Firearm and aircraft for air unmanned combat platform

Abstract

The invention discloses a firearm and an aircraft for an air unmanned combat platform, and relates to the technical field of military equipment.The firearm structurally comprises a frame component, and the frame component comprises at least one weapon system coupling device; the weapon system at least comprises a shooting weapon, and a trigger component for controlling the shooting weapon to shoot is arranged on the shooting weapon; the control system is connected with the trigger component; the control component comprises a first rod piece, a second rod piece and a first driving component connected with the first rod piece, the trigger component is connected to the position, different from the position connected with the first driving component, of the first rod piece, one position of the second rod piece is connected with the first rod piece, and the second driving component is connected to the position, different from the position connected with the first rod piece, of the second rod piece. According to the scheme disclosed by the invention, the reliability of the percussion mechanism of the unmanned combat platform is improved, so that the combat ability of the percussion mechanism in a complex battlefield environment is enhanced.

Description

Technical Field

[0001] The present invention relates to the technical field of military equipment, and in particular to a firearm and an aircraft used 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 when performing tasks. Summary of the invention

[0004] The purpose of the present invention is to overcome the shortcomings of the prior art and provide a firearm and an aircraft for an aerial unmanned combat platform. Compared with the prior art, the scheme 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 realized by the following technical scheme: The present invention discloses a firearm for an unmanned aerial combat platform, comprising:

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

[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 mechanism;

[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, and the second rod is connected to the second driving component at a position different from the position connected to the first rod.

[0010] Preferably, the shooting weapon comprises 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] The present application document also discloses an aircraft, the aircraft comprising:

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

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

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

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

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

[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] 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 mechanism comprises:

[0023] The second fuselage is loaded with firearms;

[0024] a second wing, one end of the second wing being connected to a second fuselage side wall, the second fuselage side wall 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] Wherein, when the mother unmanned aerial mechanism is mounted on the child unmanned aerial mechanism, the second power system is close to one side of the mother unmanned aerial mechanism;

[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 protective component is arranged with a storage cavity. When the driving device drives the second supporting component to flip so that the second power system deviates from the state of the mother unmanned aerial mechanism, the second power system is stored in the storage cavity.

[0030] Preferably, a second driving device is arranged to be coupled to the guard member, and the second driving device drives the guard member to rotate along a desired trajectory;

[0031] When the second driving state is activated, the angle between the shield member and the second body changes.

[0032] Preferably, the protective member comprises:

[0033] first protective plate;

[0034] A second protective plate, one end of the first protective plate is connected to a second protective plate;

[0035] A bending protection plate, wherein one end of the bending member is connected to the other end of the second protection plate;

[0036] The second protective plate is arranged corresponding to the position of the second wing, and a notch is provided on the surface of the second protective plate;

[0037] Or, a side of the bent protective plate away from the second wing is the periphery, and a protective layer is arranged on the periphery of the bent protective plate;

[0038] Or, the second protective plate is made of a light-transmitting material;

[0039] Or, the bending protection plate 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;

[0040] Alternatively, there are two protective components, and the two second protective panels are symmetrically distributed along the center line of the second fuselage.

[0041] Preferably, the connection system comprises:

[0042] A first cavity, the first cavity is opened in the fuselage, and the first cavity is arranged near the opening of one side of the sub-unmanned aerial mechanism;

[0043] A magnetic adsorption mechanism, which is arranged at the top of the first cavity;

[0044] A limiting component, the limiting component is located on the inner wall of the first cavity, and the limiting component is spaced apart from the top of the first cavity;

[0045] Among them, a limiting device is arranged on the top of the sub-unmanned flying mechanism, and the limiting device 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 component can be switched between a first state and a second state. In the first state, the first column cannot pass through the limiting component, and the second column can pass through the limiting component. In the second state, the first column can pass through the limiting component, and the second column can also pass through the limiting component.

[0046] Preferably, the limiting member can be moved along the first direction so that the first direction is parallel to the top of the first cavity;

[0047] The limiting component includes a limiting block, a groove body is opened on the surface of the limiting block, an elastic component is accommodated inside the groove body, and a buffer is arranged to be movably connected to the groove body along the longitudinal direction of the groove body, wherein one end of the buffer contacted with the elastic component.

