An embedded unmanned aerial vehicle missile launcher and an aerial weapon system

Abstract

This application relates to an embedded UAV-borne missile launcher and airborne weapon system. The launch nest body comprises multiple launch nest shells arranged side-by-side. Each launch nest shell contains a launch power assembly and a missile body. The top of each shell houses an air source assembly, an electrical plug-in mechanism, and a missile locking mechanism. A fire control assembly is located on the top of the multiple launch nest shells. A protective cover connects to the launch nest body and isolates the air source assembly, electrical plug-in mechanism, missile locking mechanism, and fire control assembly from the outside environment. The air source assembly, electrical plug-in mechanism, and other components are compactly integrated, reducing space occupation and eliminating the need for step-by-step installation. The entire system can be installed in one go within the airborne platform, minimizing the internal space requirements of the carrier platform. This improves the versatility of the UAV-borne missile launcher and reduces dependence on the carrier platform.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) missile launchers, and in particular to an embedded UAV missile launcher and airborne weapon system. Background Technology

[0002] Missile launchers are a crucial component of airborne weapon systems, providing missiles with the correct initial separation attitude and ensuring launch safety, directly impacting the combat capabilities of fighter jets. To meet the requirements of high stealth, high speed, and high maneuverability for unmanned combat aerial vehicles (UCAVs), they commonly employ internal weapon mounting methods, such as missiles.

[0003] However, in the internal mounting method, infrared imaging air-to-air missiles need to be replenished with gas and electricity before launch. The gas source components and electrical plug-in mechanisms for replenishing gas and electricity are generally embedded inside the fighter jet and separated from the missile launcher. In this case, there are certain requirements for the size of the fighter jet's internal space, and the space occupied is relatively large. In addition, during installation, the missile launcher, gas source components and electrical plug-in mechanisms need to be installed in steps. Summary of the Invention

[0004] This application provides an embedded UAV-borne missile launcher and airborne weapon system to solve the problems of complex installation steps and space occupation caused by the fact that the gas source components and electrical plug-in mechanisms for gas replenishment and power replenishment are generally embedded inside the fighter jet and separated from the missile launcher in related technologies.

[0005] Firstly, an internally embedded unmanned aerial vehicle (UAV) missile launcher is provided, comprising:

[0006] The main body of the launch pod includes multiple launch pod shells arranged side by side, and a fire control assembly located on top of the multiple launch pod shells; each launch pod shell has a launch channel, and the launch power assembly and missile body are located in the launch channel; each launch pod shell has a corresponding gas source assembly, electrical plug-in mechanism and missile locking mechanism on top;

[0007] The protective cover is connected to the main body of the launch nest and isolates the air source assembly, electrical plug-in mechanism, missile locking mechanism and fire control assembly from the outside world.

[0008] In some embodiments, the launch nest body and its corresponding protective shield body form a launch unit;

[0009] There are multiple transmitting units, which are stacked vertically; adjacent transmitting units are connected by a connecting structure.

[0010] In some embodiments, the connection structure includes a plurality of longitudinal connecting plates connected to the sidewalls of the launch cell housing, and the plurality of longitudinal connecting plates are connected to transverse connecting plates.

[0011] In some embodiments, each launch channel extends through the launch cell housing at both ends; a tail end cap is provided on the launch cell housing at one end of the launch channel; the launch power assembly is connected to the tail end cap and the inner wall of the launch channel;

[0012] The missile body and the launch power assembly are coaxially arranged, and its tail end is in contact with the launch power assembly.

[0013] In some embodiments, the protective cover and the top of the launch cell body enclose an installation space;

[0014] The top of the launch nest shell, within the installation space, is provided with multiple limiting grooves; the limiting grooves are located directly above the launch channel and in the same direction as the extension of the launch channel; the limiting grooves are provided in a one-to-one correspondence with the launch channel.

