Ejection type instant angular acceleration impact test device

Abstract

An ejection type instant angular acceleration impact test device comprises a first controller, a spring launcher, a straight track, a first iron ball, a multi-stage ejection mechanism, an ejection cabin and a circular track. The first controller is connected with the spring launcher, the spring launcher is located at one end of the straight rail, a gap exists between the straight rail and the spring launcher when the spring launcher is compressed, and the spring launcher pushes the first iron ball to be ejected out when the spring launcher is unfolded. The first iron ball is arranged at the end, close to the spring launcher, in the straight track, the multi-stage ejection mechanism and the first iron ball are arranged in the straight track at intervals, the circular track is installed at the other end of the straight track, the straight track is located in the tangential direction of the circular track, the straight track and the circular track are different in height in the same vertical direction, and the launching cabin is erected on the circular track. And the energy finally obtained by the launching cabin is increased by using the multi-stage ejection mechanism and the circular orbit, so that the angular velocity can reach a numerical value required by a test.

Description

Technical Field

[0001] The present application belongs to the field of aerospace, and specifically relates to a catapult-type instantaneous angular acceleration impact test device. Background Art

[0002] High-performance fighter jets with high angular acceleration can easily cause pilots to suffer from motion sickness. The turning radius is small and the angular acceleration is large, up to 40° / s, which is 10 times higher than the tolerance of ordinary people. When the human body is subjected to 3-6 times the horizontal forward gravity acceleration, it will cause symptoms such as difficulty breathing and chest pain. When the human body is subjected to 3-6 times the horizontal backward gravity acceleration, it will cause symptoms such as headache, increased intraocular pressure, and conjunctival congestion. These symptoms are undoubtedly fatal to pilots in space operations.

[0003] Therefore, it is urgent to establish a test station on the ground to carry out ejection-type instantaneous angular acceleration impact tests, so as to study the angular acceleration at different instantaneous sizes, so as to gain a deeper understanding of the physiological effects of angular acceleration and devise solutions to reduce the harm of angular acceleration to pilots.

[0004] Application Contents

[0005] In order to overcome the above-mentioned deficiencies of the prior art, the present application proposes a catapult-type instantaneous angular acceleration impact test device, comprising: a first controller 15, a spring launcher 2, a straight track 1, a first iron ball 3, a multi-stage catapult mechanism, a launch cabin 21 and a circular track 22;

[0006] The first controller 15 is connected to a spring launcher 2, the spring launcher 2 is located at one end of the straight track 1, and when the spring launcher 2 is compressed, there is a gap between the straight track 1 and the spring launcher 2, and when the spring launcher 2 is opened, the spring launcher 2 pushes the first iron ball 3 to eject the first iron ball 3, the first iron ball 3 is arranged in the straight track 1 near one end of the spring launcher 2, the multi-stage ejection mechanism and the first iron ball 3 are arranged in the straight track 1 at a gap, the circular track 22 is installed at the other end of the straight track 1, the straight track 1 is located in the tangent direction of the circular track 22, and the straight track 1 and the circular track 22 have different heights in the same vertical direction, and the launch cabin 21 is mounted on the circular track 2;

[0007] The first controller 15 is used to control the operation of the circuit, start the spring launcher 2 to give the first iron ball 3 a certain initial kinetic energy and eject it.

[0008] Preferably, a first threaded connection hole 4 and a telescopic shaft 9 are provided on the straight track 1, one end of the telescopic shaft 9 is connected to the first threaded connection hole 4, and a drive motor is provided on the telescopic shaft 9 away from the first threaded connection hole 4, and the drive motor is located on the outside of the straight track 1.

[0009] Preferably, two roller assemblies 25 are provided at the bottom end of the straight track 1, and the two roller assemblies 25 are respectively arranged on both sides of the straight track 1, and the roller assembly 25 comprises: a support rod, a roller 2501, a force sensor 2502, a small spring transmitter 2503 and a brake plate 2504; one end of the support rod is connected to the straight track 1 and the other end is connected to the roller 2501, the two ends of the brake plate 2504 are respectively connected to the straight track 1 and the roller 2501 and form a certain angle with the straight track 1 and the roller 2501, one end of the small spring transmitter 2503 is installed on the brake plate 2504, and the other end is connected to the support rod through the force sensor 2502.

