Unmanned aerial vehicle putting mechanism and control method

Abstract

The invention discloses an unmanned aerial vehicle launching mechanism and a control method, and relates to the technical field of unmanned aerial vehicle launching, and the unmanned aerial vehicle launching mechanism comprises a bullet type unmanned aerial vehicle cabin mechanism, a mother bomb engine propulsion cabin and a mother-son bomb separation mechanism. After an unmanned aerial vehicle throwing mechanism is driven to a specified target point by a mother bomb engine propulsion cabin, a plurality of warhead cover body connecting pins are triggered by controlling a pneumatic pin disengaging and shelling mechanism to retract, and high-pressure gas is jetted to a warhead cover body assembly so that the warhead cover body assembly can be separated from the mother bomb engine propulsion cabin; the controllable pneumatic pin-releasing shelling mechanism can more accurately and stably realize the separation of the shrapnel, so that the subsequent unmanned aerial vehicle launching action is smoothly completed, and the stability and safety of unmanned aerial vehicle launching are improved; long-distance shrapnel type large-scale launching of the unmanned aerial vehicle is achieved, interference of the environment such as weather is small, shrapnel structure separation is stable and reliable, launching of the unmanned aerial vehicle to be launched is based on gravity sliding, and the unmanned aerial vehicle launching action is stable and reliable.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle delivery, and in particular to a unmanned aerial vehicle delivery 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 drone delivery of cluster bombs, the present invention provides a drone delivery mechanism and control method. The following technical solutions are adopted:

[0006] A UAV delivery mechanism includes a bullet-type UAV cabin mechanism, a mother bomb engine propulsion cabin and a submunition separation mechanism, wherein the bullet-type UAV cabin mechanism includes a warhead connection cover assembly, a UAV mounting core assembly and a storage part release device;

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

[0008] The drone mounting core assembly comprises a core cover, a main pylon, a plurality of drone storage parts and a slow-down pin release mechanism, wherein the end of the core cover is connected to the other end of the warhead connection cover assembly through a plurality of core cover connecting pins, the core cover is sleeved on the outside of the pylon, a plurality of storage part mounting positions are arranged on the main pylon, a plurality of drone storage parts surround the plurality of storage part mounting positions of the main pylon, the drone storage part stores the drones to be launched, a storage part release device is mounted on the main pylon, and the slow-down pin release mechanism is mounted on the end of the main pylon, and is opened after the warhead cover assembly is separated from the mother bomb engine propulsion cabin, and the slow-down pin release mechanism is opened to pull back a plurality of core cover connecting pins at the same time, and the core cover is detached from the outside of the main pylon;

[0009] The storage section release device is activated to open the multiple drone storage sections, and the bottom opening of the drone storage section is moved out of the main rack and facing downward, and the drones to be launched stored in the drone storage section fall down to complete the launch.

[0010] By adopting the above technical solution, multiple warhead cover body connecting pins are used to realize the connection between the warhead cover body 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 body connecting pins can be retracted by controlling the pneumatic pin-release and shell-release mechanism to be triggered, and high-pressure gas can be sprayed to the warhead cover body assembly to separate the warhead cover body 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.

[0011] After the warhead cover assembly is separated from the mother missile engine propulsion compartment, the slow-down release mechanism of the UAV mounted core assembly needs to be activated. Specifically, when the slow-down release mechanism is activated, multiple core cover connecting pins are pulled back at the same time, and the core cover is detached from the main pylon. At the same time, the slow-down release mechanism can make the main pylon and multiple UAV storage parts present a slow-down posture. The slow-down posture means that the bottom opening of the UAV storage part faces downward. At this time, the storage part release device is activated to open the multiple UAV storage parts, and the bottom opening of the UAV storage part moves out of the main pylon and faces downward. The UAVs to be released stored in the UAV storage part fall down to complete the release.

