Unmanned aerial vehicle delivery mechanism and control method

Abstract

The application discloses a kind of unmanned aerial vehicle delivery mechanism and control method, it is related to unmanned aerial vehicle delivery technical field, including bullet head type unmanned aerial vehicle cabin mechanism, mother bullet engine propulsion cabin and sub-mother bullet separation mechanism.The application is driven to specified target point after unmanned aerial vehicle delivery mechanism by mother bullet engine propulsion cabin, multiple bullet cover body connecting pin is retracted by controlling aerodynamic release and shell separation mechanism trigger, and high-pressure gas is injected to bullet cover body assembly, so that bullet cover body assembly is separated from mother bullet engine propulsion cabin;Controllable aerodynamic release and shell separation mechanism can more accurately and stably realize the separation of sub-mother bullet, so that subsequent unmanned aerial vehicle delivery action is successfully completed, and the stability and safety of unmanned aerial vehicle delivery are improved;Realize the long-distance sub-mother bullet type scale delivery of unmanned aerial vehicle, less affected by weather and other environmental interference, sub-mother bullet structure separation is stable and reliable, and the delivery of unmanned aerial vehicle to be delivered is based on gravity sliding, and unmanned aerial vehicle delivery 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, but the battery life is limited, which restricts the distance and duration of drone missions.

[0003] Chinese invention patent application publication number CN118770615A discloses a drone-based cluster bomb structure and control method. The drone-based cluster bomb structure comprises an aircraft based on a cluster bomb structure and a drone-based delivery assembly based on a bullet structure. The aircraft includes a bomb bay, a flight control compartment, an engine compartment, and a steering gear compartment. The tail of the bomb bay is attached to the end of the flight control compartment via a controllable detachable connector. The aircraft utilizes a rocket-like body as the cluster bomb structure. After launch, the aircraft arrives within the mission area, where the bomb bay and flight control compartment separate. A descent control mechanism continuously decelerates the drone delivery assembly, allowing the bomb bay to separate from the drone delivery assembly in free fall, releasing multiple drones mounted on the cluster drone-based cluster bomb bay. These drones can then be ejected, enabling long-range drone swarm delivery. Clustered cluster bombs have high flight speeds, are less susceptible to weather influences, and are less susceptible to electronic detection and location, significantly reducing 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 aerial explosive ejection type separation mechanism. This simple aerial explosive ejection type separation mechanism is prone to the risk of barrel explosion, and the cluster bombs are not separated in a timely manner. Summary of the Invention

[0005] In order to solve the technical problems in the 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-shaped UAV cabin mechanism, a mother bomb engine propulsion cabin, and a submunition separation mechanism. The bullet-shaped UAV cabin mechanism includes a warhead connection cover assembly, a UAV mounted warhead assembly, and a storage portion release device.

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

[0008] The drone-mounted projectile core assembly includes a projectile core cover, a main pylon, multiple drone storage parts, and a slow-down release mechanism. The end of the projectile core cover is connected to the other end of the warhead connection cover assembly through multiple projectile core cover connecting pins. The projectile core cover is sleeved on the outside of the pylon. The main pylon is provided with multiple storage part mounting positions. Multiple drone storage parts surround the multiple storage part mounting positions of the main pylon. The drone storage parts store drones to be launched. The storage part release device is installed on the main pylon. The slow-down release mechanism is installed at the end of the main pylon. When the warhead cover assembly is separated from the mother bomb engine propulsion compartment and opened, the slow-down release mechanism is opened to pull back the multiple projectile core cover connecting pins at the same time, and the projectile core cover is detached from the outside of the main pylon.

[0009] The storage section release device is activated to open multiple drone storage sections, and the bottom opening of the drone storage section is moved out of the main bracket and facing downward. 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 connecting pins are used to connect the warhead cover assembly to the mother missile engine propulsion compartment. After the mother missile engine propulsion compartment drives the drone delivery mechanism to the designated target point, the multiple warhead cover connecting pins can be retracted by controlling the pneumatic ejection and shelling mechanism, and high-pressure gas is sprayed into the warhead cover assembly to separate the warhead cover assembly from the mother missile engine propulsion compartment. This controllable pneumatic ejection and shelling mechanism can more accurately and stably separate the submunitions, thereby smoothly completing the subsequent drone delivery operation and improving the stability and safety of drone delivery.