[0048] The present invention discloses a firearm and an aircraft for an unmanned aerial combat platform. Compared with the prior art:

[0049] In the present application document, both the first driving member and the second driving member can control the trigger member to fire the shooting weapon. When one driving member is in an abnormal state, the trigger member can be driven to move by controlling the other driving member. 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 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 information suitable for execution by the first driving member and the second driving member. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] Figure 1 is a schematic diagram of the structure of a firearm in one embodiment;

[0051] Figure 2 for Figure 1 A local enlarged schematic diagram of the position a in the middle;

[0052] Figure 3 is a schematic diagram of the structure of an aircraft in one embodiment;

[0053] Figure 4 A schematic diagram of the combat process of an aircraft in one embodiment;

[0054] Figure 5 This is a schematic diagram of the structure of a mother unmanned aerial vehicle mechanism in one embodiment;

[0055] Figure 6 A schematic diagram of the structure of a neutron unmanned flying mechanism in one embodiment;

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

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

[0058] Fig. 9 A schematic diagram of state changes of a limiting device in an embodiment;

[0059] Fig.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 assist in a comprehensive understanding of various exemplary embodiments of the present disclosure as defined by the claims and their equivalents. The description includes various details to assist in understanding, but these details are to be considered as merely exemplary. Accordingly, one of ordinary skill 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. In addition, 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 may 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.

[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 explanation, 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 for special limitations 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 multi-rotor aircraft) and / or a flapping-wing aircraft.

[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, firearms can be pistols, rifles, machine guns, shotguns, laser guns, or any other type of shooting weapons that can use gunpowder, gas, electromagnetic force, or other energy sources to fire bullets, shells, darts, or other projectiles. In addition to the common types mentioned above, firearms may also include various special designs and functional variants 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, 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 shooting of the shooting weapon is arranged;

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

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

[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 shooting weapons are loaded on the frame member 221. In the present application document, the weapon system 222 can be installed through a coupling device. Specifically, the structure of the coupling device can be a track-type connection structure, and one or more standardized tracks are provided on the frame member, and the weapon system is installed on the track through an adapter. The above-mentioned track-type connection structure provides high 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 in the application document is not unique, and the installation and removal of the weapon system 222 can also be achieved through a locking structure, a fastener structure, an electromagnet attraction and other structures, which will not be described one by one here.

[0072] As for the weapon system 222, it is the attack core of the firearm 22 and includes at least one shooting weapon. The shooting weapon may be a machine gun, a cannon or other types of shooting devices, depending on the actual application scenario and combat requirements. In order to control the shooting of the shooting 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 shooting 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 instructions and controls the shooting of the weapon system 222 according to the instructions. The structure of 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, and the other end is connected to the trigger member at a position different from the position 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 shooting of the shooting weapon through the trigger member;

[0075] One end of the second rod 2233 is connected to the first rod 2231, and the other end is connected to the second driving member 2234 at a position different from the connection position of the first rod. The second driving member 2234 can apply force or displacement to the first rod 2231 through the second rod 2233, and then in this application document, the shooting weapon can be fired by controlling the trigger member through the first driving member 2232 and the second driving member 2234. When one driving member is in an abnormal state, the trigger member can be driven to move by controlling the other driving member. 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 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 driving member 2232 and the second driving member 2234.

[0076] Please continue to refer to Figure 1 In one embodiment, the shooting weapon includes a firing port, the firing port is located on one side of the frame member 221, and a connecting member 224 is arranged on the side of the frame member 221 facing away from the firing port;

[0077] The firearm 22 is connected to the unmanned aerial combat platform via a connecting member 224 .

