Variable shape device and missile adapted to high heat flux environment

Abstract

The application provides a variable shape device and a missile suitable for a high heat flow environment, comprising a variable outer wing, a variable inner wing, a servo driving mechanism and a sealing elastic assembly, the wing root of the variable outer wing is fastened and installed on the surface of a missile body structure, the variable inner wing is arranged inside the variable outer wing and coaxially arranged with the variable outer wing, the servo driving mechanism is arranged inside the variable inner wing, the servo driving mechanism can drive the variable inner wing to make extension and contraction movement to switch between a contracted state and an unfolded state; a plurality of limiting pieces are arranged between the variable outer wing and the variable inner wing, the variable outer wing and the variable inner wing are fastened and connected through the limiting pieces, and the sealing elastic assembly is arranged at any connecting position of the variable outer wing and the variable inner wing. The application realizes heat protection of a large gap between the variable inner wing and the variable outer wing and arrangement design in a limited space, realizes lightweight of the variable device, and the missile realizes high lift-drag ratio at high altitude and low dynamic pressure and low drag performance at low altitude and high dynamic pressure through the variable device, and the overall performance of the missile is improved.

Description

Technical Field

[0001] This invention relates to the field of missile technology, specifically to a shape-changing device and a missile adapted to high heat flux environments. Background Technology

[0002] Faced with the current operational environment of large airspace and wide speed range, as well as the requirements of multi-mission operations, traditional fixed-shape aircraft cannot meet the needs of different flight conditions and missions. Variable-shape aircraft, on the other hand, can autonomously and timely change their shape according to flight missions, speeds, and environments, using different aerodynamic configurations to meet different flight missions. This optimizes the aerodynamic and flight performance of the aircraft throughout the entire flight phase, thus necessitating the development of variable-shape aircraft technology.

[0003] As missiles travel at increasingly higher speeds and experience higher heat fluxes, current variable shape devices are only suitable for low-speed, low-heat-flux aircraft or missiles, and are inadequate for thermal protection under high-speed, high-heat-flux conditions. Therefore, there is a need to invent a variable shape device adapted to high-heat-flux environments. Summary of the Invention

[0004] In view of the deficiencies in the prior art, the purpose of this invention is to provide a shape-changing device and missile that can adapt to high heat flux environments.

[0005] According to the present invention, a deformable shape device adapted to a high heat flux environment includes a deformable outer wing, a deformable inner wing, a servo drive mechanism, and a sealing elastic component. The root of the deformable outer wing is fastened to the surface of the projectile structure. The deformable inner wing is disposed inside the deformable outer wing and the two are coaxially arranged. The servo drive mechanism is disposed inside the deformable inner wing and can drive the deformable inner wing to perform telescopic movement to switch between a retracted state and an extended state. Multiple limiting members are provided between the deformable outer wing and the deformable inner wing. The deformable outer wing and the deformable inner wing are fastened together by the limiting members. The sealing elastic component is provided at any connection point between the deformable outer wing and the deformable inner wing.

[0006] Preferably, both the deformable outer wing and the deformable inner wing are hollow structures, and both are made of high-temperature alloy steel with a lattice structure.

[0007] Preferably, the inner surface of the deformable outer wing is provided with a wingtip protrusion, and the wingtip protrusion is provided with a groove. The outer surface of the deformable inner wing is correspondingly provided with a wingtip protrusion. The wingtip protrusion of the deformable inner wing and the groove on the wingtip protrusion of the deformable outer wing are engaged. The gap between the groove on the wingtip protrusion of the deformable inner wing and the wingtip protrusion of the deformable outer wing is greater than the relative deformation of the inner and outer wings.

[0008] Preferably, the inner surface of the deformable outer wing is provided with a central boss and a wing root boss, and the outer surface of the deformable inner wing is correspondingly provided with a wing root boss, and the wing root boss of the deformable inner wing can move between the central boss and the wing root boss of the deformable outer wing.

[0009] Preferably, when the deformable inner wing is in a retracted state, the root boss of the deformable outer wing is connected to the root boss of the deformable inner wing; When the deformable inner wing is in the deployed state, the central boss of the deformable outer wing is connected to the root boss of the deformable inner wing, and the wingtip boss of the deformable outer wing is connected to the wingtip boss of the deformable inner wing.

[0010] Preferably, the root boss of the deformable outer wing and the root boss of the deformable inner wing are both L-shaped bosses, and the two are engaged in a snap-fit ​​fit. A vibration damping device is provided on the side of the central boss of the deformable outer wing that is close to the wing root boss of the deformable inner wing.

