A submunition separation mechanism and control method

Abstract

The present invention discloses a submunition separation mechanism and a control method, which relates to the technical field of separation of submunitions for unmanned aerial vehicle delivery, and is used for the automatic separation of a warhead load assembly and a mother bomb engine propulsion cabin after reaching a target location; the submunition separation mechanism includes a plurality of warhead cover connecting pins and a pneumatic pin-dropping and shell-dropping mechanism. The present invention adopts a plurality of warhead cover connecting pins to realize the connection between the warhead load assembly and the mother bomb engine propulsion cabin. After the mother bomb engine propulsion cabin drives the unmanned aerial vehicle delivery mechanism to a designated target point, the pneumatic pin-dropping and shell-dropping mechanism is controlled to trigger the plurality of warhead cover connecting pins to retract, and high-pressure gas is sprayed to the warhead load assembly to separate the warhead load assembly from the mother bomb engine propulsion cabin; the controllable pneumatic pin-dropping and shell-dropping mechanism can realize the separation of submunitions more accurately and stably, so that the subsequent unmanned aerial vehicle delivery action can be completed smoothly, and the stability and safety of the unmanned aerial vehicle delivery can be improved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle (UAV) submunition delivery and separation, and in particular to a submunition separation mechanism and a control method. Background Art

[0002] Currently, most drones rely on batteries for power supply, but the battery life is limited, which limits the distance and duration of drone missions.

[0003] The Chinese invention patent application with the publication number CN118770615A discloses a UAV cluster bomb structure and control method. The UAV cluster bomb structure includes an aircraft based on a mother bomb structure and a UAV delivery component based on a bullet structure. The aircraft includes a bomb bay, a flight control cabin, an engine compartment and a steering gear compartment. The tail of the bomb bay is installed at the end of the flight control cabin through a controllable separation connector. The rocket-type warhead is used as an aircraft with a mother bomb structure. After the aircraft is launched and arrives in the mission area, the bomb bay is separated from the flight control cabin; the slow-down device continues to slow down the UAV delivery component, and the bomb bay and the UAV delivery component are separated from the free fall body and the UAV delivery component, leaking multiple UAVs mounted on the cluster UAV cluster bomb bay. Multiple UAVs can be ejected and released, thereby realizing the long-distance UAV group delivery. The clustered submunitions have a high flight speed and are less affected by the weather. They are not easily detected and located by electronic technology, which greatly reduces the risk of concentrated delivery.

[0004] Although the above technical solution proposes the idea of ​​drone delivery of cluster bombs, it does not provide a detailed introduction to the specific cluster bomb separation structure. It only mentions that the controllable separation connector is an aviation explosive ejection type separation mechanism. This simple aviation explosive ejection type separation mechanism is prone to the risk of barrel explosion, and the cluster bomb separation is not timely enough. Summary of the invention

[0005] In order to solve the technical problem of cluster bombs being dropped by drones, the present invention provides a cluster bomb separation mechanism and control method. The following technical solutions are adopted:

[0006] A submunition separation mechanism is used for automatically separating the warhead load assembly and the submunition engine propulsion compartment after reaching the target location;

[0007] The submunition separation mechanism includes a plurality of warhead cover connecting pins and a pneumatic pin-dropping and shell-decapping mechanism. One end of the warhead load assembly is connected to the end of the mother missile engine propulsion compartment through a plurality of warhead cover connecting pins; the pneumatic pin-dropping and shell-decapping mechanism is installed in the end of the mother missile engine propulsion compartment. When the pneumatic pin-dropping and shell-decapping mechanism is triggered, the plurality of warhead cover connecting pins are retracted, and high-pressure gas is sprayed toward the warhead load assembly to separate the warhead load assembly from the mother missile engine propulsion compartment.

[0008] By adopting the above technical solution, multiple warhead cover connecting pins are used to realize the connection between the warhead load assembly and the mother missile engine propulsion cabin. After the mother missile engine propulsion cabin drives the drone delivery mechanism to the designated target point, the multiple warhead cover connecting pins can be retracted by controlling the pneumatic pin-release and shell-release mechanism to spray high-pressure gas to the warhead load assembly to separate the warhead load assembly from the mother missile engine propulsion cabin. This controllable pneumatic pin-release and shell-release mechanism can realize the separation of submunitions more accurately and stably, so that the subsequent drone delivery action can be completed smoothly, and the stability and safety of drone delivery can be improved.

