Radar temperature shock test equipment

Abstract

This invention relates to the field of material performance testing technology and discloses a radar temperature shock testing device, including a temperature shock testing chamber and a testing cavity formed on the side of the chamber. The chamber is used for testing the physical and electrical properties of radar materials and components under temperature shock. An air outlet is provided on the inner side of the testing cavity, and an air guide assembly is provided on the inner wall to prevent high and low temperature airflows from directly blowing onto the radar under test. In this invention, a portion of the airflow enters the exhaust hood through the connecting shell, driving the fan blades to rotate and then being evenly discharged from three exhaust hoods in multiple directions. Another portion of the airflow causes the air guide cloths of different lengths to oscillate irregularly, further dispersing the airflow. This dual airflow guidance avoids the direct and forceful blowing of high and low temperature airflows onto the radar components, eliminating the influence of airflow interference on material performance testing, ensuring the authenticity and repeatability of sample test data under temperature shock, and is suitable for the testing and analysis of the thermal stability, fatigue characteristics, and electrical properties of radar materials.

Description

Technical Field

[0001] This invention relates to the field of material performance testing technology, and in particular to radar temperature shock testing equipment. Background Technology

[0002] The three-chamber thermal shock test chamber is an environmental reliability test equipment consisting of three independent chambers: a high-temperature zone, a low-temperature zone, and a test zone. It switches airflow through air ducts and valves, allowing the test sample to withstand instantaneous alternating high and low temperature shocks while in a static state. It can independently complete high-temperature tests, low-temperature tests, and thermal shock tests, making it more comprehensive in function. Unlike the two-chamber suspended basket moving structure, it has no mechanical displacement and less vibration, making it suitable for vulnerable components such as radar, precision electronics, and optoelectronic components.

[0003] Currently, when using a three-chamber thermal shock test chamber to conduct temperature shock tests on radar products, the high and low temperature conditions must be switched rapidly within a specified time according to the test standards and procedures. To ensure the temperature conversion rate and temperature field response speed, the equipment delivers high and low temperature airflow to the test area with a large air volume. However, the large air volume will generate a strong airflow impact force, which will lead to force interference on the sample, deviation of the test data from the true performance of the material, and inability to accurately obtain the physical / electrical properties of the material under temperature shock. It may also cause problems such as loose cables and poor contact, ultimately resulting in uneven temperature field distribution and distorted test data, which seriously affects the accuracy and reliability of radar temperature shock testing.

[0004] Therefore, it is necessary to design radar temperature shock testing equipment to solve the above problems. Summary of the Invention

[0005] The purpose of this invention is to address the shortcomings of existing technologies by proposing a radar temperature shock testing device.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: A radar temperature shock testing device includes a temperature shock testing chamber and a testing cavity formed on the side of the temperature shock testing chamber. The temperature shock testing chamber is used to test the physical and electrical properties of radar materials and components under temperature shock. An air outlet is provided on the inner side of the testing cavity. A temperature sensor for accurately monitoring the test temperature inside the testing cavity is provided on the inner wall of the testing cavity. An air guide assembly is provided on the inner wall of the testing cavity to prevent high and low temperature airflow from directly blowing onto the test radar. Several wire-passing holes are formed in a linear array on the side of the inner bottom surface of the testing cavity. Several sets of replacement components corresponding to the wire-passing holes are provided on the inner bottom surface of the testing cavity. Several sets of semi-sealed heads with different inner diameters are provided on the replacement components. The air guiding assembly includes an air guiding hood fixedly installed on the inner wall of the test chamber at the upper part of the air outlet, and an exhaust hood fixedly installed on the inner top surface of the test chamber. The air guiding hood and the exhaust hood are connected by a connecting shell.

[0007] As a preferred embodiment of the present invention, the inner wall of the exhaust hood is rotatably equipped with fan blades, and the outer wall of the exhaust hood is provided with three air outlet hoods, and the three air outlet hoods and the connecting shell are arranged in a ring array on the outer wall of the exhaust hood.

