working process, a performance verification test needs to be carried out on the ground stage in order to verify the reliability of an electronic product in the using process, and the reliability test is based on the principle that the influence of environmental factors on the product in the actual using process is simulated to expose the defects of the product, so that the real working environment condition is simulated as much as possible.
Most of the published patents at present mainly refer to temperature and air pressure environment simulation, for example, a practical novel patent "environment simulation detection device" (CN 212040489U) published in 5 months 2020 is provided with an environment simulation detection device which can meet the control of temperature, humidity, constant temperature time, temperature rise and drop rate and the like; the invention patent (CN 112093076A) published in 9.2020 of patent for high altitude environment test parameter control system under large flow ventilation environment realizes the simulation of temperature, altitude and humidity parameters required by the test by means of air circulation; for the simulation test of the near space aerostat in the multi-element high-altitude environment, no test system or device which can be applied is available at present.
Disclosure of Invention
The invention aims to provide a ground simulation test system for an aerostat in the near space, which is used for constructing a complex zero-wind-layer environment in a simulator mode and solving the technical problem that key equipment and devices of the aerostat cannot be effectively verified to work effectively in the high-altitude environment in the ground stage.
In order to achieve the above purpose and solve the related technical problems, the technical scheme provided by the invention is as follows:
a ground simulation test system for an approaching space aerostat comprises a sealed cabin, a temperature control device, a solar simulator, an earth simulator, a pressure simulator, a wind field simulator and a posture adjusting mechanism;
the sealed cabin is a main cabin body of the simulation test system and provides a sealed test environment for the aerostat; the sealed cabin adopts standard dovetail groove and O-shaped ring sealing measures, and adopts a pressing device to avoid cabin door leakage;
the temperature control device is positioned above the sealed cabin, one side of the solar irradiation simulator is directly connected with the sealed cabin and mainly comprises a refrigerating unit, an electric heater and circulating air, the circulating air enables air to flow through a fan to generate circulation, heat generated by the electric heater or cold generated by the refrigerating unit is brought into the sealed cabin in an air circulation mode, the temperature of the sealed cabin is controlled, and the temperatures with different heights are simulated;
the solar irradiation simulator is positioned right above the sealed cabin and provides a solar irradiation environment for a test target, the solar irradiation simulator is connected with a power supply and then excites a xenon lamp light source, and the incident angle of the sun is adjusted by adjusting a reflector, so that the solar angles in different seasons and different times are simulated, and diversified test requirements are met;
the earth simulator is ground radiation simulation equipment, is positioned at the lower end of the sealed cabin, provides a ground radiation environment for a test target, mainly simulates background infrared radiation and earth albedo solar radiation, and can realize ground radiation characteristics of different orbit heights and different earth areas;
the pressure simulator is positioned on one side of the sealed cabin, provides a low-pressure environment for the sealed cabin, and consists of a vacuum pump, a pressure regulating valve and an electric heater, wherein the vacuum pump sucks air from the inside of the test cabin, the electric heater is used for ensuring that the air temperature at the inlet of the vacuum pump is higher than 0 ℃ when the electric heater is used for a low-temperature test, and the pressure regulating valve is used for regulating the state of the vacuum pump and releasing air to restore the pressure;
the wind field simulator is positioned on the other side of the sealed cabin and provides wind field environments with different wind speeds for the sealed cabin;
the attitude adjusting mechanism is positioned in the sealed cabin and used for simulating multiple horizontal, pitching and rotating attitudes, and the test of the aerostat is realized by programming and driving the attitude adjusting mechanism.
Compared with the prior art, the invention has the following effective benefits:
1. the invention successfully realizes the simulation of various environmental factors such as solar irradiation, ground radiation, high-altitude wind, low-temperature and low-pressure environment and the like by adopting various simulators.
2. The test box with the characteristics close to the high-altitude environment of the zero wind layer is constructed, and the environment adaptability of key equipment such as a solar cell array, navigation equipment, a power supply system and the like of the aerostat in the near space can be verified by installing the attitude adjusting mechanism, so that the test box has important significance for ensuring that the aerostat has no quality problem in the day.
Drawings
FIG. 1 is a schematic structural diagram of a ground simulation test system of an aerostat in the near space of the present invention;
FIG. 2 illustrates the working principle of the solar irradiation simulation apparatus of the present invention;
fig. 3 is a schematic view of the main structure of the wind field simulator of the present invention.
