Embedded mounting air-to-air missile and mounting launching control method thereof

Abstract

The invention belongs to the technical field of design of embedded mounted air-to-air missiles, and particularly relates to an embedded mounted air-to-air missile and a mounting launching control method thereof.The embedded mounted air-to-air missile comprises a missile body, a sliding ring, a middle missile wing and a driving motor; an annular positioning groove and a plurality of arc-shaped grooves communicated with the annular positioning groove are formed in the outer side of the middle of the projectile body; the multiple sliding rings are arranged on the periphery of the projectile body in a sleeving mode, located in the annular positioning groove and flush with the outer side of the projectile body, driving blocks are arranged on the inner sides of the sliding rings, and the driving blocks extend into the inner side of the projectile body from the arc-shaped grooves. The multiple middle missile wings are connected to the sliding rings, and each middle missile wing stretches across the corresponding sliding ring in the axial direction of the missile body. The driving motor is arranged on the inner side of the missile body and connected with all the driving blocks so as to drive all the sliding rings to rotate, so that all the middle missile wings are driven to rotate, and the embedded type mounting air-to-air missile has a mounting state and a launching state.

Description

Technical Field

[0001] The present application belongs to the technical field of internally mounted air-to-air missile design, and specifically relates to an internally mounted air-to-air missile and a mounting launch control method thereof. Background Art

[0002] The air-to-air missile mainly includes a body, wings and a mounting device. The body is usually a long rod with a circular cross-section, and is usually equipped with a guidance mechanism, warhead, flight control system, propellant, rocket engine, etc.; the wings include middle wings and tail wings, which are arranged in the middle and outside of the tail of the body, usually four in number; the mounting device is used to mount the air-to-air missile on an aircraft and to control the launch of the air-to-air missile.

[0003] The mounting methods of air-to-air missiles on aircraft include external mounting, semi-internal mounting and internal mounting. Among them, the external mounting method mounts the air-to-air missile on the outside of the aircraft; the semi-internal mounting method fits part of the air-to-air missile body and wings to the aircraft; the internal mounting method mounts the air-to-air missile in the internal bomb bay of the aircraft.

[0004] Compared with external and semi-internal mounting, internally mounted air-to-air missiles are not exposed to the outside of the aircraft, will not damage the aircraft's appearance, will not increase the aircraft's aerodynamic drag and its radar reflection. However, since the wings, especially the middle wings, protrude from the outside of the missile body in many places in the circumferential direction, the air-to-air missile has a large external size and requires a large space for mounting. It is impossible to efficiently utilize the limited space in the internal bomb bay for mounting, and the number of mounts is limited.

[0005] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0006] The purpose of this application is to provide an internally mounted air-to-air missile and a mounting launch control method thereof, so as to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of this application is:

[0008] On the one hand, an internally mounted air-to-air missile is provided, including a missile body, a slip ring, a middle missile wing, and a drive motor;

[0009] The outer side of the middle part of the projectile body is provided with an annular positioning groove, and a plurality of arc-shaped grooves connected with the annular positioning groove;

[0010] There are multiple slip rings, which are sleeved on the periphery of the projectile body, located in the annular positioning groove, flush with the outer side of the projectile body, and have driving blocks on the inner side, and each driving block extends from each arc groove into the inner side of the projectile body;

[0011] There are multiple middle winglets connected to each slip ring, and each middle winglet spans across each slip ring in the axial direction of the missile body;

[0012] The drive motor is arranged inside the missile body and connected to each drive block to drive each slip ring to rotate, thereby driving each middle missile wing to rotate, so that the embedded air-to-air missile has a mounting state and a launching state:

[0013] When the internally mounted air-to-air missile is in the mounted state, the central wings are squeezed together in the circumferential direction of the missile body and biased toward one side of the missile body;

[0014] When the internally mounted air-to-air missile is in the launching state, each central wing rotates to the required angle around the missile body.

[0015] Optionally, in the above-mentioned internally mounted air-to-air missile, each arc-shaped groove has a different curvature, which is adapted to the required rotation range of each middle missile wing.

[0016] Optionally, in the above-mentioned internally mounted air-to-air missile, a plurality of protrusions are provided on the output shaft of the driving motor. During the rotation of the driving motor, each protrusion can abut against each driving block in turn, thereby driving each slip ring and its middle missile wing to rotate.

[0017] Optionally, in the above-mentioned internally mounted air-to-air missile, there are multiple drive motors, and the output shafts are connected to various drive blocks.

[0018] Optionally, in the above-mentioned internally mounted air-to-air missile, there are four slip rings and their corresponding middle wings and drive motors.

[0019] Optionally, the above-mentioned internally mounted air-to-air missile further includes a tail wing;

[0020] There are multiple tail wings, which are circumferentially connected to the outside of the tail of the missile body.

[0021] Optionally, in the above-mentioned internally mounted air-to-air missile, the tail wing has four

[0022] Optionally, the above-mentioned internally mounted air-to-air missile further includes a mounting device;

[0023] The mounting device is connected to the outside of the missile body and is used to mount the air-to-air missile in the aircraft's internal bomb bay.

