A test bench for aircraft ejection seat and test method thereof

Abstract

The present invention relates to the technical field of aircraft ejection seat detection, and in particular to an aircraft ejection seat detection test bench and a test method thereof. Its technical solution includes: a test external component, a test seat adjustment clamping component is installed inside the test external component, two groups of seat clamping components are installed on both sides of the test seat adjustment clamping component, and a variable detection component is installed on the top of the inner wall of the test external component. The present invention drives the positioning spring through the cross positioning plate through the tilt rod to give the positioning spring connected to the sensor push-pull force to obtain X-axis data, and then more detailed records of the tilt state of the aircraft ejection seat during ejection, and then cooperates with the variable detection component to more comprehensively understand the posture of the aircraft ejection seat during ejection, thereby further improving the accuracy of the aircraft ejection seat test data and reducing the problems that occur when the aircraft ejection seat is put into production.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft ejection seat detection, and in particular to a detection test bench for an aircraft ejection seat and a test method thereof. Background Art

[0002] The research and development of lightweight seat components for eVTOL aircraft has great development significance for the existing direction of aviation. Existing flying cars must pursue ultra-high strength and ultra-corrosion-resistant lightweight materials to prevent security threats caused by sudden climate change. Therefore, lightweight seat components for eVTOL aircraft must have the basic characteristics of high strength, light weight, and corrosion resistance, while ensuring the size of components and coating adhesion (durability).

[0003] When installing the ejection seat on the test bench, it may be installed inaccurately or not fixed firmly. If there is a gap, looseness or installation angle deviation in the connection between the seat and the test bench, the seat may be unevenly stressed during the ejection simulation, affecting the measurement results of the ejection trajectory and other performance parameters. Moreover, this situation may cause damage to the test bench and the seat itself, posing a safety hazard.

[0004] In the patent document with the published announcement number CN114216709B, a test bench and a test method for an aircraft ejection seat are disclosed. By setting a first hydraulic cylinder, the pressure resistance of the aircraft ejection seat can be tested by extending a plurality of first hydraulic cylinders set on the inner surface of the detection cavity during use. The aircraft ejection seat is adsorbed by a vacuum suction cup, and the tensile capacity of the aircraft ejection seat can be tested by shortening the first hydraulic cylinder, which makes the test more convenient and quick.

[0005] When the above device is in use, it utilizes a plurality of first hydraulic cylinders and vacuum suction cups to clamp the upper and lower surfaces of the aircraft ejection seat. When the aircraft ejection seat is ejected, not only its stretching capacity must be tested, but also the ejection posture of the aircraft ejection seat must be detected. If the posture is incorrect, the ejection trajectory will become uncontrollable due to uneven force. The above device does not detect the ejection posture of the aircraft ejection seat, resulting in poor detection efficiency.

[0006] Therefore, the present application proposes a test bench and a test method for an aircraft ejection seat. Summary of the invention

[0007] The purpose of the present invention is to address the problem in the background technology that when an aircraft ejection seat is ejected, not only its stretching capacity needs to be tested, but also the ejection posture of the aircraft ejection seat needs to be detected. The current device ignores the problem of seat ejection posture detection, and proposes a detection test bench for an aircraft ejection seat and a test method thereof.

[0008] On the one hand, the present invention provides a test bench for an aircraft ejection seat, comprising an external test assembly, a test seat adjustment clamp assembly is installed inside the external test assembly, two sets of seat clamp assemblies are installed on both sides of the test seat adjustment clamp assembly, and a variable detection assembly is installed on the top of the inner wall of the external test assembly;

[0009] The test external component includes a test protection frame, the test seat adjustment clamping component includes a positioning rod fixedly installed on the inner wall of the test protection frame, a side of the positioning rod away from the test protection frame is fixedly installed with a transverse slide, the inner wall of the test protection frame is fixedly installed with a second forward and reverse motor, the output shaft of the second forward and reverse motor is fixedly installed with a second threaded rod, the outer side of the second threaded rod is threadedly installed with two ejection component clamping arc blocks, and the two ejection component clamping arc blocks are slidably installed inside the transverse slide, the outer side of the ejection component clamping arc block is fixedly installed with a placement block, and one side of the placement block is fixedly installed with a snap-fit ​​positioning frame;

[0010] The seat clamping assembly includes a side ball bar rotatably installed inside a snap-fit ​​positioning frame, a turntable is fixedly installed on the outer side of the side ball bar, an arc-shaped shifting clamp is fixedly installed on the top of the turntable, two groups of hollow transmission rods are fixedly installed on the top of the arc-shaped shifting clamp, a hydraulic clamping rod is fixedly installed inside the hollow transmission rod, a group of inflatable seat clamping plates are fixedly installed on the output shaft of the hydraulic clamping rod through a slide rail, the number of the inflatable seat clamping plates is two groups, and the other group of inflatable seat clamping plates is fixedly installed on the bottom of the hollow transmission rod, and a pressure sensing assembly is fixedly installed on one side of the two groups of inflatable seat clamping plates.