[0009] In specific applications, payloads such as drones can be mounted in the warhead payload assembly, which can realize the long-distance and large-scale deployment of drones in a cluster bomb-like manner. It is less affected by environmental interference such as weather, and the separation of the cluster bomb structure is stable and reliable.

[0010] Optionally, the pneumatic de-pinning and shelling mechanism includes a mounting plate, a high-pressure gas generator, multiple sets of pneumatic de-pinning components and a pneumatic shelling component, the pneumatic de-pinning component includes a piston cavity, a spring and a piston member, the mounting plate is installed in the end of the mother missile engine propulsion compartment, a high-pressure gas generating cavity and multiple high-pressure gas conducting gas paths are provided in the mounting plate, one end of the multiple high-pressure gas conducting gas paths are respectively connected to the high-pressure gas generating cavity, the high-pressure gas generator is installed in the high-pressure gas generating cavity, and generates high-pressure gas when triggered, one side of the piston cavity of the multiple sets of pneumatic de-pinning components is respectively fixedly installed on the side of the mounting plate, the piston cavity is provided with multiple air inlet holes and multiple air outlet holes, and the multiple The air inlet holes are respectively connected to the other end of multiple high-pressure gas conduction gas paths, the piston member is assembled in the piston cavity, one end of the piston member is connected to the warhead cover connecting pin, the spring is located between the piston member and the piston cavity, when the high-pressure gas generator generates high-pressure gas, the multiple air inlet holes of the piston cavity of the multiple sets of pneumatic de-pinning assemblies enter the high-pressure gas, the piston member is actuated under the action of the high-pressure gas to cause the multiple warhead cover connecting pins to retract to complete the pneumatic de-pinning action, the high-pressure gas in the piston cavity of the multiple sets of pneumatic de-pinning assemblies continuously enters the pneumatic shelling assembly, and the pneumatic shelling assembly sprays high-pressure gas to the warhead load assembly to separate the warhead load assembly from the mother missile engine propulsion compartment.

[0011] By adopting the above technical solution, the high-pressure gas generator of the pneumatic pin removal and shell removal mechanism is the source of high-pressure gas generation, which can be implemented in the form of an aerial bomb. Of course, the high-pressure gas generator can also be implemented in the form of a high-pressure gas tank. For example, inert high-pressure gas can be poured into a closed container. When it is necessary to start the pin removal and shell removal, the opening of the closed container is opened by the solenoid valve, thereby providing high-pressure gas for multiple sets of pneumatic pin removal components and pneumatic shell removal components.

[0012] After high-pressure gas enters the multiple air inlet holes of multiple sets of pneumatic de-pinning assemblies, the piston will be pushed toward the cavity on one side of the spring, thereby driving the retraction of multiple warhead cover connecting pins. At this time, there is no rigid connection between the warhead load assembly and the mother missile engine propulsion compartment, and the conditions for separation are met.

[0013] Optionally, the pneumatic shell ejection assembly includes a boss member and a thrust plate, wherein the boss member is installed at the inner wall of the warhead load assembly, and the thrust plate is located at the boss member. When high-pressure gas enters the multiple air inlet holes of the piston cavity of multiple sets of pneumatic shell ejection assemblies, the piston member compresses the spring, and the multiple air outlet holes on the piston cavity leak out. The high-pressure gas entering the piston cavity is discharged from the multiple air outlet holes and accumulates in the space between the thrust plate and the mounting plate, forming a thrust on the thrust plate, thereby pushing the warhead load assembly away from the mother missile engine propulsion compartment.

[0014] By adopting the above technical solution, if the warhead load assembly is not quickly pushed away after the multiple warhead cover connection pins between the warhead load assembly and the mother missile engine propulsion compartment are retracted, the warhead load assembly will continue to move forward under the drive of the mother missile engine propulsion compartment, and may also cause the risk of chamber explosion due to the continuous pressure of the high-pressure gas generated by the high-pressure gas generator;

[0015] After the piston continues to push toward the cavity on one side of the spring, multiple air outlet holes are gradually exposed, and the high-pressure gas entering the piston cavity is discharged in large quantities from the multiple air outlet holes, accumulating in the space between the reverse thrust plate and the mounting plate, forming a thrust on the reverse thrust plate, pushing the warhead payload assembly away from the mother missile engine propulsion compartment, thereby achieving stable and reliable separation of the warhead payload assembly from the mother missile engine propulsion compartment.

