CN216350988U - Test bed for airborne electronic product environment control device - Google Patents
Test bed for airborne electronic product environment control device Download PDFInfo
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- CN216350988U CN216350988U CN202122526021.5U CN202122526021U CN216350988U CN 216350988 U CN216350988 U CN 216350988U CN 202122526021 U CN202122526021 U CN 202122526021U CN 216350988 U CN216350988 U CN 216350988U
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Abstract
A test bed for an airborne electronic product environment control device is characterized in that the airborne electronic product environment control device is divided into two parts, one part is arranged in an environment control cabin of an airplane, the other part is arranged in a head cabin of the airplane, and the two parts are communicated through a refrigerant circulating pipeline; the test bed comprises a simulation cabin body, an environment-controlled butt flange, a simulation heat source, a temperature polling instrument and a fixing plate; the environment-controlled butt flange is used for fixing the environment-controlled cabin, the front end of the environment-controlled cabin is connected with the fixed plate through the rigid connecting component, and the front end of the fixed plate is used for mounting the part, located in the head cabin, of the airborne electronic product environment-controlled device; the simulation cabin body is a transparent cylinder cover, the fixed plate is sleeved on the simulation cabin body, the tail section of the cylinder cover is connected with the environment-controlled butt flange, the simulation cabin body is divided into two parts by the fixed plate, and the head cabin and the electronic cabin of the airplane are simulated respectively; the front end of the fixed plate is provided with a simulation heat source for simulating the heat of the head cabin through a bracket, and the rigid connecting component is provided with a simulation heat source for simulating the heat of the electronic cabin; the temperature polling instrument is used for measuring the temperature of the simulated heat source.
Description
Technical Field
The utility model relates to a static test bed for an airborne electronic product environment control device, which is particularly suitable for an environment control system of an airborne photoelectric pod.
Background
At present, the structural layout of the existing foreign airborne photoelectric pod is developed and matured, and the pod is basically composed of three parts, wherein the head part is generally photoelectric tracking and aiming equipment, the middle part is electronic information processing/power supply equipment or a radar detection array, and the tail part is an environment control device unit. Each part basically adopts the modular design, and head and middle part each module are relatively independent, and the maintenance of being convenient for upgrade, but the environmental control device nevertheless needs to provide specific environmental characteristic for head cabin, middle part cabin because of its special functionality, so the equipment of environmental control device relates to the face the most extensively, and the troubleshooting dismantlement after breaking down is the most complicated.
At present, the environmental control devices carried by onboard electronic products at home and abroad still adopt a process of separating assembly from testing, or the testing is only roughly evaluated, so that the distribution values of the air temperature in the cabin body under different working conditions cannot be obtained before final assembly, even the environmental control components of the head cabin and the middle cabin cannot be subjected to performance testing before the final assembly, and the environmental control performance evaluation can be carried out only after the final assembly is finished. The assembly test is carried out without fully testing and evaluating the stability and reliability of the refrigeration performance of the environmental control system, and great risks can be brought to the whole airborne electronic product, particularly the failure or even the scrapping of expensive photoelectric components.
SUMMERY OF THE UTILITY MODEL
The technical problem solved by the utility model is as follows: aiming at the problem that the stability and the reliability of the refrigerating capacity of the airborne electronic product environment control device cannot be quantitatively tested before final assembly, the airborne electronic product environment control device test bed is provided.
The technical scheme of the utility model is as follows: the airborne electronic product environmental control device test bed is characterized in that the airborne electronic product environmental control device is divided into two parts, one part is arranged in an environmental control cabin of an airplane, the other part is arranged in a head cabin of the airplane, and the two parts are communicated through a refrigerant circulating pipeline; the test bed comprises a simulation cabin body, an environment-controlled butt flange, a simulation heat source, a temperature polling instrument and a fixing plate;
the environment-controlled butt flange is used for fixing the environment-controlled cabin, the front end of the environment-controlled cabin is connected with the fixed plate through the rigid connecting component, and the front end of the fixed plate is used for mounting the part, located in the head cabin, of the airborne electronic product environment-controlled device; the simulation cabin body is a transparent cylinder cover, the fixed plate is sleeved on the simulation cabin body, the tail section of the cylinder cover is connected with the environment-controlled butt flange, the simulation cabin body is divided into two parts by the fixed plate, and the head cabin and the electronic cabin of the airplane are simulated respectively; the front end of the fixed plate is provided with a simulation heat source for simulating the heat of the head cabin through a bracket, and the rigid connecting component is provided with a simulation heat source for simulating the heat of the electronic cabin; the temperature polling instrument is used for measuring the temperature of the simulated heat source.
Preferably, the tail section of the cylinder cover is in rigid connection or flexible sealing connection with the annular control butt flange.
Preferably, the environment-controlled butt flange is arranged on the working bench to complete the static test.
Preferably, the environment-controlled butt flange is installed on a mechanical arm, and the mechanical arm drives the test bed to complete a dynamic test for simulating the flight of the airplane.
Preferably, the simulation cabin body is made of acrylic transparent materials.
Preferably, the test bed further comprises a high-pressure vortex blower for simulating and providing ram air in the flight state test of the airplane.