[0012] The large-scale long-distance cluster bomb-style delivery of drones has been achieved, with less interference from weather and other environmental factors. The separation of the cluster bomb structure is stable and reliable, and the delivery of the drones to be delivered is based on gravity sliding, so the drone delivery action is stable and reliable.

[0013] Optionally, the pneumatic pin removal and shell removal mechanism includes a mounting plate, a high-pressure gas generator, a plurality of pneumatic pin removal components and a pneumatic shell removal component, the pneumatic pin removal component includes a piston cavity, a spring and a piston member, the mounting plate is mounted in the end of the mother missile engine propulsion compartment, a high-pressure gas generating cavity and a plurality of high-pressure gas conducting gas paths are arranged in the mounting plate, 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 is mounted in the high-pressure gas generating cavity, and when triggered, high-pressure gas is generated, and one side of the piston cavity of the plurality of pneumatic pin removal components is respectively fixed The piston cavity is fixedly installed on the side of the mounting plate, and a plurality of air inlet holes and a plurality of air outlet holes are provided on the piston cavity. The plurality of air inlet holes are respectively connected to the other end of the plurality of high-pressure gas conducting gas paths. The piston member is assembled in the piston cavity, and one end of the piston member is connected to the bullet 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 plurality of air inlet holes of the piston cavity of the plurality of pneumatic pin removal assemblies enter the high-pressure gas. The piston member is actuated under the action of the high-pressure gas to retract the plurality of bullet cover connecting pins to complete the pneumatic pin removal action.

[0014] The pneumatic shell stripping assembly includes a boss part and a thrust plate, wherein the boss part is installed at the inner wall of the warhead cover assembly, and the thrust plate is located at the boss part. When high-pressure gas enters multiple air inlet holes of the piston cavity of multiple sets of pneumatic shell stripping assemblies, the piston part compresses the spring, and 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 cover assembly away from the mother missile engine propulsion compartment.

[0015] 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.

[0016] After the high-pressure gas enters the multiple air inlet holes of the multiple sets of pneumatic pin removal assemblies, the piston will be pushed toward the cavity on one side of the spring, thereby driving the multiple warhead cover connecting pins to retract. At this time, there is no rigid connection between the warhead cover assembly and the mother missile engine propulsion compartment, and the separation conditions are met;

[0017] If the warhead cover assembly is not quickly pushed away at this time, the warhead cover assembly will continue to move forward under the drive of the mother missile engine propulsion compartment, 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;

[0018] 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 cover assembly away from the mother missile engine propulsion compartment, thereby achieving stable and reliable separation of the warhead cover assembly from the mother missile engine propulsion compartment.

[0019] 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.

[0020] 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 one after another. 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 cover assembly away from the mother missile engine propulsion compartment, thereby realizing stable and reliable separation of the warhead cover assembly from the mother missile engine propulsion compartment.

[0021] 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 cover 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.

[0022] Optionally, the elastic gasket is made of elastic silicone material.

[0023] 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 each warhead cover connecting pin, the warhead cover assembly is pushed backward under the action of the rebound force so that the warhead cover assembly and the pin shaft hole of the mother missile engine propulsion compartment are offset, thereby avoiding the warhead cover connecting pin from being inserted again and causing a separation failure.

[0024] Optionally, the slow-descent release pin mechanism includes a parachute, a parachute connecting pin and multiple slider connecting rod mechanisms, wherein the parachute is mounted at the end of the main bracket, and when opened under a control signal, the parachute opens, and multiple core cover connecting pins are pulled back simultaneously through the parachute connecting pin and multiple slider connecting rod mechanisms to cause the core cover to be detached from the outside of the main bracket.

[0025] By adopting the above technical solution, the parachute adopts an automatically controllable opening parachute, and completes the parachute opening action under the control signal. After the parachute is opened, the entire UAV mounted core assembly is in a slow descending posture, and the parachute pulls the parachute connecting pin upward, thereby driving multiple slider connecting rod mechanisms to pull back multiple core outer cover connecting pins at the same time to detach the core outer cover from the main bracket, thereby realizing the autonomous shedding of the core outer cover.