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

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

[0013] Optionally, the pneumatic ejection mechanism includes a mounting plate, a high-pressure gas generator, multiple sets of pneumatic ejection components and a pneumatic ejection component. The pneumatic ejection 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 multiple high-pressure gas conducting gas paths are provided in the mounting plate. One end of the multiple high-pressure gas conducting gas paths is respectively connected to the high-pressure gas generating cavity. The high-pressure gas generator is mounted in the high-pressure gas generating cavity. When triggered, high-pressure gas is generated. One side of the piston cavity of the multiple sets of pneumatic ejection components is respectively fixed. The piston cavity is fixedly mounted on the side of the mounting plate, and is provided with a plurality of air inlet holes and a plurality of air outlet holes. The plurality of air inlet holes are respectively connected to the other end of the plurality of high-pressure gas conducting 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. A 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 release pin assemblies enter the high-pressure gas. The piston member is actuated by the high-pressure gas to cause the plurality of bullet cover connecting pins to retract, completing the pneumatic release action.

[0014] The pneumatic shell ejection assembly includes a boss part and a thrust plate. The boss part is installed on the inner wall of the warhead cover assembly, and the thrust plate is located at the boss part. When high-pressure gas enters the multiple air inlet holes of the piston cavity of multiple sets of pneumatic shell ejection assemblies, the piston part 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, 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 de-pinning and de-shelling 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 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 de-pinning and de-shelling process, the opening of the sealed container is opened by a solenoid valve, thereby providing high-pressure gas to multiple sets of pneumatic de-pinning components and pneumatic de-shelling components.

[0016] When high-pressure gas enters the multiple air inlets of the multiple sets of pneumatic release pin assemblies, the pistons are 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 conditions for separation 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 is also the risk of explosion due to the continuous pressure of 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 exposed one after another, 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 and 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 one 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 solution, all three air inlet holes are connected to the air inlet chamber 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 chamber of the mounting plate. This gas is then conducted through multiple high-pressure gas conduction paths to the outside of the piston cavities of the multiple sets of pneumatic release pin assemblies, and then enters the air inlet chamber through the three air inlet holes. Initially, only the leftmost air outlet hole releases gas, and the air intake volume is much greater than the air outlet volume. This creates a high pressure in the air inlet chamber, pushing the piston member toward the spring. As the air inlet chamber moves toward the spring, air gradually leaks out from the other two air outlet holes. At this point, the multiple sets of pneumatic release pin assemblies have completed the pneumatic release action. The high-pressure gas is discharged in large quantities from the three air outlet holes in the piston cavities of the multiple sets of pneumatic release pin assemblies, and then accumulates in the space between the reverse thrust plate and the mounting plate, generating a strong 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.

[0021] Optionally, the pneumatic pin-and-shell ejection mechanism further includes an elastic washer, and a washer boss is provided on the outer ring of the mounting disk. The elastic washer is clamped on the washer boss of the mounting disk. When the warhead cover assembly is docked and installed with the mother bomb engine propulsion compartment and fixed in position by a plurality of warhead cover connecting pins, the elastic washer 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 silicone material elastic gasket is that the elastic gasket is in the maximum compression state during assembly. After multiple sets of pneumatic de-pinning assemblies complete the extraction of the warhead cover connecting pins, 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 staggered, thereby avoiding the warhead cover connecting pin from being inserted again and causing separation failure.

[0024] Optionally, the slow-descent release pin mechanism includes a parachute, a parachute connecting pin and multiple slider-link mechanisms. The parachute is installed at the end of the main bracket. 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-link mechanisms to detach the core cover from the outside of the main bracket.

