Safety control mechanism and control method for hail suppression rocket projectile

Abstract

The safety control mechanism comprises a control box, a chip box is fixedly connected to the upper end of the control box, a three-code-in-one chip is fixedly installed in the chip box, an electric detonator is fixed to the center of the control box in a penetrating mode, a transverse sliding way is formed in the control box, and a sliding block is slidably connected to the interior of the transverse sliding way; a detonating tube is fixed to the left end of the sliding block, the left end of the detonating tube is connected with a thrust spring, and a vertical sliding way is formed in the bottom in the transverse sliding way and located on the right side of the sliding block. By arranging the acceleration safety mechanism, the safety of the sliding block during production, transportation and operation on the ground can be guaranteed, the safety of the three-code-in-one chip can not execute the self-destruction step if the rocket projectile cannot be launched and flies successfully, and finally the safety of the electric pin puller can be guaranteed if the electric detonator is accidentally ignited, and the safety of the three-code-in-one chip does not execute the self-destruction step. The power of the electric detonator can be isolated through the partition plate of the sliding block, the follow-up output explosive of a larger explosive amount cannot be affected, and therefore the safety of the hail-suppression rocket projectile is improved in a multiple mode.

Description

Technical Field

[0001] The present invention relates to the technical field of hail-proof rockets, and in particular to a safety control mechanism and a control method for hail-proof rockets. Background Art

[0002] With the rapid development of civil aerospace, the use of various types of rockets is increasing, especially in the field of weather modification, where hail suppression rockets are used. However, in recent years, there have been numerous accidents involving artificial rainmaking and hail suppression ammunition falling to the ground and exploding prematurely, resulting in numerous casualties. Therefore, the safety of current hail suppression rockets is relatively low. Summary of the Invention

[0003] The purpose of the present invention is to overcome the defects of the prior art and provide a safety control mechanism and control method for anti-hail rockets to solve the problems raised in the above background technology.

[0004] A safety control mechanism for anti-hail rockets includes a control box, a chip box is fixedly connected to the upper end of the control box, a three-code-in-one chip is fixedly installed inside the chip box, an electric detonator is fixed through the center of the control box, a horizontal slide is opened inside the control box, a slider is slidably connected inside the horizontal slide, a detonating tube is fixed to the left end of the slider, and a thrust spring is connected to the left end of the detonating tube, a vertical slide is opened at the bottom of the horizontal slide and located on the right side of the slider, an acceleration safety mechanism is installed inside the vertical slide, an electric pin puller is fixedly installed at the rear of the control box, the electric pin puller is plugged into the slider, and the lower end of the control box is filled and fixed with output medicine.

[0005] Furthermore, the electric detonator is electrically connected to the three-in-one chip, and the three-in-one chip is electrically connected to the electric pin puller.

[0006] Furthermore, a pressure screw 1 is threadedly connected to the upper right corner of the control box, and the pressure screw 1 and the acceleration safety mechanism are located on the same vertical line. The left and right ends of the horizontal slide are both threadedly connected to the pressure screw 2, and the left part of the thrust spring is tightly attached to the pressure screw 2 at the left end.

[0007] Furthermore, a socket is provided at the rear end of the slider, and the electric pin puller is plugged into the socket.

[0008] Furthermore, the acceleration safety mechanism includes a guide column, a safety spring and an inertial body. The guide column is T-shaped and fixed to the bottom of the vertical slide. The inertial body is movably sleeved on the upper part of the guide column. The safety spring is connected between the lower end of the inertial body and the lower part of the guide column. The upper part of the inertial body extends into the interior of the horizontal slide and abuts against the right part of the slider.