[0026] Optionally, the storage part releasing device includes an electric lifting mechanism and a plurality of spreading paddles. The tops of the plurality of drone storage parts are respectively hinged at the storage part mounting positions of the main bracket. The slider of the electric lifting mechanism is located on the main axis of the main bracket and moves up and down. The plurality of spreading paddles are respectively installed around the outside of the slider of the electric lifting mechanism. When the electric lifting mechanism drives the slider to slide upward, it drives the plurality of spreading paddles to spread the bottoms of the plurality of drone storage parts upward.

[0027] Optionally, the drone storage portion is barrel-shaped with an open bottom.

[0028] By adopting the above technical solution, the storage part release device adopts an action similar to an umbrella opening action. When the electric lifting mechanism drives the slider to slide upward, it drives multiple opening paddles to open the bottom of multiple drone storage parts upward. The opening angle is only required to make the bottom of the drone storage part move out of the bottom baffle area of ​​the main bracket. At this time, the drone to be launched can slide out from the bottom opening of the drone storage part under the action of its own gravity. Of course, the drone to be launched can also be put into a power-on standby state. The drone to be launched can be mounted in the drone storage part through an electric control buckle. After receiving the launch command, the electric control buckle opens and the drone to be launched slides down.

[0029] Optionally, it also includes a chip-based flight control unit, which controls the execution actions of each actuator of the mother bomb engine propulsion compartment, the submunition separation mechanism and the storage part release device respectively.

[0030] By adopting the above technical solution, the flight control unit belongs to the flight control intelligent body, which can realize autonomous remote UAV batch delivery under the set flight control program and target parameters, and can also realize wireless communication with the distant ground and complete the UAV delivery action under the instructions sent from the ground.

[0031] A method for controlling a drone delivery mechanism is provided, and is used to control a drone delivery mechanism, comprising the following steps:

[0032] Step 1: The flight control unit controls the mother missile engine propulsion cabin to drive the entire UAV delivery mechanism to fly to a specified height above the target coordinates;

[0033] Step 2: The flight control unit starts the drone launch action;

[0034] The drone delivery action includes the following sub-steps:

[0035] Step 21, the flight control unit controls the high-pressure gas generator to explode and generate high-pressure gas, and the pneumatic pin-release assembly is actuated under the action of the high-pressure gas to retract the multiple warhead cover connecting pins to complete the pneumatic pin-release action;

[0036] Step 22, the pneumatic shelling assembly moves to push the warhead cover assembly away from the mother missile engine propulsion compartment;

[0037] Step 23, the flight control unit controls the parachute to open, and the parachute pulls back the multiple core cover connecting pins simultaneously through the parachute connecting pins and the multiple slider connecting rod mechanisms to separate the core cover from the main pylon;

[0038] Step 24, the flight control unit controls the storage part release device including the electric lifting mechanism to move, and the slider of the electric lifting mechanism slides upward to drive the multiple opening paddles to open the bottoms of the multiple drone storage parts upward;

[0039] Step 25, the drone to be launched slides down from the bottom of the drone storage unit, automatically powers on, unfolds its rotors and enters a flying posture, completing the drone launch action.

[0040] In summary, the present invention includes at least one of the following beneficial technical effects:

[0041] The present invention can provide a UAV delivery mechanism and control method, which adopts a plurality of warhead cover connecting pins to realize the connection between the warhead cover assembly and the mother bomb engine propulsion cabin. After the mother bomb engine propulsion cabin drives the UAV delivery mechanism to the designated target point, the plurality of warhead cover connecting pins are retracted by controlling the triggering of the pneumatic pin-dropping and shell-dropping mechanism, and high-pressure gas is sprayed to the warhead cover assembly to separate the warhead cover 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 UAV delivery action can be completed smoothly, and the stability and safety of the UAV delivery are improved.

