A device for a catapult type instantaneous angular acceleration impact test

Abstract

A catapult-type instantaneous angular acceleration impact testing device includes: a first controller, a spring launcher, a straight track, a first iron ball, a multi-stage catapult mechanism, a launch chamber, and a circular track. The first controller is connected to the spring launcher, which is located at one end of the straight track. When the spring launcher is compressed, there is a gap between the straight track and the spring launcher. When the spring launcher is open, it pushes the first iron ball, causing it to be ejected. The first iron ball is positioned within the straight track near one end of the spring launcher. The multi-stage catapult mechanism is spaced apart from the first iron ball within the straight track. The circular track is installed at the other end of the straight track. The straight track is tangential to the circular track, and the straight track and the circular track are at different heights in the same vertical direction. The launch chamber is mounted on the circular track. The use of the multi-stage catapult mechanism and the circular track increases the energy ultimately obtained by the launch chamber, thereby enabling the angular velocity to reach the required test value.

Description

Technical Field

[0001] This application belongs to the aerospace field, specifically relating to a catapult-type instantaneous angular acceleration impact test device. Background Technology

[0002] The high angular acceleration of high-performance fighter jets can easily cause motion sickness in pilots. Their small turning radius and high angular acceleration, reaching up to 40° / s², exceed the tolerance of ordinary people by more than 10 times. The human body is instantly subjected to 3-6 times the horizontal forward gravitational acceleration, leading to symptoms such as difficulty breathing and chest pain. When the human body is instantly subjected to 3-6 times the horizontal backward gravitational acceleration, it can cause headaches, increased intraocular pressure, and conjunctival congestion. These symptoms are undoubtedly fatal to pilots engaged in spaceflight operations.

[0003] Therefore, it is urgent to establish a test station on the ground to conduct catapult-type instantaneous angular acceleration impact tests, so as to study the angular acceleration at different instantaneous magnitudes, thereby gaining a deeper understanding of the physiological effects of angular acceleration and devising solutions to reduce the harm of angular acceleration to pilots.

[0004] Application content

[0005] To overcome the shortcomings of the prior art, this application proposes a catapult-type instantaneous angular acceleration impact testing 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 chamber 21, and a circular track 22;

[0006] The first controller 15 is connected to the spring launcher 2, which 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, it pushes the first iron ball 3 to eject the first iron ball 3. The first iron ball 3 is located in the straight track 1 near one end of the spring launcher 2. The multi-stage ejection mechanism is spaced apart from the first iron ball 3 in the straight track 1. 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. 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 launch it out.

[0008] Preferably, 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. A drive motor is provided on the telescopic shaft 9 away from the first threaded connection hole 4. The drive motor is located on the outside of the straight track 1.

[0009] Preferably, the bottom end of the straight track 1 is provided with two roller assemblies 25, which are respectively disposed on both sides of the straight track 1. Each roller assembly 25 includes: a support rod, a roller 2501, a force sensor 2502, a small spring launcher 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. Both 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 launcher 2503 is mounted 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 includes: a first-stage ejection assembly, a second-stage ejection assembly, and a third-stage ejection assembly arranged sequentially at intervals;

[0011] The primary ejection assembly includes: a first electromagnet 6, a second iron ball 7, and a third iron ball 8 arranged sequentially; the first electromagnet 6 is connected inside 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 sequentially; the second electromagnet 11 is connected inside 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 sequentially;

[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 the end of the straight track 1 away from the spring launcher 2. 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 both D, where D≥40dm.

[0018] Preferably, 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.

[0019] The second controller 2101 is installed 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 and are movably connected to the circular track 22. The third clamp-shaped brake 2104 and the fourth clamp-shaped brake 2105 cooperate with each other and are movably connected to the circular track 22. 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.

[0020] The second controller 2101 is used to: receive signals transmitted 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 transmitted from the monitoring cabin.

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

[0022] Preferably, 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.

[0023] Compared with the closest prior art, the beneficial effects of this application are as follows:

[0024] A projectile-type instantaneous angular acceleration impact testing device includes: a first controller 15, a spring launcher 2, a straight track 1, a first iron ball 3, a multi-stage projectile mechanism, a launch chamber 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; when the spring launcher 2 is opened, the spring launcher 2 pushes the first iron ball 3 to launch the first iron ball 3 out, the first iron ball 3 is disposed in the straight track 1 near one end of the spring launcher 2, and the multi-stage projectile mechanism is connected to the first iron ball 3. The straight track 1 is spaced apart, and the circular track 22 is installed at the other end of the straight track 1. The straight track 1 is located tangentially to the circular track 22, and the straight track 1 and the circular track 22 are at different heights in the same vertical direction. 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 launch it out. This application uses a multi-stage launch mechanism to gradually transfer kinetic energy to the launch cabin 21, so that the speed can reach a large value. The launch cabin 21 is launched along the circular track 22. Due to the huge firing speed and the instantaneous turning, an instantaneous angular acceleration is generated. Attached Figure Description

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

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

[0027] Figure 3 A cross-sectional view (AA) of a projectile-type instantaneous angular acceleration impact testing device provided in this application;

[0028] Figure 4 A partially enlarged view of the roller section of a catapult-type instantaneous angular acceleration impact testing device provided in this application;

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

[0030] Figure 6 This application provides a main sectional view of the launch chamber of a catapult-type instantaneous angular acceleration impact testing device.