[0010] Preferably, the multi-stage ejection mechanism comprises: a first-stage ejection assembly, a second-stage ejection assembly and a third-stage ejection assembly which are sequentially arranged at intervals;

[0011] The first-stage ejection assembly includes: a first electromagnet 6, a second iron ball 7 and a third iron ball 8 arranged in sequence; the first electromagnet 6 is connected to the inside of the straight track 1 and is parallel to the cross-sectional direction of the straight track 1;

[0012] The secondary ejection assembly includes: a second electromagnet 11, a fourth iron ball 16 and a fifth iron ball 17 arranged in sequence; the second electromagnet 11 is connected to the inside of the straight track 1 and is parallel to the cross-sectional direction of the straight track 1;

[0013] The three-stage ejection assembly includes: a third electromagnet 19, a sixth iron ball 20, a pressure sensor 23 and an iron partition 24 arranged in sequence;

[0014] The third electromagnet 19 is connected inside the straight track 1 and is parallel to the cross-sectional direction of the straight track 1 , the iron partition 24 is connected to one end of the straight track 1 away from the spring transmitter 2 , and the pressure sensor 23 is installed at the connection between the iron partition 24 and the straight track 1 .

[0015] Preferably, the distance between the first iron ball 3 and the first electromagnet 6 is L, and L≥1m.

[0016] Preferably, the distance between the third iron ball 8 and the second electromagnet 11 and the distance between the fifth iron ball 17 and the third electromagnet 19 are both D, and D≥40dm.

[0017] Preferably, the distance between the third iron ball 8 and the second electromagnet 11 and the distance between the fifth iron ball 17 and the third electromagnet 19 are the same as D, and D≥40dm.

[0018] Preferably, the launch cabin 21 includes: a second controller 2101, a first clamp-shaped brake 2102, a second clamp-shaped brake 2103, a third clamp-shaped brake 2104, a fourth clamp-shaped brake 2105 and a monitoring cabin;

[0019] The second controller 2101 is arranged in the monitoring cabin, the first clamp-shaped brake 2102, the second clamp-shaped brake 2103, the third clamp-shaped brake 2104, and the fourth clamp-shaped brake 2105 are installed at the bottom of the monitoring cabin, the first clamp-shaped brake 2102 and the second clamp-shaped brake 2103 cooperate with each other to be movably connected with the circular track 22, the third clamp-shaped brake 2104 and the fourth clamp-shaped brake 2105 cooperate with each other to be movably connected with the circular track 22, and the first clamp-shaped brake 2102, the second clamp-shaped brake 2103, the third clamp-shaped brake 2104, and the fourth clamp-shaped brake 2105 are in communication connection with the second controller 2101;

[0020] The second controller 2101 is used to receive signals from the monitoring cabin and control the first clamp brake 2102, the second clamp brake 2103, the third clamp brake 2104 and the fourth clamp brake 2105 to achieve braking according to the signals from the monitoring cabin.

[0021] Preferably, the monitoring cabin includes: a seat 2106 and a monitor 2107; the monitor 2107 is used to monitor the angular acceleration of the launch cabin 21 and the physical condition of the test personnel in the cabin.

[0022] Preferably, a first position sensor 26 and a second position sensor 27 are also distributed on the circular track 22, and the first position sensor 26 and the second position sensor 27 are used to send a braking signal to the second controller 2101 when the launch cabin 21 reaches the position of the first position sensor 26 and the second position sensor 27.