[0011] Preferably, the wingtip protrusion of the deformable outer wing has a dovetail-shaped groove on the side that fits with the deformable inner wing, and the wing root protrusion of the deformable inner wing has a dovetail-shaped groove on the side that fits with the deformable outer wing, and the sealing elastic component is provided in each of the dovetail-shaped grooves.

[0012] Preferably, the sealing elastic component includes a circular sealing rope with a diameter more than 1.5 times larger than the maximum size of the dovetail groove, and the diameter of the sealing rope on the wingtip boss of the deformable outer wing is larger than the diameter of the sealing rope on the wing root boss of the deformable inner wing.

[0013] Preferably, the servo drive mechanism includes a motor and an actuating rod. The servo drive mechanism is connected to the deformable inner wing via a three-bar linkage. The three-bar linkage includes a main link and two branch links. The main link is fastened to the actuating rod. The two ends of the branch links are respectively connected to the main link and the deformable inner wing. The length of the main link is less than the length of the branch links.

[0014] According to the present invention, a missile employs the aforementioned shape-adapting device for high heat flux environments.

[0015] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention effectively achieves thermal protection of the large gap between the deformable inner and outer wings by adopting a two-stage dynamic sealing device and a multi-protrusion structure.

[0016] 2. This invention achieves the arrangement of deformation devices in a limited space by embedding deformable inner and outer wings, saving space on the missile, and achieves thermal protection and lightweighting of the wing surface by using lattice high-temperature alloy steel material.

[0017] 3. This invention uses the actuator of the servo drive mechanism to drive the three-bar linkage, thereby realizing large-scale extension and retraction of the deformable inner wing in a limited space, with a high transmission ratio.

[0018] 4. By designing a variable shape device, this invention enables large-scale deformation of the missile under high heat flux, achieving high lift-to-drag ratio at high altitude with low dynamic pressure and low drag at low altitude, effectively increasing the missile's combat range and available overload, and improving the overall performance of the missile. Attached Figure Description

[0019] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram illustrating the unfolded shape device of the present invention, which is mainly adapted to high heat flux environments. Figure 2 This is a schematic diagram illustrating the folding of the shape-changing device adapted to high heat flux environments, which is the main feature of this invention. Figure 3 This is a schematic diagram illustrating the main function of the servo drive in this invention.

[0020] As shown in the figure: Deformable outer wing 1 Deformable inner wing 2 Servo drive mechanism 3 Sealing elastic component 4 Vibration damping device 5 Three-bar linkage 6 Detailed Implementation The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0021] Example 1 like Figure 1-3 As shown, a shape-changing device adapted to a high heat flux environment according to the present invention includes: a deformable outer wing 1, a deformable inner wing 2, a servo drive mechanism 3, and a sealing elastic component 4. The root of the deformable outer wing 1 is fastened to the surface of the projectile structure. The deformable inner wing 2 is disposed inside the deformable outer wing 1 and the two are coaxially arranged. The servo drive mechanism 3 is disposed inside the deformable inner wing 2 and can drive the deformable inner wing 2 to perform telescopic movement to switch between a retracted state and an extended state. Multiple limiting members are provided between the deformable outer wing 1 and the deformable inner wing 2, and the deformable outer wing 1 and the deformable inner wing 2 are fastened together by the limiting members. A sealing elastic component 4 is provided at any connection point between the deformable outer wing 1 and the deformable inner wing 2.

[0022] This application relates to large-scale deformation of missiles under high heat flux conditions, effectively increasing the missile's operational range and usable overload. Both the deformable outer wing 1 and the deformable inner wing 2 are hollow structures. The wing root of the deformable outer wing 1 is fixed to the surface of the missile body structure, and the deformable inner wing 2 is located inside the deformable outer wing 1. The deformable inner wing 2 is fixed to the deformable outer wing 1 through limiting components and a sealing elastic component 4. Both the deformable outer wing 1 and the deformable inner wing 2 are made of lattice-type high-temperature alloy steel.

[0023] The inner surface of the deformable outer wing 1 is provided with a wingtip protrusion for the extension and retraction of the deformable inner wing 2. A groove is provided on the wingtip protrusion, and a corresponding wingtip protrusion is provided on the outer surface of the deformable inner wing 2. The wingtip protrusion of the deformable inner wing 2 engages with the groove on the wingtip protrusion of the deformable outer wing 1 to reduce the heat flow velocity at the gaps between the deformable inner wing 2 and the outer shape. The gap between the grooves of the wingtip protrusions of the deformable inner wing 2 and the wingtip protrusions of the deformable outer wing 1 is greater than the relative deformation of the inner and outer wings.