Wherein, 1-blower, 2-stable section, 3-contraction section and 4-opening test section
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
The solar cell is laid on the surface area of the aerostat to generate electric energy, the energy management system with the voltage conversion device is used for supplying power to the motor and the boat-mounted flight service equipment, redundant partial energy is transferred to the corresponding boat-mounted energy storage battery, and the motor drives the propeller to achieve high-altitude wind-resistant movement. In order to comprehensively test and verify the performance of main equipment of the aerostat in the ground stage, the invention provides a multi-element high-altitude environment simulation system, which realizes ground examination on low-dynamic near space aerostat equipment.
The ground simulation test system of the near space aerostat is mainly composed of a sealed cabin, a temperature control device, a solar simulator, an earth simulator, a pressure simulator, a wind field simulator and a posture adjusting mechanism, wherein the sealed cabin, the temperature control device, the solar simulator, the earth simulator, the pressure simulator, the wind field simulator and the posture adjusting mechanism are arranged in the sealed cabin;
the sealed cabin is a main cabin body of the simulation test system and provides a sealed test environment for the aerostat, a test piece can be directly subjected to an environment test in the sealed cabin body, and the peripheral temperature control device, the solar simulator, the earth simulator, the pressure simulator and the wind field simulator are connected with the cabin body to realize the treatment of air in the cabin body;
the sealed cabin can adopt standard dovetail groove and O-shaped ring sealing measures and adopts a pressing device, so that the leakage quantity of the cabin door is ensured to be minimum, the welding quality of welding seams of the cabin body and the sealing head is improved, and the leakage detection of the vacuum container is carried out;
the temperature control device is positioned above the sealed cabin, one side of the solar irradiation simulator is directly connected with the sealed cabin and mainly comprises a refrigerating unit, an electric heater and circulating air, the circulating air enables air to flow through a fan to generate circulation, heat generated by the electric heater or cold generated by the refrigerating unit is brought into the sealed cabin in an air circulation mode, the temperature of the sealed cabin is controlled, and the temperatures with different heights are simulated;
in order to reduce the energy consumption of the system and improve the temperature control speed, effective heat insulation protection is provided for the sealed cabin, a heat insulation material can be added on the outer surface of the sealed cabin, the heat insulation layer can resist high temperature and has flame retardant property, and the thickness of the heat insulation layer can be properly increased in order to avoid the condensation condition outside the cabin during low temperature test;
the solar irradiation simulator is positioned right above the sealed cabin and provides a solar irradiation environment for a test target, the main working principle of the solar irradiation simulator is shown in figure 2, the device is connected with a power supply and then excites a xenon lamp light source, and testers adjust the incident angle of the sun by adjusting a reflector, simulate the solar angles at different times in different seasons and meet diversified test requirements;
the earth simulator is ground radiation simulation equipment, is positioned at the lower end of the sealed cabin, provides a ground radiation environment for a test target, mainly simulates background infrared radiation and earth albedo solar radiation, and can realize ground radiation characteristics of different orbit heights and different earth areas;
the pressure simulator is positioned on one side of the sealed cabin, can provide a low-pressure environment for the sealed cabin, and mainly comprises a vacuum pump, a pressure regulating valve, an electric heater and the like, wherein the vacuum pump sucks air from the inside of the test cabin body, the heater is mainly used for ensuring that the air temperature at the inlet of the vacuum pump is higher than 0 ℃ during a low-temperature test, and the regulating valve is used for regulating the state of the vacuum pump and releasing air to recover the pressure, so that the atmospheric pressure simulation within the height range of 0-20 km; in fact, in a high-altitude range of 0-20 kilometers, the maximum wind speed in a rush current area can reach 50m/s, most aerostats run in a zero wind layer, the wind speed is usually less than 10m/s, a fan is realized in an axial flow motor mode, the maximum wind speed can be realized by increasing the rotating speed of the motor by 50m/s, but the air pressure in a cabin vibrates, the environment simulation effect is influenced, and therefore the environment simulation effect is better when the wind speed is controlled within 20 m/s.