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

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

[0033] Wherein: 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-Launch compartment, 2101-Second controller Device, 2102-First clamp brake, 2103-Second clamp brake, 2104-Third clamp brake, 2105-Fourth clamp 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 launcher, 2504-Brake plate, 26-First position sensor, 27-Second position sensor, 28-Second controllable switch, 29-Second fuse. Detailed Implementation

[0034] The specific embodiments of this application will be further described in detail below with reference to the accompanying drawings.

[0035] Example 1:

[0036] To achieve the above objectives, this application provides a projectile-type instantaneous angular acceleration impact testing 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 chamber 21, and a circular track 22;

[0037] The first controller 15 is connected to the spring launcher 2, which 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 open, it pushes the first iron ball 3, causing it to be ejected. The first iron ball 3 is positioned within the straight track 1 near one end of the spring launcher 2. The multi-stage ejection mechanism is spaced apart from the first iron ball 3 within the straight track 1. The circular track 22 is installed at the other end of the straight track 1. The straight track 1 is located tangentially to the circular track 22, and the straight track 1 and the circular track 22 are at different heights in the same vertical direction. The launch chamber 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 launch it out.

[0039] Spring launcher 2 can control the extent of spring contraction, thereby controlling the initial kinetic energy of the iron ball and ultimately the magnitude of its angular acceleration. The two tracks are arranged in an alternating configuration, with the straight track 1 on top and the circular track 22 on the bottom. This arrangement facilitates the movement of the straight track 1 and allows for easy cycle-based testing.

[0040] Two control systems and one monitoring system are adopted. The first controller 15 of the control system mainly controls the power system and controls the operation 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 excessive speed, it is controlled by the other control system. The monitoring cabin in the monitoring system mainly measures the magnitude of angular acceleration and the safety of the personnel inside.

[0041] Preferably, 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. A drive motor is provided on the telescopic shaft 9 away from the first threaded connection hole 4. The drive motor is located on the outside of the straight track 1.

[0042] This device consists of a straight track 1 and a circular track 22, which are staggered vertically. Initially, an electromagnet is energized, attracting an iron ball to form a catapult system. Utilizing the electromagnet's magnetic force, the iron ball's kinetic energy increases as it is attracted, and this energy is transferred to the final iron ball through the law of conservation, thus increasing its kinetic energy. The use of a three-stage electromagnet distribution structure increases the energy ultimately acquired by the launch chamber 21, allowing for a larger angular velocity.

[0043] like Figure 3 As shown, the bottom end of the straight track 1 is provided with two roller assemblies 25, and the two roller assemblies 25 are respectively arranged on both sides of the straight track 1, as shown. Figure 4 The roller assembly 25 shown includes: a support rod, a roller 2501, a force sensor 2502, a small spring launcher 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; both ends of the brake plate 2504 are connected to the straight track 1 and the roller 2501 respectively and form a certain angle with the straight track 1 and the roller 2501; one end of the small spring launcher 2503 is mounted 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 shows that the force sensor 2502 receives a tendency for the roller 2501 to move, which is transmitted to the small spring launcher 2503. The small spring launcher 2503 releases 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 chamber 21, and the offset process ends.

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

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

[0047] The primary ejection assembly includes: a first electromagnet 6, a second iron ball 7, and a third iron ball 8 arranged sequentially; the first electromagnet 6 is connected inside 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 sequentially; the second electromagnet 11 is connected inside 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 sequentially;

[0050] The third electromagnet 19 is connected inside the straight track 1 and 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 launcher 2. The pressure sensor 23 is installed at the connection between the iron partition 24 and the straight track 1. Figure 5 As shown.

