A hidden controllable folding wing ramjet composite range-extended projectile and design method

Abstract

The present application belongs to the technical field of guidance, and particularly relates to a ramjet composite range increasing projectile with hidden controllable folding wings and a design method. The ramjet composite range increasing projectile comprises a central cone and a composite range increasing projectile body located outside the central cone, the central cone is coaxially fixedly connected with the composite range increasing projectile body, and characterized in that the composite range increasing projectile body is provided with hidden controllable folding wings, and the hidden controllable folding wings are detachably fixedly connected with the central cone through an ejection device. The present application aims to provide a ramjet composite range increasing projectile with hidden controllable folding wings and a design method. While the advantages of the ramjet composite range increasing projectile are retained, the hidden controllable folding wings are designed and applied to the ramjet composite range increasing projectile, and the design of the ramjet composite range increasing projectile with hidden controllable folding wings is completed.

Description

Technical Field

[0001] This invention belongs to the field of guidance technology, specifically relating to a ramjet composite extended-range projectile with a concealed, controllable folding wing and its design method. Background Technology

[0002] Hypersonic vehicles and the design and development of hypersonic weapons are highly valued by major military powers worldwide. Extended-range missiles, with their advantages of long range and high accuracy, have been extensively studied in the military field both domestically and internationally. The ramjet-powered composite extended-range missile is a hypersonic missile powered by a ramjet engine. Compared to rocket-powered composite extended-range missiles, ramjet-powered composite extended-range missiles not only have a higher range extension rate, significantly increasing the missile's range, but also reduce warhead yield loss and lower production costs.

[0003] CN 114329958A discloses a method for designing a curved extended-range trajectory for the mid-course guidance phase. Specifically, it discloses three steps: Step 1: Obtaining inertial navigation system (INS) output information; Step 2: Obtaining target information; Step 3: First, based on the INS output information, the missile's altitude control activation position is obtained, and simultaneously, the target position is obtained based on the target information. Then, the arc-shaped curved extended-range trajectory is determined, i.e., the desired trajectory D of the missile in the mid-course guidance phase is determined. This technical solution uses INS output information as a basis, combined with target information, to determine the desired altitude trajectory in the mid-course guidance phase. It provides a method for solving the desired altitude trajectory in the mid-course guidance phase that balances range extension and terminal velocity requirements. While it has significant guiding value in guidance, it has not been studied in depth in the design of the extended-range missile itself.

[0004] CN 101017076A discloses a ramjet-assisted extended-range ultra-long-range guided projectile, specifically comprising a solid ramjet engine, a guided warhead housing tube, and a guided warhead. After firing, the solid ramjet engine provides significant additional energy to the guided warhead, extending its range. The solid ramjet engine employs a detachable structure, with the engine fixedly connected to the guided warhead housing tube, while the housing tube and the contained guided warhead are detachably connected. The guided warhead only bears the thrust. This technical solution incorporates projectile design, but it cannot be applied to the field of hypersonic missiles and remains at the projectile stage.

[0005] Therefore, based on the current state of research abroad and the technological foundation in China, ramjet composite extended-range projectiles still require further in-depth research. Summary of the Invention

[0006] The purpose of this invention is to provide a concealed, controllable folding ramjet extended-range projectile and its design method. The ejection device is in a retracted state, and the wing is completely integrated within the ramjet extended-range projectile, thus hiding the wing inside the projectile body. This reduces the production cost of the ramjet extended-range projectile while improving its versatility and application prospects. The detailed technical solution of this invention is described below.

[0007] The present invention protects a ram-pressed composite extended-range projectile body comprising a central cone and a ram-pressed composite extended-range projectile body located outside the central cone. The central cone and the ram-pressed composite extended-range projectile body are coaxially fixedly connected. The ram-pressed composite extended-range projectile body is provided with a hidden controllable folding wing. The hidden controllable folding wing is detachably fixedly connected to the central cone via an ejection device.