[0016] Optionally, there are three air inlet holes and three air outlet holes. When the high-pressure gas generator is in an unfired state, the spring and the piston are in their original positions. The three air inlet holes are all connected to the air inlet cavity of the piston cavity. The air inlet cavity is the internal space of the piston cavity where the pin shaft is located. The outermost of the three air outlet holes is connected to the air inlet cavity. When the high-pressure gas generator is in a fired state, as the air inlet cavity moves toward the side of the spring, the other two air outlet holes leak out in sequence.

[0017] By adopting the above technical scheme, the three air inlet holes are all connected with the air inlet cavity of the piston cavity. When the high-pressure gas generator is fired, a large amount of high-pressure gas is generated in the high-pressure gas generating cavity of the mounting plate, and is respectively conducted to the outside of the piston cavity of the multiple sets of pneumatic de-pinning assemblies from multiple high-pressure gas conduction gas paths, and enters the air inlet cavity through the three air inlet holes. At the beginning, only the air outlet hole on the far left discharges gas, and the air intake amount is much greater than the air outlet amount. High pressure is formed in the air inlet cavity to push the piston member toward the spring side. As the air inlet cavity moves toward the spring side, the other two air outlet holes leak out successively. At this time, the multiple sets of pneumatic de-pinning assemblies have completed the pneumatic de-pinning action, and the high-pressure gas is discharged in large quantities from the three air outlet holes of the piston cavity of the multiple sets of pneumatic de-pinning assemblies and then accumulated in the space between the reverse thrust plate and the mounting plate, forming a strong thrust on the reverse thrust plate, pushing the warhead load assembly away from the mother missile engine propulsion compartment, thereby realizing stable and reliable separation of the warhead load assembly from the mother missile engine propulsion compartment.

[0018] Optionally, the pneumatic pin-de-shelling mechanism also includes an elastic gasket, and a gasket boss is provided on the outer ring of the mounting disk. The elastic gasket is clamped on the gasket boss of the mounting disk. When the warhead load assembly is docked and installed with the mother missile engine propulsion compartment and fixed in position by multiple warhead cover connecting pins, the elastic gasket is in a compressed state.

[0019] Optionally, the elastic gasket is made of elastic silicone material.

[0020] By adopting the above technical solution, the role of the elastic gasket made of elastic silicone material is that the elastic gasket is in the maximum compression state during assembly. After multiple sets of pneumatic pin removal assemblies complete the extraction of the warhead cover connecting pins, the warhead load assembly is pushed backward under the action of the rebound force so that the warhead load assembly and the pin shaft hole of the mother missile engine propulsion compartment are offset, thereby avoiding the re-insertion of the warhead cover connecting pin and causing a separation failure.

[0021] Optionally, a chip-based flight control unit is also included, which controls the execution actions of the mother bomb engine propulsion compartment and the submunition separation mechanism respectively.

[0022] By adopting the above technical solution, the flight control unit is a flight control intelligent body, which can realize autonomous batch delivery of remote drones under the set flight control program and target parameters, and can also realize wireless communication with the distant ground and complete the submunition separation action under the command sent from the ground. An aviation optoelectronic pod can also be set at the end of the bullet-shaped unmanned aerial vehicle cabin mechanism to provide GPS positioning, attitude data, altitude data, etc. for the flight control unit.