[0024] The inner surface of the deformable outer wing 1 is provided with a central boss and a wing root boss. The wing root boss is used to limit the deformable inner wing 2 when it retracts, and the central boss is used to limit the deformable inner wing 2 when it unfolds and to reduce the heat flow velocity at the deceleration gap. The outer surface of the deformable inner wing 2 is provided with a corresponding wing root boss. The wing root boss of the deformable inner wing 2 moves between the central boss and the wing root boss of the deformable outer wing 1.

[0025] When the deformable inner wing 2 is in a retracted state, the root boss of the deformable outer wing 1 is connected to the root boss of the deformable inner wing 2. When the deformable inner wing 2 is in the deployed state, the central boss of the deformable outer wing 1 is connected to the root boss of the deformable inner wing 2, and the wingtip boss of the deformable outer wing 1 is connected to the wingtip boss of the deformable inner wing 2.

[0026] The root boss of the deformable outer wing 1 and the root boss of the deformable inner wing 2 are both L-shaped bosses, and they are engaged with each other. The root boss of the deformable outer wing 1 and the deformable outer wing 1 are connected by threads. When the deformable inner wing 2 retracts, the two L-shaped bosses contact each other and limit the deformation of the inner wing 2.

[0027] A vibration damping device 5 is provided on the side of the central boss of the deformable outer wing 1 near the wing root boss of the deformable inner wing 2, for vibration damping when the deformable inner wing 2 is fully deployed. Preferably, the vibration damping device 5 is a vibration damping pad with good rigidity.

[0028] A dovetail-shaped groove is provided on the side of the deformable outer wing 1 where it fits with the deformable inner wing 2, and a dovetail-shaped groove is provided on the side of the deformable inner wing 2 where it fits with the deformable outer wing 1. A sealing elastic component 4 is provided in each dovetail-shaped groove to achieve a two-stage heat seal between the deformable inner wing 2 and the deformable outer wing 1.

[0029] The sealing elastic component 4 includes a circular sealing rope with a diameter more than 1.5 times larger than the maximum size of the dovetail groove. The diameter of the sealing rope on the wing tip boss of the deformable outer wing 1 is larger than the diameter of the sealing rope on the wing root boss of the deformable inner wing 2.

[0030] A servo drive mechanism 3 is installed inside the deformable inner wing 2. The servo drive mechanism 3 includes a motor and an actuator rod. When the motor operates, it drives the actuator rod to extend and retract, thereby achieving the extension and retraction of the deformable inner wing 2 through a three-bar linkage 6. The servo drive mechanism 3 is connected to the deformable inner wing 2 via the three-bar linkage 6. The three-bar linkage 6 includes a main link and two branch links. The main link is connected to the two branch links via a hinge structure and is rigidly connected to the actuator rod. The two ends of the branch links are connected to the main link and the deformable inner wing 2 respectively. The two branch links are connected to the two ends of the deformable inner wing 2 via hinges. The length of the main link is less than the length of the branch links. The extension and retraction of the actuator rod of the servo drive mechanism 3 drives the main link to translate, which in turn drives the two branch links to translate, thus achieving the extension and retraction of the deformable inner wing 2.

[0031] Before the servo drive mechanism 3 receives the missile deployment command, the deformable inner wing 2 is in a retracted state, such as... Figure 2 As shown, the two L-shaped protrusions of the deformable outer wing 1 and the deformable inner wing 2 are in contact to limit the movement. At the same time, the contact between the two L-shaped protrusions connects the internal circuit of the missile, giving the deformable inner wing 2 a retraction signal.

[0032] When the servo drive mechanism 3 receives the projectile deployment command, the deformation device extends via the actuator rod of the servo drive mechanism 3, thus deploying the deformable inner wing 2. The maximum deployed state of the deformable inner wing 2 is as follows: Figure 1 As shown, when the root protrusion of the deformable inner wing 2 impacts the vibration damping device 5, the internal circuit of the projectile is activated, giving a signal that the deformable inner wing 2 has been deployed to the designated position.

[0033] During the opening of the deformable inner wing, the deformable inner wing 2 and the deformable outer wing 1 solve the thermal protection problem of the large gap between the deformable inner and outer wings through multiple sealing elastic components 4 and multiple boss designs.

[0034] This invention achieves the arrangement of deformation devices in a limited space by embedding deformable inner and outer wings, saving space on the missile. It also achieves thermal protection and lightweighting of the wing surface by using lattice high-temperature alloy steel material.

[0035] This invention employs a two-stage dynamic sealing device and a multi-protrusion structure, which effectively achieves thermal protection of the large gap between the deformable inner and outer wings.

[0036] This invention achieves large-scale extension and retraction of the deformable inner wing in a limited space by driving the actuating rod of the servo drive mechanism 3 to drive the three-bar linkage 6, with a high transmission ratio.