[0008] When the ramjet-propelled composite extended-range projectile has not reached the set flight speed, the ejection device is close to the surface of the central cone, and the hidden controllable folding wing is located in the ejection channel of the ramjet-propelled composite extended-range projectile body. When the ramjet-propelled composite extended-range projectile reaches the set flight speed, the ejection device pops out and is flush with the outer wall of the ramjet-propelled composite extended-range projectile body. The hidden controllable folding wing unfolds outward from the ejection channel of the ramjet-propelled composite extended-range projectile body.

[0009] Preferably, the ram-pressed composite extended-range projectile body and the central cone are connected by a projectile channel, the cross-section of which is elliptical and the area of ​​the elliptical shape is the same at different heights.

[0010] Preferably, the outer wall curve of the ejection channel is an offset curve of the inner wall curve of the ejection channel in the radial outward direction, with an offset distance greater than 1 cm and less than the axial distance to the throat of the air intake.

[0011] As a preferred option, the root profile of the concealed controllable folding wing is an offset curve that is radially inward on the inner wall curve of the wing ejection channel, with an offset distance of more than 2mm.

[0012] Preferably, the ejection device is equipped with a speed sensor, which is used to measure the flight speed of the ramjet composite extended-range projectile. When the ramjet composite extended-range projectile has not reached the set flight speed, the ejection device is in a retracted state, and when the ramjet composite extended-range projectile has reached the set flight speed, the ejection device is in an extended state.

[0013] In the retracted state, the total depth of the concealed controllable folding wing and the ejection device is less than the total depth of the ejection channel.

[0014] Preferably, the set flight speed is Mach 0.9-2.

[0015] Preferably, the hidden controllable folding wings are provided in three or more forms, symmetrically distributed along the axis of the central cone.

[0016] Preferably, the concealed controllable folding wing is detachably and fixedly connected to the ejection device via a bellows.

[0017] Preferably, the composite range-extending missile body also includes a tail nozzle.

[0018] This invention also protects a design method for a concealed, controllable folding wing ramjet composite extended-range projectile, comprising the following steps:

[0019] (1) Design the incident shock wave, generate the internal contraction shock wave flow field, obtain the inlet compression profile, and complete the design of the generatrix of the central cone of the ramjet composite extended range projectile, and generate the central cone of the ramjet composite extended range projectile.

[0020] (2) Based on the shock wave flow field designed in step (1), design the inner wall generatrix and outer wall generatrix of the ram-pressed composite range-extended projectile body at the shock wave intersection point to generate the ram-pressed composite range-extended projectile body;

[0021] (3) Based on the projectile body generated in step (2), design the tail nozzle of the ramjet composite extended range projectile at the tail end to complete the overall structural design of the ramjet composite extended range projectile body.

[0022] (4) Design the inner and outer wall curves of the wing catapult channel to complete the design of the wing catapult channel;

[0023] (5) Based on the wing ejection channel in step (4), design the ejection device and the hidden controllable folding wing;

[0024] (6) By using an array method, designing wing ejection channels at other locations, hidden controllable folding wings and ejection devices, the ramjet composite extended-range projectile mentioned above can be obtained.

[0025] The beneficial effects of this invention are:

[0026] (1) The present invention aims to propose a hidden controllable folding wing ramjet composite extended range projectile and its design method. While retaining the advantages of the ramjet composite extended range projectile itself, a hidden controllable folding wing is designed and applied to the ramjet composite extended range projectile, thus completing the design of a hidden controllable folding wing ramjet composite extended range projectile.

[0027] (2) The present invention proposes a concealed, controllable folding ramjet extended-range projectile and its design method. In the design of the ramjet extended-range projectile, the ejection device is in a retracted state, and the wing is completely built into the ramjet extended-range projectile, so that the wing is hidden inside the ramjet extended-range projectile body. During the flight mission, when the flight speed reaches supersonic speed, the ramjet extended-range projectile rapidly unfolds within the wing trajectory, so that the wing pops out onto the surface of the ramjet extended-range projectile and plays its role.