[0024] Optionally, in the above-mentioned internally mounted air-to-air missile, there are two mounting devices, which are distributed on the front and rear sides of the annular positioning groove.

[0025] On the other hand, a method for controlling the launch of an internally mounted air-to-air missile is provided, which is implemented based on the above-mentioned internally mounted air-to-air missile and includes:

[0026] A plurality of internally mounted air-to-air missiles are placed in a mounted state, so that the middle wings of the internally mounted air-to-air missiles are squeezed together in the circumferential direction of the missile body and biased toward one side of the missile body, and the missile bodies are squeezed together side by side and mounted in the internally mounted missile bay of the aircraft;

[0027] After each internally mounted air-to-air missile is launched from the internal bomb bay of the aircraft, a driving motor is used to drive each slip ring and its middle missile wing to rotate, so that each middle missile wing of each internally mounted air-to-air missile is rotated to a required angle in the circumferential direction of the missile body, and each internally mounted air-to-air missile is set in a launching state. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of an internally-embedded mounted air-to-air missile provided in an embodiment of the present application in a mounted state and mounted in an internally-embedded bomb bay;

[0029] Figure 2 yes Figure 1 A partial cross-sectional view of

[0030] Figure 3 It is a schematic diagram of an internally mounted air-to-air missile in a launching state provided by an embodiment of the present application;

[0031] in:

[0032] 1- missile body; 2- slip ring; 3- middle missile wing; 4- tail missile wing; 5- mounting device; 6- driving motor.

[0033] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0034] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0035] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0036] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0037] An internally mounted air-to-air missile, such as Figure 1 As shown, it includes a projectile body 1, a slip ring 2, a middle projectile wing 3, a tail projectile wing 4, a mounting device 5, and a drive motor 6.

[0038] The body 1 is a long rod with a circular cross section, and has an annular positioning groove on the outer side of the middle part, and has a plurality of arc grooves connected with the annular positioning groove.

[0039] There are multiple slip rings 2, which are sleeved on the outer periphery of the body 1, located in the annular positioning groove, flush with the outer side of the body 1, and have driving blocks on the inner side. Each driving block extends into the inner side of the body 1 from each arc groove.

[0040] There are multiple middle wing 3, the specific number can be 2 to 32, connected to each slip ring 2, each middle wing 3 spans across each slip ring 2 in the axial direction of the missile body 1, wherein one middle wing 3 can be directly connected to the outer side of the middle part of the missile body 1.

[0041] There are multiple tail wings 4, which are connected to the outer side of the tail of the missile body 1 along the circumferential direction.

[0042] There are two mounting devices 5 connected to the outside of the missile body 1 and distributed at the front and rear sides of the annular positioning groove, so as to mount the air-to-air missile in the internal bomb bay of the aircraft.

[0043] The drive motor 6 is arranged on the inner side of the missile body 1 and connected to each drive block so as to drive each slip ring 2 to rotate, thereby driving each middle missile wing 3 to rotate, and is distributed around the missile body 1, so that the internally mounted air-to-air missile has a mounting state and a launching state.

[0044] When the internally mounted air-to-air missile is in the mounted state, each middle wing 3 is squeezed together in the circumferential direction of the missile body 1 and deviates to one side of the missile body 1, and can be deviated by about 45 degrees, so as to reduce the distribution range of each middle wing 3 in the circumferential direction of the missile body 1, so that the missile bodies 1 of multiple internally mounted air-to-air missiles can be squeezed together side by side, and the distance between the missile body 1 and the top and bottom of the internally embedded bomb bay can be reduced, so as to reduce the space required for mounting, efficiently utilize the limited space in the internally embedded bomb bay for mounting, and increase the number of mounts in the limited space of the bomb bay, such as Figure 1-2 shown.

[0045] When the embedded mounted air-to-air missile is in the launching state, each middle wing 3 rotates to a required angle in the circumferential direction of the missile body 1. For example, when the number of the middle wings 3 is four, the four middle wings 3 can be distributed at 90° intervals in the circumferential direction of the missile body 1. Figure 3 As shown, since each slip ring 2 is located in the annular positioning groove outside the missile body 1, it can cover each arc groove and be flush with the outer side of the missile body 1, so as not to damage the aerodynamic shape of the internally embedded air-to-air missile, and can ensure the flight performance of the internally embedded air-to-air missile, and each middle wing 3 spans across each slip ring 2 in the axial direction of the missile body 1, and each middle wing 3 is located in the same span range of the middle axial direction of the missile body 1, which can ensure the balance and guidance of the flight of the internally embedded air-to-air missile.

[0046] In the embedded air-to-air missile disclosed in the above embodiment, each arc groove can be designed to have a different curvature to match the required rotation range of each middle missile wing 3 so as to limit the rotation range of each middle missile wing 3.

[0047] In the embedded air-to-air missile disclosed in the above embodiment, it is possible to design a plurality of drive motors 6, which are connected to various drive blocks to drive each slip ring 2 and the middle wing 3 thereof. It is also possible to design a single drive motor 6, with a plurality of protrusions on the output shaft of the drive motor 6. During the rotation of the drive motor 6, each protrusion can be abutted against each drive block in turn, thereby driving each slip ring 2 and the middle wing 3 thereof to rotate.