[0023] Compared with the closest prior art, the present application has the following beneficial effects:

[0024] A ejection type instantaneous angular acceleration impact test device, comprising: a first controller 15, a spring launcher 2, a straight track 1, a first iron ball 3, a multi-stage ejection mechanism, a launch cabin 21 and a circular track 22; the first controller 15 is connected to the spring launcher 2, the spring launcher 2 is located at one end of the straight track 1, and when the spring launcher 2 is compressed, there is a gap between the straight track 1 and the spring launcher 2, and when the spring launcher 2 is opened, the spring launcher 2 pushes the first iron ball 3 to eject the first iron ball 3, the first iron ball 3 is arranged in the straight track 1 near one end of the spring launcher 2, and the multi-stage ejection mechanism and the first iron ball 3 The circular track 22 is installed at the other end of the straight track 1, the straight track 1 is located in the tangent direction of the circular track 22, and the straight track 1 and the circular track 22 are at different heights in the same vertical direction, and the launch cabin 21 is mounted on the circular track 2; the first controller 15 is used to: control the operation of the circuit, start the spring launcher 2 to give the first iron ball 3 a certain initial kinetic energy and eject it; the application adopts a multi-stage ejection mechanism to gradually transfer the kinetic energy to the launch cabin 21, so that the speed can reach a larger value, and the launch cabin 21 is launched along the circular track 22; due to the huge shooting speed and instant turning, an instantaneous angular acceleration is generated. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 A schematic diagram of the structure of a catapult-type instantaneous angular acceleration impact test device provided in this application;

[0026] Figure 2 A BB cross-sectional view of a catapult-type instantaneous angular acceleration impact test device provided in this application;

[0027] Figure 3 AA cross-sectional view of a catapult-type instantaneous angular acceleration impact test device provided in this application;

[0028] Figure 4 A partial enlarged view of the roller part of a catapult-type instantaneous angular acceleration impact test device provided by the present application;

[0029] Figure 5 A partial enlarged view of the connection between the launch cabin and the straight track of a catapult-type instantaneous angular acceleration impact test device provided in this application;

[0030] Figure 6 A main cross-sectional view of a launch cabin of a catapult-type instantaneous angular acceleration impact test device provided in the present application;

[0031] Figure 7 The device and equipment in the launch cabin of a catapult-type instantaneous angular acceleration impact test device provided in the present application;

[0032] Figure 8 A partial enlarged view of a quarter circle of a circular track of a catapult-type instantaneous angular acceleration impact test device provided in the present application;

[0033] Among them: 1-straight track, 2-spring launcher, 3-first iron ball, 4-first threaded connection hole, 5-first drive motor, 6-first electromagnet, 7-second iron ball, 8-third iron ball, 9-telescopic shaft, 10-second drive motor, 11-second electromagnet, 12-power supply, 13-first controllable switch, 14-first fuse, 15-first controller, 16-fourth iron ball, 17-fifth iron ball, 18-second threaded connection hole, 19-third electromagnet, 20-sixth iron ball, 21-launching cabin, 2101-second control device, 2102-the first clamping brake, 2103-the second clamping brake, 2104-the third clamping brake, 2105-the fourth clamping brake, 2106-seat, 2107-monitor, 22-circular track, 23-pressure sensor, 24-iron partition, 25-roller assembly, 2501-roller, 2502-force sensor, 2503-small spring transmitter, 2504-brake plate, 26-the first position sensor, 27-the second position sensor, 28-the second controllable switch, 29-the second fuse. DETAILED DESCRIPTION

[0034] The specific implementation methods of the present application are further described in detail below in conjunction with the accompanying drawings.

[0035] Embodiment 1:

[0036] To achieve the above purpose, the present application provides a catapult-type instantaneous angular acceleration impact test device, such as Figure 1 As shown, it includes: a first controller 15, a spring launcher 2, a straight track 1, a first iron ball 3, a multi-stage ejection mechanism, a launch cabin 21 and a circular track 22;

[0037] The first controller 15 is connected to the spring launcher 2, and the spring launcher 2 is located at one end of the straight track 1. When the spring launcher 2 is compressed, there is a gap between the straight track 1 and the spring launcher 2. When the spring launcher 2 is opened, the spring launcher 2 pushes the first iron ball 3 to eject the first iron ball 3. The first iron ball 3 is arranged in the straight track 1 near one end of the spring launcher 2. The multi-stage ejection mechanism and the first iron ball 3 are arranged in the straight track 1 at a gap. The circular track 22 is installed at the other end of the straight track 1. The straight track 1 is located in the tangent direction of the circular track 22, and the straight track 1 and the circular track 22 have different heights in the same vertical direction. The launch cabin 21 is mounted on the circular track 2. Figure 2 As shown;

[0038] The first controller 15 is used to control the operation of the circuit, start the spring launcher 2 to give the first iron ball 3 a certain initial kinetic energy and eject it.