[0028] (3) The concealed controllable folding ramjet extended-range projectile and its design method of the present invention reduce the space occupied by the wing section in external storage and make the transportation of the ramjet extended-range projectile more convenient. The wing is connected to the central cone of the ramjet extended-range projectile through a catapult device. The wing section can select the wing type according to the flight mission of the ramjet extended-range projectile. While reducing the production cost of the ramjet extended-range projectile, it improves the wide applicability of the ramjet extended-range projectile. The geometric shape of the folding wing can be controlled according to the design of the wing trajectory. Attached Figure Description

[0029] Figure 1 Schematic diagram for shock wave flow field design and inlet compression profile design;

[0030] Figure 2 A schematic diagram illustrating the generation principle of the central cone and body of a ram-pressed composite extended-range projectile.

[0031] Figure 3 A schematic diagram of the overall structure of a ramjet composite extended-range projectile with concealed and controllable folding wings;

[0032] Figure 4 A central cross-sectional view of a ramjet composite extended-range projectile with concealed, controllable folding wings;

[0033] Figure 5 A front view of a ramjet composite extended-range projectile with concealed, controllable folding wings;

[0034] Figure 6 A 45° azimuth view of a ramjet composite extended-range projectile with concealed, controllable folding wings;

[0035] Figure 7 Left view of a ramjet composite extended-range projectile with concealed, controllable folding wings;

[0036] Figure 8 A partial 45° azimuth cross-sectional view of a ramjet composite extended-range projectile with concealed, controllable folding wings;

[0037] Figure 9 A partial 45° cross-sectional view of a concealed, controllable folding wing and its central cone;

[0038] Figure 10A partial cross-sectional view of a concealed, controllable folding wing and its central cone;

[0039] Figure 11 This is a schematic diagram illustrating the working principle of a hidden, controllable folding wing.

[0040] The markings in the diagram are as follows: 1 represents hypersonic airflow; 2 represents the center volume of the shock wave field; 3 represents the incident shock wave; 4 represents the intersection of the incident and reflected shock waves; 5 represents the reflected shock wave; 6 represents the contracting shock wave field; 7 represents the boundary of the contracting shock wave field; 8 represents the inlet compression profile; 9 represents the generatrix of the central cone of the ramjet-assisted composite projectile; 10 represents the central axis; 11 represents the central cone of the ramjet-assisted composite projectile; 12 represents the generatrix of the inner wall of the tail nozzle of the ramjet-assisted composite projectile; 13 represents the inner wall of the tail nozzle of the ramjet-assisted composite projectile; 14 represents the projectile body of the ramjet-assisted composite projectile; and 15 represents the outer wall of the tail nozzle of the ramjet-assisted composite projectile. Generatrix, 16 represents the boundary line between the ramjet compound extended-range projectile body and the tail nozzle, 17 represents the generatrix of the inner wall surface of the ramjet compound extended-range projectile body, 18 represents the generatrix of the outer wall surface of the ramjet compound extended-range projectile body, 19 represents the inner wall surface of the ramjet compound extended-range projectile body, 20 represents the air intake lip, 21 represents the wing ejection channel, 22 represents the wing, 23 represents the outer wall surface of the ramjet compound extended-range projectile body, 24 represents the outer wall surface of the tail nozzle of the ramjet compound extended-range projectile, 25 represents the inner wall surface of the wing ejection channel, 26 represents the ejection device, 27 represents the tail nozzle outlet of the ramjet compound extended-range projectile, 28 represents the outer wall surface of the wing ejection channel, 29 represents the ejection direction. Detailed Implementation

[0041] The specific embodiments of the present invention will be further described below with reference to the accompanying drawings:

[0042] A type of concealed, controllable folding wing ramjet composite extended-range projectile, such as Figures 1-11 As shown, it is prepared by the following method.

[0043] (1) Design the incident shock wave 3 to generate the internal contraction shock wave flow field 6, obtain the inlet compression profile 8, and complete the design of the generatrix of the central cone of the ramjet composite extended-range projectile, generating the central cone 11 of the ramjet composite extended-range projectile. Design the incident shock wave 3 and the reflected shock wave 5 to generate the internal contraction shock wave flow field 6. Select any point on the surface of the incident shock wave 3, and use streamline tracing technology to generate streamlines in the internal contraction shock wave flow field 6. These streamlines are the compression profile 8 of the inlet. Using this point as a reference, design the central axis 10 along the flow direction of the hypersonic airflow 1. Through geometric transition and other means, design multiple splines at the intersection of the inlet compression profile 8 and the reflected shock wave 5. These splines are the generatrix of the central cone of the ramjet composite extended-range projectile, and the end of the generatrix of the central cone of the ramjet composite extended-range projectile is located on the central axis 10. The central cone generatrix 9 of the ramjet compound extended-range projectile and the air intake compression profile 8 are rotated 360° around the central axis 10, and the resulting closed surface is the central cone 11 of the ramjet compound extended-range projectile.