[0008] As a preferred embodiment of the present invention, a plurality of mounting seats are symmetrically fixedly installed on the inner wall of the test chamber at the lower half of the air outlet. Among the plurality of mounting seats, two mounting seats located at the same horizontal position have air guide cloths fixedly installed on their inner walls, and a counterweight is fixedly installed on the end of the air guide cloth away from the mounting seat.

[0009] As a preferred embodiment of the present invention, the lengths of the various air guide cloths and the weights of the counterweights are all different.

[0010] As a preferred embodiment of the present invention, the replacement component includes a housing fixedly installed on the bottom surface of the test chamber, a rotating seat rotatably installed on the inner top surface of the housing, a plurality of fixed seats arranged in a circular array fixedly installed on the outer wall of the rotating seat, two guide grooves symmetrically opened on the side of the fixed seat, a guide block slidably installed on the inner wall of the guide groove, a clamping arm fixedly installed on the side of the guide block, a spring fixedly installed between the opposite sides of the two clamping arms, and an operating structure for controlling the rotating seat provided on the housing.

[0011] As a preferred embodiment of the present invention, the outer wall of the housing is provided with a clearance opening above the wire hole, and the guide groove is inclined.

[0012] As a preferred embodiment of the present invention, the semi-sealing head is fixedly installed at the end of the clamping arm, and the semi-sealing head is located directly above the wire hole.

[0013] As a preferred embodiment of the present invention, the operating structure includes a connecting sleeve fixedly installed on the top surface of the rotating seat, with the top end of the connecting sleeve passing through the top surface of the outer shell. An operating rod is movably installed on the inner wall of the connecting sleeve, and a pressure rod is fixedly installed on the outer wall of the top end of the operating rod. The bottom end of the pressure rod passes through the inner top surface of the outer shell. Support plates are slidably installed on the top surfaces of the two clamping arms, and alignment sleeves adapted to the pressure rods are fixedly installed on the top surfaces of the support plates.

[0014] As a preferred embodiment of the present invention, the inner wall of the top end of the connecting sleeve is provided with an annular groove, and two retaining rings are symmetrically fixedly fitted on the outer wall of the operating rod.

[0015] As a preferred embodiment of the present invention, the side of the temperature shock test chamber is hinged with a sealed door corresponding to the test chamber, and the inner bottom surface of the test chamber is slidably mounted with a material placement plate via a guide rail.

[0016] The present invention has the following beneficial effects: 1. During the testing process of this invention, the air guide assembly achieves airflow guidance through a dual structure. Part of the airflow enters the exhaust hood through the air guide cover and the connecting shell, and after driving the fan blades to rotate, it is evenly discharged from the three exhaust hoods in multiple directions. The other part of the airflow blows the air guide cloths of different lengths and weights to swing irregularly, further dispersing the airflow. The dual guidance can avoid the direct and forceful blowing of high and low temperature airflows on the radar assembly, eliminate the influence of airflow interference on the material performance test, and ensure that the test data of the sample under temperature shock is true and repeatable. It is suitable for the detection and analysis of the thermal stability, fatigue characteristics and electrical properties of radar materials. 2. This invention is equipped with multiple sets of semi-sealing plugs of different specifications. Operators can quickly switch between semi-sealing plugs that are compatible with the wire harness by rotating the connecting sleeve to drive the rotating seat. Pressing the operating rod will drive the clamping arm to move closer and lower along the inclined guide groove, thereby driving the semi-sealing plug to be quickly inserted into the wire hole to complete the seal. No additional parts need to be replaced. It is compatible with wire harnesses of different diameters. The operation is simple and quick. At the same time, it ensures the temperature sealing of the test chamber, reduces the leakage of hot and cold air, and ensures the stability of the test conditions. 3. With this invention, operators can directly open the sealed box door, pull out the material plate, place the radar component smoothly, and then push it back to its original position. The operation is simple and labor-saving, avoiding damage from bumps during radar placement. The structural design of the material plate for smooth movement, combined with standardized operations such as wire threading and sealing, and airflow guidance, ensures that the radar placement position, wiring method, and sealing status are consistent each time, reducing human error, improving the standardization and repeatability of the testing process, and adapting to the batch testing needs of radar components. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the overall structure of the radar temperature shock testing equipment proposed in this invention; Figure 2 This is a schematic diagram of the inner structure of the test cavity of the radar temperature shock testing device proposed in this invention. Figure 1 ; Figure 3 for Figure 2 Enlarged structural diagram at point A in the middle; Figure 4 This is a schematic diagram of the air guide shroud, exhaust shroud, and connecting shell structure of the radar temperature shock testing equipment proposed in this invention. Figure 5 This is a schematic diagram of the inner structure of the test cavity of the radar temperature shock testing device proposed in this invention. Figure 2 ; Figure 6 for Figure 5 Enlarged structural diagram at point B; Figure 7 This is a schematic diagram of the inner structure of the outer shell of the radar temperature shock testing equipment proposed in this invention; Figure 8 This is a schematic diagram of the rotating base structure of the radar temperature shock testing equipment proposed in this invention.