[0015] The gas source assembly, electrical plug-in mechanism, and missile locking mechanism are located in the limiting groove and arranged along the extension direction of the limiting groove.

[0016] In some embodiments, the top and bottom walls of the launch channel are respectively provided with adapter pads that fit against the outer surface of the missile body; one of the adapter pads is provided with a groove.

[0017] Secondly, an airborne weapon system is provided, comprising:

[0018] The drone has a chamber inside, which is tilted and extends downward through the bottom of the drone;

[0019] The chamber is equipped with an embedded UAV-borne missile launcher. When the missile body is launched, the fire control component first controls the missile locking mechanism to unlock, and then controls the launch power component to launch the missile body from the launch channel. During the launch process, the electrical plug-in mechanism separates from the missile body.

[0020] In some embodiments, the end face of the launch pod body corresponding to the warhead of the missile body is a first inclined surface;

[0021] The end face of the protective cover corresponding to the warhead of the missile body is a second inclined surface; the bottom of the second inclined surface is in contact with the top of the first inclined surface;

[0022] When the embedded UAV-borne missile launcher is in cruise or combat mode, the horizontal planes of the second and first inclined planes are parallel to the horizontal plane of the bottom of the UAV.

[0023] In some embodiments, a sealing plate assembly for blocking the launch channel is provided on the first inclined surface; the sealing plate assembly is connected to the fire control assembly.

[0024] In some embodiments, a rotating shaft is provided inside the cavity and on both sides in the width direction of the launch nest body; the rotating shaft is connected to a driving device, which is used to drive the launch nest body to rotate around the rotating shaft by a set angle so that a part of the launch nest body protrudes from the cavity.

[0025] The beneficial effects of the technical solution provided in this application include:

[0026] This application provides an embedded UAV-borne missile launcher and airborne weapon system. The launch nest body comprises multiple launch nest shells arranged side-by-side. Each launch nest shell contains a launch power assembly and a missile body, and its top features an air source assembly, an electrical plug-in mechanism, and a missile locking mechanism. A fire control assembly is located on the top of the multiple launch nest shells. A protective cover connects to the launch nest body and isolates the air source assembly, electrical plug-in mechanism, missile locking mechanism, and fire control assembly from the outside environment. The reasonable arrangement of these components compactly integrates the air source assembly, electrical plug-in mechanism, and other components, reducing space occupation and eliminating the need for step-by-step installation. During installation, the entire system can be installed in one go within the airborne platform, minimizing the internal space requirements of the carrier platform. This improves the versatility of the UAV-borne missile launcher and reduces dependence on the carrier platform. Attached Figure Description

[0027] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0028] Figure 1 A schematic diagram of the overall structure of the embedded unmanned aerial vehicle missile launcher provided in the embodiments of this application;

[0029] Figure 2 This is a schematic diagram of the internal structure of a single launch cell housing provided in an embodiment of this application;

[0030] Figure 3 This is a schematic diagram of the structure of multiple transmitting units provided in the embodiments of this application;

[0031] Figure 4 This is a schematic diagram of the structure of the launch cell housing with an adapter pad provided in an embodiment of this application;

[0032] Figure 5 A schematic diagram of an airborne weapon system with an internally embedded UAV-borne missile launcher tilted at an angle without adjustment, provided in an embodiment of this application.

[0033] Figure 6 A schematic diagram showing the angle adjustment of an internally inclined UAV-borne missile launcher within an airborne weapon system provided in this application embodiment;

[0034] Figure 7 This is a schematic diagram of an airborne weapon system with an internally embedded UAV missile launcher, installed at an angle according to another installation posture provided in this application embodiment.