[0009] A safety control method for anti-hail rockets, applied to any of the above-mentioned safety control mechanisms, comprises the following steps: Step 1: Power on the rocket mount and launch controller to perform key matching. Once the keys are matched, the operator remotely reads the rocket's elevation angle and resistance value parameters through the launch controller to determine the rocket's status. After detecting the direction of the hail cloud through the radar, the operator adjusts the launch elevation angle according to the rocket's ballistic diagram and sets the explosion time to 20 seconds. Step 2: Charge the three-in-one chip only when the rocket is in good condition. After charging, press the launch button. The first discharge of the three-in-one chip prompts the engine ignition device to ignite, and the rocket takes off. The inertial body moves into the vertical slide due to inertia and no longer blocks the right side of the slider. Step 3: The three-in-one chip performs a second discharge, triggering the electric pin puller to retract and move out of the socket. The compressed thrust spring pushes the slider to the right, causing the noning tube and the electric detonator to be aligned. Step 4: 20 seconds after the rocket takes off, it arrives in the hail cloud. After the three-in-one chip determines that the rocket overload is normal, the three-in-one chip discharges the third channel to excite the electric detonator, which ignites the detonating tube after a delay of 100ms. The detonating tube then ignites the output charge to explode and self-destruct.

[0010] The beneficial effects of the present invention are as follows: by setting up an acceleration safety mechanism, the safety of the slider during ground production, transportation, and operation can be prevented; the safety of the three-in-one chip can prevent the rocket from launching successfully and the three-in-one chip will not execute the self-destruction step; finally, the safety of the electric pin puller can prevent the electric detonator from accidentally igniting, and the partition of the slider can isolate the power of the electric detonator without affecting the subsequent output of a larger amount of medicine, thereby improving the safety of the anti-hail rocket in multiple ways. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 This is a schematic diagram of the overall main cross-section of the present invention; Figure 2 This is a partial cross-sectional schematic diagram of a control box according to the present invention viewed from above; Figure 3 Schematic diagram of partial cross-section of the control box of the present invention when it is in ground operation, viewed from the rear and top; Figure 4 Schematic diagram of partial cross-section of the control box of the present invention when the engine is overloaded from the rear and top views; Figure 5 It is a partial cross-sectional diagram of the control box of the present invention for pushing out the slider by the thrust spring after pin removal from the rear side; Figure 6 This is a schematic diagram of the acceleration insurance mechanism of the present invention; Figure 7 This is a working sequence diagram of the safety control method of the present invention.

[0012] In the figure: 1-acceleration safety mechanism, 2-slider, 3-pressure screw 1, 4-electric detonator, 5-three-in-one chip, 6-chip box, 7-detonating tube, 8-pressure screw 2, 9-thrust spring, 10-control box, 11-output charge, 12-electric pin puller, 13-guide column, 14-safety spring, 15-inertia body. DETAILED DESCRIPTION