[0018] In the diagram: 1. Temperature shock test chamber; 2. Test chamber; 21. Temperature sensor; 3. Sealed door; 4. Air outlet; 5. Air guide assembly; 51. Mounting base; 52. Air guide cloth; 53. Counterweight; 54. Air guide cover; 55. Exhaust cover; 56. Connecting shell; 57. Fan blades; 58. Air outlet cover; 6. Material placement plate; 7. Threading hole; 8. Replacement components; 81. Housing; 82. Clearance opening; 83. Rotating seat; 84. Fixed seat; 85. Guide groove; 86. Guide block; 87. Clamping arm; 88. Spring; 9. Operating structure; 91. Connecting sleeve; 92. Operating rod; 93. Annular groove; 94. Snap ring; 95. Pressure rod; 96. Support plate; 97. Alignment sleeve; 10. Semi-sealed plug. Detailed Implementation

[0019] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0020] Example 1: The radar temperature shock testing equipment disclosed in this example is shown below. Figure 1-8 The test chamber includes a temperature shock test chamber 1 and a test cavity 2 located on the side of the temperature shock test chamber 1. The temperature shock test chamber 1 is used to test the physical and electrical properties of radar materials and components under temperature shock. A sealed door 3 corresponding to the test cavity 2 is hinged to the side of the temperature shock test chamber 1. An air outlet 4 is provided on the inner side of the test cavity 2. A temperature sensor 21 for accurately monitoring the test temperature inside the test cavity 2 is provided on the inner wall of the test cavity 2. A material placement plate 6 is slidably installed on the inner bottom surface of the test cavity 2 via a guide rail. An air guide component 5 is provided on the inner wall of the test cavity 2 to prevent high and low temperature airflow from directly blowing onto the test radar. Several wire holes 7 are provided in a linear array on the side of the inner bottom surface of the test cavity 2. Several sets of replacement components 8 corresponding to the wire holes 7 are provided on the inner bottom surface of the test cavity 2. Several sets of semi-sealed heads 10 with different inner diameters are provided on the replacement components 8.

[0021] The implementation principle of this embodiment is as follows: During actual testing, the staff first fully opens the sealed door 3 of the temperature shock test chamber 1, then smoothly pulls out the placement plate 6 inside the test chamber 2, positioning it in an easily operable position. The radar component to be tested can then be smoothly placed on the placement plate 6. After the radar component is placed, the placement plate 6 is smoothly pushed back into the test chamber 2 to reset, completing the sample placement operation. After resetting, the staff needs to orderly thread the required wiring harness of the radar component through the wiring holes 7 on the chamber, completing the external power supply and signal connection of the radar component. Simultaneously, according to the actual specifications of the wiring harness, the semi-sealed plug 10 is replaced with two semi-sealed plugs 10 adapted to the wiring harness size by replacing component 8, and the two semi-sealed plugs 10 are correspondingly embedded into the wiring holes 7 to achieve effective connection of the wiring holes 7. The test chamber 2 is sealed to ensure its internal temperature control and reduce the impact of hot and cold air leakage on the test conditions. After completing the wiring and sealing operations, the staff closes and locks the sealed door 3, and then starts the temperature shock test chamber 1 to conduct temperature shock tests on the radar components according to the preset program. During the continuous testing of the radar components, the high and low temperature airflow delivered from the air outlet 4 of the chamber can be reasonably changed in direction by the air guide component 5 built into the equipment, avoiding the high and low temperature airflow from directly and forcefully blowing on the surface of the radar components. This prevents the radar components from shaking or shifting due to direct airflow, ensuring the stability of the test process and the accuracy of the test results. Throughout the test, the temperature sensor 21 in the test chamber 2 can accurately monitor the test temperature in the test chamber 2 in real time to understand the test situation.