[0011] Optionally, a plurality of positioning springs are fixedly mounted on one side of the snap-fit ​​positioning frame facing the side club, a cross positioning plate is fixedly mounted on one side of the plurality of positioning springs, and two groups of tilting rods are hinged on both sides of the cross positioning plate.

[0012] Optionally, a movable positioning plate is fixedly installed on one side of the tilt rod away from the cross positioning plate, a limiting spring is fixedly installed on one side of the movable positioning plate, a sliding rod is provided on one side of the movable positioning plate, the limiting spring is fixedly installed on the inner wall of the snap-fit ​​positioning frame, a spherical block is rotatably installed on the outer side of the tilt rod, and a side ball rod is fixedly installed on one side of the spherical block.

[0013] Optionally, the number of the movable positioning plates, tilting rods, sliding rods and limiting springs is four groups, and the four groups of the movable positioning plates, tilting rods, sliding rods and limiting springs are arranged in a ring state with respect to the spherical block and the cross positioning plate.

[0014] Optionally, the test external component also includes two sliding channels fixedly mounted on the side walls of the test protection frame, a test door is provided on the side of the test protection frame away from the sliding channels, a first forward and reverse motor is fixedly mounted between the two sliding channels, and a first threaded rod is fixedly mounted on the output shaft of the first forward and reverse motor.

[0015] Optionally, a shielding plate is inserted into the top of the test protection frame, the shielding plate is threadedly installed on the outside of the first threaded rod, and the shielding plate is slidably installed on one side of the two sliding channels.

[0016] Optionally, the variable detection component includes a positioning chuck fixedly mounted on the bottom of the baffle plate, and a plurality of sliding cavity positioning frames arranged in a circular shape with respect to the outer surface of the positioning chuck are fixedly mounted on the bottom of the positioning chuck, and the same number of fixed connecting rods are slidably mounted inside the plurality of sliding cavity positioning frames.

[0017] Optionally, a multi-arc hole positioning plate is rotatably installed on one side of the positioning chuck, a positioning round block is slidably installed inside the sliding cavity positioning frame, the positioning round block is fixedly installed on one side of the fixed connecting rod, an arc-shaped detection plate is fixedly installed on one side of the fixed connecting rod, and a plurality of negative pressure adsorption holes are opened on the surface of the arc-shaped detection plate.

[0018] Optionally, a telescopic airbag block is fixedly installed on the side of the arc detection plate away from the fixed connecting rod, an external anti-pressure plate is fixedly installed on the side of the telescopic airbag block away from the arc detection plate, a positioning track frame is fixedly installed on the side wall of the arc detection plate, two groups of arc-shaped anti-pressure blocks are fixedly installed on the inner wall of the telescopic airbag block, the two groups of arc-shaped anti-pressure blocks are hinged on both sides of the positioning track frame, a pressure detection block is slidably installed inside the positioning track frame, and an elastic spring rod is fixedly installed between the pressure detection block and the positioning track frame.

[0019] In another aspect, the present application provides:

[0020] The test method for detecting an aircraft ejection seat comprises the following steps:

[0021] S1: The staff first opens the test door and adjusts the position of the shielding plate through the first forward and reverse motor. When the shielding plate is adjusted, the multi-variable detection assembly is driven to leave the test protection frame, and the aircraft ejection seat is placed inside the test protection frame;

[0022] S2: When the aircraft ejection seat is placed in the test protection frame, the second forward and reverse motor drives the second threaded rod to rotate, and the second threaded rod drives the two lateral slides to contact the ejector of the aircraft ejection seat, wrap it and position it, and position the aircraft ejection seat in the middle;

[0023] S3: Then, a set of inflatable seat clamping plates is attached to the bottom of the aircraft ejection seat, and another set of inflatable seat clamping plates is attached to the upper surface of the aircraft ejection seat through the hydraulic push-pull force of the hydraulic clamping rod, so that the two are in a clamping state for the aircraft ejection seat;

[0024] S4: When the aircraft ejection seat is being tested, the aircraft ejection seat transmits pressure to the inflatable seat clamping plate connected to the arc-shaped displacement clamping plate, and the spherical block deflects along the Y-axis of the aircraft ejection seat along the four wrapped tilting rods based on the tension or thrust of the side ball rods. The tilting rods follow the forces received in various directions to drive the sliding rods at the corresponding force-bearing positions on the surrounding sides to squeeze the limit springs, and then the pressure sensing components at the connection between the limit springs and the engaging positioning frame detect relevant data, and the corresponding one side tilting rod drives the positioning spring through the cross positioning plate to give tension to the sensor connected to the positioning spring, and the other side is thrust, so that the X-axis data is obtained;

