A firearm and aerial vehicle for an aerial unmanned combat platform

Abstract

The application discloses a kind of guns and aircraft for air unmanned combat platform, it is related to military equipment technical field, the structure of gun includes frame member, frame member includes at least one weapon system coupling device;Weapon system at least includes one shooting weapon, shooting weapon is arranged with the trigger mechanism component of control shooting weapon shooting;Control system is coupled with trigger mechanism component;Wherein, control component includes first lever, second lever and the first driving member of connecting first lever, first lever is distinguished from the position of connecting first driving member and connects trigger mechanism component, second lever is connected with first lever at a position, second lever is distinguished from the position of connecting first lever and connects second driving member, the reliability of the disclosed scheme in the application improves the firing mechanism of unmanned combat platform, to enhance its combat capability in complex battlefield environment.

Description

Technical Field

[0001] The present invention relates to the technical field of military equipment, and in particular to a firearm and an aircraft for an unmanned aerial combat platform. Background Art

[0002] As an intelligent weapon and equipment, unmanned combat platforms can not only assist combat personnel in performing tasks, but also independently penetrate deep into the battlefield to perform key military tasks such as reconnaissance.

[0003] In the current design of unmanned combat platforms, most systems choose to carry existing standard firearms as their firepower output units. In order to meet the shooting requirements of different firearms, these platforms are equipped with corresponding automatic firing mechanisms. The design of the automatic firing mechanism of current firearms is relatively simple, which increases the risk of failure of unmanned combat platforms during mission execution. Summary of the Invention

[0004] The purpose of the present invention is to overcome the shortcomings of the existing technology and provide a firearm and aircraft for an aerial unmanned combat platform. Compared with the existing technology, the solution disclosed in the present invention improves the reliability of the firing mechanism of the unmanned combat platform, thereby enhancing its combat capability in a complex battlefield environment.

[0005] The present invention is achieved through the following technical solutions: The present invention discloses a firearm for an unmanned aerial combat platform, comprising:

[0006] a frame member comprising at least one weapon system coupling;

[0007] A weapon system, the weapon system includes at least one shooting weapon, and the shooting weapon is provided with a trigger component for controlling the shooting of the shooting weapon;

[0008] Control system, control system connecting trigger components;

[0009] Among them, the control component includes a first rod, a second rod and a first driving component connected to the first rod, the first rod is connected to the trigger component at a position different from the position connected to the first driving component, the second rod is connected to the first rod at a position different from the position connected to the first rod.

[0010] Preferably, the shooting weapon includes a firing port, the firing port is located on one side of the frame member, and a connecting member is arranged on the side of the frame member facing away from the firing port;

[0011] Among them, the firearm is connected to the aerial unmanned combat platform through a connecting component.

[0012] This application document also discloses an aircraft, which includes:

[0013] A mother unmanned aerial vehicle mechanism, wherein the mother unmanned aerial vehicle mechanism is provided with a connection system;

[0014] The sub-UAV is mounted on the mother UAV through a connection system, and the firearm is mounted on the sub-UAV;

[0015] Cannonballs, which are mounted on the unmanned aerial vehicle;

[0016] Among them, the payload of the mother unmanned aerial vehicle is greater than the payload of the child unmanned aerial vehicle.

[0017] Preferably, the mother unmanned aerial vehicle mechanism includes:

[0018] A fuselage, wherein the fuselage is provided with a cavity, and a control system is arranged inside the cavity of the fuselage;

[0019] The wing, one end of which is connected to the side wall of the fuselage, which is the longitudinal area of ​​the fuselage;

[0020] Power system: a power system is arranged at a position of the wing away from the fuselage;

[0021] Among them, the sub-unmanned aerial mechanism includes a second power system, and a second space is arranged on the side of the mother unmanned aerial mechanism close to the second power system. When the mother unmanned aerial mechanism is mounted on the sub-unmanned aerial mechanism, the second power system is aligned with the second space.

[0022] Preferably, the sub-unmanned aerial vehicle mechanism includes:

[0023] The second fuselage is loaded with firearms;

[0024] a second wing, one end of the second wing being connected to a second fuselage sidewall, the second fuselage sidewall being a longitudinal region of the second fuselage;

[0025] The second power system is arranged at a position of the second wing different from the second fuselage;

[0026] When the mother unmanned aerial vehicle is mounted on the child unmanned aerial vehicle, the second power system is close to the mother unmanned aerial vehicle.

[0027] Alternatively, the structure of the second wing includes a first support member and a second support member rotatably connected to the first support member, and a second power system is arranged at the position of the second support member, and a driving device is arranged to drive the second support member to flip relative to the position of the first support member.

[0028] Preferably, a protective component is connected to the second fuselage side wall corresponding to the position of the second wing, and the protective component is arranged directly below the second wing;

[0029] The protection member is arranged with a receiving cavity, when the second support member is driven to overturn by the driving device, the second power system is received in the receiving cavity.

[0030] Preferably, the second driving device is arranged to connect the protection member, and the second driving device drives the protection member to rotate along the expected track.

[0031] When the second driving state is started, the angle between the protection member and the second fuselage changes.