[0022] Example 2: Based on Example 1, this example discloses a radar temperature shock testing device, such as... Figure 2-4 As shown, the air guiding assembly 5 includes an air guiding hood 54 fixedly installed on the inner wall of the test chamber 2 at the upper half of the air outlet 4. An exhaust hood 55 is fixedly installed on the inner top surface of the test chamber 2. The air guiding hood 54 and the exhaust hood 55 are connected by a connecting shell 56. A fan blade 57 is rotatably installed on the inner wall of the exhaust hood 55. Three air outlet hoods 58 are provided through the outer wall of the exhaust hood 55, and the three air outlet hoods 58 and the connecting shell 56 are arranged in a ring array on the outer wall of the exhaust hood 55. Several mounting seats 51 are symmetrically fixedly installed on the inner wall of the test chamber 2 at the lower half of the air outlet 4. Air guiding cloths 52 are fixedly installed on the inner walls of two mounting seats 51 located at the same horizontal position. A counterweight 53 is fixedly installed on the end of the air guiding cloth 52 away from the mounting seat 51. The lengths of the several air guiding cloths 52 and the weights of the counterweights 53 are different.

[0023] The implementation principle of this embodiment is as follows: During the temperature shock test, a portion of the high and low temperature airflow blown out from the test chamber outlet 4 can directly enter the interior of the air guide shroud 54 and be smoothly transported to the exhaust shroud 55 via the connecting shell 56. As the airflow continues to flow inside the exhaust shroud 55, it will generate a continuous thrust on the fan blades 57 installed on the inner wall of the exhaust shroud 55, thereby driving the fan blades 57 to rotate smoothly. Under the action of rotation, the airflow is evenly distributed and transported to the three air outlet shrouds 58, so that the high and low temperature airflow is evenly diffused outward in multiple different directions. This effectively avoids the airflow directly blowing on the radar components and allows the airflow to be rapid and uniform. The airflow is evenly distributed throughout the entire test chamber 2. Another part of the high and low temperature airflow will blow the air guide cloth 52 set below upward when it passes through the lower half of the air outlet 4. Since the length of each air guide cloth 52 is different and the weight of its end counterweight 53 is also different, the air guide cloth 52 will exhibit an irregular natural swaying state under the continuous action of the airflow, which will further disturb and change the flow direction of the airflow, and achieve the guidance and dispersion of the airflow from another path. The dual structure works together to avoid the high and low temperature airflow blowing directly on the radar component, ensuring the stability and reliability of the test process.

[0024] Example 3: Based on Example 1, this example discloses a radar temperature shock testing device, such as... Figure 5 , Figure 6 and Figure 8 As shown, the replacement component 8 includes a housing 81 fixedly installed on the bottom surface of the test chamber 2. The outer wall of the housing 81 has a clearance opening 82 located above the wire hole 7. A rotating seat 83 is rotatably installed on the inner top surface of the housing 81. Several fixed seats 84 arranged in a circular array are fixedly installed on the outer wall of the rotating seat 83. Two guide grooves 85 are symmetrically opened on the side of the fixed seat 84. The guide grooves 85 are inclined. A guide block 86 is slidably installed on the inner wall of the guide groove 85. A clamping arm 87 is fixedly installed on the side of the guide block 86. A spring 88 is fixedly installed between the opposite sides of the two clamping arms 87. A semi-sealing head 10 is fixedly installed at the end of the clamping arm 87, and the semi-sealing head 10 is located directly above the wire hole 7. An operating structure 9 for controlling the rotating seat 83 is provided on the housing 81.