[0013] See also Figures 1-6 A safety control mechanism for anti-hail rockets includes a control box 10, the upper end of the control box 10 is fixedly connected to a chip box 6, a three-code-in-one chip 5 is fixedly installed inside the chip box 6, an electric detonator 4 is fixed through the center of the control box 10, the electric detonator 4 is electrically connected to the three-code-in-one chip 5, a horizontal slide is opened inside the control box 10, a slider 2 is slidably connected inside the horizontal slide, a detonating tube 7 is fixed to the left end of the slider 2, a thrust spring 9 is connected to the left end of the detonating tube 7, a vertical slide is opened at the bottom of the horizontal slide and on the right side of the slider 2, an acceleration safety mechanism 1 is installed inside the vertical slide, and the acceleration safety mechanism 1 includes a guide column 13 and a safety spring 14 and inertial body 15, the guide column 13 is T-shaped and fixed to the bottom of the vertical slide, the inertial body 15 is movably sleeved on the upper part of the guide column 13, the safety spring 14 is connected between the lower end of the inertial body 15 and the lower part of the guide column 13, the upper part of the inertial body 15 extends into the interior of the horizontal slide and abuts against the right part of the slider 2, an electric pin puller 12 is fixedly installed at the rear of the control box 10, the three-in-one chip 5 is electrically connected to the electric pin puller 12, the electric pin puller 12 is plugged into the slider 2, a socket is opened at the rear end of the slider 2, the electric pin puller 12 is plugged into the socket, the lower end of the control box 10 is filled with an output medicine 11, and before the rocket is launched, the acceleration insurance mechanism 1 is in Figure 3 In this state, the slider 2 is held by the inertial body 15, and the electric detonator 4 is dislocated from the detonating tube 7. Even if the electric detonator 4 accidentally ignites at this time, the detonating tube 7 is in a safe state, and the output charge 11 is also in a safe state. When the rocket engine is burning, the overload acceleration is the largest, and the acceleration safety mechanism 1 is in Figure 4 In this state, the inertial body 15 moves downward under the inertial action to squeeze the safety spring 14, so that the inertial body 15 no longer presses against the slider 2. When the three-in-one chip 5 discharges and the electric pin puller 12 pulls the pin, the slider 2 slides to the position due to the thrust of the thrust spring 9 in the compressed state. Figure 5State, at this time, the electric detonator 4 and the detonating tube 7 are in the aligned state. After the flight time continues for 20s, the three-code-in-one chip 5 discharges again, the electric detonator 4 outputs to ignite the detonating tube 7, and the detonating tube 7 then ignites the output medicine 11. The output medicine 11 can ignite the passivated RDX powder column of the hail-proof rocket, so that the middle and tail self-destruction medicine boxes complete the disintegration of the middle and tail of the rocket. The explosion of the passivated RDX completes the disturbance of the hail cloud and the blasting of the warhead. Finally, the rocket debris falls freely in the form of flocs no more than 100g, and the rocket completes its work. Because of the acceleration insurance mechanism 1 of the control mechanism, the rocket can be retracted only in the flight overload state, and the slider 2 can be aligned, so the blunt force in the rocket The RDX charge column is always safe when it is on the ground, and the overload judgment of the three-in-one chip 5 after the pinning action can determine whether to work on the electric detonator 4 and the self-destruction box, thereby ensuring the safety of the self-destruction box. In this way, by setting up the acceleration safety mechanism 1, the safety of the slider 2 during production, transportation, and operation on the ground can be prevented, and the insurance of the three-in-one chip 5 can prevent the rocket from launching successfully. The three-in-one chip 5 will not execute the self-destruction step. Finally, the insurance of the electric pin puller 12 can prevent the electric detonator 4 from accidentally igniting. The partition effect of the slider 2 can isolate the power of the electric detonator 4 and will not affect the subsequent larger amount of output medicine 11, thereby multiple-fold improving the safety of the anti-hail rocket.

[0014] A pressure screw 3 is threadedly connected to the upper right side of the control box 10, and the pressure screw 3 and the acceleration safety mechanism 1 are located on the same vertical line. The left and right ends of the horizontal slide are threadedly connected to pressure screws 8, and the left part of the thrust spring 9 is in close contact with the pressure screw 8 at the left end. By setting the pressure screw 3, after the acceleration safety mechanism 1 is moved into the vertical slide, it can be screwed into the control box 10 to press against the top of the acceleration safety mechanism 1. The setting of the pressure screw 2 8 can seal the openings at both ends of the horizontal slide after the slider 2, the detonating tube 7, and the thrust spring 9 are installed into the horizontal slide.

[0015] See also Figure 1-Figure 7 A safety control method for anti-hail rockets, applied to any of the above-mentioned safety control mechanisms, comprises the following steps: Step 1: Power on the rocket mount and launch controller to perform key matching. If the keys do not match, the operation is terminated. If the keys match, the operator remotely reads the rocket's elevation angle and resistance value parameters through the launch controller to determine the rocket's status. After detecting the direction of the hail cloud by radar, the launch elevation angle is adjusted according to the rocket's ballistic diagram and the explosion time is set to 20 seconds. Step 2: If the rocket is in an unqualified state, the three-code-in-one chip 5 cannot be charged. The three-code-in-one chip 5 will be charged only when the rocket is in a qualified state. If it is disconnected or there is no operation for 6 minutes, the three-code-in-one chip 5 will be automatically discharged. After charging, press the launch button. The first discharge of the three-code-in-one chip 5 prompts the engine ignition device to ignite, and the rocket takes off. The inertial body 15 moves into the vertical slide due to inertia and no longer blocks the right part of the slider 2. Step 3: The three-in-one chip 5 performs a second discharge, triggering the electric pin puller 12 to retract and move out of the socket. The compressed thrust spring 9 pushes the slider 2 to the right, causing the detonator tube 7 and the electric detonator 4 to be aligned. Step 4: 20 seconds after the rocket takes off, it arrives in the hail cloud. The three-in-one chip 5 determines whether the rocket is overloaded. If it is determined that there is no overload, the rocket has not been launched successfully. The three-in-one chip 5 stops working. After it is determined to be normal, the third discharge of the three-in-one chip 5 excites the electric detonator 4 to ignite the detonating tube 7 after a delay of 100ms. The detonating tube 7 then ignites the output charge 11 to explode and self-destruct.