[0032] Preferably, the protection member comprises:

[0033] The first protection plate;

[0034] The second protection plate, one end of the first protection plate is connected with the second protection plate;

[0035] The bent protection plate, one end of the bent member is connected with the second protection plate;

[0036] Wherein, the second protection plate is arranged corresponding to the position of the second wing, and the second protection plate is provided with an opening;

[0037] Or, the outer periphery of the bent protection plate is arranged with a protection layer;

[0038] Or, the second protection plate is a light-transmitting material;

[0039] Or, the bent protection plate comprises a first plate arranged in a straight line and a second plate arranged in a circular arc, and one end of the second plate is connected with the first plate;

[0040] Or, the protection member is arranged with two second protection plates, and the two second protection plates are symmetrically distributed along the center line of the second fuselage.

[0041] Preferably, the connecting system comprises:

[0042] The first cavity is arranged in the fuselage, and the first cavity is arranged with an opening near one side of the sub-unmanned aerial vehicle;

[0043] The magnetic adsorption mechanism is arranged at the top of the first cavity;

[0044] The limiting member is arranged on the inner wall of the first cavity, and the limiting member is arranged spaced apart from the top of the first cavity;

[0045] The top of the sub-unmanned aerial vehicle mechanism is provided with a limiting device, the limiting device comprises a first column body made of magnetic metal and a second column body connected with the first column body, the end surface size of the first column body is larger than the end surface size of the second column body, the limiting member can be switched between a first state and a second state, in the first state, the first column body cannot pass through the limiting member, the second column body can pass through the limiting member, in the second state, the first column body can pass through the limiting member, and the second column body can also pass through the limiting member.

[0046] Preferably, the limiting member can be moved in the first direction parallel to the top of the first cavity;

[0047] The limiting member comprises a limiting block, a groove is formed in the surface of the limiting block, an elastic member is accommodated in the groove, and a buffer is movably connected with the groove in the longitudinal direction of the groove, wherein one end of the buffer is in contact with the elastic member.

[0048] The application discloses a kind of for aerial unmanned combat platform's gun and aircraft, compared with prior art:

[0049] The first driving member and the second driving member in the present application can drive the trigger mechanism to shoot by controlling the trigger mechanism, when one driving member is abnormal, the other driving member can be controlled to drive the trigger mechanism to displace, for the control system of the driving member, communication between the remote control center and the target driving member depends on stable and high-speed communication network, such as satellite communication or special wireless communication network, the control system further includes local control module, the local control module on the aircraft is responsible for receiving control instructions from the remote control center, and converts these instructions into information suitable for the first driving member and the second driving member to execute. BRIEF DESCRIPTION OF DRAWINGS

[0050] Figure 1 It is a structural schematic view of the gun in an embodiment;

[0051] Figure 2 It is Figure 1 It is a local enlarged schematic view at position a;

[0052] Figure 3 It is a structural schematic view of the aircraft in an embodiment;

[0053] Figure 4 It is a combat flow schematic view of the aircraft in an embodiment;

[0054] Figure 5 It is a structural schematic view of the mother unmanned aerial vehicle mechanism in an embodiment;

[0055] Figure 6 It is a structural schematic view of the sub-unmanned aerial vehicle mechanism in an embodiment;

[0056] Figure 7 A schematic structural diagram of a neutron unmanned flying mechanism in another embodiment;

[0057] Figure 8 This is a schematic structural diagram of a protective component in one embodiment;

[0058] Figure 9 Schematic diagram of the state change of the limiting device in one embodiment;

[0059] Figure 10 Schematic diagram of the structure of a limiting component in another embodiment. DETAILED DESCRIPTION

[0060] The following description, with reference to the accompanying drawings, is provided to facilitate a comprehensive understanding of various exemplary embodiments of the present disclosure as defined in the claims and their equivalents. The description includes numerous details to aid understanding, but these details are to be considered merely exemplary. Accordingly, those skilled in the art will recognize that various changes and modifications may be made to the various embodiments described herein without departing from the scope and spirit of the present disclosure. Furthermore, descriptions of well-known functions and structures may be omitted for clarity and brevity.

[0061] It will be understood that when an element or layer is referred to as being “on,” “connected to,” or “coupled to” another element or layer, it can be directly on, directly connected to, or coupled to the other element or layer, or one or more intervening elements or layers may also be present. When an element is referred to as being “directly on,” “directly connected to,” or “directly coupled to” another element or layer, there are no intervening elements or layers present.

[0062] It will be understood that although the terms first, second, third, etc. may be used in this article to describe various elements, components, regions, layers and / or sections, these elements, components, regions, layers and / or sections should not be limited to these terms. These terms are used to distinguish an element, component, region, layer or section from another element, component, region, layer or section. Therefore, without departing from the teachings of the exemplary embodiments, the first element, first component, first region, first layer or first section discussed below may be referred to as the second element, second component, second region, second layer or second section. In the accompanying drawings, for clarity of illustration, the sizes of various elements, layers, etc. may be exaggerated.

[0063] Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

[0064] The aircraft in this application document is an unmanned aerial vehicle (UAV), which refers to any autonomous or semi-autonomous vehicle that can perform certain functions without the actual presence of a human pilot. Except as specifically limited in some embodiments, the aircraft can take various forms. For example, the aircraft can take the form of a fixed-wing aircraft, a glider, a tail-seat aircraft, a jet aircraft, a ducted fan aircraft, a lighter-than-air airship (such as a blimp or a steerable balloon), a rotorcraft (such as a helicopter or a multirotor aircraft) and / or an ornithopter.