[0023] A control method for a submunition separation mechanism is used to control a submunition separation mechanism, comprising the following steps:

[0024] Step 1: The flight control unit controls the mother missile engine propulsion cabin to drive the warhead payload assembly and the mother missile engine propulsion cabin to fly to a specified altitude above the target coordinates;

[0025] Step 2: The flight control unit starts the submunition separation action;

[0026] The submunition separation operation includes the following sub-steps:

[0027] Step 21, the flight control unit controls the high-pressure gas generator to explode and generate high-pressure gas, and the high-pressure gas enters the multiple air inlet holes of the piston cavities of the multiple sets of pneumatic pin removal assemblies. The piston parts move under the action of the high-pressure gas to retract the multiple warhead cover body connecting pins to complete the pneumatic pin removal action;

[0028] Step 22, under the action of the resilience of the elastic gasket, the warhead load assembly and the mother missile engine propulsion compartment are staggered;

[0029] Step 23, the high-pressure gas in the piston cavity is discharged from multiple outlet holes and accumulated in the space between the reverse thrust plate and the mounting plate, forming a thrust on the reverse thrust plate. The high-pressure gas thrust separates the warhead load assembly from the mother missile engine propulsion compartment.

[0030] In summary, the present invention includes at least one of the following beneficial technical effects:

[0031] The present invention can provide a submunition separation mechanism and control method, which adopts a plurality of warhead cover connecting pins to realize the connection between the warhead load assembly and the mother warhead engine propulsion cabin, and after the mother warhead engine propulsion cabin drives the UAV delivery mechanism to the designated target point, the pneumatic pin-dropping and shell-dropping mechanism is controlled to trigger the plurality of warhead cover connecting pins to retract, and high-pressure gas is sprayed to the warhead load assembly to separate the warhead load assembly from the mother warhead engine propulsion cabin; the controllable pneumatic pin-dropping and shell-dropping mechanism can realize the separation of submunitions more accurately and stably, so that the subsequent UAV delivery action can be completed smoothly, and the stability and safety of the UAV delivery are improved;

[0032] It can realize the large-scale long-distance cluster bomb-style delivery of payloads such as drones, with less interference from weather and other environmental factors. The separation of the cluster bomb structure is stable and reliable, and the drone delivery action is stable and reliable. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is a schematic diagram of the structure of a submunition separation mechanism before being released according to the present invention;

[0034] Figure 2 It is a schematic cross-sectional structure diagram of a pneumatic pin-removing and shell-removing mechanism of a submunition separation mechanism of the present invention;

[0035] Figure 3 It is a schematic diagram of the internal structure of a submunition separation mechanism of the present invention;

[0036] Figure 4 The present invention is a schematic structural diagram of the three states of the separation of a warhead-type unmanned aircraft cabin mechanism and a mother bomb engine propulsion cabin before, during and after separation.

[0037] Explanation of the reference numerals: 1. warhead load assembly; 3. warhead cover connecting pin; 51. mounting plate; 52. high-pressure gas generator; 53. piston cavity; 531. air inlet; 532. air outlet; 54. spring; 55. piston member; 56. boss member; 57. reverse thrust plate; 58. elastic gasket; 100. mother missile engine propulsion compartment. DETAILED DESCRIPTION

[0038] The present invention is further described in detail below in conjunction with the accompanying drawings.

[0039] The embodiment of the invention discloses a submunition separation mechanism and a control method.

[0040] Reference Figure 1-Figure 4 Embodiment 1: A submunition separation mechanism for automatically separating a warhead load assembly 1 and a submunition engine propulsion compartment 100 after reaching a target location.

[0041] The submunition separation mechanism includes a plurality of warhead cover connecting pins 3 and a pneumatic pin-dropping and shell-removing mechanism. One end of the warhead load assembly 1 is connected to the end of the mother missile engine propulsion compartment 100 through a plurality of warhead cover connecting pins 3; the pneumatic pin-dropping and shell-removing mechanism is installed in the end of the mother missile engine propulsion compartment 100. When the pneumatic pin-dropping and shell-removing mechanism is triggered, the plurality of warhead cover connecting pins 3 are retracted, and high-pressure gas is sprayed toward the warhead load assembly 1 to separate the warhead load assembly 1 from the mother missile engine propulsion compartment 100.

[0042] A plurality of warhead cover connecting pins 3 are used to realize the connection between the warhead load assembly 1 and the mother bomb engine propulsion cabin 100. After the mother bomb engine propulsion cabin 100 drives the UAV delivery mechanism to the designated target point, the pneumatic pin-release and shell-release mechanism can be controlled to trigger the plurality of warhead cover connecting pins 3 to retract, and high-pressure gas can be sprayed to the warhead load assembly 1 to separate the warhead load assembly 1 from the mother bomb engine propulsion cabin 100. This controllable pneumatic pin-release and shell-release mechanism can realize the separation of the submunitions more accurately and stably, so that the subsequent UAV delivery action can be completed smoothly, and the stability and safety of the UAV delivery can be improved.