The wind field simulator is positioned at the other side of the sealed cabin, can provide wind field environments with different wind speeds for the sealed cabin, mainly comprises a fan 1, a stable section 2, a contraction section 3 and an opening test section 4, wherein the fan 1 can adopt an axial flow fan, the rotating speed of the fan is controlled through a frequency converter, the wind speed in the sealed cabin is regulated, and the maximum simulated wind speed can reach 20 m/s;
the wind field simulator stabilizing section 2 mainly has the function of eliminating airflow vortexes at the outlet of the fan 1, and a layer of honeycomb device and a damping net can be arranged in the stabilizing section to achieve a better effect;
the contraction section 3 of the wind field simulator is mainly used for adjusting the airflow of the test section, a five-stage contraction curve design is adopted, and static pressure measuring holes are formed in four surfaces of an outlet of the contraction section so as to ensure the stability of the airflow of the test section;
the attitude adjusting mechanism is positioned in the sealed cabin and used for simulating multiple attitudes of level, pitch, rotation and the like, and testers drive the attitude adjusting mechanism through programming to realize the test of the aerostat.
Claims (7)
1. A ground simulation test system for an aerostat in a near space is characterized by comprising a sealed cabin, a temperature control device, a solar simulator, an earth simulator, a pressure simulator, a wind field simulator and a posture adjusting mechanism;
the sealed cabin is a main cabin body of the simulation test system and provides a sealed test environment for the aerostat; the sealed cabin adopts standard dovetail groove and O-shaped ring sealing measures, and adopts a pressing device to avoid cabin door leakage;
the temperature control device is positioned above the sealed cabin, one side of the solar irradiation simulator is directly connected with the sealed cabin and mainly comprises a refrigerating unit, an electric heater and circulating air, the circulating air enables air to flow through a fan to generate circulation, heat generated by the electric heater or cold generated by the refrigerating unit is brought into the sealed cabin in an air circulation mode, the temperature of the sealed cabin is controlled, and the temperatures with different heights are simulated;
the solar irradiation simulator is positioned right above the sealed cabin and provides a solar irradiation environment for a test target, the solar irradiation simulator is connected with a power supply and then excites a xenon lamp light source, and the incident angle of the sun is adjusted by adjusting a reflector, so that the solar angles at different times in different seasons are simulated, and diversified test requirements are met;
the earth simulator is ground radiation simulation equipment, is positioned at the lower end of the sealed cabin, provides a ground radiation environment for a test target, mainly simulates background infrared radiation and earth albedo solar radiation, and can realize ground radiation characteristics of different orbit heights and different earth areas;
the pressure simulator is positioned on one side of the sealed cabin, provides a low-pressure environment for the sealed cabin, and consists of a vacuum pump, a pressure regulating valve and an electric heater, wherein the vacuum pump sucks air from the inside of the test cabin, the electric heater is used for ensuring that the air temperature at the inlet of the vacuum pump is higher than 0 ℃ when the electric heater is used for a low-temperature test, and the pressure regulating valve is used for regulating the state of the vacuum pump and releasing air to restore the pressure;
the wind field simulator is positioned on the other side of the sealed cabin and provides wind field environments with different wind speeds for the sealed cabin;
the attitude adjusting mechanism is positioned in the sealed cabin and used for simulating multiple horizontal, pitching and rotating attitudes, and the attitude adjusting mechanism is driven by programming to realize the test of the aerostat.
2. The ground simulation test system of the near space aerostat according to claim 1, wherein the wind field simulator comprises a fan, a stabilizing section, a contracting section and an opening test section; the fan can adopt an axial flow fan, the rotating speed of the fan is controlled through a frequency converter, and the air speed in the sealed cabin is adjusted; the wind field simulator stabilizing section is used for eliminating airflow vortexes at the outlet of the fan; the contraction section is designed by adopting a five-stage contraction curve, and static pressure measuring holes are formed in four surfaces of an outlet of the contraction section so as to ensure stable air flow of the test section.
3. The ground simulation test system of the near space aerostat according to claim 2, wherein the simulated wind speed of the fan is controlled to be 0-20m/s, and the environment simulation effect is good.
4. The ground simulation test system of the near space aerostat according to claim 2, wherein a layer of honeycomb device and a damping net are arranged in the stabilizing section, so that an effect of eliminating airflow vortexes can be better achieved.