[0065] The shooting weapon in this application document is an autonomous or semi-autonomous shooting device that is capable of performing shooting and related functions without direct human operation. Firearms can take various forms and structures. For example, a firearm can be a pistol, rifle, machine gun, shotgun, laser gun or any other type of shooting weapon that can use gunpowder, gas, electromagnetic force or other energy to fire bullets, shells, darts or other projectiles. In addition to the common types mentioned above, firearms may also include various variants with special designs and functions to meet different tactical needs. These firearms can be equipped with silencers, tactical lights or other accessories to enhance their shooting concealment and versatility, and the application document does not make specific restrictions.

[0066] Please refer to Figure 1 and Figure 2 , Figure 1 A firearm 22 for an unmanned aerial combat platform in one embodiment is shown. Figure 2 for Figure 1 The structure of the enlarged schematic diagram of the part at position a includes a frame member 221, a weapon system 222 and a control system 223.

[0067] The frame member 221 includes at least one weapon system 222 coupling device;

[0068] The weapon system includes at least one shooting weapon, on which a trigger component for controlling the firing of the shooting weapon is arranged;

[0069] Control system 223 Control system 223 connects trigger components;

[0070] Among them, the control component 223 includes a first rod 2231, a second rod 2233 and a first driving component 2232 connected to the first rod 2231, the first rod 2231 is connected to the trigger component at a position different from the position where it is connected to the first driving component 2232, the second rod 2233 is connected to the first rod 2231 at a position, and the second rod 2233 is connected to the second driving component 2234 at a position different from the position where it is connected to the first rod 2231.

[0071] As shown in the content, the frame member 221 is the basic structure of the firearm 22, which provides the overall support of the firearm 22. The coupling device is a key component connecting the frame member 221 and the weapon system 222. The weapon system 222 may include one or more shooting weapons. Figure 1 In the embodiment, two firing weapons are mounted on a frame member 221. In this application document, a weapon system 222 can be mounted via a coupling device. Specifically, the coupling device structure can be a track-type connection structure, with one or more standardized tracks provided on the frame member, and the weapon system mounted on the tracks via an adapter. The aforementioned track-type connection structure provides a high degree of flexibility, and different weapon systems can be compatible with the same track by replacing the adapter. It is worth noting that the coupling device structure described in the application document is not unique; the weapon system 222 can also be mounted and dismounted using a locking structure, a fastener structure, an electromagnet attraction, and other structures, which will not be described here one by one.

[0072] The weapon system 222, as the attack core of the firearm 22, includes at least one firing weapon. The firing weapon may be a machine gun, artillery, or other type of firing device, depending on the actual application scenario and combat requirements. In order to control the firing of the firing weapon, a trigger component is also arranged on the weapon system. This trigger component is similar to the trigger of a traditional firearm. By pulling the trigger component, the firing device can be fired. Figure 1 , Figure 1 The shooting weapon in the film is the Uzi submachine gun.

[0073] Please continue to refer to Figure 2 The control system 223 receives external commands and controls the shooting of the weapon system 222 according to these commands. The control system includes a first rod 2231, a second rod 2233, a first driving member 2232 connected to the first rod, and a second driving member 2234 connected to the second rod.

[0074] Connection between the first rod 2231 and the trigger member: One end of the first rod is connected to the first driving member 2232, while the other end is connected to the trigger member at a position different from that where it is connected to the first driving member. When the first driving member 2232 is actuated, it drives the first rod 2231 to move, thereby controlling the firing of the shooting weapon through the trigger member.

[0075] One end of the second rod member 2233 is connected to the first rod member 2231, and the other end is connected to the second driving member 2234 at a position different from the position where the first rod member is connected, and the second driving member 2234 can apply force or displacement to the first rod member 2231 through the second rod member 2233, and in this application, both the first driving member 2232 and the second driving member 2234 can drive the trigger mechanism to shoot the weapon, and when one driving member is abnormal, the other driving member can be controlled to drive the trigger mechanism to displace, and for the control system of the driving member, the communication between the remote control center and the target driving member depends on a stable and high-speed communication network, such as satellite communication or a special wireless communication network, and the control system also includes a local control module, which is responsible for receiving control instructions from the remote control center and converting these instructions into signals suitable for the first driving member 2232 and the second driving member 2234 to execute.

[0076] Please continue to refer to Figure 1 In an embodiment, the weapon includes a firing port, and the firing port is located on one side of the frame member 221, and the side of the frame member 221 opposite to the firing port is provided with a connecting member 224.

[0077] Wherein the gun 22 is connected to the aerial unmanned combat platform through the connecting member 224.

[0078] For the embodiment, the ammunition or other substances with killing effect is shot out of the gun through the firing port, and in addition to the firing port, the other side of the frame member 221 (opposite to the side of the firing port) is also provided with a connecting member 224, which is responsible for stably installing the gun on the combat platform, and in actual application, when the gun 22 needs to be installed on the combat platform, it can be fixed on the platform through the connecting member 224, and in a possible implementation, the connecting member 224 includes a main frame composed of two housings that can move relative to each other, a damping cavity is formed between the two housings, and a damping spring and a damper are arranged in the damping cavity, so that the damping cavity can absorb and disperse the recoil force when the gun shoots, reducing the impact on the unmanned combat platform, and at the same time, the damping system also helps to reduce the shaking of the gun caused by external disturbance during flight, improving the shooting stability, and in order to ensure the rigidity and stability of the connecting member, reinforcing support plates are added at key positions (such as corner positions) of the main frame, and standardized connecting interfaces are designed at both ends of the main frame, one end is connected to the frame member 221 of the gun 22, and the other end is connected to the mounting system of the aerial unmanned combat platform through an adapter, and for the housings, they can be prismatic structures to increase structural stability and disperse stress points.