[0042] After the warhead cover assembly is separated from the mother missile engine propulsion compartment, the slow-down release mechanism is opened to pull back multiple core cover connection pins at the same time, and the core cover is separated from the main pylon. At the same time, the slow-down release mechanism can make the main pylon and multiple drone storage parts in a slow-down posture, and the storage part release device is started to open the multiple drone storage parts. The bottom opening of the drone storage part moves out of the main pylon and faces downward, and the drones to be released stored in the drone storage part fall down to complete the release;

[0043] The large-scale long-distance cluster bomb-style delivery of drones has been achieved, with less interference from weather and other environmental factors. The separation of the cluster bomb structure is stable and reliable, and the delivery of the drones to be delivered is based on gravity sliding, so the drone delivery action is stable and reliable. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 This is a schematic diagram of the structure of a UAV delivery mechanism before delivery of the present invention;

[0045] Figure 2 It is a schematic structural diagram of the combined state of a warhead connection cover assembly and a UAV mounted warhead core assembly of a UAV delivery mechanism of the present invention;

[0046] Figure 3 It is a schematic diagram of the internal structure of a UAV delivery mechanism of the present invention, showing a combined state of a warhead connection cover assembly and a UAV mounted warhead core assembly;

[0047] Figure 4 It is a schematic cross-sectional structure diagram of a pneumatic pin-removing and shell-removing mechanism of a UAV delivery mechanism of the present invention;

[0048] Figure 5 This is a schematic diagram of the internal structure of a UAV delivery mechanism of the present invention;

[0049] Figure 6 It is a schematic structural diagram of the warhead-type unmanned aerial vehicle cabin mechanism of the unmanned aerial vehicle delivery mechanism of the present invention in three states before, during and after the separation from the mother missile engine propulsion cabin;

[0050] Figure 7 It is a structural schematic diagram of a bullet-shaped unmanned aerial vehicle cabin mechanism parachute just opened in a state of the unmanned aerial vehicle delivery mechanism of the present invention;

[0051] Figure 8 It is a structural schematic diagram of the state in which the parachute of the bullet-shaped unmanned aerial vehicle cabin mechanism of the unmanned aerial vehicle delivery mechanism of the present invention is opened and the outer cover of the bullet core falls off and the unmanned aerial vehicle storage part is opened.

[0052] Explanation of the reference numerals: 1. Warhead connecting cover assembly; 2. UAV mounting core assembly; 21. Core cover; 22. Main bracket; 23. UAV storage part; 241. Parachute; 242. Parachute connecting pin; 243. Slider connecting rod mechanism; 25. Core cover connecting pin; 252. Opening paddle; 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. Thrust plate; 58. Elastic gasket; 100. Mother bomb engine propulsion compartment; 102. UAV to be launched. DETAILED DESCRIPTION

[0053] The present invention is further described in detail below in conjunction with the accompanying drawings.

[0054] The embodiment of the invention discloses a UAV delivery mechanism and a control method.

[0055] Reference Figure 1-Figure 8 Embodiment 1: A UAV delivery mechanism includes a bullet-type UAV cabin mechanism, a mother bomb engine propulsion cabin 100 and a submunition separation mechanism. The bullet-type UAV cabin mechanism includes a warhead connection cover assembly 1, a UAV mounting core assembly 2 and a storage release device;

[0056] The submunition separation mechanism includes a plurality of warhead cover connecting pins 3 and a pneumatic pin-dropping and shell-dropping mechanism. One end of the warhead cover assembly 1 is connected to the end of the mother missile engine propulsion compartment 100 through the plurality of warhead cover connecting pins 3; the pneumatic pin-dropping and shell-dropping mechanism is installed in the end of the mother missile engine propulsion compartment 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 cover assembly 1 to separate the warhead cover assembly 1 from the mother missile engine propulsion compartment 100.