5. The ground simulation test system of the near space aerostat according to claim 1, wherein the pressure simulator is capable of simulating atmospheric pressure within the height range of 0-20 km.
6. The ground simulation test system of the near space aerostat according to any one of claims 1 to 5, wherein an insulating layer capable of resisting high temperature and having flame retardant property is added on the outer surface of the sealed cabin for reducing system energy consumption and increasing temperature control speed to provide effective heat insulation protection for the sealed cabin.
7. The ground simulation test system of the near space aerostat according to claim 6, wherein the thickness of the heat insulation layer is increased, so that the condensation condition outside the cabin during a low-temperature test can be effectively avoided.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110331999.8A CN113050456A (en) | 2021-03-26 | 2021-03-26 | Ground simulation test system for near space aerostat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110331999.8A CN113050456A (en) | 2021-03-26 | 2021-03-26 | Ground simulation test system for near space aerostat |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113050456A true CN113050456A (en) | 2021-06-29 |
Family
ID=76515934
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110331999.8A Pending CN113050456A (en) | 2021-03-26 | 2021-03-26 | Ground simulation test system for near space aerostat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113050456A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113920804A (en) * | 2021-09-26 | 2022-01-11 | 哈尔滨工业大学 | Large-scale multi-factor space irradiation environment integrated simulation device and simulation method |
| CN114104348A (en) * | 2021-12-17 | 2022-03-01 | 重庆哈丁环境试验技术股份有限公司 | Near space environment simulation system |
| CN114104347A (en) * | 2021-11-18 | 2022-03-01 | 哈尔滨工业大学 | Vacuum container device for simulating low-pressure dust storm environment of mars |
| CN115596693A (en) * | 2022-09-02 | 2023-01-13 | 中国电子科技集团公司第三十八研究所（Cn） | Performance test system and method of centrifugal fan in near space simulation environment |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7997130B1 (en) * | 2009-03-27 | 2011-08-16 | The Boeing Company | System and method for measuring deformation of an object in a fluid tunnel |
| CN103318427A (en) * | 2013-06-25 | 2013-09-25 | 上海宇航系统工程研究所 | Space environment simulation testing system |
| CN105181565A (en) * | 2015-08-31 | 2015-12-23 | 北京天航华创科技股份有限公司 | Combined type temperature, air pressure and irradiation three integrated experiment test system |
| CN205748872U (en) * | 2016-06-01 | 2016-11-30 | 大连理工大学 | A kind of simulation of wind device for ocean engineering model test |
| CN106855693A (en) * | 2016-12-30 | 2017-06-16 | 北京天恒长鹰科技股份有限公司 | A kind of near space aerostatics semi-physical system, avionics system test and winged control semi-physical simulation method and ground controlling method |
| CN109473025A (en) * | 2018-12-27 | 2019-03-15 | 北京航天长征飞行器研究所 | Space multiple orbital attitudes photo-thermal coupling ring border ground simulation device and method |
| CN111458170A (en) * | 2020-04-15 | 2020-07-28 | 北京卫星环境工程研究所 | Comprehensive environment heat balance test system for single-machine product of Mars detector |
| CN111591475A (en) * | 2020-06-04 | 2020-08-28 | 北京航天长征飞行器研究所 | Space photoelectric environment stress comprehensive loading reliability test system and method |
-
2021
- 2021-03-26 CN CN202110331999.8A patent/CN113050456A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7997130B1 (en) * | 2009-03-27 | 2011-08-16 | The Boeing Company | System and method for measuring deformation of an object in a fluid tunnel |
| CN103318427A (en) * | 2013-06-25 | 2013-09-25 | 上海宇航系统工程研究所 | Space environment simulation testing system |
| CN105181565A (en) * | 2015-08-31 | 2015-12-23 | 北京天航华创科技股份有限公司 | Combined type temperature, air pressure and irradiation three integrated experiment test system |
| CN205748872U (en) * | 2016-06-01 | 2016-11-30 | 大连理工大学 | A kind of simulation of wind device for ocean engineering model test |
| CN106855693A (en) * | 2016-12-30 | 2017-06-16 | 北京天恒长鹰科技股份有限公司 | A kind of near space aerostatics semi-physical system, avionics system test and winged control semi-physical simulation method and ground controlling method |