[0043] In specific applications, payloads such as drones can be mounted in the warhead payload assembly 1, so that long-distance cluster bomb-like large-scale delivery of drones can be achieved, which is less affected by environmental interference such as weather, and the separation of the cluster bomb structure is stable and reliable.

[0044] Embodiment 2, the pneumatic pin removal and shell removal mechanism comprises a mounting plate 51, a high-pressure gas generator 52, a plurality of pneumatic pin removal components and a pneumatic shell removal component, the pneumatic pin removal component comprises a piston cavity 53, a spring 54 and a piston member 55, the mounting plate 51 is mounted in the end of the mother missile engine propulsion cabin 100, a high-pressure gas generating chamber and a plurality of high-pressure gas conducting gas paths are arranged in the mounting plate 51, one end of the plurality of high-pressure gas conducting gas paths are respectively connected to the high-pressure gas generating chamber, the high-pressure gas generator 52 is mounted in the high-pressure gas generating chamber, and generates high-pressure gas when triggered, one side of the piston cavity 53 of the plurality of pneumatic pin removal components is respectively fixedly mounted on the side of the mounting plate 51, a plurality of air inlet holes 531 and a plurality of air outlet holes 532 are arranged on the piston cavity 53, and a plurality of The air inlet holes 531 are respectively connected to the other ends of multiple high-pressure gas conduction gas paths, the piston member 55 is assembled in the piston cavity 53, one end of the piston member 55 is connected to the warhead cover connecting pin 3, and the spring 54 is located between the piston member 55 and the piston cavity 53. When the high-pressure gas generator 52 generates high-pressure gas, the multiple air inlet holes 531 of the piston cavity 53 of the multiple sets of pneumatic de-pinning assemblies enter the high-pressure gas, and the piston member 55 is actuated under the action of the high-pressure gas to cause the multiple warhead cover connecting pins 3 to retract to complete the pneumatic de-pinning action. The high-pressure gas in the piston cavity 53 of the multiple sets of pneumatic de-pinning assemblies continuously enters the pneumatic shelling assembly, and the pneumatic shelling assembly sprays high-pressure gas to the warhead payload assembly 1 to separate the warhead payload assembly 1 from the mother missile engine propulsion compartment 100.

[0045] The high-pressure gas generator 52 of the pneumatic pin-off and shell-off mechanism is the source of high-pressure gas, which can be implemented in the form of an aerial bomb. Of course, the high-pressure gas generator 52 can also be implemented in the form of a high-pressure gas tank. For example, inert high-pressure gas can be poured into a sealed container. When it is necessary to start the pin-off and shell-off, the opening of the sealed container is opened by the solenoid valve, thereby providing high-pressure gas for multiple sets of pneumatic pin-off components and pneumatic shell-off components.

[0046] After the high-pressure gas enters the multiple air inlet holes 531 of the multiple sets of pneumatic de-pinning assemblies, the piston 55 will be pushed toward the cavity on one side of the spring 54, thereby driving the multiple warhead cover connecting pins 3 to retract. At this time, there is no rigid connection between the warhead load assembly 1 and the mother missile engine propulsion compartment 100, and the separation conditions are met.

[0047] Embodiment 3, the pneumatic shell ejection assembly includes a boss member 56 and a thrust plate 57, the boss member 56 is installed on the inner wall of the warhead load assembly 1, and the thrust plate 57 is located at the boss member 56. When high-pressure gas enters the multiple air inlet holes 531 of the piston cavity 53 of multiple sets of pneumatic shell ejection assemblies, the piston member 55 compresses the spring 54, and the multiple air outlet holes 532 on the piston cavity 53 leak out. The high-pressure gas entering the piston cavity 53 is discharged from the multiple air outlet holes 532 and accumulates in the space between the thrust plate 57 and the mounting plate 51, forming a thrust on the thrust plate 57, and pushing the warhead load assembly 1 away from the mother missile engine propulsion compartment 100.