[0051] The device has a launching platform on the left, including a spring launcher 2 on the left and a straight track 1 on the right. A first drive motor 5 and a second drive motor 10 are fixedly connected to the straight track 1. The straight track 1 is characterized by being connected to the first and second drive motors 5 and 10 via a threaded connection hole-like structure. 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 a catapult device, which is further divided into three stages of catapult launch. The first stage catapult device includes a first electromagnet 6, a second iron ball 7, and a third iron ball 8. The first electromagnet 6 is connected to the straight track 1 via a threaded connection hole, and the other electromagnets use the same method. The second stage catapult includes a second electromagnet 11, a fourth iron ball 16, and a fifth iron ball 17. The third stage catapult includes a third electromagnet 19, a sixth iron ball 20, a pressure sensor 23, and an iron partition 24. Below the track... The unit is connected by two roller assemblies 25, which consist of a roller 2501, a force sensor 2502, a small spring launcher 2503, and a brake plate 2504. The rightmost part is the launch chamber 21, which consists of a second controller 2101, a first clamp brake 2102, a second clamp brake 2103, a third clamp brake 2104, a fourth clamp brake 2105, a seat 2106, and a monitor 2107. The launch chamber 21 is tightly connected to the circular track 22, on which two sensors are distributed: a first position sensor 26 and a second position sensor 27. The circular track 22 and the straight track 1 are staggered. The entire unit is operated by a control circuit system controlled by the first controller. The circuit system consists 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] This device consists of a straight track 1 and a circular track 22, which are staggered vertically. Figure 2 The black area represents the region of straight track 1, and the white circle represents the location of circular track 22. Initially, the first electromagnet 6, the second electromagnet 11, and the third electromagnet 19 are energized. The first electromagnet 6 attracts the second iron ball 7 and the third iron ball 8, forming a first-stage launching system; the second electromagnet 11 attracts the fourth iron ball 16 and the fifth iron ball 17, forming a second-stage launching system; and the third electromagnet 19 attracts the sixth iron ball 20 without any gaps between it and the iron partition 24, forming a third-stage launching system. The electromagnets are installed on the straight track 1 with one corner of the second threaded connection hole 18 as a reference, and are installed at all four corners.

[0053] Pressure sensor 23 detects the separation of launch chamber 21 and transmits a signal to first controller 15. First controller 15 controls second control switch 28, and first drive motor 5 and second drive motor 10 start to control 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] Initially, the distance between the first iron ball 3 and the first electromagnet 6 is L, and L ≥ 1m. This prevents the first iron ball 3 from being attracted by the first electromagnet 6 without being launched 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, where D ≥ 40 dm. This is to prevent the next stage electromagnet from having a stronger attraction than the current stage, thus attracting the iron ball first.

[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 both D, where D≥40dm.

[0059] The distance between the fifth iron ball 17 and the third electromagnet 19 is D, where D ≥ 40 dm. This is to prevent the next electromagnet from having a stronger attraction than the current one, thus attracting the iron ball first.

[0060] The test personnel enter the test chamber and sit in seat 2106. The aforementioned structure is activated by the first controller 15 via the first controllable switch 13, which initiates the spring launcher 2, imparting initial kinetic energy to the first iron ball 3 and launching it. Subsequently, the first iron ball 3 is attracted and impacted by the first electromagnet 6, gradually transferring kinetic energy to the third iron ball 8 at the end of the first-stage launch device. The third iron ball 8 gains kinetic energy, overcomes the attraction of the first electromagnet 6, and moves towards the second-stage launch device; similarly, it is attracted and impacted by the second-stage magnet 11, transferring kinetic energy to the fifth iron ball 17, which overcomes the attraction of the second electromagnet 11 and moves towards the third-stage launch device; the fifth iron ball 17 is attracted and impacted by the third electromagnet 19, gradually transferring kinetic energy to the launch chamber 21, which launches along the circular track 22; due to the enormous acceleration and immediate turn, a large instantaneous angular acceleration is generated, and the launch process ends.

[0061] Pressure sensor 23 is tightly connected to launch chamber 21 before launch. Iron partition 24 is tightly connected to straight track 1 to prevent the sixth iron ball 20 from detaching due to movement of 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 installed 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 and are movably connected to the circular track 22. The third clamp-shaped brake 2104 and the fourth clamp-shaped brake 2105 cooperate with each other and are movably connected to the circular track 22. 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.

[0064] The second controller 2101 is used to: receive signals transmitted 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 transmitted from the monitoring cabin.

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

[0066] The monitor 2107 is used to monitor the angular acceleration of the launch capsule 21 and the physical condition of the test personnel inside the capsule.

[0067] like Figure 8 As shown, 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.

[0068] The three-stage ejection system ejects the launch capsule 21 and moves it along the circular track 22. When it reaches 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 to achieve braking. This provides time for the straight track 1 to deviate and provides a solution to prevent the launch capsule 21 from failing to stop in a short time due to excessive force.

[0069] This device can also perform cyclic tests. The clamping tightness of the clamping brake is controlled by the second controller 2101, thereby controlling the stopping position of the launch chamber 21 and enabling the return of the launch chamber 21. The first control system 15 controls the drive motor, thereby controlling the retraction of the telescopic shaft 9 to return the straight track 1 to its original position for repeated testing.

