An aircraft wing apparatus, drone and cruise missile

Abstract

The embodiment of the present application relates to an aircraft wing device, comprising a shell, a wing aerodynamic center adjusting assembly, a wing assembly, a linear potentiometer and a cover; the shell comprises a shell body and a slide rail on the inner side wall of the shell body; the wing aerodynamic center adjusting assembly comprises a wing unfolding pushing part and a wing unfolding angle adjusting part; the wing unfolding pushing part and the wing unfolding angle adjusting part are symmetrically arranged at the two ends of the shell body; the wing assembly comprises a wing mounting seat and a wing; the wing mounting seat comprises a wing mounting seat body and a slide groove arranged on the side of the wing mounting seat body; the slide groove is connected with the slide rail; a group of wings are arranged on the top of the wing mounting seat body; the leading edge of the wing is provided with a slide column; the linear potentiometer is arranged on the side of the wing mounting seat body and below the slide groove, and is used for monitoring the axial position of the wing; the cover is arranged on the top of the wing, and the bottom surface of the cover is provided with a slide way, and the slide way is connected with the slide column.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to an aircraft wing device, a UAV and a cruise missile. BACKGROUND

[0002] At present, the wings of UAVs and cruise missiles are mainly divided into fixed wings and folding wings. The fixed wings are fixedly installed on the body of the aircraft during the general assembly of the aircraft, and the wing state remains unchanged during launching and flight. The main advantages of the fixed wings are simple structure, low cost and high reliability. The folding wings are connected to the body of the UAV / cruise missile through a folding mechanism, and can be folded inside or on the surface of the body before launching. The main advantages of the folding wings are that the lateral size of the UAV / cruise missile is reduced, and the UAV / cruise missile is convenient to transport and launch.

[0003] However, the states of the two wings remain unchanged after launching, i.e. during flight. Even after the folding wings are unfolded, the wing unfolding angle and the relative position of the wing and the body are fixed and unchanged.

[0004] However, the demand for static stability of the UAV changes during launching, flight and landing, and the demand for static stability of the cruise missile also changes during different stages of flight. The current structure of the wing / cruise missile cannot meet the changing demand, and the UAV / cruise missile cannot always maintain a high-efficiency and high-reliability flight state. SUMMARY

[0005] The present application aims at the defects of the prior art, and provides an aircraft wing device, a UAV and a cruise missile.

[0006] To achieve the above-mentioned purpose, the first aspect of the present application provides an aircraft wing device, which comprises a shell, a wing body aerodynamic center adjusting assembly, a wing body assembly, a linear potentiometer and a cover body.

[0007] The shell comprises a shell body and a sliding rail located on the inner side wall of the shell body.

[0008] The wing body aerodynamic center adjusting assembly comprises a wing body unfolding pushing part and a wing body unfolding angle adjusting part; the wing body unfolding pushing part and the wing body unfolding angle adjusting part are symmetrically arranged at two ends of the shell body.

[0009] The wing body assembly comprises a wing body mounting seat and a group of wing bodies.

[0010] The wing body mounting seat comprises a wing body mounting seat body and a sliding groove arranged on the side surface of the wing body mounting seat body; the sliding groove is connected with the sliding rail in a matched mode, so that the wing body mounting seat slides relative to the shell.

[0011] The set of wings are arranged on the top of the wing mounting base body; the leading edge of the wings has a slide post;

[0012] The linear potentiometer is arranged on the side of the wing mounting base body and below the slide groove, for monitoring the axial position of the wings;

[0013] The cover is arranged on the top of the wings, the bottom surface of the cover has a slide with a preset angle along the direction of the wings, the slide and the slide post are connected in cooperation, so that the wings and the cover are connected in sliding;

[0014] The wing unfolding pushing component generates a first driving force according to the received wing unfolding signal, drives the wing mounting base body to slide along the first direction of the shell body, so as to drive the wings on the top of the wing mounting base body to open along the slide, when the wing mounting base body slides to contact with the wing unfolding angle adjusting component, the wing mounting base body is locked with the wing unfolding angle adjusting component; the wing unfolding angle adjusting component generates a second driving force according to the received function conversion signal, drives the wing mounting base to slide along the second direction of the shell body, so as to adjust the unfolding angle of the wings, and the linear potentiometer monitors the sliding position of the wings in real time, wherein the second direction is the opposite direction of the first direction.