[0025] S5: the output shaft of the third forward and reverse motor drives the multi-arc hole positioning plate to rotate along the positioning chuck and the sliding cavity positioning frame. The rotation of the multi-arc hole positioning plate causes the positioning round block to move along the sliding cavity positioning frame toward the center of the aircraft ejection seat, and the arc detection plate wraps the aircraft ejection seat. The negative pressure adsorption hole generates negative pressure adsorption on the aircraft ejection seat through the built-in air pump. When the multi-arc hole positioning plate rotates in the opposite direction, the fixed connecting rod moves away from the aircraft ejection seat, generating a pulling force on the aircraft ejection seat, and the stretching degree of the aircraft ejection seat is detected through the pressure detection component.

[0026] S6: Finally, when the arc detection plate passes through the farthest distance from the aircraft ejection seat and is at a distance close to the stretching degree of the aircraft ejection seat, it contacts the aircraft ejection seat ejected by the ejector respectively, and the arc detection plate obtains corresponding pressure data by squeezing the pressure detection block, thereby obtaining the test data of the aircraft ejection seat.

[0027] In summary, the present application includes at least one of the following beneficial technical effects:

[0028] 1. The spherical block deflects along the Y-axis of the aircraft ejection seat based on the pulling force or thrust of the side ball rods along the four wrapped tilt rods. At the same time, the tilt rod drives the positioning spring through the cross positioning plate to give the sensor connected to the positioning spring a push-pull force to obtain X-axis data, thereby recording the tilt state of the aircraft ejection seat during ejection in more detail. In combination with the variable detection components, the posture problems of the aircraft ejection seat during ejection can be more comprehensively understood, thereby further improving the accuracy of the aircraft ejection seat test data and reducing the problems that occur when the aircraft ejection seat is put into production;

[0029] 2. The negative pressure adsorption hole generates negative pressure adsorption on the aircraft ejection seat through the built-in air pump. When the multi-arc hole positioning plate rotates in the opposite direction, the fixed connecting rod moves away from the aircraft ejection seat, generating tension on the aircraft ejection seat. A pressure detection component is arranged inside the external pressure plate. The stretching degree of the aircraft ejection seat is detected through the pressure detection component, and then the stretching degree and quality of the aircraft ejection seat are tested, thereby ensuring the production quality of the aircraft ejection seat;

[0030] 3. If the ejection seat of the aircraft applies too much pressure to the arc detection plate, the arc-shaped pressure-resistant block will open through the pressure of the telescopic airbag block to avoid directly transmitting the pressure of the arc detection plate to a point of the external pressure-resistant plate, causing the external pressure-resistant plate to be damaged by excessive force. The external pressure-resistant plate uses the telescopic airbag block to buffer the force, reducing the damage of the external pressure-resistant plate to the inner wall of the test protection frame. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 A schematic structural diagram of a test bench for an aircraft ejection seat according to the present invention is provided;

[0032] Figure 2 A structural schematic diagram of the test protection frame of the present invention is given;

[0033] Figure 3 A schematic structural diagram of a first threaded rod of the present invention is provided;

[0034] Figure 4 A schematic structural diagram of the external pressure-resistant plate of the present invention is given;

[0035] Figure 5 A schematic structural diagram of a multi-arc hole positioning disk of the present invention is given;

[0036] Figure 6 A structural schematic diagram of the arc detection plate of the present invention is given;

[0037] Figure 7 A schematic diagram of the structure of the ejection assembly clamping the arc block of the present invention is given;

[0038] Figure 8 A structural schematic diagram of the positioning rod of the present invention is given;

[0039] Fig. 9 The present invention is given Figure 8 Enlarged view of the middle A area;

[0040] Fig.10 A structural schematic diagram of the hydraulic clamping rod of the present invention is given;

[0041] Fig.11 A schematic structural diagram of a side club of the present invention is provided.