[0078] Regarding the content of the embodiment, ammunition or other lethal substances are ejected from the inside of the firearm through the launch port. In addition to the launch port, a connecting member 224 is arranged on the other side of the frame member 221 (the side facing away from the launch port), which is responsible for firmly mounting the firearm on the combat platform. In actual application, when the firearm 22 needs to be installed on the combat platform, it only needs to be fixed on the platform through the connecting member 224. In a possible implementation, the connecting member 224 includes a main frame, which is composed of two shells that can move relative to each other, and a shock absorbing cavity is formed between the two shells. A shock absorbing spring and a damper are arranged in the shock absorbing cavity. The shock-absorbing chamber can absorb and disperse the recoil force when the firearm is fired, reducing the impact on the unmanned combat platform. At the same time, the shock-absorbing system also helps to reduce the shaking of the firearm caused by external disturbances during flight and improve shooting stability. In order to ensure the rigidity and stability of the connecting components, reinforced support plates are added to the key positions of the main frame (such as corners). Standardized connection interfaces are designed at both ends of the main frame, one end is connected to the frame component 221 of the firearm 22, and the other end is connected to the mounting system of the aerial unmanned combat platform through an adapter. The outer shell can be a prismatic structure to increase the structural stability and disperse the stress points.

[0079] See also 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] A mother unmanned aerial mechanism 1, wherein the mother unmanned aerial mechanism 1 is provided with a connection system;

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

[0082] Shell 3, the shell is mounted on the sub-unmanned flying mechanism 2;

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

[0084] In the embodiment, the aircraft is a combined unmanned aerial vehicle system, which is composed of a mother unmanned aerial vehicle mechanism 1 and a child unmanned aerial vehicle mechanism 2. The mother unmanned aerial vehicle mechanism 1 is the main body of the entire system, has a large size and a strong payload capacity, and is used to mount and transport the child unmanned aerial vehicle mechanism 2. The child unmanned aerial vehicle mechanism 2 is a small, flexible aircraft, which is mounted below the mother unmanned aerial vehicle mechanism 1 through the connection system thereof, and is equipped with weapon systems such as guns 22 and shells 3.

[0085] Furthermore, the mother unmanned aerial vehicle 1 is the carrier part of the entire aircraft system, responsible for mounting, transporting and dropping the sub-unmanned aerial vehicle 2. It has a large payload capacity, can carry more fuel (batteries), equipment and other necessities, and has a strong endurance. The mother unmanned aerial vehicle 1 also has high flight performance and navigation capabilities, and can fly in various harsh environmental conditions. The mother unmanned aerial vehicle is also equipped with a higher-precision navigation system and sensor than the sub-flight mechanism 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 mechanism 2 is a small, flexible aircraft, which is usually mounted below the mother unmanned aerial mechanism 1 through the connection system. The main weapon systems of the sub-unmanned aerial mechanism 2 are firearms 22 and shells 3. Relying on the mother unmanned aerial mechanism 1, it can accurately strike targets on the ground or in the air. The sub-unmanned aerial mechanism 2 also has the ability to fly and fight independently and can perform tasks independently. Among them, the firearm 22 is mounted in front of the sub-unmanned aerial mechanism, and it can be shot by remote control. It can accurately strike the target at a safe distance, thereby reducing the combat risk. The shells 3 are mounted at the bottom or internal bomb bay of the sub-unmanned aerial mechanism, and can be flexibly dropped according to the mission requirements to provide fire coverage or accurate strikes on ground targets. The type and quantity of shells 3 can be selected according to actual needs to meet different combat needs.

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

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

[0089] S200: Fire strike phase: After arriving at the combat area, the sub-unmanned aerial mechanism 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 unmanned aerial vehicle and the child unmanned aerial vehicle 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 unmanned aerial vehicle 1 first mounts the child unmanned aerial vehicle 2 to take off and move to the designated combat area. During this process, the mother unmanned aerial vehicle 1 is responsible for tasks such as navigation, flight control and communication, while the child unmanned aerial vehicle 2 is on standby. After arriving at the combat area, the child unmanned aerial vehicle 2 launches artillery shells 3 to carry out fire strikes on ground targets according to the combat plan. At the same time, the firearm 22 remains on standby, ready to accurately shoot at sudden targets. This flexible weapon configuration allows the child aircraft to quickly adapt to battlefield changes and perform various complex tasks.

[0093] After completing the fire strike mission, the decision to continue or evacuate is made according to the actual situation. If it is necessary to continue the battle or perform other tasks, the mother unmanned aerial vehicle 1 can separate from the child unmanned aerial vehicle 2 and return to the base for replenishment and maintenance. The child unmanned aerial vehicle 2 can continue to stay on the battlefield to perform combat missions. This separation design enhances the endurance and battlefield adaptability of the entire system.