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

[0026] Optionally, the storage portion releasing device includes an electric lifting mechanism and a plurality of spreading paddles. The tops of the plurality of drone storage portions are respectively hinged at the storage portion 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, the plurality of spreading paddles are driven upward to spread the bottoms of the plurality of drone storage portions.

[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 that of an umbrella opening. 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 the power-on standby state. The drone to be launched can be mounted in the drone storage part through the electric control buckle. After receiving the launch command, the electric control buckle opens and the drone to be launched slides down.

[0029] Optionally, a chip-based flight control unit is also included, which controls the execution actions of the actuators of the mother bomb engine propulsion compartment, the submunition separation mechanism and the storage 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 drone batch delivery under the set flight control program and target parameters, and can also realize wireless communication with the distant ground and complete the drone delivery action under the instructions sent from the ground.

[0031] A method for controlling a drone delivery mechanism, comprising the following steps:

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

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

[0034] The drone delivery operation 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. Under the action of the high-pressure gas, the pneumatic release assembly operates to retract the multiple warhead cover connecting pins to complete the pneumatic release action.

[0036] Step 22: The pneumatic ejection assembly pushes the warhead cover assembly away from the mother missile engine propulsion compartment;

[0037] Step 23: The flight control unit controls the parachute to open. The parachute pulls back the multiple core cover connecting pins simultaneously through the parachute connecting pins and multiple slider linkage mechanisms, so that the core cover is separated from the main pylon.

[0038] Step 24: The flight control unit controls the storage portion release device including the electric lifting mechanism to operate. The slider of the electric lifting mechanism slides upward to drive the multiple opening paddles to open the bottoms of the multiple drone storage portions upward.

[0039] In step 25, the drone to be launched slides down from the bottom of the drone storage portion, automatically powers on, unfolds its rotors and enters a flying attitude, completing the drone launch operation.

[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 uses multiple warhead cover connecting pins to connect the warhead cover assembly with the mother missile engine propulsion compartment. After the mother missile engine propulsion compartment drives the UAV delivery mechanism to a designated target point, the multiple warhead cover connecting pins are retracted by controlling a pneumatic pin-dropping and shell-dropping mechanism, and high-pressure gas is sprayed toward the warhead cover assembly to separate the warhead cover assembly from the mother missile engine propulsion compartment. The controllable pneumatic pin-dropping and shell-dropping mechanism can more accurately and stably separate the submunitions, thereby smoothly completing the subsequent UAV delivery action and improving the stability and safety of UAV delivery.

[0042] After the warhead cover assembly is separated from the mother missile engine propulsion compartment, the slow-descent release mechanism is activated to pull back the multiple core cover connecting pins at the same time, and the core cover is detached from the main pylon. At the same time, the slow-descent release mechanism can make the main pylon and the multiple drone storage parts assume a slow-descent posture. The storage part release device is activated 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 launched stored in the drone storage part fall down to complete the launch.

[0043] The large-scale long-distance cluster bomb-style delivery of drones has been achieved, which is less affected by environmental interference such as weather. The separation of the cluster bomb structure is stable and reliable. The delivery of the drones to be delivered is based on gravity sliding, and 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;

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

[0047] Figure 4 This is a schematic cross-sectional view of a pneumatic pin-and-shell removal 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 This is a schematic structural diagram of the warhead-type unmanned aerial vehicle (UAV) launch mechanism of the present invention, showing the three states before, during, and after separation from the mother missile engine propulsion compartment;

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

[0051] Figure 8 The present invention is a schematic structural diagram of a bullet-shaped unmanned aerial vehicle (UAV) cabin mechanism of a UAV delivery mechanism in an open state with the core outer cover falling off and the UAV storage portion after the parachute is opened.

[0052] Explanation of the accompanying 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 part; 56. Boss part; 57. Thrust plate; 58. Elastic washer; 100. Mother bomb engine propulsion compartment; 102. UAV to be launched. DETAILED DESCRIPTION

[0053] The present invention will be further described in detail below with reference to the accompanying drawings.