Preferably, an o-shaped sealing ring or a soft sealing material is arranged on the fixing plate and used for realizing the sealing isolation between the head cabin and the electronic cabin.
Preferably, the temperature sensing color changing material is additionally arranged on the rigid connecting part and the bracket or the temperature sensing color changing gas is filled in the cabin body.
Preferably, the number of the thermocouple temperature sensors of the temperature polling instrument distributed around each simulated heat source is at least four, the simulated heat sources are used as the center for arrangement, and the interval between the thermocouple temperature sensors is 50-100 mm.
Compared with the prior art, the utility model has the beneficial effects that:
the static experimental device can provide an assembly and static simulation test environment for the environment control device, complete environment control performance detection before the assembly of the onboard electronic product, and avoid loss risk and production invalid working hour waste caused by the assembly and disassembly of the head cabin and the middle cabin after the performance is abnormal after the assembly.
The static test bench can more visually display and test the temperature change condition and the temperature field uniformity in the cabin body by changing the layout of the aluminum alloy frame and additionally arranging the temperature-sensitive color-changing material or the temperature-sensitive color-changing gas.
Drawings
FIG. 1 is a schematic view of a test stand according to the present invention;
FIG. 2 is a schematic structural view of embodiment 1 of the present invention;
FIGS. 3 to 8 are schematic views of the assembly of embodiment 1 of the present invention;
FIG. 9 is a schematic view of example 2 of the present invention;
FIG. 10 is a schematic diagram of the clockwise tumbling motion of the robot arm driven environmental control unit of the present invention;
FIG. 11 is a schematic diagram illustrating the counterclockwise rotation of the robot arm driving the ring control device according to the present invention;
FIG. 12 is a schematic view of the dive attitude of the robot arm with the environmental control device;
FIG. 13 is a schematic view of the climbing posture of the robot arm driven environmental control device according to the present invention;
the blower and its duct are omitted from fig. 10-13 for ease of illustration.
Detailed Description
The utility model is further illustrated by the following examples.
Example 1
The embodiment provides a static test bed, which is based on a movable workbench frame (vehicle) built by an all-aluminum alloy frame, and an environment-controlled butt flange 6 is fixedly connected with the workbench frame (vehicle) 25 through a flange 24, as shown in fig. 3. Sequentially arranging an airborne electronic product ring control device to be tested in an airplane ring control cabin and assembling the ring control cabin on one side of a ring control butt flange (for example, assembling parts such as a skeleton structure of the ring control device, ring control components, an upper cabin body 1 of the ring control cabin, a lower cabin body 2 of the ring control cabin, a lower cabin body air hopper 3 of the ring control cabin, an upper cabin body air inlet hopper 4 of the ring control cabin, a wedge-shaped air inlet 5, a cabin body A heat exchanger 7, a cabin body A turbulent flow fan 22 and the like, as shown in figure 4); in fig. 1, 20 is an electrical appliance communication interface of the ring control cabin of the ring control device in this example, and 21 is a debugging wiring interface.
The other side of the environmental control butt flange 6 is fixed by adopting two aluminum profiles 9, the other ends of the aluminum profiles 9 are fixed on an annular evaporator fixing plate 16, and the annular evaporator 10 is fixed on a circular evaporator fixing plate through bolt pairs. The evaporator 10 and the evaporator fixing plate 16 are fixed on the environmental control butt flange through the aluminum alloy section 9 to realize rigid connection. As shown in fig. 5.
Connecting an environment-controlled air pipe 11 of a cabin body B of the environment-controlled device, a turbulent flow fan 12 of the cabin body B and a refrigerant circulating pipeline 19, respectively installing a simulation heat source 14/17 on aluminum alloy frames 15/9 of a head cabin 13 and a middle cabin 8, and finally adhering thermocouple temperature sensors of a multi-channel temperature patrol instrument on the aluminum alloy frames near the simulation heat source 14/17 to form an array; as shown in fig. 6.
And finally, sequentially sleeving an integrated transparent cylinder cover 18 made of an acrylic material into an annular evaporator fixing plate provided with an O-shaped ring or soft sealing material, and finally, carrying out rigid bolt connection or flexible sealing connection on the tail end of the cylinder cover and an annular control butt flange to form a simulation cabin body which is relatively closed in the front and the back, as shown in fig. 7.
Finally, installing a high-pressure vortex blower 23, starting an environment control device and a simulation heat source, and measuring the temperature distribution in the simulation cabin body in a stable state and the time required for reaching the stable state; and adjusting the power of the simulated heat source to simulate different working conditions, recording the temperature distribution of the simulated cabin body and the time curve for reaching the steady state, and finally obtaining the stability and reliability data of the performance of the environment control device, as shown in fig. 8.
The static test bed can simultaneously meet the requirements of assembling of the environment control device and evaluating the static running performance, avoids various loss risks and invalid working hours waste caused by repeated assembly and disassembly in the production process of the airborne electronic product, and greatly improves the productivity and reliability of the airborne electronic product.