[0042] Figure numerals: 1. Test external component; 101. Test protection frame; 102. Slide cavity; 103. Shielding plate; 104. First forward and reverse motor; 105. First threaded rod; 2. Test seat adjustment clamping component; 201. Positioning plug rod; 202. Second forward and reverse motor; 203. Second threaded rod; 204. Ejection component clamping arc block; 205. Placement block; 206. Horizontal slide; 207. Engagement positioning frame; 3. Multi-variable detection component; 301. Multi-arc hole positioning plate; 302. Arc detection plate; 303. Negative pressure adsorption hole; 304. Positioning chuck; 305. Slide cavity positioning frame; 306. External anti Pressure plate; 307, fixed connecting rod; 308, positioning round block; 309, telescopic airbag block; 310, positioning track frame; 311, arc-shaped anti-pressure block; 312, pressure detection block; 313, elastic spring rod; 4, seat clamping assembly; 401, arc-shaped displacement clamping plate; 402, turntable; 403, side ball rod; 404, inflatable seat clamping plate; 405, pressure sensing assembly; 406, hollow transmission rod; 407, hydraulic clamping rod; 408, spherical block; 409, tilt rod; 410, cross positioning plate; 411, positioning spring; 412, movable positioning plate; 413, sliding rod; 414, limiting spring. DETAILED DESCRIPTION

[0043] The technical solution of the present invention is further described below in conjunction with the accompanying drawings and specific embodiments.

[0044] like Figure 1-Figure 3 As shown, the present invention provides a test bench for an aircraft ejection seat, comprising a test external component 1, a test seat adjustment clamping component 2 is installed inside the test external component 1, two sets of seat clamping components 4 are installed on both sides of the test seat adjustment clamping component 2, and a variable detection component 3 is installed on the top of the inner wall of the test external component 1;

[0045] The test external component 1 also includes two slide channels 102 fixedly mounted on the side wall of the test protection frame 101, a test door is arranged on the side of the test protection frame 101 away from the slide channel 102, a first forward and reverse motor 104 is fixedly mounted between the two slide channels 102, a first threaded rod 105 is fixedly mounted on the output shaft of the first forward and reverse motor 104, a shielding plate 103 is plugged into the top of the test protection frame 101, a third forward and reverse motor is fixedly mounted on the top of the shielding plate 103, and the output shaft of the third forward and reverse motor is connected to the multi-arc hole positioning plate 301, and the shielding plate 103 is threaded Installed on the outside of the first threaded rod 105, the baffle plate 103 is slidably installed on one side of the two sliding channels 102. First, open the test door and start to place the aircraft ejection seat in the test protection frame 101. First, the first forward and reverse motor 104 drives the first threaded rod 105 to rotate, and the baffle plate 103 moves upward along the sliding channel 102 under the guidance of the thread of the first threaded rod 105. Then the baffle plate 103 drives the variable detection component 3 to leave the test protection frame 101. Without the interference of the variable detection component 3, the aircraft ejection seat is placed inside the test protection frame 101.

[0046] like Figure 1-Figure 8 As shown, the test external component 1 includes a test protection frame 101, and the test seat adjustment clamping component 2 includes a positioning rod 201 fixedly installed on the inner wall of the test protection frame 101, and a horizontal slide 206 is fixedly installed on the side of the positioning rod 201 away from the test protection frame 101. The inner wall of the test protection frame 101 is fixedly installed with a second forward and reverse motor 202, and the output shaft of the second forward and reverse motor 202 is fixedly installed with a second threaded rod 203. The outer side of the second threaded rod 203 is threadedly installed with two ejection component clamping arc blocks 204, and the two ejection component clamping arc blocks 204 are slidably installed on Inside the transverse slide 206, a placement block 205 is fixedly installed on the outside of the ejection assembly clamping arc block 204, and a locking positioning frame 207 is fixedly installed on one side of the placement block 205. When the aircraft ejection seat is placed in the test protection frame 101, the second forward and reverse motor 202 drives the second threaded rod 203 to rotate, and the threads of the second threaded rod 203 and the two transverse slides 206 are opposite. Therefore, the second threaded rod 203 drives the two transverse slides 206 to contact the ejector of the aircraft ejection seat, wrap it and position it, and position the aircraft ejection seat in the middle.

[0047] like Figure 1-Figure 6As shown, the variable detection component 3 includes a positioning chuck 304 fixedly mounted on the bottom of the shielding plate 103, a plurality of sliding cavity positioning frames 305 arranged in a circular shape about the outer surface of the positioning chuck 304 are fixedly mounted on the bottom of the positioning chuck 304, the same number of fixed connecting rods 307 are slidably mounted inside the plurality of sliding cavity positioning frames 305, a multi-arc hole positioning disk 301 is rotatably mounted on one side of the positioning chuck 304, a positioning round block 308 is slidably mounted inside the sliding cavity positioning frame 305, the positioning round block 308 is fixedly mounted on one side of the fixed connecting rod 307, a curved detection plate 302 is fixedly mounted on one side of the fixed connecting rod 307, a plurality of negative pressure adsorption holes 303 are opened on the surface of the curved detection plate 302, after the aircraft ejection seat is placed, the shielding plate 103 follows the guidance of the first threaded rod 105 and fits against the top of the test protection frame 101, at this time, the aircraft ejection seat is wrapped in the plurality of curved detection plates 302 Next, first, the output shaft of the third forward and reverse motor drives the multi-arc hole positioning disk 301 to rotate along the positioning chuck 304 and the sliding cavity positioning frame 305. When the multi-arc hole positioning disk 301 rotates, the arc groove on its surface guides the positioning round block 308 to slide along the arc groove. At this time, the positioning round block 308 moves toward the center of the aircraft ejection seat along the sliding cavity positioning frame 305, and the arc detection plate 302 wraps the aircraft ejection seat. The negative pressure adsorption hole 303 generates negative pressure adsorption on the aircraft ejection seat through the built-in air pump. When the multi-arc hole positioning disk 301 rotates in the opposite direction, the fixed connecting rod 307 moves away from the aircraft ejection seat, generating tension on the aircraft ejection seat. A pressure detection component is arranged inside the external pressure-resistant plate 306. The stretching degree of the aircraft ejection seat is detected by the pressure detection component, and then the stretching degree and quality of the aircraft ejection seat are detected, thereby ensuring the production quality of the aircraft ejection seat.