[0037] Example 2 According to the present invention, a missile employs the shape-shifting device adapted to high heat flux environments as described in Embodiment 1. By designing the shape-shifting device, the missile achieves large-scale deformation under high heat flux environments, realizing high lift-to-drag ratio at high altitudes with low dynamic pressure and low drag at low altitudes. This effectively increases the missile's operational range and available overload, thereby improving the overall performance of the missile.

[0038] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They 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. Therefore, they should not be construed as limitations on this application.

[0039] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A shape-changing device adapted to high heat flux environments, characterized in that, include: The projectile comprises a deformable outer wing (1), a deformable inner wing (2), a servo drive mechanism (3), and a sealing elastic component (4). The deformable outer wing (1) is fixedly mounted at its root on the surface of the projectile structure. The deformable inner wing (2) is located inside the deformable outer wing (1) and the two are coaxially arranged. The servo drive mechanism (3) is located inside the deformable inner wing (2). The servo drive mechanism (3) can drive the deformable inner wing (2) to perform telescopic motion to switch between the retracted state and the extended state. Multiple limiting members are provided between the deformable outer wing (1) and the deformable inner wing (2). The deformable outer wing (1) and the deformable inner wing (2) are fastened together by the limiting members. The sealing elastic component (4) is provided at any connection point between the deformable outer wing (1) and the deformable inner wing (2). The inner surface of the deformable outer wing (1) is provided with a wingtip protrusion, and the wingtip protrusion is provided with a groove. The outer surface of the deformable inner wing (2) is provided with a corresponding wingtip protrusion. The wingtip protrusion of the deformable inner wing (2) and the groove on the wingtip protrusion of the deformable outer wing (1) are engaged. The gap between the wingtip protrusion of the deformable inner wing (2) and the groove on the wingtip protrusion of the deformable outer wing (1) is greater than the relative deformation of the inner and outer wings. The inner surface of the deformable outer wing (1) is provided with a central boss and a wing root boss, and the outer surface of the deformable inner wing (2) is provided with a corresponding wing root boss. The wing root boss of the deformable inner wing (2) moves between the central boss and the wing root boss of the deformable outer wing (1).

2. The shape-changing device adapted to high heat flux environments as described in claim 1, characterized in that, Both the deformable outer wing (1) and the deformable inner wing (2) are hollow structures, and both the deformable outer wing (1) and the deformable inner wing (2) are made of high-temperature alloy steel with a dot matrix.

3. The shape-changing device adapted to high heat flux environments as described in claim 1, characterized in that, When the deformable inner wing (2) is in a retracted state, the root boss of the deformable outer wing (1) is connected to the root boss of the deformable inner wing (2). When the deformable inner wing (2) is in the deployed state, the central boss of the deformable outer wing (1) is connected to the wing root boss of the deformable inner wing (2), and the wingtip boss of the deformable outer wing (1) is connected to the wingtip boss of the deformable inner wing (2).

4. The shape-changing device adapted to high heat flux environments as described in claim 1, characterized in that, The root boss of the deformable outer wing (1) and the root boss of the deformable inner wing (2) are both L-shaped bosses, and they are engaged in a snap-fit ​​fit. A vibration damping device (5) is provided on the side of the central boss of the deformable outer wing (1) near the wing root boss of the deformable inner wing (2).

5. The shape-changing device adapted to high heat flux environments as described in claim 1, characterized in that, The wingtip protrusion of the deformable outer wing (1) is provided with a dovetail-shaped groove on the side that fits with the deformable inner wing (2), and the wing root protrusion of the deformable inner wing (2) is provided with a dovetail-shaped groove on the side that fits with the deformable outer wing (1). The sealing elastic component (4) is provided in any of the dovetail-shaped grooves.

6. The shape-changing device adapted to high heat flux environments as described in claim 5, characterized in that, The sealing elastic component (4) includes a circular sealing rope with a diameter more than 1.5 times larger than the maximum size of the dovetail groove, and the diameter of the sealing rope on the wingtip boss of the deformable outer wing (1) is larger than the diameter of the sealing rope on the wing root boss of the deformable inner wing (2).

7. The shape-changing device adaptable to high heat flux environments as described in claim 1, characterized in that, The servo drive mechanism (3) includes a motor and an actuating rod. The servo drive mechanism (3) is connected to the deformable inner wing (2) via a three-bar linkage (6). The three-bar linkage (6) includes a main link and two branch links. The main link is fastened to the actuating rod. The two ends of the branch links are connected to the main link and the deformable inner wing (2) respectively. The length of the main link is less than the length of the branch links.

8. A missile, characterized in that, The variable shape device adapted to high heat flux environment as described in any one of claims 1-7 is adopted.

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