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

[0055] Reference Figures 1-8 In 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 mounted core assembly 2, and a storage portion release device.

[0056] The submunition separation mechanism includes multiple warhead cover connecting pins 3 and a pneumatic de-pinning and de-shelling mechanism. One end of the warhead cover assembly 1 is connected to the end of the mother missile engine propulsion compartment 100 via the multiple warhead cover connecting pins 3. The pneumatic de-pinning and de-shelling mechanism is installed at the end of the mother missile engine propulsion compartment 100. When the pneumatic de-pinning and de-shelling mechanism is triggered, the multiple warhead cover connecting pins 3 are retracted and high-pressure gas is sprayed into 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 includes a core cover 21, a main pylon 22, a plurality of drone storage parts 23 and a slow-down 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 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 compartment 100 and opened, the slow-down 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 portion release device is activated to open the multiple drone storage portions 23, and the bottom openings of the drone storage portions 23 are moved out of the main hanger 22 and face downward, and the drones 102 to be launched stored in the drone storage portions 23 fall down to complete the launch.

[0059] Multiple warhead cover connecting pins 3 are used to connect the warhead cover assembly 1 to the mother missile engine propulsion compartment 100. After the mother missile engine propulsion compartment 100 drives the drone delivery mechanism to the designated target point, the pneumatic de-pinning and de-shelling mechanism can be controlled to trigger the multiple warhead cover connecting pins 3 to retract and spray high-pressure gas into the warhead cover assembly 1 to separate the warhead cover assembly 1 from the mother missile engine propulsion compartment 100. This controllable pneumatic de-pinning and de-shelling mechanism can more accurately and stably separate the submunitions, thereby smoothly completing the subsequent drone delivery operation and improving the stability and safety of drone delivery.

[0060] After the warhead cover assembly 1 is separated from the mother missile engine propulsion compartment 100, the slow-descent and release mechanism of the drone-mounted core assembly 2 needs to be activated. Specifically, when the slow-descent and release mechanism is activated, multiple core cover connecting pins 25 are pulled back at the same time, and the core cover 21 is separated from the outside of the main pylon 22. At the same time, the slow-descent and release mechanism can make the main pylon 22 and multiple drone storage parts 23 be in a slow-descent posture. The slow-descent posture means that the bottom opening of the drone storage part 23 is facing downward. At this time, the storage part release device is activated to open the multiple drone storage parts 23. 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. 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] In embodiment 2, the pneumatic ejection mechanism includes a mounting plate 51, a high-pressure gas generator 52, a plurality of pneumatic ejection components and a pneumatic ejection component. The pneumatic ejection component includes 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 compartment 100. A high-pressure gas generating chamber 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 is 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 ejection components is respectively fixedly mounted on the mounting plate 51. On the side of the mounting plate 51, a 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 are respectively connected to the other end of the plurality of high-pressure gas conducting paths. 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. 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 release assemblies enter the high-pressure gas. Under the action of the high-pressure gas, the piston member 55 actuates to retract the plurality of bullet cover connecting pins 3, completing the pneumatic release operation.

[0063] The pneumatic shell ejection assembly includes a boss part 56 and a thrust plate 57. The boss part 56 is installed on the inner wall of the warhead cover assembly 1, and the thrust plate 57 is located on the boss part 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 part 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 de-pinning and de-shelling mechanism is the source of high-pressure gas, and 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 de-pinning and de-shelling process, the opening of the sealed container is opened by a solenoid valve, thereby providing high-pressure gas to multiple sets of pneumatic de-pinning components and pneumatic de-shelling components.

[0065] After the high-pressure gas enters the multiple air inlet holes 531 of the multiple sets of pneumatic release pin assemblies, the piston 55 will be pushed toward the cavity on the 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 compartment 100, and the conditions for separation are 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 is also the 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 continues to push 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 and 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 conducted to the outside of the piston cavity 53 of the multiple sets of pneumatic de-pinning components from multiple high-pressure gas conduction 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 is out of the air, and the air intake volume is much greater than the air outlet volume. A high pressure is formed in the air inlet cavity to push the piston member 55 toward the side of the spring 54. As the air is in the air, the piston 55 is pushed toward 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 one after another. At this time, the multiple sets of pneumatic release assemblies have completed the pneumatic release 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 release assemblies and then accumulates 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 achieving stable and reliable separation of the warhead cover assembly 1 and the mother missile engine propulsion compartment 100.