[0048] A telescopic airbag block 309 is fixedly installed on one side of the arc detection plate 302 away from the fixed connecting rod 307, an external anti-pressure plate 306 is fixedly installed on one side of the telescopic airbag block 309 away from the arc detection plate 302, a positioning track frame 310 is fixedly installed on the side wall of the arc detection plate 302, two groups of arc-shaped anti-pressure blocks 311 are fixedly installed on the inner wall of the telescopic airbag block 309, the two groups of arc-shaped anti-pressure blocks 311 are hinged on both sides of the positioning track frame 310, a pressure detection block 312 is slidably installed inside the positioning track frame 310, an elastic spring rod 313 is fixedly installed between the pressure detection block 312 and the positioning track frame 310, and at the same time, when the arc detection plate 302 passes through the farthest distance from the aircraft ejection seat and is at a distance close to the degree of stretching of the aircraft ejection seat, it is respectively in contact with the ejection seat of the ejection device. When the aircraft ejection seat comes into contact with the arc detection plate 302, the arc detection plate 302 obtains corresponding pressure data by squeezing the pressure detection block 312, thereby understanding the attenuation of the force applied to the aircraft ejection seat between these two distances, and thereby better understanding the ejection force of the aircraft ejection seat. If the pressure applied by the aircraft ejection seat to the arc detection plate 302 is too large, the arc pressure-resistant block 311 opens through the pressure of the telescopic airbag block 309, thereby avoiding directly transmitting the pressure of the arc detection plate 302 to a point of the external pressure-resistant plate 306, causing the external pressure-resistant plate 306 to be damaged by excessive force, and the external pressure-resistant plate 306 uses the telescopic airbag block 309 to buffer the force, thereby reducing the damage of the external pressure-resistant plate 306 to the inner wall of the test protection frame 101.

[0049] In this embodiment, Figure 7-Figure 11 As shown, the seat clamping assembly 4 includes a side ball rod 403 rotatably mounted inside the locking positioning frame 207, a turntable 402 is fixedly mounted on the outer side of the side ball rod 403, an arc-shaped position-changing clamping plate 401 is fixedly mounted on the top of the turntable 402, two groups of hollow transmission rods 406 are fixedly mounted on the top of the arc-shaped position-changing clamping plate 401, a hydraulic clamping rod 407 is fixedly mounted inside the hollow transmission rod 406, and a group of inflatable seat clamping plates 404 are fixedly mounted on the output shaft of the hydraulic clamping rod 407 through a slide rail, and the number of the inflatable seat clamping plates 404 is two. The first and second inflatable seat clamping plates 404 are fixedly mounted on the bottom of the hollow transmission rod 406. A pressure sensing component 405 is fixedly mounted on one side of the two inflatable seat clamping plates 404. One group of inflatable seat clamping plates 404 is attached to the bottom of the aircraft ejection seat, while the other group of inflatable seat clamping plates 404 is attached to the upper surface of the aircraft ejection seat through the hydraulic push-pull force of the hydraulic clamping rod 407, so that the two are in a clamping state for the aircraft ejection seat. The pressure sensing component 405 is used to test various data of the aircraft ejection seat during the test.