[0079] Please refer to Figure 3In one embodiment of the present application, an aircraft is disclosed, a firearm 22 is mounted on the aircraft, and the aircraft includes:

[0080] The mother unmanned aerial vehicle 1 is provided with a connection system;

[0081] The sub-unmanned aerial vehicle 2 is mounted on the main unmanned aerial vehicle 2 via a connection system, and the firearm 22 is mounted on the sub-unmanned aerial vehicle 2;

[0082] Cannonball 3, the cannonball is mounted on the sub-unmanned aerial vehicle 2;

[0083] Among them, the payload of the mother unmanned aerial vehicle 1 is greater than the payload of the child unmanned aerial vehicle 2.

[0084] In this embodiment, the aircraft is a modular UAV system consisting of a mother UAV 1 and a daughter UAV 2. The mother UAV 1 is the main component of the system, boasting a large size and a strong payload capacity, and is used to mount and transport the daughter UAV 2. The daughter UAV 2 is a small, flexible aircraft, mounted below the mother UAV 1 via a connection system, and equipped with weapon systems such as firearms 22 and projectiles 3.

[0085] Furthermore, the mother UAV 1 is the carrier part of the entire aircraft system, responsible for mounting, transporting and deploying the daughter UAV 2. It has a large payload capacity and can carry more fuel (batteries), equipment and other necessities, and has a strong endurance. The mother UAV 1 also has high flight performance and navigation capabilities, and can fly in various harsh environmental conditions. The mother UAV is also equipped with a higher-precision navigation system and sensors than the daughter UAV 2, which can obtain flight status and environmental information in real time, and accurately plan and adjust the flight trajectory according to mission requirements;

[0086] The sub-unmanned aerial vehicle 2 is a small, flexible aircraft, which is normally mounted below the mother unmanned aerial vehicle 1 through its connection system. The main weapon systems of the sub-unmanned aerial vehicle 2 are firearms 22 and artillery shells 3. Relying on the mother unmanned aerial vehicle 1, it can accurately strike targets on the ground or in the air. The sub-unmanned aerial vehicle 2 also has the ability to fly and fight independently and can perform tasks independently. Among them, the firearms 22 are mounted in front of the sub-unmanned aerial vehicle and can be fired by remote control. It can accurately strike targets from a safe distance, thereby reducing combat risks. The artillery shells 3 are mounted on the bottom or internal bomb bay of the sub-unmanned aerial vehicle and can be flexibly deployed according to mission requirements to provide fire coverage or precise strikes on ground targets. The type and quantity of artillery shells 3 can be selected according to actual needs to meet different combat requirements.

[0087] Please refer to Figure 4 , the aircraft's operation includes the following steps:

[0088] S100: Deployment phase: The mother UAV takes off with the child UAV and moves to the designated combat area.

[0089] S200: Fire strike phase: After arriving at the combat area, the sub-unmanned aerial vehicle releases shells according to the combat plan and launches fire strikes on ground targets.

[0090] S300: Combat Assessment and Adjustment: During the fire strike, the mother UAV and the child UAV maintain real-time communication and feed back battlefield information to the commander.

[0091] S400: Endurance and Evacuation: After completing the fire strike mission, make endurance or evacuation decisions based on the actual battlefield information.

[0092] Specifically, during combat, the mother UAV 1 first mounts the child UAV 2, takes off, and moves toward the designated combat zone. During this process, the mother UAV 1 is responsible for tasks such as navigation, flight control, and communications, while the child UAV 2 remains on standby. Upon arrival at the combat zone, the child UAV 2 deploys projectiles 3 according to the combat plan to launch a fire attack on ground targets. Simultaneously, the firearm 22 remains on standby, ready to fire accurately at unexpected targets. This flexible weapon configuration allows the child UAV to quickly adapt to battlefield changes and execute a variety of complex missions.

[0093] After completing the fire strike mission, a decision is made to continue the flight or evacuate based on the actual situation. If continued combat or other missions are required, the mother UAV 1 can separate from the daughter UAV 2 and return to base for resupply and maintenance. The daughter UAV 2 can remain on the battlefield and continue the combat mission. This split design enhances the overall system's endurance and battlefield adaptability.

[0094] When the mission is complete or the battlefield situation becomes unfavorable and evacuation is necessary, the mother UAV 1 can carry the child UAV 2 to evacuate the battlefield together. This coordinated evacuation method not only speeds up the evacuation but also reduces risks. Furthermore, during the evacuation process, the mother UAV 1 can leverage its high-precision counter-reconnaissance, high-precision navigation, and high maneuverability to provide the necessary protection and support for the child UAV 2, ensuring its safe evacuation.

[0095] Step S400: Endurance and evacuation: After completing the fire strike mission, the decision on whether to continue or evacuate is made based on the actual battlefield information. The battlefield information includes the following information:

[0096] A: Mission execution status: Commanders will evaluate whether the sub-UAV organization has completed the fire strike mission as planned, or whether the strike strategy needs to be adjusted.