[0070] Example 2:

[0071] The projectile-type instantaneous angular acceleration impact testing device described in this application adopts the following technical solution:

[0072] Step 1): The test personnel enter the test chamber and sit in seat 2106. The aforementioned structure is activated by the first controller 15 via the first controllable switch 13, which initiates the spring launcher 2, giving the first iron ball 3 initial kinetic energy and launching it. The first iron ball 3 is attracted and impacted by the first electromagnet 6, gradually transferring its kinetic energy to the third iron ball 8 at the end of the first-stage launch device. The third iron ball 8 gains kinetic energy, escapes the attraction of the first electromagnet 6, and moves towards the second-stage launch device; similarly, it is attracted and impacted by the second electromagnet 11, transferring the energy to the fifth iron ball 17, which escapes the attraction of the second electromagnet 11 and moves towards the third-stage launch device; the fifth iron ball 17 is attracted and impacted by the third electromagnet 19, gradually transferring its kinetic energy to the launch chamber 21, which launches it along the circular track 22; due to the high velocity and immediate turning, instantaneous angular acceleration is generated.

[0073] Step 2): Pressure sensor 23 detects that launch chamber 21 has detached and transmits a signal to first controller 15. First controller 15 opens second controllable switch 28 and closes first controllable switch 13. First drive device 5 and second drive motor 10 control telescopic shaft 9 to push straight track 1. Force sensor 2502 senses the thrust and transmits it to small spring launcher 2503, which pops the brake plate 2504 open and pushes 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 capsule 21 that has not been fully reset, and the first controller 15 controls the first drive motor 5 and the second drive motor 10 to reset the straight track 1. The test is repeated.

[0076] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application and not to limit its protection scope. Although this application has been described in detail with reference to the above embodiments, those skilled in the art should understand that after reading this application, they can still make various changes, modifications or equivalent substitutions to the specific implementation of the application, but these changes, modifications or equivalent substitutions are all within the protection scope of the claims pending approval.

Claims

1. A projectile-type instantaneous angular acceleration impact testing device, characterized in that, include: The system comprises a first controller (15), a spring launcher (2), a straight track (1), a first iron ball (3), a multi-stage ejection mechanism, a launch chamber (21), and a circular track (22); The first controller (15) is connected to the spring launcher (2), which 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, it pushes the first iron ball (3) to eject the first iron ball (3). The first iron ball (3) is located in the straight track (1) near the end of the spring launcher (2). The multi-stage ejection mechanism is spaced apart from the first iron ball (3) in the straight track (1). The circular track (22) is installed at the other end of the straight track (1). The straight track (1) is located in the tangential 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. The launch cabin (21) is mounted on the circular track (22). 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 launch it.

2. The apparatus as claimed in 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). The telescopic shaft (9) is provided with a drive motor away from the first threaded connection hole (4). The drive motor is located on the outside of the straight track (1).

3. The apparatus as described in claim 2, characterized in that, The bottom end of the straight track (1) is provided with two roller assemblies (25), and the two roller assemblies (25) are respectively arranged on both sides of the straight track (1). The roller assembly (25) includes: a support rod, a roller (2501), a force sensor (2502), a small spring launcher (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 launcher (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 apparatus as claimed in claim 1, characterized in that, The multi-stage ejection mechanism includes: a first-stage ejection assembly, a second-stage ejection assembly, and a third-stage ejection assembly arranged at intervals in sequence; The first-stage ejection assembly includes: a first electromagnet (6), a second iron ball (7), and a third iron ball (8) arranged sequentially; 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 includes: a second electromagnet (11), a fourth iron ball (16), and a fifth iron ball (17) arranged sequentially; 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 includes: a third electromagnet (19), a sixth iron ball (20), a pressure sensor (23), and an iron partition (24) arranged sequentially; 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 the end of the straight track (1) away from the spring launcher (2). The pressure sensor (23) is installed at the connection between the iron partition (24) and the straight track (1).

5. The apparatus as described in 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 apparatus as claimed in 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 apparatus as claimed in 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, where D≥40dm.

8. The apparatus as claimed in claim 3, characterized in that, 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; The second controller (2101) is installed in the monitoring cabin. The first clamp brake (2102), the second clamp brake (2103), the third clamp brake (2104), and the fourth clamp brake (2105) are installed at the bottom of the monitoring cabin. The first clamp brake (2102) and the second clamp brake (2103) cooperate with each other and are movably connected to the circular track (22). The third clamp brake (2104) and the fourth clamp brake (2105) cooperate with each other and are movably connected to the circular track (22). The first clamp brake (2102), the second clamp brake (2103), the third clamp brake (2104), and the fourth clamp 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 apparatus as claimed in claim 8, characterized in that, 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 inside the cabin.

10. The apparatus as claimed in claim 8, characterized in that, The circular track (22) is also equipped with a first position sensor (26) and a second position sensor (27). 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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