[0070] In Example 4, the pneumatic pin-and-shell removal mechanism further includes an elastic gasket 58. The outer ring of the mounting plate 51 is provided with a gasket boss. 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 connecting pin 3, the warhead cover assembly 1 is pushed backward under the action of the rebound force so that the warhead cover assembly 1 and the pin shaft hole of the mother missile engine propulsion compartment 100 are staggered, thereby avoiding the warhead cover connecting pin 3 from being inserted again and causing a separation failure.

[0073] In Example 6, the slow-descent release mechanism includes a parachute 241, a parachute connecting pin 242 and multiple slider connecting rod mechanisms 243. The parachute 241 is installed at the end of the main bracket 22. When opened under a control signal, the parachute 241 opens, and the multiple core cover connecting pins 25 are pulled back simultaneously through the parachute connecting pin 242 and multiple slider connecting rod mechanisms 243 to detach the core cover 21 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 drone-mounted core assembly 2 is in a slow-descent 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 cover connecting pins 25 at the same time to separate the core cover 21 from the outside of the main bracket 22, thereby realizing the autonomous detachment of the core cover 21.

[0075] Example 7, the storage part releasing device includes 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 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, and 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 drone 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 opening an umbrella. 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 only needs 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 the power-on standby state. The drone 102 to be launched can be mounted in the drone storage part 23 through an electric control buckle. After receiving the launch command, the electric control buckle opens and the drone 102 to be launched slides down.

[0078] Example 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, a member of the flight control intelligent body, can autonomously deploy batches of remote drones under predefined flight control programs and target parameters. It can also wirelessly communicate with distant ground forces, executing drone deployment actions based on ground-based commands. An aeronautical optoelectronic pod can also be installed at the end of the bullet-shaped drone cabin structure to provide the flight control unit with GPS positioning, attitude data, altitude data, and more.

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

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

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

[0083] The drone delivery operation 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. Under the action of the high-pressure gas, the pneumatic release assembly operates to retract the multiple warhead cover connecting pins 3 to complete the pneumatic release action.

[0085] Step 22: The pneumatic ejection assembly pushes 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. The parachute 241 simultaneously pulls back the multiple core cover connecting pins 25 through the parachute connecting pin 242 and multiple slider linkage mechanisms 243, so that the core cover 21 is separated from the main pylon 22.

[0087] Step 24: The flight control unit controls the storage portion release device including the electric lifting mechanism to operate. The slider of the electric lifting mechanism slides upward to drive the multiple opening paddles 252 to open the bottoms of the multiple drone storage portions 23 upward.

[0088] In step 25, the drone 102 to be launched slides down from the bottom of the drone storage portion 23, automatically powers on, unfolds its rotors and enters a flying attitude, completing the drone launching operation.

[0089] The above are all preferred embodiments of the present invention, and are not intended to limit the scope of protection 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 scope of protection of the present invention.