[0015] Preferably, the wing mounting base further comprises a wing connecting part; the wing connecting part is arranged on the top of the wing mounting base body, for connecting the wing mounting base with the wings.

[0016] Further preferably, the wing connecting part is a ring-shaped step, comprising an upper step ring and a lower step ring; the upper step ring has an upper annular groove, and the lower step ring has a lower annular groove; the outer diameter of the upper annular groove is smaller than the outer diameter of the lower annular groove.

[0017] More preferably, the set of wings comprises a first wing and a second wing; the leading edge of the first wing has a first connecting ring, and the leading edge of the second wing has a second connecting ring; the diameter of the first connecting ring matches the outer diameter of the upper annular groove, and the diameter of the second connecting ring matches the outer diameter of the lower annular groove.

[0018] Preferably, the wing unfolding pushing component is an actuator cylinder; the power output part of the actuator cylinder extends into the shell body, for pushing the wing mounting base to slide along the shell body.

[0019] Preferably, the wing mounting base further comprises a locking mechanism; the locking mechanism is arranged on the end face opposite to the wing unfolding pushing component of the wing mounting base body.

[0020] Further preferably, the wing body opening angle adjusting component comprises a locking member, a screw rod and a motor;

[0021] The locking member has a threaded hole and a locking hole; the locking hole matches the locking mechanism and is used for locking the wing body mounting seat;

[0022] One end of the screw rod is connected with the output of the motor, and the other end is connected with the locking member through the threaded hole.

[0023] Preferably, the length of the slide rail matches the distance between the wing body mounting seat and the wing body opening angle condition component.

[0024] In the second aspect, the present application provides a UAV, which comprises the aircraft wing device according to any one of the first aspect.

[0025] In the third aspect, the present application provides a cruise missile, which comprises the aircraft wing device according to any one of the first aspect.

[0026] The aircraft wing device provided by the embodiment of the present application comprises a slide rail arranged on the inner side wall of the shell and a slide groove arranged on the side surface of the wing body mounting seat, so that the wing body mounting seat can slide along the first direction of the shell under the driving of the wing body opening pushing component, thereby driving the wing body located on the top of the wing body mounting seat to open along the slide rail of the cover body, and the wing body opening angle adjusting component is locked with the wing body mounting seat, which overcomes the air damping moment suffered by the wing body in flight, so that the wing body can still maintain a stable position under the driving of the wing body opening angle adjusting component. When it is necessary to adjust the opening angle of the wing body, the wing body opening angle adjusting component drives the wing body mounting seat to move along the second direction of the shell, thereby adjusting the opening angle of the wing body, and the linear potentiometer can monitor the axial sliding position of the wing body in real time and record the aerodynamic center of the aircraft wing device. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 FIG. 1 is a sectional view of the aircraft wing device provided by the embodiment of the present application;

[0028] Figure 2 FIG. 2 is another sectional view of the aircraft wing device provided by the embodiment of the present application;

[0029] Figure 3 FIG. 3 is a partial sectional view of the aircraft wing device provided by the embodiment of the present application;

[0030] Figure 4 FIG. 4 is a partial top view of the aircraft wing device provided by the embodiment of the present application;

[0031] Figure 5 FIG. 5 is a structural view of the second wing body provided by the embodiment of the present application;

[0032] Figure 6 A structural diagram of a cover provided for an embodiment of the present application;

[0033] Figure 7 A partial side sectional view of an aircraft wing device provided for an embodiment of the present application;

[0034] Figure 8 One of the wing body state schematic diagrams provided for an embodiment of the present application;

[0035] Figure 9 One of the wing body state schematic diagrams provided for an embodiment of the present application;

[0036] Figure 10 One of the wing body state schematic diagrams provided for an embodiment of the present application. DETAILED DESCRIPTION

[0037] In order to make the objectives, technical solutions and advantages of the present application clearer, the present application will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application.