[0050] A plurality of positioning springs 411 are fixedly installed on the side of the locking positioning frame 207 facing the side ball rod 403, a cross positioning plate 410 is fixedly installed on one side of the plurality of positioning springs 411, two sets of tilting rods 409 are hinged on both sides of the cross positioning plate 410, a movable positioning plate 412 is fixedly installed on one side of the tilting rod 409 away from the cross positioning plate 410, a limited spring 414 is fixedly installed on one side of the movable positioning plate 412, a sliding rod 413 is provided on one side of the movable positioning plate 412, and the limited spring 414 is fixedly installed on the inner wall of the locking positioning frame 207, and the tilting rod 412 is hinged on both sides of the cross positioning plate 410. 09 is rotatably mounted on the outer side of the spherical block 408, and a side ball rod 403 is fixedly mounted on one side of the spherical block 408. There are four groups of movable positioning plates 412, tilting rods 409, sliding rods 413 and limiting springs 414, and the four groups of movable positioning plates 412, tilting rods 409, sliding rods 413 and limiting springs 414 are arranged in a ring state with respect to the spherical block 408 and the cross positioning plate 410. When the aircraft ejection seat is being tested, such as when the aircraft ejection seat is ejected, the aircraft ejection seat transmits pressure to the inflatable seat clamp connected to the arc-shaped displacement clamp 401. On the plate 404, if the ejection seat of the aircraft deflects or tilts in different directions during ejection, the arc-shaped displacement clamp plate 401 transmits the pulling force or thrust to the spherical block 408 through the side ball rod 403, and the spherical block 408 deflects along the Y-axis of the ejection seat of the aircraft along the four wrapped tilting rods 409 based on the pulling force or thrust of the side ball rod 403, and the tilting rod 409 follows the forces received in various directions to drive the sliding rod 413 at the corresponding force position on the side to squeeze the limiting spring 414, so that the pressure sensing portion of the connection between the limiting spring 414 and the engaging positioning frame 207 is The relevant data should be detected by the components. If the aircraft ejection seat is tilted during ejection, the corresponding tilt rod 409 on one side drives the positioning spring 411 through the cross positioning plate 410 to give a pulling force to the sensor connected to the positioning spring 411, while the other side is a thrust, so as to obtain X-axis data, and then record the tilt state of the aircraft ejection seat during ejection in more detail, and then cooperate with the variable detection component 3 to have a more comprehensive understanding of the posture problems of the aircraft ejection seat during ejection, thereby further improving the accuracy of the aircraft ejection seat test data and reducing the problems that occur when the aircraft ejection seat is put into production.

[0051] In another aspect, the present application provides:

[0052] The test method for detecting an aircraft ejection seat comprises the following steps:

[0053] S1: The staff first opens the test door and adjusts the position of the shielding plate 103 through the first forward and reverse motor 104. When the shielding plate 103 is adjusted, the multi-variable detection assembly 3 is driven to leave the test protection frame 101, and the aircraft ejection seat is placed inside the test protection frame 101;

[0054] S2: When the aircraft ejection seat is placed in the test protection frame 101, the second forward and reverse motor 202 drives the second threaded rod 203 to rotate, and the second threaded rod 203 drives the two transverse slides 206 to contact the ejector of the aircraft ejection seat, wrap it and position it, and position the aircraft ejection seat in the middle;

[0055] S3: Then, a set of inflatable seat clamping plates 404 is attached to the bottom of the aircraft ejection seat, and another set of inflatable seat clamping plates 404 is attached to the upper surface of the aircraft ejection seat through the hydraulic push-pull force of the hydraulic clamping rod 407, so that the two are in a clamping state for the aircraft ejection seat;

[0056] S4: When the aircraft ejection seat is being tested, the aircraft ejection seat transmits pressure to the inflatable seat clamping plate 404 connected to the arc-shaped displacement clamping plate 401, and the spherical block 408 deflects along the Y-axis of the aircraft ejection seat along the four wrapped tilting rods 409 based on the tension or thrust of the side ball rod 403, and the tilting rod 409 follows the forces received in various directions to drive the sliding rod 413 at the corresponding force position on the surrounding side to squeeze the limiting spring 414, and then the pressure sensing component at the connection between the limiting spring 414 and the engaging positioning frame 207 detects relevant data, and the corresponding side tilting rod 409 drives the positioning spring 411 through the cross positioning plate 410 to give tension to the sensor connected to the positioning spring 411, and the other side is thrust, so that the X-axis data is obtained;

[0057] S5: The output shaft of the third forward and reverse motor drives the multi-arc hole positioning plate 301 to rotate along the positioning chuck 304 and the sliding cavity positioning frame 305. The rotation of the multi-arc hole positioning plate 301 causes the positioning round block 308 to move toward the center of the aircraft ejection seat along the sliding cavity positioning frame 305, and then the arc detection plate 302 wraps the aircraft ejection seat, and the negative pressure adsorption hole 303 generates negative pressure adsorption on the aircraft ejection seat through the built-in air pump. When the multi-arc hole positioning plate 301 rotates in the opposite direction, the fixed connecting rod 307 moves away from the aircraft ejection seat, generating a pulling force on the aircraft ejection seat, and the stretching degree of the aircraft ejection seat is detected through the pressure detection component;

[0058] S6: Finally, when the arc detection plate 302 is at the farthest distance from the aircraft ejection seat and at a distance close to the stretched degree of the aircraft ejection seat, it contacts the aircraft ejection seat ejected by the ejector. The arc detection plate 302 obtains corresponding pressure data by squeezing the pressure detection block 312, and then obtains the test data of the aircraft ejection seat.

