CN114942118A - Environment simulation system for testing high-altitude unmanned aerial vehicle radio frequency equipment - Google Patents
Environment simulation system for testing high-altitude unmanned aerial vehicle radio frequency equipment Download PDFInfo
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/002—Thermal testing
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- G—PHYSICS
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- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/40—Means for monitoring or calibrating
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- G—PHYSICS
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- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/48—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S17/00
- G01S7/497—Means for monitoring or calibrating
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Abstract
The application provides an environment simulation system for testing high-altitude unmanned aerial vehicle radio frequency equipment, which simulates a stratospheric pressure environment in a vacuum container through a pressure control system, and simulates a stratospheric temperature environment in the vacuum container through a heat sink temperature adjustment system controlling a cylindrical heat sink; a fan is arranged in the air duct to simulate the airflow environment of a stratosphere; microwave signals generated by the radio frequency equipment are absorbed by the microwave absorption module, and the infrared irradiation heat flow generated by the heat flow simulation module equivalently simulates solar irradiation heat flow to irradiate and heat the radio frequency equipment, so that a simulated stratospheric environment for in-situ testing is provided for testing the actual running state of the radio frequency equipment of the unmanned aerial vehicle on the ground. This application simple structure, occupation space is little, simulation stratosphere temperature, pressure, air current and equivalent solar radiation heat flow environment that can be stable, has solved among the prior art and can not carry out the problem that actual running state tested at ground simulation stratosphere environment to unmanned aerial vehicle radio frequency equipment.
Description
Technical Field
The invention relates to the technical field of special ground tests, in particular to an environment simulation system for testing high-altitude unmanned aerial vehicle radio frequency equipment, and specifically relates to an environment simulation system for simulating stratospheric environment to carry out in-situ test on radio frequency equipment.
Background
The environmental parameters of the stratosphere are between the flight range of a common aircraft and the track environment, and the stratosphere low-speed aircraft comprises an aerial unmanned aerial vehicle, a stratosphere airship and the like, is an important remote sensing and communication platform, generally runs at 16km to 30km high altitude, has the pressure of 1.2kPa to 10.3kPa, the temperature range of-60 ℃ to-40 ℃ and the wind speed of about 20 m/s. For low Reynolds number flow under low air pressure, basic data support and convection and heat exchange experience correlation support are lacked, and simulation data are often corrected by a test means. Therefore, in order to achieve the purposes of thermal model correction, thermal control system performance assessment and the like, it is necessary to perform thermal environment simulation tests on the key loads of the high-altitude unmanned aerial vehicle and the stratospheric airship in a ground simulation environment. In order to form a stable, uniform and continuous wind field under low pressure, the current technical solutions include a reflux type and an injection type, wherein the latter can be used only for short-time simulation, it is difficult to accurately evaluate the heat exchange characteristics,
in addition, radio frequency loads such as radars, communication carried by high-altitude unmanned aerial vehicles and stratospheric airships can generate a large amount of heat in the working process, and the heat is dissipated through structures such as holes of a machine body.
At present, thermal tests and radio frequency load tests of radio frequency equipment of an unmanned aerial vehicle are usually performed in a plurality of tests respectively, and a system for directly testing the actual running state of microwave radio frequency equipment in a stratospheric environment is not available.
Therefore, the design and invention of the unmanned aerial vehicle radio frequency equipment testing system based on the space environment simulation container have positive practical significance.
Disclosure of Invention
In view of the above problems, the present application aims to provide an environment simulation system for testing high altitude unmanned aerial vehicle radio frequency equipment, which can stably simulate stratospheric temperature, pressure, airflow and equivalent solar radiation heat flow environment, and provide an environment for in-situ testing for testing the actual running state of the radio frequency load of an aircraft on the ground.
The application provides an environmental simulation system for high altitude unmanned aerial vehicle radio frequency equipment test, environmental simulation system includes:
the vacuum container is connected with a pressure control system and is used for simulating the stratospheric pressure environment;
the cylindrical heat sink is arranged in the vacuum container and connected with a heat sink temperature regulating system and is used for simulating the temperature environment of a stratosphere;
the cylindrical structure is arranged inside the cylindrical heat sink; an outer air duct is formed between the outer wall of the cylindrical structure and the inner wall of the cylindrical heat sink, an inner air duct is arranged in the cylindrical structure, and the outer air duct is communicated with the inner air duct to form an annular backflow type air duct for simulating an airflow environment of a stratosphere; the inner air duct is provided with a power device for simulating an airflow environment of a stratosphere; a radio frequency device to be tested is arranged in the inner air duct;
the microwave absorption module is arranged in the cylindrical heat sink corresponding to the radio frequency equipment and is used for absorbing microwave signals generated by the radio frequency equipment;
and the heat flow simulation module is arranged on the cylindrical structure corresponding to the radio frequency equipment and is used for generating infrared irradiation heat flow to simulate solar irradiation heat flow to irradiate and heat the radio frequency equipment.