[0094] When the mission is completed or the battlefield situation is unfavorable and evacuation is required, the mother unmanned aerial vehicle 1 can carry the child unmanned aerial vehicle 2 to evacuate the battlefield together. This coordinated evacuation method not only increases the evacuation speed, but also reduces the risk. At the same time, during the evacuation process, the mother unmanned aerial vehicle 1 can also rely on its high-precision anti-reconnaissance, high-precision navigation, high maneuverability and other performance to provide the child unmanned aerial vehicle 2 with necessary protection and support to ensure its safe evacuation.

[0095] Step S400: Endurance and evacuation: After completing the fire strike mission, make an endurance or evacuation decision based on the actual battlefield information. The battlefield information includes the following information:

[0096] A: Mission execution: Commanders will evaluate whether the sub-unmanned aerial vehicle 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-unmanned aerial vehicle 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 drone to be unable to fly stably, or changes in terrain may provide new hiding places for the enemy.

[0099] D: Resource consumption: The consumption of fuel, ammunition and other resources of the parent and child UAVs. If resources are consumed too quickly, you may need to consider evacuation or resupply in advance.

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

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

[0102] 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;

[0103] 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;

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

[0105] Among them, the sub-unmanned aerial mechanism 2 includes a second power system 233, and a second space is arranged on the 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.

[0106] Continue to refer Figure 5 , Figure 5 The position A in the middle is the second space. In the embodiment, the second power system 233 is composed of a motor, a fan blade, an electronic speed regulator, etc. The traditional mounting method may cause the wings or other parts of the mother unmanned flying mechanism 1 to contact the power system of the child unmanned flying mechanism 2, thereby affecting the flight performance of the child unmanned flying mechanism and even causing a safety accident. In order to avoid this situation, in the embodiment, a second space is reserved on the side of the mother unmanned flying mechanism close to the power system of the child unmanned flying mechanism. In order to ensure the stability and safety of the mother unmanned flying mechanism 1 and the child unmanned flying mechanism 2 during flight and avoid structural conflicts or interference, the second space can accommodate the second power system 233 of the child unmanned flying mechanism to ensure that the two will not conflict in structure. In addition, the second space can also be used as an airflow channel to optimize the airflow distribution of the mother unmanned flying mechanism and the child unmanned flying mechanism during flight. This helps to reduce air resistance and improve flight efficiency.

[0107] Please continue reading Figure 3 In one embodiment, the sub-unmanned aerial mechanism 2 includes:

[0108] A second body 21 , wherein the second body 21 is loaded with a firearm 22 ;

[0109] A second wing 23, one end of the second wing 23 is connected to the side wall of the second fuselage 21, 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 different from the second fuselage 21;

[0111] Among them, when the mother unmanned aerial mechanism 1 is mounted on the child unmanned aerial mechanism 2, the second power system 233 is close to one side of the mother unmanned aerial mechanism 1, and the second space can accommodate the second power system 233 of the child unmanned aerial mechanism, thereby improving safety.

[0112] See also 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, further effectively avoiding 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 second support member 232 is flipped by the driving device, 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 information, please refer to Figure 6 A protective component 24 is connected to the side wall of the second fuselage 21 and the position of the second wing 23 leg, and the protective component 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 supporting member 232 to flip so that the second power system 233 is away from the state of the mother unmanned flying 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 flying mechanism is performing a mission. When the aircraft is performing a mission, if the mother unmanned flying mechanism mounts the sub-unmanned flying mechanism, the second power system 233 faces the side away from the mother unmanned flying mechanism to avoid collision with the mother unmanned flying 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 avoid foreign objects (shells, birds) colliding with 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 fire attack or high-speed bird collision during flight, the protective component 24 made of bulletproof material 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 connect the guard member 24, and the second driving device drives the guard member 24 to rotate along an expected trajectory, and the expected trajectory is a predetermined path or movement route followed by the guard member 24 when performing its movement function;

[0116] When the second driving 24 state 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 embodiment in an unfolded state. The protective member 24 is a rotatable structure. One end of the protective member 24 is connected to the side wall of the second body 21, and the other end of the protective member 24 can be driven by the second driving device to rotate along a desired trajectory. The protective member 24 can be flexibly switched between the stored state and the unfolded state.