[0048] If the multiple warhead cover connecting pins 3 between the warhead load assembly 1 and the mother missile engine propulsion compartment 100 are not quickly pushed away after the warhead load assembly 1 is retracted, the warhead load assembly 1 will continue to move forward under the drive of the mother missile engine propulsion compartment 100, and there may also be a risk of explosion due to the continuous pressure of the high-pressure gas generated by the high-pressure gas generator 52;

[0049] After the piston member 55 is continuously pushed toward the cavity on one side of the spring 54, multiple air outlet holes 532 are gradually exposed, and the high-pressure gas entering the piston cavity 53 is discharged in large quantities from the multiple air outlet holes 532, and accumulates in the space between the reverse thrust plate 57 and the mounting plate 51, forming a thrust on the reverse thrust plate 57, pushing the warhead payload assembly 1 away from the mother missile engine propulsion compartment 100, thereby achieving stable and reliable separation of the warhead payload assembly 1 from the mother missile engine propulsion compartment 100.

[0050] In Example 4, there are three air inlet holes 531 and three air outlet holes 532. When the high-pressure gas generator 52 is in an unfired state, the spring 54 and the piston member 55 are in their original positions. The three air inlet holes 531 are all connected to the air inlet chamber 533 of the piston chamber 53. The air inlet chamber 533 is the internal space of the piston chamber 53 where the pin shaft is located. The outermost of the three air outlet holes 532 is connected to the air inlet chamber 533. When the high-pressure gas generator 52 is in a fired state, as the air inlet chamber 533 moves toward the side of the spring 54, the other two air outlet holes 532 leak out in sequence.

[0051] The three air inlet holes 531 are all connected to the air inlet cavity 533 of the piston cavity 53. When the high-pressure gas generator 52 is fired, a large amount of high-pressure gas is generated in the high-pressure gas generating cavity of the mounting plate 51, and is respectively conducted to the outside of the piston cavity 53 of the multiple sets of pneumatic de-pinning components through multiple high-pressure gas conduction gas paths, and enters the air inlet cavity 533 through the three air inlet holes 531. At the beginning, only the air outlet hole 532 on the far left discharges gas, and the air intake amount is much greater than the air outlet amount, forming a high pressure in the air inlet cavity 533 to push the piston member 55 to the side of the spring 54. As the air inlet chamber 533 moves toward the side of the spring 54, the other two air outlet holes 532 leak out successively. At this time, the multiple sets of pneumatic de-pinning assemblies have completed the pneumatic de-pinning action. High-pressure gas is discharged in large quantities from the three air outlet holes 532 of the piston chamber 53 of the multiple sets of pneumatic de-pinning assemblies and then accumulated in the space between the reverse thrust plate 57 and the mounting plate 51, forming a strong thrust on the reverse thrust plate 57, pushing the warhead payload assembly 1 away from the mother missile engine propulsion compartment 100, thereby achieving stable and reliable separation of the warhead payload assembly 1 from the mother missile engine propulsion compartment 100.

[0052] Embodiment 5, the pneumatic pin-de-shelling mechanism also includes an elastic gasket 58, and the outer ring of the mounting plate 51 is provided with a gasket boss, and the elastic gasket 58 is clamped on the gasket boss of the mounting plate 51. When the warhead load assembly 1 and the mother missile engine propulsion compartment 100 are docked and installed and fixed in position by multiple warhead cover connecting pins 3, the elastic gasket 58 is in a compressed state.

[0053] In embodiment 6, the elastic gasket 58 is made of elastic silicone material.

[0054] The function of the elastic gasket 58 made of elastic silicone is to be in the maximum compression state during assembly. After multiple sets of pneumatic pin removal assemblies complete the extraction of the warhead cover connecting pin 3, the warhead load assembly 1 is pushed backward under the action of the rebound force so that the warhead load assembly 1 is offset from the pin shaft hole of the mother missile engine propulsion compartment 100, thereby avoiding the warhead cover connecting pin 3 from being inserted again and causing a separation failure.

[0055] Embodiment 7 also includes a chip-based flight control unit, which controls the execution actions of the mother bomb engine propulsion compartment 100 and the submunition separation mechanism respectively.