[0044] (2) Based on the shock wave flow field designed in step (1), the inner wall generatrix 17 and the outer wall generatrix 18 of the ramjet composite extended-range projectile body are designed at the shock wave intersection point to generate the ramjet composite extended-range projectile body. Taking the intersection point 4 of the incident shock wave and the reflected shock wave as the lip point of the air inlet, two polymorphic curves are designed along the flow direction of the hypersonic airflow 1. The first section intersects at the lip point of the air inlet, and the second section is a straight line segment along the flow direction of the hypersonic airflow 1. The curve near the central cone 11 of the ramjet composite extended-range projectile is taken as the inner wall generatrix 17 of the ramjet composite extended-range projectile body, and the other is taken as the outer wall generatrix 18 of the ramjet composite extended-range projectile body. The generatrix 17 of the inner wall surface of the ram-pressed composite extended-range projectile body and the generatrix 18 of the outer wall surface of the ram-pressed composite extended-range projectile body rotate 360° around the central axis 10 to generate the ram-pressed composite extended-range projectile body structure, including the inner wall surface 19 and the outer wall surface 23 of the ram-pressed composite extended-range projectile body.

[0045] (3) Based on the projectile body generated in step (2), a ramjet composite extended-range projectile tail nozzle is designed at the tail end to complete the overall structural design of the ramjet composite extended-range projectile body 14. By extending the outer wall generatrix 18 of the ramjet composite extended-range projectile body along the hypersonic airflow 1 direction, the outer wall generatrix 15 of the ramjet composite extended-range projectile tail nozzle is obtained; based on the end of the inner wall generatrix 17 of the ramjet composite extended-range projectile body, multiple splines are designed along the hypersonic airflow 1 flow direction to obtain the inner wall generatrix 12 of the ramjet composite extended-range projectile tail nozzle; and the inner wall generatrix 12 of the ramjet composite extended-range projectile tail nozzle and the outer wall generatrix 15 of the ramjet composite extended-range projectile tail nozzle have the same design length along the hypersonic airflow 1 flow direction. The generatrix 12 of the inner wall surface of the ramjet extended-range projectile's tail nozzle and the generatrix 15 of the outer wall surface of the ramjet extended-range projectile's tail nozzle are rotated 360° around the central axis 10 to obtain the inner wall surface 13 and the outer wall surface 24 of the ramjet extended-range projectile's tail nozzle. Curved surfaces are designed to enclose the tail of the inner wall surface 13 and the outer wall surface 24 of the ramjet extended-range projectile's tail nozzle, completing the overall structural design of the ramjet extended-range projectile body 14. The designed ramjet extended-range projectile body 14 is a solid with a certain wall thickness.

[0046] (4) A closed curve is designed along the direction perpendicular to the central axis 10. The closed curve is elliptical in shape, with arcs of unequal radii at both ends. The arc near the air intake throat has a larger radius. The arcs are connected by two straight lines, and the arcs are tangent to the straight lines. The projection curve of the closed curve on the central cone 11 of the ramjet composite extended-range projectile is the inner wall curve 25 of the wing catapult channel. An offset curve of the inner wall curve 25 of the wing catapult channel is designed on the outer side in the radial direction. The offset distance is greater than 1 cm and less than the axial distance to the air intake throat. The offset curve of the inner wall curve 25 of the wing catapult channel is the outer wall curve 28 of the wing catapult channel. The offset distance is the thickness of the wall of the wing catapult channel 21. The inner wall 25 curve of the wing ejection channel and the outer wall 28 curve of the wing ejection channel extend in a direction with an angle of 60° along the flow direction, intersecting with the central cone 11 of the ramjet composite extended-range projectile and the body of the ramjet composite extended-range projectile, respectively, to form the wall of the wing ejection channel 21. The cross-section of the wing ejection channel 21 is quasi-elliptical, and the shape of the quasi-elliptical shape is the same at different heights; the extension direction of the wing ejection channel 21 wall is the sweep angle of the wing 22.