[0097] B: Enemy response: By analyzing the enemy's firepower distribution and movement trajectory, commanders can determine whether the enemy has discovered the existence of the sub-UAV and whether they are organizing a counterattack.

[0098] C: Changes in battlefield environment: Changes in natural factors such as weather and terrain. For example, a sudden storm may cause the UAV to lose its stable flight, or a change in terrain may provide new cover for the enemy.

[0099] D: Resource Consumption: This shows the consumption of fuel, ammunition, and other resources by the parent and child UAVs. If resources are depleted too quickly, consider evacuating or resupplying in advance.

[0100] When a child UAV needs to perform a mission independently, and the presence of the mother UAV may expose the child UAV or limit its mobility, separation of the parent and child can be considered. When the child UAV needs to perform reconnaissance or strike missions in a certain area for a long time, and the mother UAV needs to return to base for resupply or perform other tasks, separation of the parent and child can also be considered. When the commander confirms that the child UAV has completed all fire strike missions as planned and there are no new targets to strike, withdrawal can be considered. If the battlefield situation has changed fundamentally and it may no longer make sense to stay on the battlefield, or if withdrawal can avoid unnecessary risks and losses, withdrawal can also be considered. When enemy firepower suddenly increases, threatening the safety of the mother or child UAV, withdrawal needs to be considered immediately. If the battlefield environment changes in a way that is unfavorable to our operations, such as weather deterioration or terrain changes, withdrawal may also be necessary. When the key systems of the mother or child UAV fail and cannot continue to perform the mission or ensure safe flight, withdrawal is also a necessary option.

[0101] Please refer to Figure 5 In one embodiment, the structure of the mother unmanned aerial vehicle mechanism 1 includes:

[0102] A fuselage 11 is provided with a cavity, and a control system is arranged inside the cavity of the fuselage 11;

[0103] a wing 12, one end of the wing 12 being connected to a side wall of the fuselage 11, the side wall of the fuselage 11 being a longitudinal region of the fuselage 11;

[0104] A power system 13 is arranged at a position of the wing 12 away from the fuselage 11;

[0105] The sub-unmanned aerial vehicle 2 comprises a second power system 233, and the second space is arranged on the side of the second power system 233 of the mother unmanned aerial vehicle 1. When the mother unmanned aerial vehicle 1 is hung on the sub-unmanned aerial vehicle 2, the second power system 233 is arranged in alignment with the second space.

[0106] With reference to the foregoing Figure 5 , Figure 5 The second space is at the A position in the embodiment, and the second power system 233 in the embodiment is composed of a motor, a fan blade, an electronic speed controller and the like. The conventional hanging mode may cause the wing or other part of the mother unmanned aerial vehicle 1 to be in contact with the power system of the sub-unmanned aerial vehicle 2, thereby affecting the flight performance of the sub-unmanned aerial vehicle, and even causing a safety accident. In order to avoid this situation, the second space is reserved on the side of the mother unmanned aerial vehicle close to the power system of the sub-unmanned aerial vehicle in the embodiment. In order to ensure the stability and safety of the mother unmanned aerial vehicle 1 and the sub-unmanned aerial vehicle 2 in flight and avoid structural conflicts or interference, the second space can accommodate the second power system 233 of the sub-unmanned aerial vehicle, so as to ensure that the two do not conflict in structure. In addition, the second space can also serve as an air flow channel to optimize the air flow distribution of the mother unmanned aerial vehicle and the sub-unmanned aerial vehicle in flight. This helps to reduce air resistance and improve flight efficiency.

[0107] Please continue to refer to Figure 3 In an embodiment, the sub-unmanned aerial vehicle 2 comprises:

[0108] The second fuselage 21 is loaded with a gun 22;

[0109] The second wing 23 is connected to the side wall of the second fuselage 21 at one end, and the side wall of the second fuselage 21 is a longitudinal area of the second fuselage 21;

[0110] The second power system 233 is arranged at a position of the second wing 23 away from the second fuselage 21;

[0111] When the mother unmanned aerial vehicle 1 is hung on the sub-unmanned aerial vehicle 2, the second power system 233 is close to the side of the mother unmanned aerial vehicle 1, and the second space can accommodate the second power system 233 of the sub-unmanned aerial vehicle, thereby improving safety.

[0112] Please refer to Figure 6In another embodiment, the structure of the second wing 23 includes a first support member 231 and a second support member 232 rotatably connected to the first support member 231. A second power system 233 is arranged at the position of the second support member 232, and a driving device is arranged to drive the second support member 232 to flip relative to the position of the first support member 231; the angle of the second power system 233 can be adjusted, which further effectively avoids structural and spatial conflicts between the sub-unmanned aerial mechanism and the mother unmanned aerial mechanism. When the mother unmanned aerial mechanism mounts the sub-unmanned aerial mechanism, the second power system 233 faces the side away from the mother unmanned aerial mechanism, thereby avoiding collision with the mother unmanned aerial mechanism. When the sub-unmanned aerial mechanism 2 needs to fly independently to perform a mission, the driving device drives the flipping of the second support member 232, so that the second power system faces the side of the mother unmanned aerial mechanism, ensuring that the sub-unmanned aerial mechanism 2 can fly normally.