[0035] In the diagram: 1. Launch pod shell; 2. Launch channel; 3. Launch power assembly; 4. Missile body; 5. Protective shield; 6. Gas source assembly; 7. Electrical plug-in mechanism; 8. Missile locking mechanism; 9. Fire control assembly; 10. Longitudinal connecting plate; 11. Lateral connecting plate; 12. Groove; 13. Tail sealing plate; 14. Limiting groove; 15. Adaptor pad; 16. UAV; 17. First inclined surface; 18. Second inclined surface; 19. Sealing plate assembly; 20. Rotation shaft. Detailed Implementation

[0036] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0037] This application provides an embedded UAV-borne missile launcher and airborne weapon system to solve the problems of complex installation steps and space occupation caused by the fact that the gas source components and electrical plug-in mechanisms for gas replenishment and power replenishment are generally embedded inside the fighter jet and separated from the missile launcher in related technologies.

[0038] Please see Figures 1-7 An embedded unmanned aerial vehicle missile launcher, comprising a launch nest body and a protective cover 5;

[0039] The launch nest body includes multiple launch nest shells 1 arranged side by side, and a fire control assembly 9 located on top of the multiple launch nest shells 1; there are mutually abutting contact planes between adjacent launch nest shells 1;

[0040] Each launch cell housing 1 is equipped with a launch channel 2, and the launch channel 2 is equipped with a launch power assembly 3 and a missile body 4; the top of each launch cell housing 1 is equipped with a corresponding air source assembly 6, an electrical plug-in mechanism 7 and a missile locking mechanism 8;

[0041] The protective cover 5 is connected to the main body of the launch cell and isolates the air source assembly 6, electrical plug-in mechanism 7, missile locking mechanism 8 and fire control assembly 9 from the outside world.

[0042] Before launch, the fire control unit 9 controls the gas supply unit 6 to replenish the air supply to the missile body 4. When the missile body 4 is launched, the fire control unit 9 first controls the missile locking mechanism 8 to unlock, and then controls the launch power unit 3 to eject the missile body 4 from the launch channel 2. During the ejection process, the electrical plug-in mechanism 7 separates from the missile body 4. The fire control unit 9 communicates via a cable network.

[0043] The above configuration features a launch power assembly 3 and a missile body 4 inside each launch pod shell 1. Each launch pod shell 1 has an air source assembly 6, an electrical plug-in mechanism 7, and a missile locking mechanism 8 on its top. Multiple launch pod shells 1 are equipped with a fire control assembly 9 on their tops. The protective cover 5 isolates the air source assembly 6, electrical plug-in mechanism 7, missile locking mechanism 8, and fire control assembly 9 from the outside. The above configuration rationally integrates the air source assembly 6, electrical plug-in mechanism 7, and other components, reducing space occupation and eliminating the need for step-by-step installation. During installation, the entire assembly can be installed in one go within the airborne platform, requiring less internal space on the carrier platform. This improves the versatility of the UAV-borne missile launcher and reduces dependence on the carrier platform.

[0044] In addition, each launch cell housing 1 has an air supply assembly 6, an electrical plug-in mechanism 7, and a missile locking mechanism 8 on its top, which can realize the air supply operation of each missile body 4.

[0045] In the above, it can be understood that the fire control assembly 9, the gas source assembly 6, the electrical plug-in mechanism 7, and the missile locking mechanism 8 are existing structures. For example, one can refer to a launch tube electromechanical fuse with status feedback (application number: 202011622865.3).

[0046] In some preferred embodiments, see Figure 3 Some carrier platforms have relatively large internal spaces, thus they can accommodate more missile bodies 4, with the following configurations:

[0047] The main body of the launch nest and its corresponding protective shield 5 form a launch unit;

[0048] There are multiple launching units, stacked vertically; adjacent launching units are connected by a connecting structure. The number of launching units can be set as needed. The connecting structure includes multiple longitudinal connecting plates 10 connected to the side wall of the launching nest housing 1, and the multiple longitudinal connecting plates 10 are connected to transverse connecting plates 11.

[0049] The electrical plug-in mechanism 7 includes a plug that is plugged into and connected to the missile body 4. The plug contains an air supply nozzle and an air supply nozzle; the air supply nozzle is connected to the air source assembly 6. The structure of the electrical plug-in mechanism 7 is an existing structure, and reference can be made to the ramp-type passive air path separation mechanism and launch box (application number: 202120256908.4).