[0057] The drone mounting core assembly 2 comprises a core cover 21, a main pylon 22, a plurality of drone storage parts 23 and a slow-down pin release mechanism. The end of the core cover 21 is connected to the other end of the warhead connection cover assembly 1 through a plurality of core cover connecting pins 25. The core cover 21 is sleeved on the outside of the pylon 22. The main pylon 22 is provided with a plurality of storage part mounting positions. The plurality of drone storage parts 23 surround the plurality of storage part mounting positions of the main pylon 22. The drone storage part 23 stores the drone 102 to be launched. The storage part release device is installed on the main pylon 22. The slow-down pin release mechanism is installed at the end of the main pylon 22. When the warhead cover assembly 1 is separated from the mother bomb engine propulsion cabin 100 and then opened, the slow-down pin release mechanism is opened to pull back the plurality of core cover connecting pins 25 at the same time, and the core cover 21 is detached from the outside of the main pylon 22.

[0058] The storage part release device is activated to open the multiple drone storage parts 23, and the bottom opening of the drone storage part 23 moves out of the main bracket 22 and faces downward, and the drones 102 to be launched stored in the drone storage part 23 fall down to complete the launch.

[0059] A plurality of warhead cover connecting pins 3 are used to realize the connection between the warhead cover assembly 1 and the mother bomb engine propulsion cabin 100. After the mother bomb engine propulsion cabin 100 drives the drone delivery mechanism to the designated target point, the plurality of warhead cover connecting pins 3 can be retracted by controlling the pneumatic pin-release and shell-release mechanism to be triggered, and high-pressure gas can be sprayed to the warhead cover assembly 1 to separate the warhead cover 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 drone delivery action can be completed smoothly, and the stability and safety of the drone delivery can be improved.

[0060] After the warhead cover assembly 1 is separated from the mother missile engine propulsion compartment 100, the slow-down and pin-out mechanism of the drone mounted core assembly 2 needs to be activated. Specifically, when the slow-down and pin-out mechanism is activated, multiple core cover connecting pins 25 are pulled back at the same time, and the core cover 21 is detached from the main pylon 22. At the same time, the slow-down and pin-out mechanism can make the main pylon 22 and multiple drone storage parts 23 present a slow-down posture. The slow-down posture means that the bottom opening of the drone storage part 23 faces downward. At this time, the storage part release device is activated to open the multiple drone storage parts 23, and the bottom opening of the drone storage part 23 moves out of the main pylon 22 and faces downward. The drone 102 to be launched stored in the drone storage part 23 falls to complete the launch;

[0061] The large-scale long-distance cluster bomb-like delivery of drones is achieved, which is less affected by environmental interference such as weather, and the separation of the cluster bomb structure is stable and reliable. The delivery of the drone 102 to be delivered is based on gravity sliding, and the drone delivery action is stable and reliable.

[0062] 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, and one side of the piston cavity 53 of the plurality of pneumatic pin removal components is respectively fixedly mounted on the mounting plate 51, and ... On the side of the mounting plate 51, a plurality of air inlet holes 531 and a plurality of air outlet holes 532 are provided on the piston cavity 53, and the plurality of air inlet holes 531 are respectively connected to the other end of the plurality of high-pressure gas conducting gas paths, and a piston member 55 is assembled in the piston cavity 53, one end of the piston member 55 is connected to the bullet cover connecting pin 3, and a 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, and the piston member 55 is actuated under the action of the high-pressure gas to retract the plurality of bullet cover connecting pins 3 to complete the pneumatic pin removal action;

[0063] The pneumatic shell stripping assembly includes a boss member 56 and a thrust plate 57. The boss member 56 is installed on the inner wall of the warhead cover 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 stripping 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, pushing the warhead cover assembly 1 away from the mother missile engine propulsion compartment 100.

[0064] 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.