[0059] The above specific embodiments are only several optional embodiments of the present invention. Based on the technical solutions of the present invention and the relevant inspirations of the above embodiments, those skilled in the art can make various alternative improvements and combinations to the above specific embodiments.

Claims

1. A test bench for an aircraft ejection seat, comprising a test external component (1), characterized in that: A test seat adjustment clamping assembly (2) is installed inside the test external assembly (1), two sets of seat clamping assemblies (4) are installed on both sides of the test seat adjustment clamping assembly (2), and a variable detection assembly (3) is installed on the top of the inner wall of the test external assembly (1); The test external component (1) comprises a test protection frame (101), the test seat adjustment clamping component (2) comprises a positioning rod (201) fixedly mounted on the inner wall of the test protection frame (101), a side of the positioning rod (201) away from the test protection frame (101) is fixedly mounted with a transverse slideway (206), a second forward and reverse motor (202) is fixedly mounted on the inner wall of the test protection frame (101), an output shaft of the second forward and reverse motor (202) is fixedly mounted with a second threaded rod (203), two ejection component clamping arc blocks (204) are threadedly mounted on the outer side of the second threaded rod (203), and the two ejection component clamping arc blocks (204) are slidably mounted inside the transverse slideway (206), a placement block (205) is fixedly mounted on the outer side of the ejection component clamping arc block (204), and a locking positioning frame (207) is fixedly mounted on one side of the placement block (205); The seat clamping assembly (4) comprises a side ball rod (403) rotatably mounted inside the locking positioning frame (207), a turntable (402) being fixedly mounted on the outer side of the side ball rod (403), an arc-shaped displacement clamping plate (401) being fixedly mounted on the top of the turntable (402), two groups of hollow transmission rods (406) being fixedly mounted on the top of the arc-shaped displacement clamping plate (401), a hydraulic clamping rod (407) being fixedly mounted inside the hollow transmission rod (406), an output shaft of the hydraulic clamping rod (407) being fixedly mounted with a group of inflatable seat clamping plates (404) via a slide rail, the number of the inflatable seat clamping plates (404) being two groups, another group of the inflatable seat clamping plates (404) being fixedly mounted on the bottom of the hollow transmission rod (406), and a pressure sensing assembly (405) being fixedly mounted on one side of the two groups of the inflatable seat clamping plates (404); A plurality of positioning springs (411) are fixedly mounted on one side of the locking positioning frame (207) facing the side ball bar (403), a cross positioning plate (410) is fixedly mounted on one side of the plurality of positioning springs (411), and two sets of tilting rods (409) are hingedly connected on both sides of the cross positioning plate (410); A movable positioning plate (412) is fixedly mounted on one side of the tilting rod (409) away from the cross positioning plate (410), a limiting spring (414) is fixedly mounted on one side of the movable positioning plate (412), a sliding rod (413) is provided on one side of the movable positioning plate (412), the limiting spring (414) is fixedly mounted on the inner wall of the locking positioning frame (207), a spherical block (408) is rotatably mounted on the outer side of the tilting rod (409), and a side ball rod (403) is fixedly mounted on one side of the spherical block (408).

2. The test bench for an aircraft ejection seat according to claim 1, characterized in that: The number of the movable positioning plates (412), the tilting rods (409), the sliding rods (413) and the limiting springs (414) is four groups, and the four groups of the movable positioning plates (412), the tilting rods (409), the sliding rods (413) and the limiting springs (414) are arranged in a ring state with respect to the spherical block (408) and the cross positioning plate (410).

3. The test bench for an aircraft ejection seat according to claim 2, characterized in that: The test external component (1) further comprises two slide channels (102) fixedly mounted on the side wall of the test protection frame (101); a test door is provided on a side of the test protection frame (101) away from the slide channels (102); a first forward and reverse motor (104) is fixedly mounted between the two slide channels (102); and a first threaded rod (105) is fixedly mounted on an output shaft of the first forward and reverse motor (104).

4. The test bench for an aircraft ejection seat according to claim 3, characterized in that: A shielding plate (103) is inserted at the top of the test protection frame (101), the shielding plate (103) is threadedly mounted on the outside of the first threaded rod (105), and the shielding plate (103) is slidably mounted on one side of the two sliding channels (102).