[0025] The implementation principle of this embodiment is as follows: During the installation of the wire harness and sealing of the threading hole 7, the operator first drives the rotating seat 83 to rotate via the operating mechanism 9, rotating a set of semi-sealing heads 10, which are compatible with the outer diameter of the current wire harness, to a position directly above the threading hole 7. Then, a downward pressing force is applied to the operating mechanism 9, causing the two clamping arms 87 to move downwards synchronously. During the downward movement of the two clamping arms 87, the guide blocks 86 at their ends can slide along the corresponding inclined guide grooves 85. Guided by the inclined guide grooves 85, the two clamping arms 87 will... As they slide downwards, they gradually move closer together. This clamping and moving action acts on the two semi-sealing heads 10, causing them to move downwards synchronously while they are close together. This allows the two semi-sealing heads 10 to be accurately and quickly inserted into the wire hole 7, tightly enclosing and forming a complete sealing structure, thus achieving a reliable seal for the wire hole 7. At the same time, since multiple sets of semi-sealing heads 10 of different specifications are pre-set inside the housing 81, they can be used to adapt to different wire diameters and different numbers of wiring harnesses without the need for additional parts replacement, making the overall operation simpler and faster.

[0026] Example 4: Based on Example 1, this example discloses a radar temperature shock testing device, such as... Figure 7 and Figure 8 As shown, the operating structure 9 includes a connecting sleeve 91 fixedly installed on the top surface of the rotating seat 83, with the top end of the connecting sleeve 91 passing through the top surface of the outer shell 81. An operating rod 92 is movably installed on the inner wall of the connecting sleeve 91. An annular groove 93 is opened on the inner wall of the top end of the connecting sleeve 91. Two retaining rings 94 are symmetrically fixedly fitted on the outer wall of the operating rod 92. A pressure rod 95 is fixedly installed on the outer wall of the top end of the operating rod 92, with the bottom end of the pressure rod 95 passing through the inner top surface of the outer shell 81. A support plate 96 is slidably installed on the top surface of the two clamping arms 87. An alignment sleeve 97 adapted to the pressure rod 95 is fixedly installed on the top surface of the support plate 96.

[0027] The implementation principle of this embodiment is as follows: During the selection of the semi-sealing head 10 according to the wiring harness specifications and the rotation of the rotating seat 83, the operator can rotate the connecting sleeve 91, which will directly drive the rotating seat 83 to rotate synchronously, realizing the rapid switching and alignment of the corresponding specification semi-sealing head 10. During this process, because the pressure rod 95 is installed through the top surface of the outer shell 81, the operating rod 92 cannot rotate circumferentially under the limiting action of the pressure rod 95. Then, when applying downward pressure to the clamping arm 87 to complete the sealing action, the operator can press the operating rod 92 downward, so that the operating rod 92 moves along the connecting sleeve 81 to rotate circumferentially. The sleeve 91 slides downward inside, at which time the pressure rod 95 can smoothly enter the alignment sleeve 97 and simultaneously apply downward pressure to the alignment sleeve 97 and the support plate 96, thereby driving the two clamping arms 87 to move downward to complete the clamping and sealing action. When the operating rod 92 is in the upper rotation adjustment position and the lower pressing and sealing position, the retaining ring 94 can be stably engaged in the corresponding annular groove 93, so that the position of the operating rod 92 is reliably limited, ensuring that the overall structure can operate stably during adjustment and sealing, and improving the reliability of operation.