[0056] The flight control unit is an intelligent flight control entity that can realize autonomous batch delivery of remote drones under the set flight control program and target parameters, and can also realize wireless communication with the distant ground and complete the separation of submunitions under the command sent from the ground. An aviation optoelectronic pod can also be set at the end of the bullet-shaped unmanned aerial vehicle cabin mechanism to provide GPS positioning, attitude data, altitude data, etc. for the flight control unit.

[0057] Embodiment 8, a control method of a submunition separation mechanism, used for controlling a submunition separation mechanism, comprises the following steps:

[0058] Step 1, the flight control unit controls the mother missile engine propulsion cabin 100 to drive the warhead payload assembly 1 and the mother missile engine propulsion cabin 100 to fly to a specified altitude above the target coordinates;

[0059] Step 2: The flight control unit starts the submunition separation action;

[0060] The submunition separation operation includes the following sub-steps:

[0061] Step 21, the flight control unit controls the high-pressure gas generator 52 to explode and generate high-pressure gas, and the multiple air inlet holes 531 of the piston cavity 53 of the multiple sets of pneumatic pin removal assemblies enter the high-pressure gas, and the piston member 55 moves under the action of the high-pressure gas to retract the multiple warhead cover body connecting pins 3 to complete the pneumatic pin removal action;

[0062] Step 22, under the action of the resilience of the elastic gasket 58, the warhead load assembly 1 and the mother missile engine propulsion compartment 100 are offset from each other;

[0063] In step 23, the high-pressure gas in the piston cavity 53 is discharged from the multiple air outlets 532 and accumulated in the space between the reverse thrust plate 57 and the mounting plate 51, forming a thrust on the reverse thrust plate 57. The high-pressure gas thrust separates the warhead payload assembly 1 from the mother missile engine propulsion compartment 100.

[0064] The above are all preferred embodiments of the present invention, and are not intended to limit the protection scope of the present invention. Therefore, any equivalent changes made based on the structure, shape, and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A submunition separation mechanism, characterized in that: Used for automatically separating the warhead payload assembly (1) and the mother warhead engine propulsion compartment (100) after reaching the target location. The submunition separation mechanism comprises a plurality of warhead cover connecting pins (3) and a pneumatic pin-dropping and shell-dropping mechanism. One end of the warhead load assembly (1) is connected to the end of a mother warhead engine propulsion cabin (100) via the plurality of warhead cover connecting pins (3). The pneumatic pin-dropping and shell-dropping mechanism is installed in the end of the mother warhead engine propulsion cabin (100). When the pneumatic pin-dropping and shell-dropping mechanism is triggered, the plurality of warhead cover connecting pins (3) are retracted, and high-pressure gas is sprayed toward the warhead load assembly (1) to separate the warhead load assembly (1) from the mother warhead engine propulsion cabin (100).

2. A submunition separation mechanism according to claim 1, characterized in that: The pneumatic pin removal and shell removal mechanism comprises a mounting plate (51), a high-pressure gas generator (52), a plurality of pneumatic pin removal components and a pneumatic shell removal component. The pneumatic pin removal component comprises a piston cavity (53), a spring (54) and a piston member (55). The mounting plate (51) is mounted in the end of a mother missile engine propulsion cabin (100). A high-pressure gas generating cavity and a plurality of high-pressure gas conducting gas paths are provided in the mounting plate (51). One end of the plurality of high-pressure gas conducting gas paths are respectively connected to the high-pressure gas generating cavity. The high-pressure gas generator (52) is mounted in the high-pressure gas generating cavity and generates high-pressure gas when triggered. One side of the piston cavity (53) of the plurality of pneumatic pin removal components is respectively fixedly mounted on the side of the mounting plate (51). The piston cavity (53) is provided with a plurality of air inlet holes (531) and a plurality of air outlet holes (532). The plurality of air inlet holes (531) and the plurality of air outlet holes (532) are respectively connected to the mother missile engine propulsion cabin (100). 31) are respectively connected to the other ends of the plurality of high-pressure gas conducting gas paths, the piston member (55) is assembled in the piston cavity (53), one end of the piston member (55) is connected to the warhead cover body connecting pin (3), the spring (54) is located between the piston member (55) and the piston cavity (53), when the high-pressure gas generator (52) generates high-pressure gas, the plurality of air inlet holes (531) of the piston cavity (53) of the plurality of pneumatic pin removal assemblies enter the high-pressure gas, the piston member (55) moves under the action of the high-pressure gas to make the plurality of warhead cover body connecting pins (3) retract to complete the pneumatic pin removal action, the high-pressure gas in the piston cavity (53) of the plurality of pneumatic pin removal assemblies continuously enters the pneumatic shell removal assembly, and the pneumatic shell removal assembly sprays the high-pressure gas to the warhead load assembly (1) to separate the warhead load assembly (1) from the mother missile engine propulsion cabin (100).