[0039] The spring launcher 2 can control the size of the spring contraction, thereby controlling the size of the kinetic energy of the iron ball at the beginning, thereby controlling the size of the final angular acceleration. The two tracks are staggered up and down, with the straight track 1 on the top and the circular track 22 on the bottom. This form makes it easy to move the straight track 1 and also makes it easy to realize the cycle of the test.

[0040] Two control systems and one monitoring system are used. The first controller 15 of one control system mainly controls the power system and controls the progress and start of the entire test device. When the launch cabin 21 cannot stop or return to its original position in a short time due to its excessive speed, it is controlled by another control system. The monitoring cabin in the monitoring system mainly measures and controls the size of the angular acceleration and the safety of the personnel inside.

[0041] Preferably, a first threaded connection hole 4 and a telescopic shaft 9 are provided on the straight track 1, one end of the telescopic shaft 9 is connected to the first threaded connection hole 4, and a drive motor is provided on the telescopic shaft 9 away from the first threaded connection hole 4, and the drive motor is located on the outside of the straight track 1.

[0042] The device is composed of a straight track 1 and a circular track 22, and the straight track 1 and the circular track 22 are staggered up and down. Initially, the electromagnet is energized, and the electromagnet absorbs the iron ball to form a ejection system. When the iron ball is attracted by the magnetic force of the electromagnet, the kinetic energy of the iron ball increases, and then it is transferred to the iron ball at the end by the law of conservation of kinetic energy, thereby achieving kinetic energy increase. The three-stage electromagnet distribution structure is adopted to increase the energy finally obtained by the launch cabin 21, so that the angular velocity can reach a larger value.

[0043] like Figure 3 As shown, two roller assemblies 25 are provided at the bottom end of the straight track 1, and the two roller assemblies 25 are respectively arranged on both sides of the straight track 1. Figure 4 The roller assembly 25 shown includes: a support rod, a roller 2501, a force sensor 2502, a small spring transmitter 2503 and a brake plate 2504; one end of the support rod is connected to the straight track 1 and the other end is connected to the roller 2501, the two ends of the brake plate 2504 are respectively connected to the straight track 1 and the roller 2501 and form a certain angle with the straight track 1 and the roller 2501, one end of the small spring transmitter 2503 is installed on the brake plate 2504, and the other end is connected to the support rod through the force sensor 2502.

[0044] A partial enlarged view of the roller device 25, in which the force sensor 2502 receives the movement tendency of the roller 2501 and transmits it to the small spring transmitter 2503. The small spring transmitter 2503 pops open the brake plate 2504, and the roller 2501 moves with the telescopic shaft 9. The straight track 1 deviates from its original position until it does not hinder the return of the launch cabin 21, and the deviation process ends.

[0045] The force sensor 2502 detects that the launch cabin 21 is detached and transmits a signal to the first controller 15. The first controller 15 turns on the second controllable switch 28 and turns off the first controllable switch 13. The first drive motor 5 and the second drive motor 10 control the telescopic shaft 9 to push the straight track 1. The force sensor 2502 senses the thrust and transmits it to the small spring launcher 2503, which pops open the brake plate 2504 and pushes the straight track 1 away from its original position.

[0046] Preferably, the multi-stage ejection mechanism comprises: a first-stage ejection assembly, a second-stage ejection assembly and a third-stage ejection assembly which are sequentially arranged at intervals;

[0047] The first-stage ejection assembly includes: a first electromagnet 6, a second iron ball 7 and a third iron ball 8 arranged in sequence; the first electromagnet 6 is connected to the inside of the straight track 1 and is parallel to the cross-sectional direction of the straight track 1;

[0048] The secondary ejection assembly includes: a second electromagnet 11, a fourth iron ball 16 and a fifth iron ball 17 arranged in sequence; the second electromagnet 11 is connected to the inside of the straight track 1 and is parallel to the cross-sectional direction of the straight track 1;

[0049] The three-stage ejection assembly includes: a third electromagnet 19, a sixth iron ball 20, a pressure sensor 23 and an iron partition 24 arranged in sequence;

[0050] The third electromagnet 19 is connected to the inside of the straight track 1 and is parallel to the cross-sectional direction of the straight track 1. The iron partition 24 is connected to the end of the straight track 1 away from the spring transmitter 2. The pressure sensor 23 is installed at the connection between the iron partition 24 and the straight track 1. Figure 5 shown.