[0065] After the high-pressure gas enters the multiple air inlet holes 531 of the multiple sets of pneumatic pin removal 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 cover assembly 1 and the mother missile engine propulsion cabin 100, and the separation condition is met;

[0066] If the warhead cover assembly 1 is not quickly pushed away at this time, the warhead cover 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;

[0067] 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 cover assembly 1 away from the mother missile engine propulsion compartment 100, thereby achieving stable and reliable separation of the warhead cover assembly 1 from the mother missile engine propulsion compartment 100.

[0068] In Example 3, 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 of the piston cavity 53. The air inlet cavity is the internal space of the piston cavity 53 where the pin shaft is located. The outermost one of the three air outlet holes 532 is connected to the air inlet cavity. When the high-pressure gas generator 52 is in a fired state, as the air inlet cavity moves toward the side of the spring 54, the other two air outlet holes 532 leak out in sequence.

[0069] The three air inlet holes 531 are all connected to the air inlet cavity 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 transmitted to the outside of the piston cavity 53 of the multiple sets of pneumatic de-pinning components from multiple high-pressure gas conduction gas paths, and enters the air inlet cavity 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 to push the piston member 55 to the side of the spring 54. As the air inlet hole 531 is discharged, the piston member 55 is pushed to the side of the spring 54. The air cavity moves toward the side of the spring 54, and 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 cavity 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 cover assembly 1 away from the mother missile engine propulsion compartment 100, thereby realizing stable and reliable separation of the warhead cover assembly 1 and the mother missile engine propulsion compartment 100.

[0070] Embodiment 4, 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 cover 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.

[0071] In embodiment 5, the elastic gasket 58 is made of elastic silicone material.

[0072] 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 body connecting pins 3, the warhead cover body assembly 1 is pushed backward under the action of the rebound force so that the warhead cover body assembly 1 and the pin shaft hole of the mother missile engine propulsion compartment 100 are offset, thereby avoiding the warhead cover body connecting pin 3 from being inserted again and causing a separation failure.

[0073] Embodiment 6, the slow-descent release pin mechanism includes a parachute 241, a parachute connecting pin 242 and a plurality of slider connecting rod mechanisms 243, the parachute 241 is mounted at the end of the main bracket 22, when opened under a control signal, the parachute 241 opens, and the plurality of core cover connecting pins 25 are pulled back simultaneously through the parachute connecting pin 242 and the plurality of slider connecting rod mechanisms 243 to cause the core cover 21 to be detached from the outside of the main bracket 22.

[0074] The parachute 241 adopts an automatically controllable opening parachute, which completes the parachute opening action under the control signal. After the parachute 241 is opened, the entire UAV mounted core assembly 2 is in a slow descending posture, and the parachute 241 pulls the parachute connecting pin 242 upward, thereby driving multiple slider connecting rod mechanisms 243 to pull back multiple core outer cover connecting pins 25 at the same time to make the core outer cover 21 detach from the main bracket 22, thereby realizing the autonomous detachment of the core outer cover 21.

[0075] Embodiment 7, the storage part release device includes an electric lifting mechanism and a plurality of spreading paddles 252, the tops of the plurality of UAV storage parts 23 are respectively hinged at the storage part mounting positions of the main bracket 22, the slider of the electric lifting mechanism is located on the main axis of the main bracket 22 and moves up and down, the plurality of spreading paddles 252 are respectively installed around the outside of the slider of the electric lifting mechanism, when the electric lifting mechanism drives the slider to slide upward, it drives the plurality of spreading paddles 252 to spread the bottoms of the plurality of UAV storage parts 23 upward.

[0076] In Example 8, the drone storage portion 23 is barrel-shaped with an open bottom.