According to the technical scheme provided by the embodiment of the application, the microwave absorption module comprises,
the wave-transmitting plate is connected to the cylindrical structure corresponding to the radio frequency equipment in a random mode, is integrated with the cylindrical structure, and has an inner wall flush with the inner wall of the cylindrical structure, so that microwave signals generated by the radio frequency equipment can be transmitted to the outer air duct on the premise of not influencing the airflow field, and the influence of the reflection of the microwave signals on the airflow field on the stability of the airflow field is prevented;
the wave absorbing device is arranged in the outer air duct and comprises a first wave absorbing plate coaxial with the cylindrical structure, one side, relatively close to the radio frequency equipment, of the first wave absorbing plate is connected with a plurality of second wave absorbing plates parallel to each other, the other end of each second wave absorbing plate is close to the cylindrical structure and used for absorbing microwave signals generated by the radio frequency equipment so as to reduce the influence on the airflow field of the outer air duct.
According to the technical scheme provided by the embodiment of the application, the heat flow simulation module comprises,
the infrared simulation board is connected to the cylindrical structure in a random mode corresponding to the radio frequency equipment, is integrated with the cylindrical structure, has an inner wall flush with the inner wall of the cylindrical structure, and is used for generating infrared irradiation heat flow to simulate solar irradiation heat flow to heat the radio frequency equipment;
the heating rods are circumferentially arranged in the infrared simulation board along the cylindrical structure and used for providing a heat source for the infrared simulation board;
the thermal insulation board is used for connecting the infrared simulation board and the cylindrical structure so as to prevent the infrared simulation board from transferring heat to other parts of the cylindrical structure;
and the infrared heating system is used for controlling the heating rod to adjust the temperature of the infrared simulation board to generate infrared irradiation heat flow to simulate solar irradiation heat flow, and adjusting the density of the infrared irradiation heat flow generated by the infrared simulation board by adjusting the heating temperature of the heating rod.
According to the technical scheme provided by the embodiment of the application, an equivalent heat flow simulation method is adopted to simulate the solar irradiation heat flow.
According to the technical scheme provided by the embodiment of the application, the temperature calculation formula of the infrared simulation plate required by simulating the solar radiation heat flow is as follows,
in the formula, Q solar The heat flux density of solar radiation is in W/m 2 (ii) a Alpha is the solar absorption ratio of the radio frequency equipment; t is a unit of heat The temperature of the infrared simulation plate is expressed in K; t is the temperature of the surface of the radio frequency equipment and is in a unit K; epsilon 1 The infrared emissivity of the radio frequency equipment; a. the 1 The surface area of the heated surface of the radio frequency device heated by the infrared radiation heat flow is m 2 (ii) a X is a space angle coefficient between the radio frequency equipment and the infrared simulation board; epsilon 2 The infrared emissivity of the infrared simulation board is shown.
According to the technical scheme provided by the embodiment of the application, the radio frequency equipment and the infrared simulation board are both provided with temperature sensors.
According to the technical scheme provided by the embodiment of the application, the second wave absorption plate is of a flat plate structure, and the surface with the relatively larger surface area is parallel to the axis of the cylindrical structure.
According to the technical scheme provided by the embodiment of the application, the wave-transmitting plate is made of polyimide; the wave absorbing device is made of silicon carbide or carbon foam and has the characteristics of high hardness and low outgassing rate.
According to the technical scheme provided by the embodiment of the application, a rectifier and a turbulence reducing net for stabilizing an airflow field are sequentially arranged in the inner air channel along the airflow flowing direction; the rectifier comprises a first honeycomb rectifier and a second honeycomb rectifier which are sequentially arranged along the airflow direction.
According to the technical scheme provided by the embodiment of the application, the cylindrical heat sink is a tube fin type or honeycomb inflatable plate type heat exchange structure, and gas nitrogen is adopted for temperature regulation; the cylindrical heat sink is divided into a plurality of areas capable of independently regulating and controlling the temperature along the airflow flowing direction and is respectively connected with the cylindrical heat sink temperature regulating system, so that the temperature regulation and control of different areas in the air duct can be better realized, and the temperature balance of the environment simulation system is ensured.
According to the technical scheme provided by the embodiment of the application, the radio frequency equipment is provided with the radiant heat flow meter which is used for measuring the infrared irradiation heat flow density reaching the surface of the radio frequency equipment and generated by the infrared simulation board.