[0051] The device has a launch workbench on the left, including a spring launcher 2 on the left, and a straight track 1 on the right. The straight track 1 is fixedly connected with a first drive motor 5 and a second drive motor 10. The device is characterized in that the straight track 1 and the first drive motor 5 and the second drive motor 10 are first connected through a threaded connection hole with a similar structure, and the drive motors control the telescopic shaft 9 respectively; from left to right on the straight track 1 are a first iron ball 3 and an ejection device, and the ejection device is divided into one, two and three levels of ejection; the first level of the ejection device includes a first electromagnet 6, a second iron ball 7 and a third iron ball 8, wherein the first electromagnet 6 is connected to the straight track 1 by a threaded connection hole, and the other electromagnets are connected in the same manner; the second level of the ejection includes a second electromagnet 11, a fourth iron ball 16 and a fifth iron ball 17; the third level of the ejection includes a third electromagnet 19, a sixth iron ball 20, a pressure sensor 23 and an iron partition 24; the lower track The rightmost part is connected by two roller assemblies 25, and the roller assembly 25 is composed of a roller 2501, a force sensor 2502, a small spring launcher 2503 and a brake plate 2504; the rightmost is the launch cabin 21, and the launch cabin 21 is composed of a second controller 2101, a first clamp-shaped brake 2102, a second clamp-shaped brake 2103, a third clamp-shaped brake 2104, a fourth clamp-shaped brake 2105, a seat 2106 and a monitor 2107; the launch cabin 21 is tightly connected to the circular track 22, and two sensors are distributed on the circular track 22, namely a first position sensor 26 and a second position sensor 27; the circular track 22 and the straight track 1 are staggered with each other; the whole is controlled by the first controller to realize the operation of the circuit system; the circuit system is composed of a power supply 12, a first controllable switch 13, a second controllable switch 28, a first fuse 14 and a second fuse 29.

[0052] The device is composed of a straight track 1 and a circular track 22, and the straight track 1 and the circular track 22 are staggered up and down. Figure 2 The black part is the straight track 1 area, and the white circle is where the circular track 22 is located. Initially, the first electromagnet 6, the second electromagnet 11 and the third electromagnet 19 are energized, and the first electromagnet 6 adsorbs the second iron ball 7 and the third iron ball 8 to form a first-level ejection system; the second electromagnet 11 adsorbs the fourth iron ball 16 and the fifth iron ball 17 to form a second-level ejection system; the third electromagnet 19 adsorbs the sixth iron ball 20 and the iron partition 24 without any interval to form a third-level ejection system. Among them, the installation of the electromagnet and the straight track 1 is based on the installation of the second threaded connection hole 18 at one corner, and the four corners are installed.

[0053] The pressure sensor 23 senses the separation of the launch cabin 21 and transmits a signal to the first controller 15. The first controller 15 controls the second control switch 28, and the first drive motor 5 and the second drive motor 10 start to control the telescopic shaft 9 to extend forward.

[0054] Preferably, the distance between the first iron ball 3 and the first electromagnet 6 is L, and L≥1m.

[0055] In the initial state, the distance between the first iron ball 3 and the first electromagnet 6 is L, and L≥1m, so as to prevent the first iron ball 3 from being sucked away by the first electromagnet 6 without being ejected by the spring launcher 2 .

[0056] Preferably, the distance between the third iron ball 8 and the second electromagnet 11 and the distance between the fifth iron ball 17 and the third electromagnet 19 are both D, and D≥40dm.

[0057] The distance between the third iron ball 8 and the second electromagnet 11 is D, D≥40dm, to prevent the electromagnet of the next level from sucking the iron ball away first because the suction force is stronger than the electromagnet of the first level.

[0058] Preferably, the distance between the third iron ball 8 and the second electromagnet 11 and the distance between the fifth iron ball 17 and the third electromagnet 19 are the same as D, and D≥40dm.