[0077] The storage part release device adopts an action similar to that of an umbrella opening. When the electric lifting mechanism drives the slider to slide upward, it drives multiple opening paddles 252 to open the bottom of multiple drone storage parts 23 upward. The opening angle is only required to make the bottom of the drone storage part 23 move out of the bottom baffle area of ​​the main bracket 22. At this time, the drone 102 to be launched can slide out from the bottom opening of the drone storage part 23 under the action of its own gravity. Of course, the drone 102 to be launched can also be put into a power-on standby state. The drone 102 to be launched can be mounted in the drone storage part 23 through an electrically controlled buckle. After receiving the launch command, the electrically controlled buckle opens, and the drone 102 to be launched slides down.

[0078] Embodiment 9 also includes a chip-based flight control unit, which controls the execution actions of the actuators of the mother bomb engine propulsion compartment 100, the submunition separation mechanism and the storage part release device respectively.

[0079] The flight control unit is a flight control intelligent body, which can realize autonomous remote batch delivery of UAVs under the set flight control program and target parameters, and can also realize wireless communication with the distant ground and complete the delivery of UAVs under the instructions sent from the ground. An aviation optoelectronic pod can also be set at the end of the bullet-shaped UAV cabin mechanism to provide GPS positioning, attitude data, altitude data, etc. for the flight control unit.

[0080] Embodiment 10, a method for controlling a drone delivery mechanism, for controlling a drone delivery mechanism, comprises the following steps:

[0081] Step 1: The flight control unit controls the mother missile engine propulsion cabin 100 to drive the entire UAV delivery mechanism to fly to a specified height above the target coordinates;

[0082] Step 2: The flight control unit starts the drone launch action;

[0083] The drone delivery action includes the following sub-steps:

[0084] Step 21, the flight control unit controls the high-pressure gas generator 52 to explode and generate high-pressure gas, and the pneumatic pin-off assembly is actuated under the action of the high-pressure gas to retract the multiple warhead cover body connecting pins 3 to complete the pneumatic pin-off action;

[0085] Step 22, the pneumatic shelling assembly moves to push the warhead cover assembly 1 away from the mother missile engine propulsion compartment 100;

[0086] Step 23, the flight control unit controls the parachute 241 to open, and the parachute 241 simultaneously pulls back the multiple core cover connecting pins 25 through the parachute connecting pin 242 and the multiple slider connecting rod mechanisms 243 to separate the core cover 21 from the main pylon 22;

[0087] Step 24, the flight control unit controls the storage part release device including the electric lifting mechanism to move, and the slider of the electric lifting mechanism slides upward to drive the multiple opening paddles 252 to open the bottom of the multiple drone storage parts 23 upward;

[0088] Step 25, the drone 102 to be launched slides down from the bottom of the drone storage portion 23, automatically powers on, unfolds the rotors and enters a flying posture, completing the drone launching action.

[0089] 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 drone delivery mechanism, characterized in that: It comprises a bullet-type unmanned aerial vehicle cabin mechanism, a mother missile engine propulsion cabin (100) and a submunition separation mechanism, wherein the bullet-type unmanned aerial vehicle cabin mechanism comprises a warhead connection cover assembly (1), a UAV mounted missile core assembly (2) and a storage portion release device; 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 cover 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 cover assembly (1) to separate the warhead cover assembly (1) from the mother warhead engine propulsion cabin (100). The unmanned aerial vehicle mounting core assembly (2) comprises a core outer cover (21), a main pylon (22), a plurality of unmanned aerial vehicle storage parts (23) and a slow-down pin release mechanism, wherein the end of the core outer cover (21) is connected to the other end of the warhead connection cover assembly (1) via a plurality of core outer cover connecting pins (25), the core outer cover (21) is sleeved on the outside of the pylon (22), a plurality of storage part mounting positions are provided on the main pylon (22), and the plurality of unmanned aerial vehicle storage parts (23) are surrounded by the main pylon. The main rack (22) has a plurality of storage section mounting positions, the drone storage section (23) stores the drone (102) to be launched, the storage section release device is mounted on the main rack (22), the slow-down pin release mechanism is mounted at the end of the main rack (22), and when the warhead cover assembly (1) is separated from the mother warhead engine propulsion cabin (100), the slow-down pin release mechanism is opened to pull back a plurality of core cover connecting pins (25) at the same time, and the core cover (21) is separated from the outside of the main rack (22); The storage section release device is activated to open the plurality of drone storage sections (23), the bottom openings of the drone storage sections (23) are moved out of the main hanger (22) and face downward, and the drones (102) to be launched stored in the drone storage sections (23) fall down to complete the launch.