In conclusion, the application discloses an environment simulation system for testing high-altitude unmanned aerial vehicle radio frequency equipment, and the beneficial effects based on the scheme are that the cylindrical heat sink is arranged in the vacuum container, the cylindrical structure is arranged in the cylindrical heat sink to form the inner air duct and the outer air duct, and the inner air duct and the outer air duct are communicated to form the annular backflow type air duct which can enable air flow to circularly flow, so that the structure of the environment simulation system is greatly simplified, and the occupied space of the environment simulation system is reduced; a power device for generating airflow is designed in the inner air duct, so that the simulation of the airflow environment of the stratosphere is realized; simulating a stratospheric pressure environment in the vacuum container through a pressure control system, and controlling a cylindrical heat sink to simulate a stratospheric temperature environment in the vacuum container through a heat sink temperature regulating system; through the microwave absorption module for absorbing microwave signals generated by radio frequency equipment in the barrel-shaped heat sink, the heat flow simulation module for generating infrared irradiation heat flow to simulate solar irradiation heat flow to perform irradiation heating on the radio frequency equipment is connected to the barrel-shaped structure, so that the condition of performing a thermal test on the radio frequency equipment of the unmanned aerial vehicle is met on the premise of not increasing the complexity of an environment simulation system and not influencing an inner air duct airflow field, the temperature, the pressure, the airflow and the solar irradiation heat flow environment of a stratosphere can be stably simulated finally, the simulated stratosphere environment of in-situ test is provided for testing the actual running state of the radio frequency equipment of the unmanned aerial vehicle on the ground, and the problem that the actual running state of the radio frequency equipment of the unmanned aerial vehicle cannot be directly tested in the stratosphere environment in the prior art is solved.
In a certain scheme of this application, thermal current analog module includes that the infrared simulation board that is connected along with the type through heat insulating board and tubular structure reaches along tubular structure circumference setting at the inside heating rod of infrared simulation board, and infrared heating board inner wall with tubular structure inner wall flushes, has realized the integration of thermal current analog module with tubular structure, produces infrared irradiation thermal current under the prerequisite that does not influence interior wind channel airflow field, and equivalent simulation solar irradiation thermal current carries out the irradiation heating to radio frequency equipment, has solved among the prior art and has set up radio frequency equipment heating structure in the wind channel and influence the problem of airflow field stability, has guaranteed to carry out the validity and the accuracy nature of the thermal test of simulation solar irradiation thermal current to unmanned aerial vehicle radio frequency equipment under not influencing wind channel airflow field and unmanned aerial vehicle radio frequency equipment actual running state.
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.
Fig. 1 is a schematic diagram of an environment simulation system for testing high altitude unmanned aerial vehicle radio frequency equipment according to an embodiment of the present application.
Fig. 2 is a schematic cross-sectional view of a test area of an environmental simulation system for testing high altitude unmanned aerial vehicle radio frequency equipment according to an embodiment of the present application.
In the figure, 101, a barrel type heat sink; 102. a vacuum vessel; 103. a pressure control system; 103-1, an air extraction pipeline; 103-2, a gas supplementing pipeline; 201. an inlet connection; 202. a rectifying section; 202-1, a first cellular rectifier; 202-2, a second cellular rectifier; 202-3, reducing turbulence net; 203. a test zone; 203-1, infrared simulation board; 203-2, wave-transparent plate; 203-3, a wave absorbing device; 203-4, a heat insulation plate; 203-5, a radiant heat flow meter; 203-6, heating rods; 203-7, a cylindrical structure; 204. a divergent zone; 205. a power zone; 205-1, a head cover; 205-2, a support frame; 205-3, fan blades; 205-4, tail cap; 205-5, a motor; 205-6, anti-twisting guide vanes; 206. an outlet connection; 301. a radio frequency device.
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. The present application will now be described in detail with reference to the drawings, in conjunction with the following examples.
An environment simulation system for high altitude unmanned aerial vehicle radio frequency equipment test as shown in fig. 1-2, the environment simulation system comprises,
a vacuum vessel 102, wherein the vacuum vessel 102 is connected with a pressure control system and is used for simulating an stratospheric pressure environment;
the cylindrical heat sink 101 is arranged inside the vacuum container 102, is connected with a heat sink temperature regulating system and is used for simulating the temperature environment of a stratosphere;
a cylindrical structure 203-7 disposed inside the cylindrical heat sink 101; an outer air duct is formed between the outer wall of the cylindrical structure 203-7 and the inner wall of the cylindrical heat sink 101, an inner air duct is arranged in the cylindrical structure 203-7, and the outer air duct is communicated with the inner air duct to form an annular backflow type circulating air duct for simulating an airflow environment of a stratosphere; the inner air duct is provided with a power device for simulating the stratosphere airflow environment; the radio frequency equipment to be tested 301 is arranged in the inner air duct;
the microwave absorption module is arranged in the barrel-type heat sink 101 corresponding to the radio frequency device 301 and is used for absorbing microwave signals generated by the radio frequency device 301;
and the heat flow simulation module is arranged on the cylindrical structure 203-7 corresponding to the radio frequency equipment 301 and is used for generating infrared irradiation heat flow to simulate solar irradiation heat flow to irradiate and heat the radio frequency equipment 301.