[0028] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A radar temperature shock testing device, comprising a temperature shock testing chamber (1) and a test cavity (2) formed on the side of the temperature shock testing chamber (1), wherein the temperature shock testing chamber (1) is used for testing the physical and electrical properties of radar materials and components under temperature shock, and an air outlet (4) is provided on the inner side of the test cavity (2), and a temperature sensor (21) is provided on the inner wall of the test cavity (2) for accurately monitoring the test temperature inside the test cavity (2), characterized in that, The inner wall of the test chamber (2) is provided with a wind guide assembly (5) to prevent high and low temperature airflow from blowing directly onto the test radar. Several wire holes (7) are provided on the inner bottom side of the test chamber (2) in a linear array. Several sets of replacement assemblies (8) corresponding to the wire holes (7) are provided on the inner bottom surface of the test chamber (2). Several sets of semi-sealing heads (10) with different inner diameters are provided on the replacement assemblies (8). The air guide assembly (5) includes an air guide hood (54) fixedly installed on the inner wall of the test chamber (2) at the upper half of the air outlet (4), and an exhaust hood (55) fixedly installed on the inner top surface of the test chamber (2). The air guide hood (54) and the exhaust hood (55) are connected by a connecting shell (56).

2. The radar temperature shock testing equipment according to claim 1, characterized in that, The inner wall of the exhaust hood (55) is rotatably equipped with fan blades (57), and the outer wall of the exhaust hood (55) is provided with three air outlet hoods (58), and the three air outlet hoods (58) and the connecting shell (56) are arranged in a ring array on the outer wall of the exhaust hood (55).

3. The radar temperature shock testing equipment according to claim 1, characterized in that, The inner wall of the test chamber (2) is symmetrically fixed with several mounting seats (51) at the lower half of the air outlet (4). Among the several mounting seats (51), two mounting seats (51) located at the same horizontal position are fixedly installed with air guide cloth (52) on their inner walls. The end of the air guide cloth (52) away from the mounting seat (51) is fixedly installed with a counterweight (53).

4. The radar temperature shock testing equipment according to claim 3, characterized in that, The lengths of the various air guide cloths (52) and the weights of the counterweights (53) are all different.

5. The radar temperature shock testing equipment according to claim 1, characterized in that, The replacement component (8) includes a housing (81) fixedly installed on the bottom surface of the test chamber (2). A rotating seat (83) is rotatably installed on the inner top surface of the housing (81). Several fixed seats (84) arranged in a ring array are fixedly installed on the outer wall of the rotating seat (83). Two guide grooves (85) are symmetrically opened on the side of the fixed seat (84). A guide block (86) is slidably installed on the inner wall of the guide groove (85). A clamping arm (87) is fixedly installed on the side of the guide block (86). A spring (88) is fixedly installed between the opposite sides of the two clamping arms (87). An operating structure (9) for controlling the rotating seat (83) is provided on the housing (81).

6. The radar temperature shock testing equipment according to claim 5, characterized in that, The outer wall of the outer casing (81) has a clearance opening (82) located above the wire hole (7), and the guide groove (85) is inclined.

7. The radar temperature shock testing equipment according to claim 5, characterized in that, The semi-sealing head (10) is fixedly installed at the end of the clamping arm (87), and the semi-sealing head (10) is located directly above the wire hole (7).

8. The radar temperature shock testing equipment according to claim 5, characterized in that, The operating structure (9) includes a connecting sleeve (91) fixedly installed on the top surface of the rotating seat (83), and the top end of the connecting sleeve (91) passes through the top surface of the outer shell (81). An operating rod (92) is movably installed on the inner wall of the connecting sleeve (91). A pressure rod (95) is fixedly installed on the outer wall of the top end of the operating rod (92), and the bottom end of the pressure rod (95) passes through the inner top surface of the outer shell (81). A support plate (96) is slidably installed on the top surface of the two clamping arms (87), and an alignment sleeve (97) adapted to the pressure rod (95) is fixedly installed on the top surface of the support plate (96).

9. The radar temperature shock testing equipment according to claim 8, characterized in that, The inner wall of the top end of the connecting sleeve (91) is provided with an annular groove (93), and two retaining rings (94) are symmetrically fixedly fitted on the outer wall of the operating rod (92).

10. The radar temperature shock testing equipment according to claim 1, characterized in that, The side of the temperature shock test chamber (1) is hinged with a sealed door (3) corresponding to the test chamber (2), and the inner bottom surface of the test chamber (2) is slidably mounted with a material plate (6) via a guide rail.

Images