2. The UAV delivery 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 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 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), and the plurality of air inlet holes (531) 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), and one end of the piston member (55) is connected to the bullet cover 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) is actuated under the action of the high-pressure gas to cause the plurality of bullet cover connecting pins (3) to retract, thereby completing the pneumatic pin removal action. 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 cover 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 cover assembly (1) away from the mother missile engine propulsion cabin (100).

3. The UAV delivery mechanism according to claim 2, 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 of the piston cavity (53). The air inlet cavity 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. When the high-pressure gas generator (52) is in a fired state, as the air inlet cavity moves toward the side of the spring (54), the other two air outlet holes (532) leak out in sequence.

4. The UAV delivery mechanism according to claim 3, 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 cover 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.

5. The UAV delivery mechanism according to claim 4, characterized in that: The elastic gasket (58) is made of elastic silicone material.

6. The UAV delivery mechanism according to claim 1, characterized in that: The slow-descent release mechanism comprises a parachute (241), a parachute connecting pin (242) and a plurality of slider connecting rod mechanisms (243). The parachute (241) is mounted on the end of a main pylon (22). When the parachute (241) is opened under a control signal, a plurality of core cover connecting pins (25) are simultaneously pulled back through the parachute connecting pin (242) and the plurality of slider connecting rod mechanisms (243) so that the core cover (21) is released from the outside of the main pylon (22).

7. The UAV delivery mechanism according to claim 2, characterized in that: The storage part release device comprises an electric lifting mechanism and a plurality of spreading paddles (252); the tops of the plurality of drone storage parts (23) are respectively hinged at the storage part mounting positions of the main rack (22); a slider of the electric lifting mechanism is located on the main axis of the main rack (22) and moves up and down; the plurality of spreading paddles (252) are respectively mounted around the outside of the slider of the electric lifting mechanism; when the electric lifting mechanism drives the slider to slide upward, the plurality of spreading paddles (252) are driven to spread the bottoms of the plurality of drone storage parts (23) upward.

8. The UAV delivery mechanism according to claim 3, characterized in that: The drone storage part (23) is barrel-shaped, and the bottom is open.

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

10. A control method for a drone delivery mechanism, characterized in that: A method for controlling a drone delivery mechanism according to any one of claims 1 to 9, comprising the following steps: Step 1, the flight control unit controls the mother missile engine propulsion cabin (100) to drive the entire UAV delivery mechanism to fly to a specified height above the target coordinates; Step 2: The flight control unit starts the drone launch action; The drone delivery action 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 pneumatic pin-release assembly is actuated under the action of the high-pressure gas to retract the multiple warhead cover body connecting pins (3) to complete the pneumatic pin-release action; Step 22, the pneumatic shelling assembly moves to push the warhead cover assembly (1) away from the mother missile engine propulsion compartment (100); Step 23, the flight control unit controls the parachute (241) to open, and the parachute (241) simultaneously pulls back the multiple core cover connecting pins (25) through the parachute connecting pin (242) and the multiple slider connecting rod mechanisms (243) so that the core cover (21) is separated from the main pylon (22); Step 24, the flight control unit controls the storage part release device including the electric lifting mechanism to move, and the slider of the electric lifting mechanism slides upward to drive the multiple opening paddles (252) to open the bottom of the multiple drone storage parts (23) upward; Step 25, the drone (102) to be launched slides down from the bottom of the drone storage portion (23), automatically starts up, unfolds its rotors and enters a flying posture, completing the drone launching action.

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