The cylindrical structure 203-7 and the cylindrical heat sink 101 are both cylindrical and are coaxially arranged; the inner air duct comprises a rectifying area 202, a test area 203, a divergent area 204 and a power area 205 which are sequentially arranged along the air flow direction, the inner diameter of the test area 203 is smaller than that of the power area 205, and the test area 203 is connected with the power area 205 through the divergent area 204; the radio frequency equipment 301 is provided with a radio frequency load capable of emitting microwaves; the two ends of the inner air duct and the outer air duct are respectively communicated through an inlet connecting piece 201 and an outlet connecting piece 206, and airflow can turn 180 degrees at the inlet connecting piece 201 and the outlet connecting piece 206, so that an annular backflow type air duct is formed, the structure is simple, and the occupied space of an environment simulation system is greatly reduced; the microwave absorption module is located above the radio frequency load of the radio frequency device 301, and the heat flow simulation module is arranged below the radio frequency device 301 corresponding to the microwave absorption module.
The power device is arranged in the power area 205 of the inner air duct, can drive the air in the vacuum container 102 to flow, and simulates the airflow environment of a stratosphere in the air duct; the rectifying area 202 is sequentially provided with a rectifier and a turbulence reducing net 202-3 along the airflow direction; the rectifier comprises a first honeycomb rectifier 202-1 and a second honeycomb rectifier 202-2 which are arranged in sequence along the airflow direction, and the airflow passing through the inlet connecting piece 201 can be adjusted into stable airflow with consistent direction and speed.
The vacuum container 102 is a cylindrical stainless steel tank type container, can bear negative pressure of 1 standard atmospheric pressure, and simulates the pressure environment of a stratosphere through a pressure control system 103; the cylindrical heat sink 101 is a tube fin or honeycomb inflatable plate type heat exchange structure, is arranged in the vacuum container 102 and is coaxial with the vacuum container 102, and adopts gas nitrogen to regulate and control the temperature; the cylindrical heat sink 101 is divided into at least 10 areas with independently adjustable temperatures along the airflow flowing direction and is respectively connected with a heat sink temperature adjusting system, and the heat sink temperature adjusting system is provided with an automatic control module, so that the temperature of each area can be automatically adjusted and controlled by a temperature sensor in the vacuum container 102 in the actual operation test process of the radio frequency equipment 301, the temperature of different areas in an air duct can be better adjusted and controlled, the temperature environment of an stratosphere can be simulated, and the temperature of the stratosphere environment simulation system can be kept balanced during the test.
The environmental simulation system can simulate the pressure environment (being the vacuum environment), the low temperature environment, the gas flow environment and the solar irradiation environment of stratosphere, satisfies and tests unmanned aerial vehicle radio frequency equipment 301 with actual operating condition on ground to acquire the actual condition data of unmanned aerial vehicle radio frequency equipment 301 at the stratosphere during operation, thereby provide more reliable data support for optimizing unmanned aerial vehicle radio frequency equipment 301's design.
In some embodiments, the microwave absorption module includes,
the wave-transmitting plate 203-2 is positioned in the test area 203 of the inner air duct, is connected to the cylindrical structure 203-7 in a form-following manner corresponding to the radio frequency equipment 301, and has an inner wall flush with the inner wall of the cylindrical structure 203-7;
the wave absorbing device 203-3 is arranged in the outer air duct and comprises a first wave absorbing plate coaxial with the cylindrical structure 203-7, one side, relatively close to the radio frequency equipment 301, of the first wave absorbing plate is connected with a plurality of second wave absorbing plates which are parallel to each other, and the other end of each second wave absorbing plate is close to the cylindrical structure 203-7.
The cylindrical structure 203-7 is provided with a wave-transmitting hole matched with the wave-transmitting plate 203-2, the wave-transmitting plate 203-2 is connected to the cylindrical structure 203-7 through the wave-transmitting hole, and forms an integrated structure with the cylindrical structure 203-7, and a smooth inner air duct is formed inside the integrated structure after connection, so that the stability of an airflow field of the test area 203 is ensured; the wave-transmitting plate 203-2 is made of polyimide, and can transmit microwave signals generated by radio frequency loads of the radio frequency equipment 301 to the outer air duct, so that the microwave signals are prevented from being reflected by the inner air duct to influence the stability of air flow; the wave absorbing device 203-3 is made of silicon carbide or carbon foam, has the characteristics of high hardness and low air release rate, can absorb microwave signals penetrating through the wave transmitting plate 203-2, and prevents the microwave signals from reflecting in an external air duct to influence the stability of air flow so as to reduce the influence on the air flow of the external air duct; the first wave absorbing plate is an arc-shaped plate coaxial with the cylindrical structure 203-7, one side of the arc-shaped plate, which is relatively close to the radio frequency equipment 301, is connected with a plurality of second wave absorbing plates which are parallel to each other, and the other end of each second wave absorbing plate is close to the wave transmitting plate 203-2, so that microwave signals can be absorbed, and the influence of the wave absorbing device 203-3 on airflow can be reduced to the maximum extent.
In some embodiments, the second wave absorbing plate is a flat plate structure with a relatively large surface area parallel to the axis of the cylindrical structure 203-7, as shown in FIG. 2.