[0047] (5) Design the ejection device 26 according to the curve of the inner wall surface 25 of the wing ejection channel in step (4). The outer contour of the ejection device 26 is an offset curve of the inner wall surface 25 of the wing ejection channel in the radial inward direction. The offset distance is controlled at 1cm-2cm. On the one hand, this avoids mutual friction between the ejection device 26 and the inner wall surface 25 of the wing ejection channel, which would generate resistance and make ejection difficult. On the other hand, it ensures the heat dissipation of the ejection device 26 and ensures that the wing ejection channel 21 has sufficient ejection strength, ensuring that the ejection direction is the extension direction of the wing ejection channel 21. The ejection device 26 contains a speed sensor. When the ramjet composite extended-range projectile does not reach supersonic flight conditions, the ejection device 26 is in a retracted state, close to the surface of the central cone 11 of the ramjet composite extended-range projectile. When the flight Mach number reaches the supersonic condition, the ejection device 26 immediately ejects to the same horizontal height as the outer wall surface 23 of the ramjet composite extended-range projectile body. When the velocity sensor is working, the offset distance between the ejection device 26 and the outer wall surface 23 of the ramjet extended-range projectile is small, making it approximately a seamless wall surface. In the non-ejection state, the total depth of the wing 22 and the ejection device 26 is less than the total depth of the wing ejection channel 21, ensuring that the wing 22 can be completely hidden within the outer wall surface 23 of the ramjet extended-range projectile under these flight conditions. The wing root profile of the wing 22 is an offset curve that is radially inward from the curve of the inner wall surface 25 of the wing ejection channel. The offset distance of the wing root profile is greater than 2mm. On the one hand, during ejection, the wing 22 can eject normally and avoid wear caused by friction with the inner wall surface 25 of the wing ejection channel. On the other hand, when the offset distance of the wing root profile is less than the profile of the ejection device 26, the gap between the ejection device 26 and the inner wall surface 25 of the wing ejection channel can be reduced after the wing 22 is ejected. The wing 22 is connected to the catapult 26 by a bellows, which ensures the durability and wide adaptability of the connector and facilitates the detachable replacement of the wing 22.

[0048] In step (6), the wing ejection channels 21, ramjet wings 22, and ejection devices 26 at other locations of the ramjet composite extended-range projectile are designed using an array method, thus completing the overall design of a concealed, controllable folding-wing ramjet composite extended-range projectile. The array angle is 90°, and there are four sets of wing ejection channels 21, ramjet wings 22, and ejection devices 26 on the ramjet composite extended-range projectile, ensuring the integrity and strict symmetry of the overall layout of the concealed, controllable folding-wing ramjet composite extended-range projectile.

[0049] This invention aims to propose a concealed, controllable folding-wing ramjet-assisted composite extended-range projectile and its design method. While retaining the inherent advantages of ramjet-assisted composite projectiles, a concealed, controllable folding wing is designed and applied to the projectile, thus completing the design of a concealed, controllable folding-wing ramjet-assisted composite projectile. In this invention, the ejection device is in a retracted state, and the wing is completely integrated within the ejection channel, thus concealing the wing within the projectile body. During flight, when the projectile reaches supersonic speeds, the wing rapidly deploys within the ejection channel, ejecting onto the surface of the projectile to perform its function. This concealed, controllable folding-wing ramjet-assisted composite projectile and its design method reduce the space occupied by the wing in external storage and facilitate the transportation of the projectile. The wing is connected to the central cone of the ramjet composite extended-range projectile via a catapult. The wing type can be selected according to the flight mission of the ramjet composite extended-range projectile, which reduces the production cost of the ramjet composite extended-range projectile and improves its wide applicability. The design of the wing trajectory can ensure that the geometry of the folding wing is controllable.