[0038] The technical solutions of the present application will be further described in detail below with reference to the accompanying drawings and embodiments.

[0039] The aircraft wing device provided by the embodiment of the present application can be applied to a UAV / cruise missile, can meet the demand of the UAV / cruise missile for static stability in different stages, optimizes the aerodynamic layout of the UAV / cruise missile, and improves the maneuverability, reliability and stability of the UAV / cruise missile.

[0040] Embodiment one

[0041] Figure 1 One of the sectional views of the aircraft wing device provided for an embodiment of the present application will be described below in combination with Figure 1 The technical solutions of the present application will be described in specific embodiments.

[0042] The aircraft wing device provided by the embodiment of the present application mainly comprises a shell 1, a wing body assembly 2, a cover 3, a wing body aerodynamic center adjusting assembly 4 and a linear potentiometer (not shown in the figure).

[0043] The shell 1 is a support structure of the aircraft wing device, and specifically comprises a shell body 11 and a slide rail. The structure of the shell body 11 can specifically be a long cuboid without a cover. The slide rail is specifically located at the inner side wall of the shell body 11, i.e. is arranged in parallel with the long side of the long cuboid. In order to maintain the balance and stability of the wing body assembly 2 during sliding, as a preferred solution, a linear potentiometer is arranged on the slide rail. Figure 2As shown, the slide rail includes a first slide rail (not shown in the figure) and a second slide rail 120. The first slide rail is arranged opposite to the second slide rail 120, and the depth of the first slide rail is less than that of the second slide rail 120 for facilitating the subsequent installation of the linear potentiometer.

[0044] The wing assembly 2 specifically includes a wing mounting seat 21 and a set of wings 22.

[0045] The wing mounting seat 21 is a mounting and supporting structure of the wings 22, and is also an important structure for realizing the axial movement of the wings along the shell 1. In combination with Figure 3 As shown, the wing mounting seat 21 specifically includes a wing mounting seat body 210 and a slide groove (not shown in the figure). The wing mounting seat body 210 is axially provided with a through hole 2101. The slide groove is arranged on the side surface of the wing mounting seat body 210.

[0046] In a preferred scheme, the wing mounting seat 21 further includes a linear potentiometer mounting groove (not shown in the figure). The linear potentiometer mounting groove can be specifically arranged on the side surface of the wing mounting seat body 210 and below the slide groove, for facilitating the subsequent installation and fixation of the linear potentiometer 5.

[0047] In another preferred scheme, the wing mounting seat 21 further includes a locking mechanism 211. The locking mechanism 211 is specifically arranged on one end surface of the wing mounting seat body 210 and above the through hole 2101. In this example, the locking mechanism 211 is specifically realized in the form of a protruding structure.

[0048] Further, the wing mounting seat 21 further includes a wing connecting portion 212. The wing connecting portion 212 is arranged on the top of the wing mounting seat body 210 and protrudes above the top of the shell body 11, and is mainly used for the fixation of the set of wings 22. By way of example but not limitation, the wing connecting portion 212 of the present application is a ring-shaped step, and specifically includes an upper step ring 2121 and a lower step ring 2122. The upper step ring 2121 has an upper annular groove (not shown in the figure), and the lower step ring 2122 has a lower annular groove (not shown in the figure), wherein the outer diameter of the upper annular groove is less than that of the lower annular groove.