The coverage range of the wave absorbing device 203-3 is larger than the radiation range of the microwave signal after passing through the wave transmitting plate 203-2, so that the microwave signal can be completely captured and absorbed, the second wave transmitting plate with the flat plate structure can also play a role in pre-rectifying the airflow flowing through the second wave transmitting plate, and the stability of an airflow flow field can be further improved by matching with the rectifier and the turbulence reducing net 202-3.
In some embodiments, the heat flow simulation module includes,
the infrared simulation board 203-1 is positioned in the test area 203, is connected to the cylindrical structure 203-7 along with the radio frequency device 301, has an inner wall flush with the inner wall of the cylindrical structure 203-7, is structurally integrated with the cylindrical structure 203-7, and is used for generating infrared irradiation heat flow to simulate solar irradiation heat flow to heat the radio frequency device 301;
the heating rod 203-6 is arranged in the infrared simulation plate 203-1 along the circumferential direction of the cylindrical structure 203-7 and is used for providing a heat source for the infrared simulation plate 203-1;
the heat insulation board 203-4 is used for connecting the infrared simulation board 203-1 with the cylindrical structure 203-7 so as to prevent the infrared simulation board 203-1 from transferring heat to other parts of the cylindrical structure 203-7;
and the infrared heating system is used for controlling the heating rod 203-6 to adjust the infrared simulation plate 203-1 to generate infrared irradiation heat flow to simulate solar irradiation heat flow.
The cylindrical structure 203-7 is provided with an infrared hole matched with the infrared simulation plate 203-1, the infrared simulation plate 203-1 is installed on the infrared hole of the cylindrical structure 203-7 in a conformal manner through a thermal insulation plate 203-4 and is specifically positioned below the radio frequency equipment 301, as shown in fig. 1, the infrared simulation plate and the cylindrical structure 203-7 form an integrated structure, and a smooth inner air duct is formed inside the infrared simulation plate after connection, so that the stability of the airflow field of the test area 203 is ensured; the cylindrical structure 203-7 is matched and connected with the wave-transmitting plate 203-2 and the infrared simulation plate 203-1 to form a circumferentially closed test area 203.
In the infrared simulation board 203-1, 7 heating rods 203-6 are uniformly distributed along the circumference of the cylindrical structure 203-7, as shown in fig. 2, the heating rods 203-6 are controlled by an infrared heating system to heat the infrared simulation board 203-1, the infrared simulation board 203-1 can generate infrared irradiation heat flow, and the infrared radiation heat exchange between the infrared simulation board 203-1 and the radio frequency equipment 301 can be adjusted by controlling the temperature of the infrared simulation board 203-1, so that the radio frequency equipment 301 can keep absorbing the infrared radiation heat flow generated by the infrared simulation board 203-1 during the whole test period, and further the equivalent heat flow simulation of the solar irradiation heat flow is realized. Meanwhile, the balance adjustment of the flow field temperature rise brought by the heating rod 203-6 can be carried out by adjusting the temperature of the gas nitrogen in each area of the cylindrical heat sink 101.
The principle of simulating solar irradiation heat flow by equivalent heat flow is as follows:
the heat flux of solar radiation absorbed by the rf device 301 in the stratosphere is,
Q in ＝α*Q solar (1)
in the formula, Q solar The heat flux density of solar radiation is in W/m 2 (ii) a α is the solar absorption ratio of the radio frequency device 301; q in Is the solar radiation heat flow absorbed by the radio frequency device 301 in unit area, the unit is W/m 2 。
The infrared simulation board 203-1 absorbed by the radio frequency device 301 in the environment simulation system irradiates heat flux of,
wherein Q is the radiation heat flow of the infrared simulation board 203-1 absorbed by the radio frequency device 301 in the environment simulation system.
According to the equivalent heat flow simulation method, the solar irradiation heat flow absorbed by the radio frequency device 301 in the stratosphere is equal to the irradiation heat flow absorbed by the infrared simulation board 203-1 in the environment simulation system, that is,
in the formula, Q solar The heat flux density of solar radiation is in W/m 2 (ii) a α is the solar absorptance of the radio frequency equipment 301; t is heat Is the temperature of the infrared simulation plate 203-1, unit K; t is the temperature of the surface of the radio frequency device 301 in K; epsilon 1 Is the infrared emissivity of the radio frequency device 301; a. the 1 Is the surface area of the heated surface of the infrared radiation heat flow of the radio frequency device 301, and the unit m 2 (ii) a X is a space angle coefficient between the radio frequency equipment and the infrared simulation board 203-1; epsilon 2 The infrared emissivity of the infrared simulation board 203-1.
As can be known from the formula (3), when the structure, the installation position, the material, the solar radiation heat flux density and other parameters of the infrared simulation board 203-1 and the radio frequency device 301 are determined, only T is available heat T is variable, so that the temperature T of the infrared simulation plate 203-1 is adjusted by the heating rod 203-6 along with the change of the temperature T on the surface of the radio frequency equipment 301 heat Equivalent simulation of solar irradiation heat flow can be realized.