[0118] When the mother unmanned aerial mechanism and the child unmanned aerial mechanism are not separated, they are in the stowed state. In the 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. At this time, 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 driving device will be activated to drive the protective member 24 to rotate along the expected trajectory. During this process, the angle between the protective member 24 and the second fuselage 21 changes, so that it gradually unfolds from the stowed state to the landing gear state. In the landing gear state, the end of the protective member 24 will unfold and lock in a suitable position to support the weight of the sub-unmanned aerial mechanism and provide the necessary stability.

[0120] Please refer to Figure 8 Further, 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 is to contact the ground when the sub-unmanned aerial mechanism 2 needs to land, so as to play a better supporting role;

[0121] The second protection plate 242 is arranged corresponding to the position of the second wing 23, and a notch is provided on the surface of the second protection 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 protection member 24.

[0122] Or, 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. The protective layer is made of a flexible material and has a Mohs hardness of 6.5 to 7. The bending protection plate 243 contacts the ground when the sub-unmanned aerial mechanism 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, there are two protective components 24 , and the two second protective plates 243 are symmetrically distributed along the center line of the second fuselage 21 .

[0126] See also Fig. 9 In yet another embodiment, the connection system comprises:

[0127] A first cavity 111, which is opened on the fuselage 11, and is arranged close to an opening on one side of the sub-unmanned aerial mechanism 2;

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

[0129] A limiting member 113, the limiting member 113 is located on the inner wall of the first cavity 11, and the limiting member 113 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 position C in the middle 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 Fig. 9 An embodiment of Figure 5 The area selected at position B corresponds to Fig. 9 Schematic diagram of the change of different states in the figure, when the sub-unmanned aerial mechanism needs to be flipped, the magnetic adsorption mechanism 112 first stops adsorbing the limit device. At this time, due to the gravity of the sub-unmanned aerial mechanism, the limit device falls to the position of the limit member 113. In this process, the gap between the first wing and the second wing gradually increases, providing the necessary space for the flipping of the sub-unmanned aerial mechanism.

[0132] As the limit device falls and the gap increases, the sub-unmanned aerial mechanism begins to rotate from the side facing away from the main unmanned aerial mechanism to the side close to the main unmanned aerial mechanism. In this process, the sub-unmanned aerial mechanism needs to overcome the influence of gravity and air resistance to ensure the smooth and accurate flipping action.

[0133] When the sub-unmanned aerial mechanism completes the flip, the state of the limiting member 113 switches to the second state. In this state, both the first column and the second column can pass through the limiting member 113. Therefore, the sub-unmanned aerial mechanism can smoothly pass through the limiting member 113 and separate from the mother unmanned aerial mechanism. During the separation process, the magnetic adsorption mechanism 112 no longer generates adsorption force on the limiting device, ensuring the thoroughness and safety of the separation.

[0134] The specific steps are as follows:

[0135] In the initial state, if Fig. 9 As shown in S001, the sub-unmanned aerial mechanism is tightly connected to the main unmanned aerial mechanism through a connection system. The magnetic adsorption mechanism 112 adsorbs and fixes the limit device on the top of the sub-unmanned aerial mechanism to ensure a stable connection between the two. At this time, the limit member 113 is in the first state, preventing the limit device from passing through;

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

[0137] Due to the gravity of the unmanned aerial vehicle, Fig. 9 As shown in S002, the limiting device begins to fall to the position of the limiting member 113. During the falling process, the limiting device gradually approaches the 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 main unmanned aerial mechanism to the side close to the main unmanned aerial mechanism.

[0139] When the sub-unmanned aerial vehicle mechanism completes the flip, Fig. 9 As shown in S003, the state of the limiting member 113 is controlled to switch to the second state. In this state, the limiting member 113 allows the limiting device to pass through. This step is to separate the mother unmanned aerial mechanism from the child unmanned aerial mechanism, and it provides a passage for the limiting device to pass through the first cavity. In S003, the limiting member 13 is retracted to not occupy the space of the first cavity.