[0048] A method for controlling the launch of an internally mounted air-to-air missile is provided, based on the internally mounted air-to-air missile provided in the above embodiment, and comprises:

[0049] A plurality of internally mounted air-to-air missiles are placed in a mounted state, so that the middle wings 3 of the internally mounted air-to-air missiles are pressed together in the circumferential direction of the missile body 1 and biased toward one side of the missile body 1, and the missile body 1 is pressed together side by side and mounted in the internally mounted bomb bay of the aircraft by the mounting device 5;

[0050] After each internally mounted air-to-air missile is launched from the internal bomb bay of the aircraft through the mounting device 5, the driving motor 6 drives each slip ring 2 and its middle missile wing 3 to rotate, so that each middle missile wing 3 of each internally mounted air-to-air missile is rotated to a required angle in the circumferential direction of the missile body 1, and each internally mounted air-to-air missile is set in a launching state.

[0051] The internally mounted air-to-air missile launch control method disclosed in the above embodiment is implemented based on the internally mounted air-to-air missile provided in the above embodiment. The description is relatively simple. For specific related matters, please refer to the relevant description of the internally mounted air-to-air missile part. Its technical effect can also refer to the technical effect of the relevant part of the internally mounted air-to-air missile, which will not be repeated here.

[0052] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. An internally mounted air-to-air missile, characterized in that: It comprises a projectile body (1), a slip ring (2), a middle projectile wing (3), and a driving motor (6); The outer side of the middle part of the body (1) is provided with an annular positioning groove, and a plurality of arc-shaped grooves connected with the annular positioning groove; There are a plurality of slip rings (2), which are sleeved on the outer periphery of the body (1), are located in the annular positioning groove, are flush with the outer side of the body (1), and have drive blocks on the inner side, and each drive block extends from each arc groove into the inner side of the body (1); There are a plurality of middle winglets (3) connected to each slip ring (2), and each middle winglet (3) spans across each slip ring (2) in the axial direction of the projectile body (1); The driving motor (6) is arranged inside the missile body (1) and connected to each driving block so as to drive each slip ring (2) to rotate, thereby driving each middle missile wing (3) to rotate, so that the embedded mounted air-to-air missile has a mounted state and a launching state: When the internally mounted air-to-air missile is in a mounted state, the middle missile wings (3) are pressed together in the circumferential direction of the missile body (1) and are biased toward one side of the missile body (1); When the internally mounted air-to-air missile is in a launching state, each middle missile wing (3) rotates to a required angle in the circumferential direction of the missile body (1).

2. The internally mounted air-to-air missile according to claim 1 is characterized in that: Each arc-shaped groove has a different curvature, which is adapted to the required rotation range of each middle elastic wing (3).

3. The internally mounted air-to-air missile according to claim 1 is characterized in that: The output shaft of the driving motor (6) is provided with a plurality of protrusions. When the driving motor (6) rotates, each protrusion can abut against each driving block in turn, thereby driving each slip ring (2) and its middle elastic wing (3) to rotate.

4. The internally mounted air-to-air missile according to claim 1 is characterized in that: There are multiple drive motors (6), and the output shafts are connected to the various drive blocks.

5. The internally mounted air-to-air missile according to claim 4 is characterized in that: There are four slip rings (2) and their corresponding middle elastic wings (3) and drive motors (6).

6. The internally mounted air-to-air missile according to claim 1 is characterized in that: Also includes a tail wing (4); There are a plurality of tail wings (4) which are connected to the outer side of the tail of the projectile body (1) along the circumferential direction.

7. The internally mounted air-to-air missile according to claim 6 is characterized in that: There are four tail fins (4).

8. The internally mounted air-to-air missile according to claim 1 is characterized in that: Also includes a mounting device (5); The mounting device (5) is connected to the outside of the missile body (1) and is used for mounting the air-to-air missile in the internal bomb bay of the aircraft.

9. The internally mounted air-to-air missile according to claim 8 is characterized in that: There are two mounting devices (5), which are distributed on the front and rear sides of the annular positioning groove.

10. A method for controlling the launch of an internally mounted air-to-air missile, based on the internally mounted air-to-air missile according to claim 1, characterized in that: include: A plurality of internally mounted air-to-air missiles are placed in a mounted state, so that the middle wings (3) of the internally mounted air-to-air missiles are pressed together in the circumferential direction of the missile body (1) and biased toward one side of the missile body (1), and the missile bodies (1) are pressed together side by side and mounted in the internally mounted bomb bay of the aircraft; After each internally mounted air-to-air missile is launched from the internally mounted bomb bay of the aircraft, a driving motor (6) drives each slip ring (2) and its middle missile wing (3) to rotate, so that each middle missile wing (3) of each internally mounted air-to-air missile is rotated to a required angle in the circumferential direction of the missile body (1), and each internally mounted air-to-air missile is set in a launching state.

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