[0050] Based on the disclosure and teachings of the foregoing specification, those skilled in the art can make changes and modifications to the above embodiments. Therefore, the present invention is not limited to the specific embodiments disclosed and described above, and some modifications and changes to the invention should also fall within the protection scope of the claims of the present invention. Furthermore, although some specific terms are used in this specification, these terms are only for convenience of explanation and do not constitute any limitation on the present invention.

Claims

1. A concealed, controllable folding wing ramjet-charged composite extended-range projectile, comprising a central cone and a ramjet-charged composite extended-range projectile body located outside the central cone, wherein the central cone and the ramjet-charged composite extended-range projectile body are coaxially and fixedly connected, characterized in that, The ram-pressed composite extended-range projectile is equipped with a hidden, controllable folding wing, which is detachably and fixedly connected to the central cone via an ejection device. When the ramjet-propelled composite extended-range projectile has not reached the set flight speed, the ejection device is close to the surface of the central cone and the hidden controllable folding wing is located in the ejection channel of the ramjet-propelled composite extended-range projectile body. When the ramjet-propelled composite extended-range projectile reaches the set flight speed, the ejection device pops out and is flush with the outer wall of the ramjet-propelled composite extended-range projectile body. The hidden controllable folding wing unfolds outward from the ejection channel of the ramjet-propelled composite extended-range projectile body. The ram-pressed composite extended-range projectile body is connected to the central cone through a projectile channel. The cross-section of the projectile channel is elliptical, and the elliptical shape is the same at different heights.

2. The stamped composite range extender projectile according to claim 1, characterized in that, The outer wall curve of the ejection channel is an offset curve of the inner wall curve of the ejection channel in the radial outward direction. The offset distance is greater than 1cm and less than the axial distance to the throat of the air intake.

3. The stamped composite range extender projectile according to claim 2, characterized in that, The root profile of the concealed controllable folding wing is an offset curve that is radially inward from the inner wall curve of the wing ejection channel, with an offset distance of more than 2mm.

4. The stamped composite range extender projectile according to claim 1, characterized in that, The ejection device is equipped with a speed sensor, which is used to measure the flight speed of the ramjet composite extended-range projectile. When the ramjet composite extended-range projectile has not reached the set flight speed, the ejection device is in a retracted state. When the ramjet composite extended-range projectile has reached the set flight speed, the ejection device is in an extended state. In the retracted state, the total depth of the concealed controllable folding wing and the ejection device is less than the total depth of the ejection channel.

5. The stamped composite range extender projectile according to claim 4, characterized in that, The set flight speed is Mach 0.9-2.

6. The stamped composite range extender projectile according to claim 1, characterized in that, The hidden controllable folding wings are provided in more than three units, which are symmetrically distributed along the central axis of the cone.

7. The stamped composite range extender projectile according to claim 6, characterized in that, The concealed, controllable folding wing is detachably and fixedly connected to the ejection device via a corrugated pipe.

8. The stamped composite range extender projectile according to claim 1, characterized in that, The composite range-extending missile body also includes a tail nozzle.

9. A design method for a concealed, controllable folding wing ram-pressed composite extended-range projectile, characterized in that, Includes the following steps: (1) Design the incident shock wave, generate the internal contraction shock wave flow field, obtain the inlet compression profile, and complete the design of the generatrix of the central cone of the ramjet composite extended range projectile, and generate the central cone of the ramjet composite extended range projectile; (2) Based on the shock wave flow field designed in step (1), design the inner wall generatrix and the outer wall generatrix of the ram-pressed composite range-extended projectile body at the shock wave intersection to generate the ram-pressed composite range-extended projectile body. (3) Based on the projectile body generated in step (2), design the tail nozzle of the ramjet composite extended range projectile at the tail end to complete the overall structural design of the ramjet composite extended range projectile body. (4) Design the inner and outer wall curves of the wing catapult channel to complete the design of the wing catapult channel; (5) Based on the wing ejection channel in step (4), design the ejection device and the hidden controllable folding wing; (6) By using an array method, designing wing ejection channels at other locations, concealed controllable folding wings and ejection devices, the ramjet composite extended-range projectile described in any one of claims 1-8 can be obtained.

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