[0049] Further in combination with Figure 4 As shown in the figure, the set of wings 22 is arranged on the top of the wing mounting seat body 210, and specifically includes a first wing 221 and a second wing 222. The leading edge of the first wing 221 has a first connecting ring (not shown in the figure), and the trailing edge of the second wing 222 has a second connecting ring (not shown in the figure). Figure 5As shown, the leading edge of the second wing body 222 has a second connecting ring 2221, and the diameter of the first connecting ring is smaller than that of the second connecting ring 2221. The diameter of the first connecting ring matches the outer diameter of the upper annular groove, so that the first connecting ring is in sliding connection with the upper stepped ring 2121; the diameter of the second connecting ring 2221 matches the outer diameter of the lower annular groove, so that the second connecting ring 2221 is in sliding connection with the lower stepped ring 2122, thereby realizing the connection between the wing body 22 and the wing body mounting seat 21. The provision of the upper and lower annular grooves limits the wing body 22, preventing it from moving up and down during flight.

[0050] Further, the leading edge of the wing body 22 also has a slide column 220. The slide column 220 is located outside the first connecting ring and outside the second connecting ring 2221.

[0051] The wing body mounting seat 21 is connected with the slide rail through the slide groove, and can slide along the axis of the shell 1, thereby driving the wing body 22 to slide along the axis of the shell 1.

[0052] As shown in Figure 6 , the cover body 3 is the main structure for guiding and limiting the unfolding of the wing body 22, and the bottom surface of the cover body 3 has a slide 31 with a preset angle along the unfolding direction of the wing body 22. The length, position and shape of the slide 31 are determined according to the actual requirements of the aircraft matched with the aircraft wing, for example, to meet the requirements of the static stability of the aircraft. By way of example but not limitation, the shape of the slide 31 can be linear. When the cover body 3 is covered on the top of the wing body 22, the slide 31 and the slide column 220 are connected in cooperation, so that the wing body 22 and the cover body 3 are in sliding connection.

[0053] The wing body aerodynamic center adjusting assembly 4 is the main structure for adjusting the aerodynamic center of the aircraft wing device. As shown in Figure 3 and Figure 7 , it specifically includes a wing body unfolding pushing component 41 and a wing body unfolding angle adjusting component 42.

[0054] The wing body unfolding pushing component 41 is a structure for providing power for the wing body mounting seat 21 to move in the first direction along the axis of the shell body 11, which is specifically realized by an actuator. The actuator is arranged at one end of the shell body 11, and the power output part extends into the shell body 11. It should be noted that during the specific work of the aircraft wing device, the unfolding time of the wing body 22 can be controlled by adjusting various parameters of the actuator.

[0055] The wing body unfolding angle adjusting component 42 is a power structure for adjusting the unfolding angle of the wing body, which is symmetrically arranged with the wing body unfolding pushing component 41, i.e. located at the other end of the shell body 11.

[0056] In this example, the wing deployment angle adjustment component 42 specifically includes a locking element 421, a motor 422, and a lead screw 423.

[0057] The locking element 421 is a structure that limits and locks the wing mounting base 21 when it moves along the first axial direction. It has a threaded hole 4211 and a locking hole 4212.

[0058] One end of the lead screw 423 is connected to the output of the motor 422, and the other end passes through the threaded hole 4211 and is connected to the locking member 421. When the motor 422 drives the lead screw 423 to rotate, it can drive the locking member 421 to move axially. The outer diameter of the lead screw 423 is smaller than the diameter of the through hole 2101, that is, after the lead screw 423 passes through the locking member 421, it can be inserted into the through hole of the wing mounting base 21, but there is no contact between the lead screw 423 and the wing mounting base 21.