Claims

1. A safety control mechanism for anti-hail rockets, comprising a control box (10), characterized in that: The upper end of the control box (10) is fixedly connected to a chip box (6), a three-code-in-one chip (5) is fixedly installed inside the chip box (6), an electric detonator (4) is fixed through the center of the control box (10), a horizontal slide is provided inside the control box (10), a slider (2) is slidably connected inside the horizontal slide, a detonating tube (7) is fixed at the left end of the slider (2), a thrust spring (9) is connected to the left end of the detonating tube (7), a vertical slide is provided at the bottom of the horizontal slide and located on the right side of the slider (2), an acceleration safety mechanism (1) is installed inside the vertical slide, an electric pin puller (12) is fixedly installed at the rear of the control box (10), the electric pin puller (12) is plugged into the slider (2), and an output drug (11) is filled and fixed at the lower end of the control box (10).

2. The safety control mechanism for anti-hail rockets according to claim 1, characterized in that: The electric detonator (4) is electrically connected to the three-in-one chip (5), and the three-in-one chip (5) is electrically connected to the electric pin puller (12).

3. The safety control mechanism for anti-hail rockets according to claim 1, characterized in that: The control box (10) is threadedly connected to a pressure screw 1 (3) on the upper right side. The pressure screw 1 (3) and the acceleration safety mechanism (1) are located on the same vertical line. The left and right ends of the horizontal slide are threadedly connected to pressure screw 2 (8). The left part of the thrust spring (9) is tightly attached to the pressure screw 2 (8) at the left end.

4. The safety control mechanism for anti-hail rockets according to claim 1, characterized in that: The rear end of the slider (2) is provided with a socket, and the electric pin puller (12) is plugged into the socket.

5. The safety control mechanism for anti-hail rockets according to claim 1, characterized in that: The acceleration safety mechanism (1) includes a guide column (13), a safety spring (14) and an inertia body (15), wherein the guide column (13) is T-shaped and fixed to the bottom of the vertical slide, the inertia body (15) is movably sleeved on the upper part of the guide column (13), the safety spring (14) is connected between the lower end of the inertia body (15) and the lower part of the guide column (13), and the upper part of the inertia body (15) extends into the interior of the horizontal slide and abuts against the right part of the slider (2).

6. A safety control method for anti-hail rockets, applied to the safety control mechanism according to any one of claims 1 to 5, characterized in that: The following steps are involved: Step 1: Power on the rocket mount and launch controller to perform key matching. Once the keys are matched, the operator remotely reads the rocket's elevation angle and resistance value parameters through the launch controller to determine the rocket's status. After detecting the direction of the hail cloud through the radar, the operator adjusts the launch elevation angle according to the rocket's ballistic diagram and sets the explosion time to 20 seconds. Step 2: The three-in-one chip (5) is charged only when the rocket is in a qualified state. After charging, the launch button is pressed, and the first discharge of the three-in-one chip (5) causes the engine ignition device to ignite, and the rocket is launched. Due to inertia, the inertial body (15) moves into the vertical slide and no longer blocks the right part of the slider (2); Step 3: The three-in-one chip (5) performs a second discharge, triggering the electric pin puller (12) to work and retract and move out of the socket, and the thrust spring (9) in a compressed state pushes the slider (2) to move to the right, so that the detonating tube (7) and the electric detonator (4) are in an aligned state; Step 4: 20 seconds after the rocket is launched, it arrives in the hail cloud. After the three-in-one chip (5) determines that the rocket is overloaded and is normal, the third discharge of the three-in-one chip (5) excites the electric detonator (4) and ignites the detonating tube (7) after a delay of 100ms. The detonating tube (7) then ignites the output charge (11) to cause explosion and self-destruction.

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