[0050] In some preferred embodiments, reference Figure 2 and Figure 1 The locations of the launch power assembly 3, the missile body 4, the air source assembly 6, the electrical plug-in mechanism 7, and the missile locking mechanism 8 are described in detail:

[0051] Each launch channel 2 has two ends that penetrate the launch nest shell 1; a tail end plate 13 is provided on the launch nest shell 1 and at one end of the launch channel 2; the launch power assembly 3 is connected to the tail end plate 13 and the inner wall of the launch channel 2; the missile body 4 is coaxially arranged with the launch power assembly 3, and its tail end is in contact with the launch power assembly 3.

[0052] The protective cover 5 and the top of the launch nest body form an installation space; the top of the launch nest shell 1, located within the installation space, is provided with multiple limiting grooves 14; the limiting grooves 14 are located directly above the launch channel 2 and are in the same direction of extension as the launch channel 2; the limiting grooves 14 are arranged one-to-one with the launch channel 2; the air source assembly 6, the electrical plug-in mechanism 7, and the missile locking mechanism 8 are located within the limiting grooves 14 and are arranged along the direction of extension of the limiting grooves 14.

[0053] In some preferred embodiments, reference Figure 4 The launch channel 2 has a rectangular cross-section. The top and bottom walls of the launch channel 2 are respectively provided with adapter pads 15 that fit against the outer surface of the missile body 4; one of the adapter pads 15 has a groove 12. Through the setting of the adapter pads 15, the adapter pads 15 with grooves 12 cooperate with the outer diameter of the missile body 4 and the protrusion of the missile belly, providing support for the missile body 4 and restricting the missile's roll.

[0054] This application proposes an airborne weapon system, which includes:

[0055] The drone 16 has a chamber inside, which is tilted and extends downward through the bottom of the drone 16;

[0056] The chamber is equipped with the aforementioned embedded UAV-borne missile launcher; when the missile body 4 is launched, the fire control component 9 first controls the missile locking mechanism 8 to unlock, and then controls the launch power component 3 to launch the missile body 4 from the launch channel 2. During the launch process, the electrical plug-in mechanism 7 separates from the missile body 4.

[0057] The above configuration, due to the inclined chamber, also allows the embedded UAV-borne missile launcher to be inclined. During launch, only launch channel 2 needs to be opened; no attitude adjustment is required, saving launch time. This solves the problem of existing internal missile mounting methods, where the missile bay door must be opened first, and then the missile extended outside the bay via a retractable launcher or ejected from the bay via an ejection launcher, requiring the door to be closed after launch. Retractable launchers are complex, bulky, and slow to respond; ejection launchers require power, are complex systems, and have bulky auxiliary equipment. Existing launchers cannot meet the high-speed, high-maneuverability, and rapid-response operational requirements of small and medium-sized unmanned combat aircraft.

[0058] In some preferred embodiments, Figure 1 and Figure 2 ,as well as Figure 7 The end face of the launch nest body corresponding to the warhead of the missile body 4 is the first inclined surface 17;

[0059] The end face of the protective cover 5 corresponding to the warhead of the missile body 4 is the second inclined surface 18; the bottom of the second inclined surface 18 is in contact with the top of the first inclined surface 17.

[0060] When the embedded UAV-borne missile launcher is in cruise or combat mode, the horizontal planes of the second inclined plane 18 and the first inclined plane 17 are parallel to the horizontal plane of the bottom of the UAV 16.

[0061] By setting the bottom of the second inclined surface 18 and the first inclined surface 17 as described above, the embedded UAV-borne missile launcher and the bottom of the UAV 16 are on the same plane, thus having a good aerodynamic shape and reducing wind resistance.