Claims

1. A drone delivery mechanism, characterized by: It comprises a bullet-type unmanned aerial vehicle cabin mechanism, a mother bomb 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 warhead 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, wherein one end of the warhead connecting cover assembly (1) is connected to the end of the mother warhead engine propulsion compartment (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 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 ejected toward the warhead connecting cover assembly (1) to separate the warhead connecting cover assembly (1) from the mother warhead engine propulsion compartment (100); The UAV mounted projectile core assembly (2) comprises a projectile core outer cover (21), a main hanger (22), a plurality of UAV storage parts (23) and a slow-down pin release mechanism, wherein the end of the projectile core outer cover (21) is connected to the other end of the warhead connection cover assembly (1) through a plurality of projectile core outer cover connecting pins (25), the projectile core outer cover (21) is sleeved on the outside of the hanger (22), the main hanger (22) is provided with a plurality of storage part mounting positions, and the plurality of UAV storage parts (23) surround the main hanger. (22) has multiple storage portion mounting positions, the drone storage portion (23) stores the drone (102) to be launched, the storage portion release device is installed on the main hanger (22), and the slow-down release mechanism is installed at the end of the main hanger (22). When the warhead connection cover assembly (1) is separated from the mother warhead engine propulsion compartment (100), the slow-down release mechanism is opened to pull back multiple core cover connection pins (25) at the same time, and the core cover (21) is separated from the outside of the main hanger (22); The storage portion release device is activated to open the plurality of drone storage portions (23), the bottom openings of the drone storage portions (23) are moved out of the main hanger (22) and face downward, and the drones (102) to be launched stored in the drone storage portions (23) fall down to complete the launch.

2. The UAV delivery mechanism according to claim 1, characterized in that: The pneumatic ejection mechanism comprises a mounting plate (51), a high-pressure gas generator (52), a plurality of pneumatic ejection components and a pneumatic ejection component, wherein the pneumatic ejection 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 compartment (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, and one side of the piston cavity (53) of the plurality of pneumatic ejection components is respectively fixedly mounted on the side of the mounting plate (51), so that 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 communicated with 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 de-pinning assemblies enter the high-pressure gas. The piston member (55) is actuated by the high-pressure gas to cause the plurality of bullet cover connecting pins (3) to retract, thereby completing the pneumatic de-pinning action. The pneumatic ejection assembly includes a boss member (56) and a reverse thrust plate (57), wherein the boss member (56) is mounted on the inner wall of the warhead connection cover assembly (1), and the reverse thrust plate (57) is located at the boss member (56). When high-pressure gas enters the multiple air inlet holes (531) of the piston chambers (53) of the multiple sets of pneumatic ejection assemblies, the piston member (55) compresses the spring (54), and the multiple air outlet holes (532) on the piston chamber (53) leak out. The high-pressure gas entering the piston chamber (53) is discharged from the multiple air outlet holes (532) and accumulates 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 connection cover assembly (1) away from the mother missile engine propulsion compartment (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 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.

4. The UAV delivery mechanism according to claim 3, characterized in that: The pneumatic ejection and shelling mechanism further comprises an elastic washer (58), an outer ring of the mounting plate (51) is provided with a washer boss, and the elastic washer (58) is clamped on the washer boss of the mounting plate (51). When the warhead connecting cover assembly (1) and the mother warhead engine propulsion compartment (100) are docked and mounted 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 2, 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 the main pylon (22). When the parachute (241) is opened under a control signal, the parachute (241) is opened, and the 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 separated from the outside of the main pylon (22).

7. The UAV delivery mechanism according to claim 6, characterized in that: The storage portion releasing device comprises an electric lifting mechanism and a plurality of spreading paddles (252), the tops of the plurality of drone storage portions (23) are respectively hinged at the storage portion mounting positions of the main pylon (22), the slider of the electric lifting mechanism is located on the main axis of the main pylon (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, and 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 portions (23) upward.

8. The UAV delivery mechanism according to claim 3, characterized in that: The drone storage portion (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 method for controlling a drone delivery mechanism, characterized in that: The method for controlling the drone delivery mechanism according to claim 7 comprises 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 altitude above the target coordinates; Step 2: The flight control unit starts the drone launch operation; The drone delivery 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. The pneumatic release assembly is activated by the high-pressure gas to retract the multiple warhead cover connecting pins (3) to complete the pneumatic release action. Step 22, the pneumatic ejection assembly moves to push the warhead connection 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 outside of the main pylon (22); Step 24, the flight control unit controls the storage portion 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 bottoms of the multiple drone storage portions (23) upward; In step 25, the drone (102) to be launched slides down from the bottom of the drone storage portion (23), automatically powers on, unfolds its rotors and enters a flying attitude, completing the drone launching action.

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