[0059] The locking hole 4212 matches the locking mechanism 211, locking the wing mounting base 21 and the locking element 421 to form a fixed connection. The self-locking function of the lead screw 423 overcomes the air damping torque on the wing 22, ensuring the wing remains stable in a non-powered state. When a function switch is required, the motor 422 drives the lead screw 423 to rotate, which in turn moves the wing mounting base 21 along the second axial direction via the locking element 421, thereby adjusting the deployment angle of the wing 22 to achieve the effect of adjusting the aerodynamic center of the aircraft wing.

[0060] To detect the axial position of the airfoil in real time, this application includes a linear potentiometer 5. The linear potentiometer 5 is installed in a linear potentiometer mounting slot.

[0061] The above describes the components of an aircraft wing device and the connection relationships between them. The working principle of the aircraft wing will be described below.

[0062] like Figures 8-10 The diagram shows various configurations of the aircraft wing assembly within the UAV 100 / loitering munition 100. Figure 8 This is the state before the wings are deployed. Figure 9 This is the state when the wing is fully deployed. Figure 10 This refers to the state when the wing is deployed at a certain angle.

[0063] The wing deployment push component 41 generates a first driving force based on the received wing deployment signal, driving the wing mounting base body 210 to slide along the axial direction of the housing body 11 in a first direction, thereby causing the wing 22 on the top of the wing mounting base body 210 to open along the slide rail 31 of the cover 3. When the wing mounting base body 210 slides to contact the locking member 421 of the wing deployment angle adjustment component 42, that is, when the wing is deployed in place, such as... Figure 9As shown, the locking mechanism 211 of the wing body mounting seat 21 cooperates with the locking hole 4212 of the locking piece 421, and the two are locked to form a fixed connection.

[0064] The motor 422 of the wing body unfolding angle adjusting part 42 generates a second driving force according to the received function conversion signal, drives the lead screw 423 to rotate, thereby driving the locking piece 421 to slide along the axial second direction of the shell body 11, thereby driving the wing body mounting seat body 210 to slide along the second direction; wherein the second direction is the opposite direction of the first direction; when the wing body mounting seat body 210 slides along the second direction, the wing body 22 can be driven to move in the opposite direction of the slide 31, thereby adjusting the unfolding angle of the wing body 22, as shown in the figure. Figure 10 As shown, at the same time, the linear potentiometer 5 monitors the sliding position of the wing body 22 in real time, records the aerodynamic center of the aircraft wing device, and can adjust the static stability of the unmanned aerial vehicle / patrol missile in real time according to the aerodynamic center of the aircraft wing device and the center of gravity of the unmanned aerial vehicle / patrol missile, thereby maintaining the good aerodynamic performance of the unmanned aerial vehicle / patrol missile, and improving the maneuverability, reliability and stability of the unmanned aerial vehicle / patrol missile.

[0065] The aircraft wing device provided by the embodiment of the present application can slide along the first direction of the shell under the driving of the wing body unfolding pushing part, thereby driving the wing body located at the top of the wing body mounting seat to unfold along the slide of the cover body, and the wing body unfolding angle adjusting part is locked with the wing body mounting seat, which overcomes the air damping moment received by the wing body during flight, so that the wing body can still maintain a stable position under the driving of the wing body unfolding angle adjusting part. When it is necessary to adjust the unfolding angle of the wing body, the wing body unfolding angle adjusting part drives the wing body mounting seat to move along the second direction of the shell, thereby adjusting the unfolding angle of the wing body, and at the same time, the linear potentiometer can monitor the axial sliding position of the wing body in real time and record the aerodynamic center of the aircraft wing device.

[0066] Embodiment two

[0067] The embodiment two of the present application provides an unmanned aerial vehicle, which comprises the aircraft wing device according to any one of the above-mentioned embodiment one.

[0068] Embodiment three

[0069] The embodiment three of the present application provides a patrol missile, which comprises the aircraft wing device according to any one of the above-mentioned embodiment one.