[0062] Based on this, a sealing plate assembly 19 is provided on the first inclined surface 17 to block the launch channel 2; the sealing plate assembly 19 is connected to the fire control assembly 9; the specific structure of the sealing plate assembly 19 is a drive shaft, the sealing plate is connected to the drive shaft, the drive shaft is connected to a drive motor, and the drive motor is communicatively connected to the fire control assembly 9.

[0063] The sealing plate assembly 19 and the tail sealing plate 13 provide a sealed environment for the missile body 4 inside the launch cell housing 1 and further reduce wind resistance.

[0064] In some preferred embodiments, reference Figure 5 and Figure 6It also has the following settings:

[0065] Inside the cavity, and on both sides of the launch nest body in the width direction, there are rotating shafts 20; the rotating shafts 20 are connected to a driving device, which is used to drive the launch nest body to rotate around the rotating shafts 20 at a set angle so that part of the launch nest body protrudes out of the cavity.

[0066] The internal chamber of the UAV 16 is made larger, and a drive mechanism is installed to rotate the embedded UAV-borne missile launcher, allowing for different launch angles. Under normal conditions, the horizontal planes of the second inclined plane 18 and the first inclined plane 17, as shown above, are parallel to the horizontal plane of the bottom of the UAV 16 (e.g., Figure 7 During launch, the probe is tilted downwards at a certain angle, which simplifies the launch process.

[0067] In this embodiment, m×n missile bodies 4 are loaded simultaneously; the upper and lower adapter pads 15 provide support and constraint for the internally installed missile bodies 4; the missile locking mechanism 8 achieves mechanical locking of the missile bodies 4 within the launch device; and the gas source assembly 6 and the electrical plug-in mechanism 7 supply gas and communication to the missiles, respectively.

[0068] When the UAV 16 reaches the combat zone and receives combat orders, the internally mounted UAV missile launcher quickly deflects downward at a certain angle and extends its nose downward under the action of the rotating mechanism. After receiving the order, the fire control assembly 9 opens the sealing plate assembly 19 and simultaneously supplies air and power to the missile body 4 through the air source assembly 6 and the electrical plug-in mechanism 7. After receiving the release command, the missile locking mechanism 8 releases the missile's mechanical lock, and then the launch power assembly 3 operates to launch the missile body 4. Multiple missile bodies 4 can be launched in succession or salvo according to combat requirements.

[0069] After the missile body 4 is launched, the fire control component 9 issues an instruction and the sealing plate component 19 closes; the rotating mechanism quickly retracts the embedded UAV-borne missile launcher, and the UAV 16 can quickly leave the combat area.

[0070] This application has the following effects:

[0071] The device features a compact structure, high integration, small footprint, and good aerodynamic shape. Internally, it integrates an air source assembly 6, a fire control assembly 9, a launch power assembly 3, an electrical plug-in mechanism 7, and a missile locking mechanism 8. It boasts high platform versatility and low dependence on the carrier aircraft platform. The device employs an internally embedded inclined launch system, enabling rapid operational response. It also offers a high missile load capacity within a limited space; in this embodiment, it can carry six missiles within a 320mm × 280mm cross-section. The device enables salvo / series firing of infrared imaging air-to-air missiles; its tail is sealed, eliminating the need for exhaust gas; and its modular design allows for large-scale expansion of multiple launchers.

[0072] In the description of this application, it should be noted that the terms "upper," "lower," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application. Unless otherwise expressly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two elements. For those skilled in the art, the specific meaning of the above terms in this application can be understood according to the specific circumstances.

[0073] It should be noted that in this application, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0074] The above description is merely a specific embodiment of this application, enabling those skilled in the art to understand or implement this application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this application. Therefore, this application is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features claimed herein.