3. A submunition separation mechanism according to claim 2, characterized in that: The pneumatic shell stripping assembly comprises a boss member (56) and a reverse thrust plate (57), wherein the boss member (56) is mounted on the inner wall of a warhead load assembly (1), and the reverse thrust plate (57) is located at the boss member (56). When high-pressure gas enters a plurality of air inlet holes (531) of a piston cavity (53) of a plurality of sets of pneumatic shell stripping assemblies, the piston member (55) compresses a spring (54), and a plurality of air outlet holes (532) on the piston cavity (53) leak out. The high-pressure gas entering the piston cavity (53) is discharged from the plurality of air outlet holes (532), and is accumulated in the space between the reverse thrust plate (57) and the mounting plate (51), thereby forming a thrust on the reverse thrust plate (57), and pushing the warhead load assembly (1) away from the mother missile engine propulsion cabin (100).

4. A submunition separation mechanism according to claim 3, characterized in that: There are three air inlet holes (531) and three air outlet holes (532). When the high-pressure gas generator (52) is in an unfired state, the spring (54) and the piston member (55) are in their original positions. The three air inlet holes (531) are all connected to the air inlet cavity (533) of the piston cavity (53). The air inlet cavity (533) is the internal space of the piston cavity (53) where the pin shaft is located. The outermost of the three air outlet holes (532) is connected to the air inlet cavity (533). When the high-pressure gas generator (52) is in a fired state, as the air inlet cavity (533) moves toward the side of the spring (54), the other two air outlet holes (532) leak out in sequence.

5. A submunition separation mechanism according to claim 4, characterized in that: The pneumatic pin-removing and shell-removing mechanism further comprises an elastic washer (58), the outer ring of the mounting plate (51) is provided with a washer boss, the elastic washer (58) is clamped on the washer boss of the mounting plate (51), and when the warhead load assembly (1) and the mother warhead engine propulsion compartment (100) are docked and installed and fixed in position by a plurality of warhead cover connecting pins (3), the elastic washer (58) is in a compressed state.

6. A submunition separation mechanism according to claim 5, characterized in that: The elastic gasket (58) is made of elastic silicone material.

7. The submunition separation mechanism according to claim 1, characterized in that: It also includes a chip-based flight control unit, which controls the execution actions of the mother bomb engine propulsion compartment (100) and the submunition separation mechanism respectively.

8. A control method for a submunition separation mechanism, characterized in that: A method for controlling a submunition separation mechanism according to any one of claims 1 to 7, comprising the following steps: Step 1, the flight control unit controls the mother missile engine propulsion cabin (100) to drive the warhead payload assembly (1) and the mother missile engine propulsion cabin (100) to fly to a specified altitude above the target coordinates; Step 2: The flight control unit starts the submunition separation action; The submunition separation operation includes the following sub-steps: Step 21, the flight control unit controls the high-pressure gas generator (52) to explode and generate high-pressure gas, and the high-pressure gas enters the multiple air inlet holes (531) of the piston chambers (53) of the multiple sets of pneumatic pin removal assemblies, and the piston member (55) moves under the action of the high-pressure gas to retract the multiple warhead cover body connecting pins (3) to complete the pneumatic pin removal action; Step 22, under the action of the resilience of the elastic gasket (58), the warhead load assembly (1) and the mother missile engine propulsion compartment (100) are offset from each other; In step 23, the high-pressure gas in the piston cavity (53) is discharged from the multiple air outlets (532) and accumulated in the space between the reverse thrust plate (57) and the mounting plate (51), forming a thrust on the reverse thrust plate (57). The thrust of the high-pressure gas separates the warhead payload assembly (1) from the mother missile engine propulsion compartment (100).

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