[0113] For further reference, Figure 6 A protective member 24 is connected to the side wall of the second fuselage 21 and the position of the second wing 23 leg, and the protective member 24 is arranged directly below the second wing 23;

[0114] The protective component 24 is arranged with a storage cavity. When the driving device drives the second support member 232 to flip, so that the second power system 233 is away from the mother unmanned aerial mechanism 1, the second power system 233 is stored in the storage cavity. The protective component 24 provides a safe storage space for the second power system 233, ensuring that the sub-unmanned aerial mechanism is performing its mission. When the aircraft is performing its mission, if the mother unmanned aerial mechanism is mounted with the sub-unmanned aerial mechanism, the second power system 233 faces the side away from the mother unmanned aerial mechanism to avoid collision with the mother unmanned aerial mechanism. At this time, the second power system 233 is stored in the storage cavity, and the protective component 24 provides better protection for the second power system to prevent foreign objects (shells, birds) from hitting the second power system during the flight of the aircraft, causing direct damage to it. The second protective component can be made of bulletproof material, specifically a ceramic composite material composed of ceramic particles and a polymer matrix. Even if the aircraft encounters artillery attack or high-speed flying birds during flight, the bulletproof material protective component 24 can provide sufficient protection for the second power system 233 to ensure its safety and integrity.

[0115] Please refer to Figure 7 In another embodiment, a second driving device is arranged to be coupled to the guard member 24, and the second driving device drives the guard member 24 to rotate along an expected trajectory, which is a predetermined path or movement route followed by the guard member 24 when performing its movement function;

[0116] When the second driving state 24 is activated, the angle between the protective member 24 and the second body 21 changes;

[0117] Figure 7 The protective member 24 is shown in the deployed state in this embodiment. In this embodiment, the protective member 24 is a rotatable structure. One end is connected to the side wall of the second body 21, while the other end can rotate along a desired trajectory driven by a second driving device. The protective member 24 can flexibly switch between the stowed and deployed states.

[0118] When the mother and child UAVs are not separated, they are in the stowed state. In this stowed state, the protective member 24 is closely attached to the side wall of the second fuselage 21, corresponding to the position directly below the second wing 23. In this state, its main function is to protect the second power system 233 from interference and damage from the external environment.

[0119] When landing is required, the second drive element is activated, driving the protective member 24 to rotate along the desired trajectory. During this process, the angle between the protective member 24 and the second fuselage 21 changes, gradually deploying it from its stowed position to its landing gear position. In the landing gear position, the ends of the protective member 24 deploy and lock into place, supporting the weight of the sub-UAV and providing necessary stability.

[0120] Please refer to Figure 8 Furthermore, the protective member 24 includes a first protective plate 241; a second protective plate 242, one end of the first protective plate 242 is connected to the second protective plate 242; a bent protective plate 243, one end of the bent member 243 is connected to the other end of the second protective plate 243, and the design of the bent member 243 allows the sub-unmanned aerial mechanism 2 to contact the ground when it needs to land, thereby providing better support.

[0121] The second protective plate 242 is arranged corresponding to the position of the second wing 23. A notch is provided on the surface of the second protective plate 242. The notch design not only reduces the overall weight but also facilitates the rotation of the second wing 23, thereby preventing the second power system from colliding with the protective member 24.

[0122] Alternatively, the side of the bending protection plate 243 away from the second wing 23 is the outer periphery, and a protective layer is arranged on the outer periphery of the bending protection plate 243. The protective layer is made of a flexible material with a Mohs hardness of 6.5 to 7. The bending protection plate 243 contacts the ground when the sub-unmanned aerial vehicle 2 needs to land, and has good wear resistance.

[0123] Alternatively, the second protective plate 242 is made of a light-transmitting material, so that the state of the second power system can be observed through the second protective plate 242 to determine whether it needs maintenance;

[0124] Alternatively, the bending protection plate 243 includes a first plate member arranged in a straight line and a second plate member arranged in an arc shape, and the second plate member is connected to one end of the first plate member. This combination design not only ensures the stability of the structure but also provides more buffer space;

[0125] Alternatively, two protective members 24 are arranged, and the two second protective plates 243 are symmetrically distributed along the center line of the second fuselage 21 .

[0126] See also Figure 9 In another embodiment, the connection system includes:

[0127] The first cavity 111 is opened in the fuselage 11 and is arranged near the opening of the sub-unmanned aerial vehicle mechanism 2;

[0128] A magnetic adsorption mechanism 112 is arranged on the top of the first cavity 111;

[0129] A limiting member 113 is located on the inner wall of the first cavity 11 and is spaced apart from the top of the first cavity 111 ;

[0130] Among them, a limit device is arranged on the top of the sub-unmanned aerial mechanism 2. Figure 7 The middle C position is a limiting device, which includes a first column made of magnetic metal and a second column connected to the first column. The end face size of the first column is larger than the end face size of the second column. The limiting member 113 can switch between a first state and a second state. In the first state, the first column cannot pass through the limiting member 113, and the second column can pass through the limiting member. In the second state, the first column can pass through the limiting member 113, and the second column can also pass through the limiting member.