5. The test bench for an aircraft ejection seat according to claim 4, characterized in that: The variable detection assembly (3) comprises a positioning chuck (304) fixedly mounted on the bottom of the shielding plate (103); a plurality of sliding cavity positioning frames (305) arranged in a circular shape with respect to the outer surface of the positioning chuck (304) are fixedly mounted on the bottom of the positioning chuck (304); and the same number of fixed connecting rods (307) are slidably mounted inside the plurality of sliding cavity positioning frames (305).

6. The test bench for an aircraft ejection seat according to claim 5, characterized in that: A multi-arc hole positioning plate (301) is rotatably mounted on one side of the positioning chuck (304), a positioning round block (308) is slidably mounted inside the sliding cavity positioning frame (305), the positioning round block (308) is fixedly mounted on one side of a fixed connecting rod (307), an arc-shaped detection plate (302) is fixedly mounted on one side of the fixed connecting rod (307), and a plurality of negative pressure adsorption holes (303) are provided on the surface of the arc-shaped detection plate (302).

7. The test bench for an aircraft ejection seat according to claim 6, characterized in that: A telescopic airbag block (309) is fixedly mounted on one side of the arc detection plate (302) away from the fixed connecting rod (307); an external pressure-resistant plate (306) is fixedly mounted on one side of the telescopic airbag block (309) away from the arc detection plate (302); a positioning track frame (310) is fixedly mounted on the side wall of the arc detection plate (302); two groups of arc-shaped pressure-resistant blocks (311) are fixedly mounted on the inner wall of the telescopic airbag block (309); the two groups of arc-shaped pressure-resistant blocks (311) are hinged on two sides of the positioning track frame (310); a pressure detection block (312) is slidably mounted inside the positioning track frame (310); and an elastic spring rod (313) is fixedly mounted between the pressure detection block (312) and the positioning track frame (310).

8. A test method for an aircraft ejection seat, using the test bench for an aircraft ejection seat as claimed in claim 7, characterized in that: The following steps are involved: S1: The staff first opens the test door and adjusts the position of the shielding plate (103) by means of the first forward and reverse motor (104). When the shielding plate (103) is adjusted to drive the multi-variable detection assembly (3) to leave the test protection frame (101), the aircraft ejection seat is placed inside the test protection frame (101); S2: When the aircraft ejection seat is placed in the test protection frame (101), the second forward and reverse motor (202) drives the second threaded rod (203) to rotate, and the second threaded rod (203) drives two lateral slideways (206) to contact the ejector of the aircraft ejection seat, wrap it and position it, and position the aircraft ejection seat in the middle; S3: Then, a set of inflatable seat clamping plates (404) are attached to the bottom of the aircraft ejection seat, and another set of inflatable seat clamping plates (404) are attached to the upper surface of the aircraft ejection seat through the hydraulic push-pull force of the hydraulic clamping rod (407), so that the two are in a clamping state for the aircraft ejection seat; S4: When the aircraft ejection seat is being tested, the aircraft ejection seat transmits pressure to the inflatable seat clamping plate (404) connected to the arc-shaped displacement clamping plate (401), and the spherical block (408) deflects along the Y-axis of the aircraft ejection seat along the four wrapped tilting rods (409) based on the tension or thrust of the side ball rod (403), and the tilting rod (409) drives the sliding rod (413) at the corresponding force position on the peripheral side to squeeze the limiting spring (414) according to the forces received in various directions, and then the pressure sensing component at the connection between the limiting spring (414) and the engaging positioning frame (207) detects relevant data, and the corresponding side tilting rod (409) drives the positioning spring (411) through the cross positioning plate (410) to give tension to the sensor connected to the positioning spring (411), and the other side is thrust, so that X-axis data is obtained; S5: the output shaft of the third forward and reverse motor drives the multi-arc hole positioning plate (301) to rotate along the positioning chuck (304) and the sliding cavity positioning frame (305), and the rotation of the multi-arc hole positioning plate (301) causes the positioning round block (308) to move along the sliding cavity positioning frame (305) toward the center of the aircraft ejection seat, and then the arc detection plate (302) wraps the aircraft ejection seat, and the negative pressure adsorption hole (303) generates negative pressure adsorption on the aircraft ejection seat through the built-in air pump, and when the multi-arc hole positioning plate (301) rotates in the opposite direction, the fixed connecting rod (307) moves away from the aircraft ejection seat, generating a pulling force on the aircraft ejection seat, and the stretching degree of the aircraft ejection seat is detected through the pressure detection component; S6: Finally, the arc-shaped detection plate (302) contacts the aircraft ejection seat ejected by the ejector when it is at the farthest distance from the aircraft ejection seat and at a distance close to the stretched degree of the aircraft ejection seat. The arc-shaped detection plate (302) obtains corresponding pressure data by squeezing the pressure detection block (312), thereby obtaining test data of the aircraft ejection seat.

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