[0070] The above detailed description of the specific embodiments of the present application has been given to understand the purpose, technical solutions and beneficial effects of the present application. It should be understood that the above description is only a specific embodiment of the present application and is not used to limit the protection scope of the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A wing device for an aircraft, characterized in that, The aircraft wing assembly includes: a shell, a wing body aerodynamic center adjustment assembly, a wing body assembly, a linear potentiometer, and a cover; The housing includes a housing body and a slide rail located on the inner sidewall of the housing body; The wing aerodynamic center adjustment assembly includes a wing deployment thrust component and a wing deployment angle adjustment component; the wing deployment thrust component and the wing deployment angle adjustment component are symmetrically arranged at both ends of the housing body; The wing assembly includes a wing mounting base and a set of wing bodies; The wing mounting base includes a wing mounting base body and a sliding groove disposed on the side of the wing mounting base body; the sliding groove is connected to the slide rail, so that the wing mounting base slides relative to the shell; The set of wing bodies is disposed on the top of the wing body mounting base body; the leading edge of the wing body has a sliding column; The linear potentiometer is disposed on the side of the wing mounting base body and below the slide groove, and is used to monitor the axial position of the wing. The cover is disposed on the top of the wing, and the bottom surface of the cover has a slide rail at a preset angle along the direction of the wing's unfolding. The slide rail and the slide post are connected to each other, so that the wing and the cover are slidably connected. The wing deployment push component generates a first driving force based on the received wing deployment signal, driving the wing mounting base body to slide along a first direction of the housing body, thereby causing the wing at the top of the wing mounting base body to open along the slide rail. When the wing mounting base body slides to contact the wing deployment angle adjustment component, the wing mounting base body and the wing deployment angle adjustment component lock together. The wing deployment angle adjustment component generates a second driving force based on the received function conversion signal, driving the wing mounting base to slide along a second direction of the housing body, thereby adjusting the deployment angle of the wing. At the same time, the linear potentiometer monitors the sliding position of the wing in real time, wherein the second direction is the opposite direction of the first direction.

2. The aircraft wing device according to claim 1, characterized in that, The wing body mounting base also includes a wing body connecting part; the wing body connecting part is disposed on the top of the wing body mounting base body and is used to connect the wing body mounting base to the wing body.

3. The aircraft wing device according to claim 2, characterized in that, The wing body connection is an annular step, including an upper step ring and a lower step ring; the upper step ring has an upper annular groove, and the lower step ring has a lower annular groove, the outer diameter of the upper annular groove is smaller than the outer diameter of the lower annular groove.

4. The aircraft wing device according to claim 3, characterized in that, The set of wing bodies includes a first wing body and a second wing body; the leading edge of the first wing body has a first connecting ring, and the leading edge of the second wing body has a second connecting ring; the diameter of the first connecting ring matches the outer diameter of the upper annular groove, and the diameter of the second connecting ring matches the outer diameter of the lower annular groove.

5. The aircraft wing device according to claim 1, characterized in that, The wing deployment propulsion component is an actuator; the power output part of the actuator extends into the housing body to push the wing mounting base to slide along the housing body.

6. The aircraft wing device according to claim 1, characterized in that, The wing mounting base also includes a locking mechanism; the locking mechanism is disposed on one end face of the wing mounting base body opposite to the wing deployment push component.

7. The aircraft wing device according to claim 6, characterized in that, The wing deployment angle adjustment components include locking mechanisms, lead screws, and motors; The locking element has a threaded hole and a locking hole; the locking hole matches the locking mechanism and is used to lock the wing mounting base. One end of the lead screw is connected to the output of the motor, and the other end passes through the threaded hole and is connected to the locking member.

8. The aircraft wing device according to claim 1, characterized in that, The length of the slide is matched with the distance between the wing mount and the wing deployment angle condition component.

9. A drone, characterized in that, The drone includes the aircraft wing device as described in any one of claims 1 to 8.

10. A loitering munition, characterized in that, The loitering munition includes the aircraft wing device described in any one of claims 1 to 8.

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