| CN109473025A (en) * | 2018-12-27 | 2019-03-15 | 北京航天长征飞行器研究所 | Space multiple orbital attitudes photo-thermal coupling ring border ground simulation device and method |
| CN111458170A (en) * | 2020-04-15 | 2020-07-28 | 北京卫星环境工程研究所 | Comprehensive environment heat balance test system for single-machine product of Mars detector |
| CN111591475A (en) * | 2020-06-04 | 2020-08-28 | 北京航天长征飞行器研究所 | Space photoelectric environment stress comprehensive loading reliability test system and method |
Non-Patent Citations (2)
| Title |
|---|
| 李德富: "平流层浮空器的热特性及其动力学效应研究", 《中国优秀博硕士学位论文全文数据库(硕士)工程科技Ⅱ辑》 * |
| 王益平等: "临近空间浮空器区域驻留控制策略研究", 《中国空间科学技术》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113920804A (en) * | 2021-09-26 | 2022-01-11 | 哈尔滨工业大学 | Large-scale multi-factor space irradiation environment integrated simulation device and simulation method |
| CN114104347A (en) * | 2021-11-18 | 2022-03-01 | 哈尔滨工业大学 | Vacuum container device for simulating low-pressure dust storm environment of mars |
| CN114104348A (en) * | 2021-12-17 | 2022-03-01 | 重庆哈丁环境试验技术股份有限公司 | Near space environment simulation system |
| CN114104348B (en) * | 2021-12-17 | 2024-01-12 | 重庆哈丁环境试验技术股份有限公司 | Near space environment simulation system |
| CN115596693A (en) * | 2022-09-02 | 2023-01-13 | 中国电子科技集团公司第三十八研究所（Cn） | Performance test system and method of centrifugal fan in near space simulation environment |
| CN115596693B (en) * | 2022-09-02 | 2024-04-16 | 中国电子科技集团公司第三十八研究所 | Performance test system and method of centrifugal fan in near space simulation environment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113050456A (en) | Ground simulation test system for near space aerostat | |
| US20120235410A1 (en) | Lighter than air wind and solar energy conversion system | |
| CN108414260B (en) | Martian surface thermal environment simulation system | |
| CN207300832U (en) | Cold district littoral environment climatic simulation equipment and laboratory | |
| CN106553775B (en) | Environmental simulation test box and environmental simulation method thereof | |
| CN106605446A (en) | Apparatus and method for controlled heating of a vehicle window | |
| KR101372351B1 (en) | Flight simulation system for evaluation of unmanned aerial vehicle based on solar energy | |
| CN106484011B (en) | A kind of method that damp and hot integrated aging testing apparatus of light carries out accelerated ageing test | |
| KR101961452B1 (en) | Hybrid generator using outdoor fan of the air conditioner and air conditioning system having the same | |
| CN108502188A (en) | A kind of plant protection drone spraying operation wind field test system and method | |
| CN111458170A (en) | Comprehensive environment heat balance test system for single-machine product of Mars detector | |
| CN111426978A (en) | All-weather simulation test system of solar street lamp | |
| CN114013692B (en) | Rotation test mechanism and method under vacuum low-temperature condition | |
| CN107272749A (en) | For rotary-wing flight test and the test platform and method of proof of algorithm | |
| CN109515744A (en) | Contracting is than aerostatics experimental rig under a kind of complex environment | |
| CN105044290A (en) | Device for anti-freezing performance testing of anti-freezing coating of wind generating set blade | |
| CN108757342A (en) | A kind of equipment for fan blade flaw detection | |
| CN104634814A (en) | Indoor heat environment experiment device with phase-change material curtain wall on one side and application method of indoor heat environment experiment device | |
| KR20190025351A (en) | Solar panel cooling system using drone | |
| CN115180174B (en) | Icing test method for airplane test | |
| CN208310963U (en) | A kind of equipment for fan blade flaw detection | |
| CN108106813B (en) | A kind of airplane skin material wind detection device | |
| CN114112354A (en) | Test method of helicopter air inlet channel anti-icing system | |
| CN112129691B (en) | Solid insulating material aging experimental device and sampling method under extreme environment | |
| CN114942118A (en) | Environment simulation system for testing high-altitude unmanned aerial vehicle radio frequency equipment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210629 |