[0059] The distance between the fifth iron ball 17 and the third electromagnet 19 is D, D≥40dm, to prevent the electromagnet of the next level from sucking the iron ball away first because the suction force is stronger than the electromagnet of the first level.

[0060] The test personnel enter the test cabin and sit in the seat 2106. The first controller 15 controls the first controllable switch 13 to start the spring launcher 2 to give the first iron ball 3 a certain initial kinetic energy and eject it. Subsequently, the first iron ball 3 is attracted and hit by the first electromagnet 6, and the kinetic energy is gradually transferred to the third iron ball 8 at the end of the first ejection device. The third iron ball 8 obtains kinetic energy and gets rid of the attraction of the first electromagnet 6 and moves to the second ejection device; similarly, it is attracted and hit by the second magnet 11, and the kinetic energy is transferred to the fifth iron ball 17, and the fifth iron ball 17 gets rid of the attraction of the second electromagnet 11 and moves to the third ejection device; the fifth iron ball 17 is attracted and hit by the third electromagnet 19, and the kinetic energy is gradually transferred to the launch cabin 21, and the launch cabin 21 is launched along the circular track 22; due to the huge acceleration and the instant turn, a large instantaneous angular acceleration is generated, and the launch process ends.

[0061] The pressure sensor 23 is tightly connected to the launch cabin 21 before launching. The iron partition 24 is tightly connected to the straight track 1 to prevent the sixth iron ball 20 from being separated due to the movement of the straight track 1.

[0062] like Figure 6 As shown, the launch cabin 21 includes: a second controller 2101, a first clamp brake 2102, a second clamp brake 2103, a third clamp brake 2104, a fourth clamp brake 2105 and a monitoring cabin;

[0063] The second controller 2101 is arranged in the monitoring cabin, the first clamp-shaped brake 2102, the second clamp-shaped brake 2103, the third clamp-shaped brake 2104, and the fourth clamp-shaped brake 2105 are installed at the bottom of the monitoring cabin, the first clamp-shaped brake 2102 and the second clamp-shaped brake 2103 cooperate with each other to be movably connected with the circular track 22, the third clamp-shaped brake 2104 and the fourth clamp-shaped brake 2105 cooperate with each other to be movably connected with the circular track 22, and the first clamp-shaped brake 2102, the second clamp-shaped brake 2103, the third clamp-shaped brake 2104, and the fourth clamp-shaped brake 2105 are in communication connection with the second controller 2101;

[0064] The second controller 2101 is used to receive signals from the monitoring cabin and control the first clamp brake 2102, the second clamp brake 2103, the third clamp brake 2104 and the fourth clamp brake 2105 to achieve braking according to the signals from the monitoring cabin.

[0065] like Figure 7 As shown, the monitoring cabin includes: a seat 2106 and a monitor 2107; the monitor 2107 is used to monitor the angular acceleration of the launch cabin 21 and the physical condition of the test personnel in the cabin.

[0066] The function of the monitor 2107 is to monitor the angular acceleration of the launch cabin 21 and the physical condition of the test personnel in the cabin.

[0067] like Figure 8 As shown, the circular track 22 is also provided with a first position sensor 26 and a second position sensor 27 , and the first position sensor 26 and the second position sensor 27 are used to send a braking signal to the second controller 2101 when the launch cabin 21 reaches the position of the first position sensor 26 and the second position sensor 27 .

[0068] The three-stage ejection system ejects the launch capsule 21 and moves along the circular track 22. When it moves to 1 / 4 of the track, the first position sensor 26 and the second position sensor 27 receive the arrival signal of the launch capsule 21 and transmit it to the second controller 2101. The second controller 2101 controls the first clamp brake 2102, the second clamp brake 2103, the third clamp brake 2104 and the fourth clamp brake 2105, thereby achieving braking. Accordingly, it provides time for the deviation of the straight track 1 and provides a solution to prevent the launch capsule 21 from being unable to stop in a short time due to excessive force.

[0069] The device can also realize a cyclic test, by controlling the tightness of the clamping brake through the second controller 2101, thereby controlling the stop position of the launch cabin 21, so as to realize the return of the launch cabin 21. By controlling the drive motor through the first control system 15, the telescopic shaft 9 is controlled to retract, so that the straight track 1 returns to its original position, and the test is repeated.