In some embodiments, temperature sensors are disposed on both the radio frequency device 301 and the infrared analog board 203-1.
In the initial stage of the test, along with the long-time operation of the radio frequency load in the radio frequency device 301, the internal temperature of the radio frequency device 301 gradually increases, that is, the temperature of the surface of the radio frequency device 301 increases, the heat flow exchange between the radio frequency device 301 and the infrared simulation board 203-1 changes, and the solar radiation heat flow can not be simulated equivalently any more, so that the temperature of the infrared simulation board 203-1 needs to be adjusted according to the temperature of the radio frequency device 301 at this time, and the solar radiation heat flow can be kept to be simulated equivalently. Specifically, the infrared heating system is provided with an automatic temperature control module, the temperature data of the radio frequency equipment 301 is collected in real time through a temperature sensor, the temperature of the infrared simulation board 203-1 is calculated according to the formula (3), then the heating rod 203-6 is controlled to adjust the temperature of the infrared simulation board 203-1 required by equivalent simulation of solar irradiation heat flow according to the temperature data of the infrared heating board 203-1 collected in real time by the temperature sensor, the temperature of the heating rod 203-6 is kept, the infrared simulation board 203-1 can generate the infrared irradiation heat flow of the equivalent simulation of solar irradiation heat flow all the time, and therefore the equivalent solar irradiation heat flow required by the test of the radio frequency equipment 301 is kept all the time.
In some embodiments, the radio frequency device 301 is provided with a bolometer 203-5, configured to measure an infrared radiation heat flow density generated by the infrared simulation board 203-1 and reaching the surface of the radio frequency device 301, as a measure for assisting in monitoring whether the infrared simulation board 203-1 has an equivalent effect of simulating solar radiation heat flow, and once an infrared radiation heat flow density data is found to be abnormal, the test may be stopped, and the problem may be checked and eliminated.
In certain embodiments, as shown in fig. 1, the power plant is a fan; in the inner air duct power area 205, an anti-twisting guide vane 205-6 for reducing the rotation speed of the air flow is arranged on one side of the fan, which is relatively far away from the radio frequency equipment 301, so that the flow direction of the air flow is parallel to the direction of the inner air duct, and the flow field of the air flow is optimized; the fan is provided with a head cover 205-1 and a tail cover 205-4 for guiding airflow, and an airflow field is optimized.
The fan is arranged in the middle of the power area 205 through a support frame 205-2, and the front end and the rear end of the fan are respectively provided with a head cover 205-1 and a tail cover 205-4 for guiding airflow; the motor 205-5 is arranged inside the tail cover 205-4 and used for driving the fan blades 205-3 to rotate and generate air flow; because the initial airflow has higher circumferential rotation speed, is a rotating airflow, is not beneficial to forming a stable airflow flow field and simulating the stratosphere environment, the anti-twisting guide vane 205-6 for reducing the airflow rotation speed is arranged at the tail end of the power area 205, namely the downwind direction of the fan, so that the airflow flowing direction is parallel to the air channel direction, the airflow flow field is optimized, and the stratosphere airflow is simulated. Continuous circulating airflow can be formed in the annular backflow type air duct through the fan.
And a wind speed sensor is arranged on the cylindrical structure 203-7 between the rectifying area 202 and the radio frequency device 301 and is used for detecting the speed of the airflow and controlling the fan to generate an airflow environment required by the test according to the speed of the airflow.
In some embodiments, the vacuum vessel 102 is connected with an air pumping line 103-1 and an air replenishing line 103-2; the extraction pipeline 103-1 and the air supply pipeline 103-2 are respectively connected with a pressure control system 103.
During the test process of the radio frequency device 301, the internal pressure of the vacuum container 102 may be increased due to the temperature rise of the environment simulation system, the external air slowly entering the vacuum container 102, and the like, and at this time, the pressure control system 103 needs to be operated to pump the internal air out through the air pumping pipeline 103-1, so as to reduce the pressure in the vacuum container 102 and maintain the pressure balance of the environment simulation system; the pressure inside the vacuum container 102 is reduced due to the reasons of temperature reduction of the environment simulation system and the like, and at this time, the pressure control system 103 needs to be operated to inject gas into the vacuum container 102 through the gas supply pipeline 103-2, so that the pressure inside the vacuum container 102 is increased, and the pressure balance of the environment simulation system is maintained; the gas is oxygen-nitrogen mixed gas or pure nitrogen. The pressure control system 103 has an automatic control module, which can automatically pump or supplement air according to the pressure variation of the pressure sensor in the vacuum container 102, so as to realize the pressure balance in the vacuum container 102 during the test of the radio frequency device 301, and maintain the pressure in the predetermined stratosphere, and the pressure control precision can reach +/-5 Pa.