Example 2
When the airplane carries the airborne electronic product to fly, the flying attitude of the airplane comprises pitching and rolling. The environment control device of the airborne electronic product is mainly divided into an inverse boosting turbine refrigeration environment control system and a closed circulation evaporation environment control system. The core components of the two environment control systems are a turbo compressor and a refrigerant compressor. When the aircraft has pitching and rolling postures, the rotor shaft of the compressor is subjected to unbalanced moment, so that the refrigerating capacity of the environment control system can be reduced, and the service life of the compressor can be prolonged. The embodiment provides a dynamic test device for simulating pitching and rolling postures of an airplane in a flying state and verifying functional kinetic energy of an airborne electronic product environment control device in a high dynamic range, namely a dynamic test bed.
Different from the embodiment 1, in the embodiment, the working bench (vehicle) 25 in the embodiment 1 is replaced by the mechanical arm 26, as shown in fig. 9, the cabin is controlled by fixing a ring flange to the mechanical arm gripper, the ring flange is butted with the mechanical arm gripper, the mechanical arm gripper rotates at different angles in different directions, the rolling and pitching postures of the airplane in the flying state are simulated, and the stability and the reliability of the refrigerating capacity of the test ring control device are judged by measuring the air temperature distribution in the simulated cabin under the same input working condition.
When simulating the ground refrigeration mode of the environmental control device, the mechanical arm 26 holds the hand in a horizontal state, and unloads the high-pressure vortex blower 23 and the blower air duct 27. When the environmental control device is used for refrigerating in the flight state of the simulated airplane, a high-pressure vortex blower and a blower air duct provide a high-pressure simulated air source.
The robot arm grippers swing up and down when the rolling attitude of the aircraft is simulated in the flying state, as shown in fig. 10 (clockwise rolling) -fig. 11 (counterclockwise rolling).
The gripper arms swing left and right when pitching in the flight state of the simulated aircraft, as shown in fig. 12 (dive attitude) -fig. 13 (climb attitude).
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (9)
1. The airborne electronic product environmental control device test bed is characterized in that the airborne electronic product environmental control device is divided into two parts, one part is arranged in an environmental control cabin of an airplane, the other part is arranged in a head cabin of the airplane, and the two parts are communicated through a refrigerant circulating pipeline; the method is characterized in that: the test bed comprises a simulation cabin body, an environment-controlled butt flange, a simulation heat source, a temperature polling instrument and a fixing plate;
the environment-controlled butt flange is used for fixing the environment-controlled cabin, the front end of the environment-controlled cabin is connected with the fixed plate through the rigid connecting component, and the front end of the fixed plate is used for mounting the part, located in the head cabin, of the airborne electronic product environment-controlled device; the simulation cabin body is a transparent cylinder cover, the fixed plate is sleeved on the simulation cabin body, the tail section of the cylinder cover is connected with the environment-controlled butt flange, the simulation cabin body is divided into two parts by the fixed plate, and the head cabin and the electronic cabin of the airplane are simulated respectively; the front end of the fixed plate is provided with a simulation heat source for simulating the heat of the head cabin through a bracket, and the rigid connecting component is provided with a simulation heat source for simulating the heat of the electronic cabin; the temperature polling instrument is used for measuring the temperature of the simulated heat source.
2. The test stand of claim 1, wherein: and the tail section of the cylinder cover is in rigid connection or flexible sealing connection with the environment-controlled butt flange.
3. The test stand of claim 1, wherein: the environment-controlled butt flange is arranged on the working bench to complete the static test.
4. The test stand of claim 1, wherein: the environment-controlled butt flange is arranged on the mechanical arm, and the mechanical arm drives the test bed to complete a dynamic test for simulating the flight of the airplane.
5. The test stand of claim 1, wherein: the simulation cabin body is made of acrylic transparent materials.
6. Test bench according to claim 1 or 3 or 4, characterized in that: the test device also comprises a high-pressure vortex blower which is used for simulating and providing ram air in the process of aircraft flight state test.
7. The test stand of claim 1, wherein: the fixing plate is provided with an o-shaped sealing ring or a soft sealing material and used for realizing the sealing isolation between the head cabin and the electronic cabin.
8. The test stand of claim 1, wherein: the temperature sensing color changing material is additionally arranged on the rigid connecting component and the bracket or the temperature sensing color changing gas is filled in the cabin body.
9. The test stand of claim 1, wherein: the number of the thermocouple temperature sensors of the temperature polling instrument distributed around each simulated heat source is at least four, the simulated heat sources are used as the center for layout, and the interval between the thermocouple temperature sensors is 50-100 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122526021.5U CN216350988U (en) | 2021-10-20 | 2021-10-20 | Test bed for airborne electronic product environment control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122526021.5U CN216350988U (en) | 2021-10-20 | 2021-10-20 | Test bed for airborne electronic product environment control device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216350988U true CN216350988U (en) | 2022-04-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202122526021.5U Active CN216350988U (en) | 2021-10-20 | 2021-10-20 | Test bed for airborne electronic product environment control device |
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| CN (1) | CN216350988U (en) |
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2021
- 2021-10-20 CN CN202122526021.5U patent/CN216350988U/en active Active
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