[0070] Embodiment 2:

[0071] The ejection type instantaneous angular acceleration impact test device described in this application adopts the following technical scheme:

[0072] Step 1): The test personnel enter the test cabin and sit in the seat 2106. The first controller 15 controls the first controllable switch 13 to start the spring launcher 2 to give the first iron ball 3 a certain initial kinetic energy and eject it. The first iron ball 3 is attracted and hit by the first electromagnet 6, and the kinetic energy is gradually transferred to the third iron ball 8 at the end of the first ejection device. The third iron ball 8 obtains kinetic energy to get rid of the attraction of the first electromagnet 6 and move to the second ejection device; similarly, it is attracted and hit by the second electromagnet 11, and the kinetic energy is transferred to the fifth iron ball 17, and the fifth iron ball 17 gets rid of the attraction of the second electromagnet 11 and moves to the third ejection device; the fifth iron ball 17 is attracted and hit by the third electromagnet 19, and the kinetic energy is gradually transferred to the launch cabin 21, and the launch cabin 21 is launched along the circular track 22; due to the huge shooting speed and instantaneous turning, instantaneous angular acceleration is generated.

[0073] Step 2): The pressure sensor 23 detects that the launch cabin 21 is detached and transmits a signal to the first controller 15. The first controller 15 opens the second controllable switch 28 and closes the first controllable switch 13. The first drive device 5 and the second drive motor 10 control the telescopic shaft 9 to push the straight track 1. The force sensor 2502 senses the thrust and transmits it to the small spring launcher 2503, which pops open the brake plate 2504 and pushes the straight track 1 away from its original position.

[0074] Step 3): The launch cabin 21 moves along the circular track 22. When it moves to 1 / 4 of the circular track 22, the first position sensor 26 and the second position sensor 27 receive signals and transmit them to the second controller 2101. The second controller 2101 controls the first clamp brake 2102, the second clamp brake 2103, the third clamp brake 2104 and the fourth clamp brake 2105 to achieve braking.

[0075] Step 4): The staff resets the launch cabin 21 that has not been completely reset, and the first controller 15 controls the first drive motor 5 and the second drive motor 10 to reset the straight track 1, and repeats the test.

[0076] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application rather than to limit its protection scope. Although the present application has been described in detail with reference to the above embodiments, ordinary technicians in the relevant field should understand that after reading the present application, those skilled in the art can still make various changes, modifications or equivalent substitutions to the specific implementation methods of the application, but these changes, modifications or equivalent substitutions are all within the protection scope of the claims to be approved.

Claims

1. A catapult-type instantaneous angular acceleration impact test device, characterized in that: include: A first controller (15), a spring launcher (2), a straight track (1), a first iron ball (3), a multi-stage ejection mechanism, a launch cabin (21) and a circular track (22); The first controller (15) is connected to a spring launcher (2), the spring launcher (2) is located at one end of the straight track (1), and when the spring launcher (2) is compressed, there is a gap between the straight track (1) and the spring launcher (2), and when the spring launcher (2) is opened, the spring launcher (2) pushes the first iron ball (3) to eject the first iron ball (3), the first iron ball (3) is arranged in the straight track (1) near one end of the spring launcher (2), the multi-stage ejection mechanism and the first iron ball (3) are arranged in the straight track (1) at a gap, the circular track (22) is installed at the other end of the straight track (1), the straight track (1) is located in the tangent direction of the circular track (22), and the straight track (1) and the circular track (22) have different heights in the same vertical direction, and the launch cabin (21) is mounted on the circular track (2); The first controller (15) is used to control the operation of the circuit, start the spring launcher (2) to give the first iron ball (3) a certain initial kinetic energy and eject it.

2. The device according to claim 1, characterized in that The straight track (1) is provided with a first threaded connection hole (4) and a telescopic shaft (9), one end of the telescopic shaft (9) is connected to the first threaded connection hole (4), and the telescopic shaft (9) is provided with a drive motor away from the first threaded connection hole (4), and the drive motor is located outside the straight track (1).