When the environment simulation system is used, the method comprises the following steps:
completing preparation work, including installing radio frequency equipment 301, arranging a temperature sensor, connecting a measuring cable and the like;
starting the pressure control system 103, pumping the vacuum container 102 to vacuum for dehumidification, wherein the vacuum degree is preferably below 10Pa, introducing gas to a preset pressure, namely simulating the pressure environment of a stratosphere, and then setting the pressure control system 103 to enter an automatic control mode;
starting a heat sink temperature regulating system, reducing the temperature in the vacuum container 102 to a set temperature, namely simulating the temperature environment of a stratosphere, generally ranging from-80 ℃ to-30 ℃, and then setting the heat sink temperature regulating system to enter an automatic control mode;
starting a fan, and driving the flow speed of the gas in the air duct to reach a set speed, namely simulating the stratospheric airflow environment;
starting an infrared heating system, heating the infrared simulation plate 203-1 through the heating rod 203-6 to achieve the temperature corresponding to the equivalent simulation of the solar irradiation heat flow density in the preset stratosphere, and setting the temperature of the infrared simulation plate 203-1 to enter an automatic control mode;
switching on a power supply of the radio frequency equipment 301, starting a radio frequency load, keeping the radio frequency load continuously working for a preset time, and regularly recording data of each temperature sensor in the radio frequency equipment 301 during the continuous working period of the radio frequency load;
and after the test is finished, the radio frequency load, the heating rod 203-6 and the radio frequency equipment 301 are powered off, the fan is stopped, the environment in the vacuum container 102 is restored to the ground environment state, and the radio frequency equipment 301 is taken out.
Further, when the working state of the radio frequency device 301 is tested, the pressure environment, the temperature environment, the airflow environment and the infrared radiation heat flow of the simulation system may also be adjusted, different stratospheric environments may be simulated to continuously test the working state of the radio frequency device 301, and data of each temperature sensor in the radio frequency device 301 may be recorded.
The actual working state of the radio frequency equipment 301 is directly tested by a ground stratosphere environment simulation system, so that the temperature data of each part of the radio frequency equipment 301 during working is obtained, whether the design of the radio frequency equipment 301 meets the requirements can be analyzed by analyzing the temperature data, the design problem is found, and targeted optimization and improvement are performed.
It can be seen from the above embodiments that, the application provides an environmental simulation system for testing high altitude unmanned aerial vehicle radio frequency equipment, an inner air duct and an outer air duct are formed by arranging a coaxial cylindrical heat sink 101 in a vacuum container 102 and arranging a coaxial cylindrical structure 203-7 in the cylindrical heat sink 101, and an annular backflow type air duct capable of enabling air flow to circularly flow is formed after the inner air duct and the outer air duct are communicated, so that the occupied space of the environmental simulation system is greatly reduced; a fan for generating airflow, a rectifier for adjusting an airflow field and a turbulence reduction net 202-3 are designed in the inner air channel, so that stable and continuous airflow is formed in the air channel, and the airflow environment of a stratosphere is simulated; by designing the wave-transmitting plate 203-2 with an integrated structure on the cylindrical structure 203-7 and arranging the wave-absorbing device 203-3 corresponding to the wave-transmitting plate 203-2 on the outer air duct, the influence of microwaves on the stability of an airflow field in the air duct when the radio frequency equipment 301 runs is eliminated, so that the radio frequency equipment 301 can be kept running continuously during actual test; by designing the infrared simulation plate 203-1 integrated with the cylindrical structure 203-7 on the cylindrical structure 203-7 and arranging the heating rod 203-6 in the infrared simulation plate 203-1, the infrared simulation plate 203-1 can be controlled to generate infrared irradiation heat flow through the infrared heating control system, and the solar irradiation heat flow is equivalently simulated, so that a thermal test for equivalently simulating the solar irradiation heat flow can be carried out on the radio frequency equipment 301 under the condition of not influencing an airflow flow field when the radio frequency equipment 301 is kept in actual operation, and the problems that the airflow flow field is influenced and the thermal test cannot be carried out on the structure heated by the radio frequency equipment 301 in the prior art are solved; the stratosphere pressure environment is simulated in the vacuum container 102 through the pressure control system, the tubular heat sink 101 is controlled through the heat sink temperature regulating system to simulate the stratosphere temperature environment in the vacuum container 102, and finally the stratosphere temperature, pressure, airflow and solar irradiation environment can be stably simulated, so that the simulated stratosphere environment for in-situ testing is provided for testing the actual running state of the unmanned aerial vehicle radio frequency equipment 301 on the ground, and the problem that the actual running state of the unmanned aerial vehicle radio frequency equipment 301 cannot be directly tested in the stratosphere environment in the prior art is solved.
The above examples are given for the purpose of illustrating the present invention clearly and not for the purpose of limiting the same, and it will be apparent to those skilled in the art that various changes and modifications can be made in the above examples without departing from the scope of the invention.