[0131] for Figure 9 An embodiment of Figure 5 The area selected at position B corresponds to Figure 9 Schematic diagram of the transition between different states. When the sub-UAV needs to be flipped, magnetic attraction mechanism 112 first stops adsorbing the stopper. Then, due to the gravity of the sub-UAV, the stopper falls to the position of stop member 113. During this process, the gap between the first and second wings gradually increases, providing the necessary space for the sub-UAV to flip.

[0132] As the stopper falls and the gap increases, the daughter UAV begins to rotate from the side facing away from the mother UAV to the side facing the mother UAV. During this process, the daughter UAV needs to overcome the effects of gravity and air resistance to ensure a smooth and accurate flip.

[0133] After the sub-UAV completes its flip, the position-limiting member 113 switches to its second state. In this state, both the first and second columns can pass through the position-limiting member 113. Therefore, the sub-UAV can smoothly pass through the position-limiting member 113 and separate from the main UAV. During the separation process, the magnetic attraction mechanism 112 no longer exerts an attraction force on the position-limiting member, ensuring a thorough and safe separation.

[0134] The specific steps are as follows:

[0135] In the initial state, if Figure 9 As shown in S001, the sub-UAV and the main UAV are tightly connected via a connection system. The magnetic adsorption mechanism 112 adsorbs and fixes the limiter on the top of the sub-UAV, ensuring a stable connection between the two. At this time, the limiter 113 is in the first state, preventing the limiter from passing through.

[0136] When the sub-unmanned aerial vehicle mechanism needs to be turned over, the magnetic adsorption mechanism 112 is first controlled to stop adsorbing the limiting component, so that the sub-unmanned aerial vehicle mechanism can start to fall under the action of gravity.

[0137] Due to the gravity of the unmanned aerial vehicle mechanism, such as Figure 9 As shown in step S002 , the position limiting device begins to fall to the position of the position limiting member 113 . During the falling process, the position limiting device gradually approaches the position limiting member 113 .

[0138] As the limiting device falls and the wing gap increases, the sub-unmanned aerial mechanism begins to rotate from the side facing away from the mother unmanned aerial mechanism to the side close to the mother unmanned aerial mechanism.

[0139] When the sub-unmanned aerial vehicle mechanism completes the flip, Figure 9 As shown in S003, the control position limiting member 113 is switched to the second state. In this state, the position limiting member 113 allows the position limiting device to pass through. This step separates the mother UAV from the daughter UAV and provides a passage for the position limiting device to pass through the first cavity. In S003, the position limiting member 13 is retracted until it no longer occupies the space in the first cavity.

[0140] After the limiting member 113 switches state, the limiting device passes through the first cavity smoothly. With the passing of the limiting device, the connection between the sub-UAV and the main UAV is completely released, and the sub-UAV can perform related tasks independently.

[0141] See also Figure 10 , further, the limiting member 113 can be moved along the first direction to a position parallel to the top of the first cavity 111;

[0142] The limiting member 113 includes a limiting block 1131, a groove is provided on the surface of the limiting block 1131, an elastic member is accommodated inside the groove, and a buffer member 1132 is arranged to be movably connected to the groove along the longitudinal direction of the groove, wherein one end of the buffer member 1132 contacts the elastic member, and the force generated when the limiting device starts to fall to the position of the limiting member 113 can be buffered by the limiting member 113.

[0143] To sum up, in this application document, the first drive component 2232 and the second drive component 2234 can both control the trigger component to make the shooting weapon fire. When one drive component is in an abnormal state, the trigger component can be driven to move by controlling the other drive component. For the control system of the drive component, the communication between the remote control center and the target drive component depends on a stable, high-speed communication network, such as satellite communication or a dedicated wireless communication network. The control system also includes a local control module. The local control module located on the aircraft is responsible for receiving control instructions from the remote control center and converting these instructions into signals suitable for execution by the first drive component 2232 and the second drive component 2234.

[0144] The above are only preferred specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with this technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solutions and inventive concepts of the present invention, should be covered by the scope of protection of the present invention.

[0145] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply the existence of any such actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article, or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or elements inherent to such process, method, article, or device. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not exclude the presence of other identical elements in the process, method, article, or device comprising the element.

Claims

1. An aircraft, characterized in that: include: A mother unmanned aerial vehicle (1), wherein the mother unmanned aerial vehicle (1) is provided with a connection system; A sub-unmanned aerial mechanism (2), the sub-unmanned aerial mechanism (2) being mounted on the mother unmanned aerial mechanism (1) via a connection system, and the firearm (22) being mounted on the sub-unmanned aerial mechanism (2); a cannonball (3), the cannonball being mounted on the sub-unmanned flying mechanism (2); Wherein, the effective load of the mother unmanned aerial vehicle (1) is greater than the effective load of the child unmanned aerial vehicle (2); The sub-unmanned aerial mechanism (2) comprises a second fuselage (21) and a second wing (23); the structure of the second wing (23) comprises a first support member (231) and a second support member (232) rotatably connected to the first support member (231); a second power system (233) is arranged at the position of the second support member (232), and a driving device is arranged to drive the second support member (232) to flip relative to the position of the first support member (231); A protective component (24) is connected to the side wall of the second fuselage (21) at a position corresponding to the position of the leg of the second wing (23), and the protective component (24) is arranged directly below the second wing (23); The protective member (24) is provided with a storage cavity, and when the driving device drives the second supporting member (232) to flip, causing the second power system (233) to deviate from the state of the mother unmanned aerial mechanism (1), the second power system (233) is stored in the storage cavity.