3. The device according to claim 2, characterized in that Two roller assemblies (25) are provided at the bottom end of the straight track (1), and the two roller assemblies (25) are respectively arranged on both sides of the straight track (1), and the roller assembly (25) comprises: a support rod, a roller (2501), a force sensor (2502), a small spring transmitter (2503) and a brake plate (2504); one end of the support rod is connected to the straight track (1) and the other end is connected to the roller (2501), the two ends of the brake plate (2504) are respectively connected to the straight track (1) and the roller (2501) and form a certain angle with the straight track (1) and the roller (2501), one end of the small spring transmitter (2503) is installed on the brake plate (2504), and the other end is connected to the support rod through the force sensor (2502).

4. The device according to claim 1, characterized in that The multi-stage ejection mechanism comprises: a first-stage ejection assembly, a second-stage ejection assembly and a third-stage ejection assembly which are arranged in sequence and at intervals; The first-stage ejection assembly comprises: a first electromagnet (6), a second iron ball (7) and a third iron ball (8) arranged in sequence; the first electromagnet (6) is connected inside the straight track (1) and is parallel to the cross-sectional direction of the straight track (1); The secondary ejection assembly comprises: a second electromagnet (11), a fourth iron ball (16) and a fifth iron ball (17) which are arranged in sequence; the second electromagnet (11) is connected inside the straight track (1) and is parallel to the cross-sectional direction of the straight track (1); The three-stage ejection assembly comprises: a third electromagnet (19), a sixth iron ball (20), a pressure sensor (23) and an iron partition (24) which are arranged in sequence; The third electromagnet (19) is connected inside the straight track (1) and is parallel to the cross-sectional direction of the straight track (1), the iron partition (24) is connected to an end of the straight track (1) away from the spring transmitter (2), and the pressure sensor (23) is installed at the connection between the iron partition (24) and the straight track (1).

5. The device according to claim 4, characterized in that The distance between the first iron ball (3) and the first electromagnet (6) is L, and L≥1m.

6. The device according to claim 4, characterized in that The distance between the third iron ball (8) and the second electromagnet (11) and the distance between the fifth iron ball (17) and the third electromagnet (19) are both D, and D≥40dm.

7. The device according to claim 4, characterized in that The distance between the third iron ball (8) and the second electromagnet (11) and the distance between the fifth iron ball (17) and the third electromagnet (19) are both the same, D, and D≥40dm.

8. The device according to claim 3, characterized in that The launch cabin (21) comprises: a second controller (2101), a first clamp-shaped brake (2102), a second clamp-shaped brake (2103), a third clamp-shaped brake (2104), a fourth clamp-shaped brake (2105) and a monitoring cabin; The second controller (2101) is arranged in the monitoring cabin, the first clamp-shaped brake (2102), the second clamp-shaped brake (2103), the third clamp-shaped brake (2104), and the fourth clamp-shaped brake (2105) are installed at the bottom of the monitoring cabin, the first clamp-shaped brake (2102) and the second clamp-shaped brake (2103) cooperate with each other to be movably connected to the circular track (22), the third clamp-shaped brake (2104) and the fourth clamp-shaped brake (2105) cooperate with each other to be movably connected to the circular track (22), and the first clamp-shaped brake (2102), the second clamp-shaped brake (2103), the third clamp-shaped brake (2104), and the fourth clamp-shaped brake (2105) are communicatively connected to the second controller (2101); The second controller (2101) is used to receive signals from the monitoring cabin and control the first clamp brake (2102), the second clamp brake (2103), the third clamp brake (2104) and the fourth clamp brake (2105) to achieve braking according to the signals from the monitoring cabin.

9. The device according to claim 8, characterized in that The monitoring cabin comprises: a seat (2106) and a monitor (2107); the monitor (2107) is used to monitor the angular acceleration of the launch cabin (21) and the physical condition of the test personnel in the cabin.

10. The device according to claim 8, characterized in that A first position sensor (26) and a second position sensor (27) are also distributed on the circular track (22). The first position sensor (26) and the second position sensor (27) are used to send a braking signal to the second controller (2101) when the launch cabin (21) reaches the position of the first position sensor (26) and the second position sensor (27).

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