Claims

1. An internally-buried unmanned aerial vehicle missile launcher apparatus, characterized by, It includes: The launch nest body includes multiple launch nest shells (1) arranged side by side, and a fire control assembly (9) located on top of the multiple launch nest shells (1); each launch nest shell (1) is provided with a launch channel (2), and the launch channel (2) is provided with a launch power assembly (3) and a missile body (4); each launch nest shell (1) is provided with a corresponding air source assembly (6), an electrical plug-in mechanism (7) and a missile locking mechanism (8) on top. The protective cover (5) is connected to the main body of the launch nest and isolates the air source assembly (6), electrical plug-in mechanism (7), missile locking mechanism (8) and fire control assembly (9) from the outside world; The protective cover (5) and the top of the launch nest body form an installation space; The top of the launch nest housing (1) and within the installation space are provided with multiple limiting grooves (14); the limiting grooves (14) are located directly above the launch channel (2) and are in the same direction as the extension of the launch channel (2); the limiting grooves (14) are provided in a one-to-one correspondence with the launch channel (2); The gas source assembly (6), electrical plug-in mechanism (7) and missile locking mechanism (8) are located in the limiting groove (14) and arranged along the extension direction of the limiting groove (14).

2. The embedded unmanned aerial vehicle (UAV) missile launcher as described in claim 1, characterized in that: The launch nest body and its corresponding protective cover (5) form a launch unit; There are multiple transmitting units, which are stacked vertically; adjacent transmitting units are connected by a connecting structure.

3. The embedded unmanned aerial vehicle (UAV) missile launcher as described in claim 2, characterized in that: The connection structure includes multiple longitudinal connecting plates (10) connected to the side wall of the launch cell housing (1), and the multiple longitudinal connecting plates (10) are connected to transverse connecting plates (11).

4. The embedded unmanned aerial vehicle (UAV) missile launcher as described in claim 1, characterized in that: Each launch channel (2) has a launch nest shell (1) extending through both ends; a tail end plate (13) is provided on the launch nest shell (1) and located at one end of the launch channel (2); the launch power assembly (3) is connected to the tail end plate (13) and also to the inner wall of the launch channel (2); The missile body (4) is coaxially arranged with the launch power assembly (3), and its tail end is in contact with the launch power assembly (3).

5. The embedded unmanned aerial vehicle (UAV) missile launcher as described in claim 1, characterized in that: The top and bottom walls of the launch channel (2) are respectively provided with adapter pads (15) that fit the outer surface of the missile body (4); one of the adapter pads (15) is provided with a groove (12).

6. An airborne weapon system, characterized in that, It includes: The drone (16) has a chamber inside, which is inclined and extends downward through the bottom of the drone (16); The chamber is equipped with an embedded UAV-borne missile launcher as described in any one of claims 1-5; when the missile body (4) is launched, the fire control component (9) first controls the missile locking mechanism (8) to unlock, and then controls the launch power component (3) to launch the missile body (4) from the launch channel (2). During the launch process, the electrical plug-in mechanism (7) separates from the missile body (4).

7. The airborne weapon system as described in claim 6, characterized in that: The end face of the launch nest body corresponding to the warhead of the missile body (4) is the first inclined surface (17). The end face of the protective cover (5) corresponding to the warhead of the missile body (4) is the second inclined surface (18); the bottom of the second inclined surface (18) is in contact with the top of the first inclined surface (17); When the embedded UAV-borne missile launcher is in cruise or combat mode, the planes on which the second inclined plane (18) and the first inclined plane (17) are located are parallel to the plane on which the bottom of the UAV (16) is located.

8. The airborne weapon system as described in claim 7, characterized in that: The first inclined surface (17) is provided with a sealing plate assembly (19) that blocks the launch channel (2); the sealing plate assembly (19) is connected to the fire control assembly (9).

9. The airborne weapon system as described in claim 6, characterized in that: Inside the cavity, and on both sides of the launch nest body in the width direction, there are rotating shafts (20); the rotating shafts (20) are connected to a driving device, which is used to drive the launch nest body to rotate around the rotating shafts (20) at a set angle so that part of the launch nest body protrudes from the cavity.

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