[0140] After the state of the limiting member 113 is switched, the limiting device passes through the first cavity smoothly. As the limiting device passes, the connection between the sub-unmanned aerial mechanism and the main unmanned aerial mechanism is completely released, and the sub-unmanned aerial mechanism can independently perform related tasks.

[0141] See also Fig.10 Further, the limiting member 113 can be moved along the first direction so that the first direction is 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] In summary, in the present application document, the shooting weapon can be fired by controlling the trigger component through the first driving component 2232 and the second driving component 2234. When one driving component is in an abnormal state, the trigger component can be driven to move by controlling the other driving component. For the control system of the driving component, the communication between the remote control center and the target driving component depends on a stable and 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 driving component 2232 and the second driving component 2234.

[0144] The above are only preferred specific implementation modes of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical solutions and inventive concepts of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

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

Claims

1. A firearm (22) for an unmanned aerial combat platform, characterized in that: 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 component; The control member (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 the first driving member (2232) is connected; the second rod (2233) is connected to the first rod (2231) at a position different from that at which the first driving member (2232) is connected; the second rod (2233) is connected to the second driving member (2234) at a position different from that at which the first rod (2231) is connected.

2. A firearm (22) for an unmanned aerial combat platform according to claim 1, 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 component (224).

3. An aircraft, characterized in that: The firearm (22) as claimed in any one of claims 1 to 2 is mounted on the aircraft, and the aircraft comprises: 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 main unmanned aerial mechanism (2) via a connection system, and the firearm (22) being mounted on the sub-unmanned aerial mechanism (2); A shell (3), the shell being mounted on the sub-unmanned flying mechanism (2); The effective load of the mother unmanned aerial mechanism (1) is greater than the effective load of the daughter unmanned aerial mechanism (2).

4. An aircraft according to claim 3, 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) 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); A power system (13), wherein the wing (12) is provided with the power system (13) at a position away from the fuselage (11); The sub-unmanned aerial mechanism (2) comprises 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 arranged in alignment with the second space.

5. An aircraft according to claim 4, characterized in that: The sub-unmanned aerial mechanism (2) comprises: A second body (21), wherein the second body (21) is loaded with a firearm (22); a second wing (23), wherein one end of the second wing (23) is connected to a side wall of the second fuselage (21), and the side wall of the second fuselage (21) is a longitudinal region of the second fuselage (21); The second power system (233) is arranged at a position of the second wing (23) different from the second fuselage (21); Wherein, when the mother unmanned aerial mechanism (1) is mounted on the child unmanned aerial mechanism (2), the second power system (233) is close to one side of the mother unmanned aerial mechanism (1); Alternatively, 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), and the second support member (232) is provided with a second power system (233) and a driving device for driving the second support member (232) to flip relative to the first support member (231).

6. An aircraft according to claim 5, characterized in that: 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 component (24) is provided with a storage cavity, and when the driving device drives the second supporting component (232) to flip so that the second power system (233) is away from the state of the mother unmanned aerial mechanism (1), the second power system (233) is stored in the storage cavity.

7. An aircraft according to claim 6, 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.

8. An aircraft according to claim 7, characterized in that: The protective component (24) comprises: A first protective plate (241); A second protective plate (242), wherein one end of the first protective plate (242) is connected to the second protective plate (242); A bending protection plate (243), wherein one end of the bending member (243) is 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); Or, a side of the bending protection plate (243) away from the second wing (23) is an outer periphery, and a protection layer is arranged on the outer periphery of the bending protection plate (243), and the protection layer is made of a flexible material and has a Mohs hardness of 6.5 to 7; Or, 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, and 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).

9. An aircraft according to claim 8, 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), wherein the magnetic adsorption mechanism (112) is arranged on the top of the first cavity (111); a limiting component (113), the limiting component (113) being located on the inner wall of the first cavity (11), and the limiting component (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 surface size of the first column being larger than the end surface 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), but 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.

10. An aircraft according to claim 9, characterized in that: The limiting member (113) can be moved along a first direction so that the first direction is parallel to the top of the first cavity (111); The limiting component (113) comprises a limiting block (1131), a groove body is provided on the surface of the limiting block (1131), an elastic component is accommodated inside the groove body, and a buffer component (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 component (1132) contacts the elastic component.

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