Claims (10)
1. An environmental simulation system for high altitude unmanned aerial vehicle radio frequency equipment testing, characterized in that, the environmental simulation system includes:
the vacuum container is connected with a pressure control system and is used for simulating the stratospheric pressure environment;
the cylindrical heat sink is arranged in the vacuum container and connected with a heat sink temperature regulating system and is used for simulating the temperature environment of a stratosphere;
the cylindrical structure is arranged inside the cylindrical heat sink; an outer air duct is formed between the outer wall of the cylindrical structure and the inner wall of the cylindrical heat sink, an inner air duct is arranged in the cylindrical structure, and the outer air duct is communicated with the inner air duct to form an annular backflow type air duct for simulating an airflow environment of a stratosphere; the inner air duct is provided with a power device for simulating the stratosphere airflow environment; a radio frequency device to be tested is arranged in the inner air duct;
the microwave absorption module is arranged in the cylindrical heat sink corresponding to the radio frequency equipment and is used for absorbing microwave signals generated by the radio frequency equipment;
and the heat flow simulation module is arranged on the cylindrical structure corresponding to the radio frequency equipment and is used for generating infrared irradiation heat flow to simulate solar irradiation heat flow to irradiate and heat the radio frequency equipment.
2. The environmental simulation system for high altitude unmanned aerial vehicle radio frequency equipment testing of claim 1, wherein the microwave absorption module comprises,
the wave-transmitting plate is connected to the cylindrical structure corresponding to the radio frequency equipment in a random mode, and the inner wall of the wave-transmitting plate is flush with the inner wall of the cylindrical structure, so that microwave signals generated by the radio frequency equipment can be transmitted to an external air duct on the premise of not influencing an airflow field;
the wave absorbing device is arranged in the outer air duct and comprises a first wave absorbing plate coaxial with the cylindrical structure, one side, relatively close to the radio frequency equipment, of the first wave absorbing plate is connected with a plurality of second wave absorbing plates parallel to each other, and the other end of each second wave absorbing plate is close to the cylindrical structure.
3. The environment simulation system for high altitude unmanned aerial vehicle radio frequency equipment test according to claim 1, wherein the heat flow simulation module comprises,
the infrared simulation board is connected to the cylindrical structure along with the radio frequency equipment, and the inner wall of the infrared simulation board is flush with the inner wall of the cylindrical structure;
the heating rod is arranged in the infrared simulation plate along the circumferential direction of the cylindrical structure;
the thermal insulation board is used for connecting the infrared simulation board and the cylindrical structure;
and the infrared heating system is used for controlling the heating rod to adjust the temperature of the infrared simulation plate to generate infrared irradiation heat flow to simulate solar irradiation heat flow.
4. The environment simulation system for high-altitude unmanned aerial vehicle radio frequency equipment test is characterized in that an equivalent heat flow simulation method is adopted to simulate solar irradiation heat flow.
5. The environment simulation system for high-altitude unmanned aerial vehicle radio frequency equipment testing according to claim 4, wherein the temperature of the infrared simulation board required for simulating solar radiation heat flow is calculated as,
in the formula, Q solar The heat flux density is the solar radiation; alpha is the solar absorption ratio of the radio frequency equipment; t is heat The temperature of the infrared simulation plate; t is the temperature of the surface of the radio frequency equipment; epsilon 1 The infrared emissivity of the radio frequency equipment; a. the 1 The surface area of the heated surface of the radio frequency device by infrared radiation heat flow; x is a space angle coefficient between the radio frequency equipment and the infrared simulation board; epsilon 2 The infrared emissivity of the infrared simulation board is shown.
6. The environmental simulation system for high altitude unmanned aerial vehicle radio frequency equipment testing of claim 5, characterized in that, temperature sensor is equipped on both the radio frequency equipment and the infrared simulation board.
7. The environmental simulation system for high altitude unmanned aerial vehicle radio frequency equipment test is characterized in that the second wave absorbing plate is of a flat plate structure, and the surface with the relatively large surface area is parallel to the axis of the cylinder-shaped structure.
8. The environmental simulation system for the high altitude unmanned aerial vehicle radio frequency equipment test is characterized in that the wave-transmitting plate is made of polyimide; the wave absorbing device is made of silicon carbide or carbon foam.
9. The environmental simulation system for high altitude unmanned aerial vehicle radio frequency equipment testing according to claim 1, characterized in that a rectifier and a turbulence reduction net for stabilizing an airflow field are sequentially arranged inside the inner air duct along the airflow flowing direction; the rectifier comprises a first honeycomb rectifier and a second honeycomb rectifier which are sequentially arranged along the airflow direction.
10. The environmental simulation system for testing the radio frequency equipment of the high altitude unmanned aerial vehicle of claim 1, wherein the cylindrical heat sink is a tube fin type or honeycomb inflatable plate type heat exchange structure, a plurality of areas capable of independently regulating and controlling the temperature are divided along the flow direction of the air flow, and the areas are respectively connected with the cylindrical heat sink temperature regulation system.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
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