2. An aircraft according to claim 1, characterized in that: The mother unmanned aerial vehicle mechanism (1) comprises: A fuselage (11), wherein the fuselage (11) is provided with a cavity, and a control system is arranged inside the cavity of the fuselage (11); A wing (12), one end of the wing (12) is connected to a side wall of the fuselage (11), and the side wall of the fuselage (11) is a longitudinal region of the fuselage (11); A power system (13), wherein the wing (12) is provided with a power system (13) at a position away from the fuselage (11); The sub-unmanned aerial mechanism (2) includes a second power system (233), and a second space is arranged on a side of the mother unmanned aerial mechanism (1) close to the second power system (233). When the mother unmanned aerial mechanism (1) is mounted on the sub-unmanned aerial mechanism (2), the second power system (233) is aligned with the second space.

3. An aircraft according to claim 1, characterized in that: The sub-unmanned aerial vehicle mechanism (2) comprises: a second body (21), wherein the second body (21) is loaded with a firearm (22); a second wing (23), one end of the second wing (23) being connected to a side wall of the second fuselage (21), the side wall of the second fuselage (21) being a longitudinal region of the second fuselage (21); The second power system (233) is arranged at a position of the second wing (23) that is different from the second fuselage (21); When the mother unmanned aerial vehicle (1) is mounted on the child unmanned aerial vehicle (2), the second power system (233) is close to one side of the mother unmanned aerial vehicle (1).

4. An aircraft according to claim 1, characterized in that: A second driving device is arranged to be coupled to the protection member (24), and the second driving device drives the protection member (24) to rotate along a desired trajectory; When the second driving (24) state is activated, the angle between the protective member (24) and the second body (21) changes.

5. An aircraft according to claim 4, characterized in that: The protective component (24) comprises: a first protective plate (241); A second protective plate (242), one end of the first protective plate (242) being connected to the second protective plate (242); A bending protection plate (243), one end of the bending member (243) being connected to the other end of the second protection plate (243); The second protective plate (242) is arranged corresponding to the position of the second wing (23), and a notch is provided on the surface of the second protective plate (242); Alternatively, the side of the bending protection plate (243) away from the second wing (23) is the periphery, and a protective layer is arranged on the periphery of the bending protection plate (243), and the protective layer is made of a flexible material and has a Mohs hardness of 6.5 to 7; Alternatively, the second protective plate (242) is made of a light-transmitting material; Alternatively, the bending protection plate (243) comprises a first plate member arranged in a straight line and a second plate member arranged in an arc shape, wherein the second plate member is connected to one end of the first plate member; Alternatively, two protective components (24) are arranged, and the two second protective plates (243) are symmetrically distributed along the center line of the second fuselage (21).

6. An aircraft according to claim 5, characterized in that: The connection system comprises: A first cavity (111), the first cavity (111) being opened on the fuselage (11), and the first cavity (111) being arranged close to an opening on one side of the sub-unmanned aerial mechanism (2); a magnetic adsorption mechanism (112), the magnetic adsorption mechanism (112) being arranged on the top of the first cavity (111); a limiting member (113), the limiting member (113) being located on the inner wall of the first cavity (111), and the limiting member (113) being spaced apart from the top of the first cavity (111); A limiting device is arranged on the top of the sub-unmanned aerial mechanism (2), the limiting device comprising a first column made of magnetic metal and a second column connected to the first column, the end face size of the first column being larger than the end face size of the second column, the limiting member (113) being switchable between a first state and a second state, in which, in the first state, the first column cannot pass through the limiting member (113), and the second column can pass through the limiting member, and in the second state, the first column can pass through the limiting member (113), and the second column can also pass through the limiting member.

7. An aircraft according to claim 6, characterized in that: The limiting member (113) can be moved in a first direction so that the first direction is parallel to the top of the first cavity (111); The limiting member (113) comprises a limiting block (1131), a groove body is provided on the surface of the limiting block (1131), an elastic member is accommodated inside the groove body, and a buffer member (1132) is arranged to be movably connected to the groove body along the longitudinal direction of the groove body, wherein one end of the buffer member (1132) contacts the elastic member.

8. A firearm (22) for an unmanned aerial combat platform, characterized in that: The firearm (22) is mounted on an aircraft as claimed in any one of claims 1 to 7. include: A frame member (221) including at least one weapon system (222) coupling device; A weapon system (222), the weapon system comprising at least one shooting weapon, the shooting weapon being provided with a trigger component for controlling the shooting of the shooting weapon; A control system (223), the control system (223) being connected to the trigger member; The control system (223) comprises a first rod (2231), a second rod (2233) and a first driving member (2232) connected to the first rod (2231); the first rod (2231) is connected to a trigger member at a position different from that at which it is connected to the first driving member (2232); the second rod (2233) is connected to the first rod (2231) at a position different from that at which it is connected to the first driving member (2232); the second rod (2233) is connected to the second driving member (2234) at a position different from that at which it is connected to the first rod (2231).

9. A firearm (22) for an unmanned aerial combat platform according to claim 8, characterized in that: The shooting weapon comprises a firing port, the firing port being located on one side of a frame member (221), and a connecting member (224) being arranged on a side of the frame member (221) facing away from the firing port; The firearm (22) is connected to the unmanned aerial combat platform via a connecting member (224).

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