Morphing wing structure capable of synchronously and continuously changing elongation

Abstract

The invention discloses a morphing wing structure capable of synchronously and continuously changing elongation. The morphing wing structure comprises a synchronous transmission mechanism, a continuous telescopic mechanism, an inner side wing, an outer side wing and a fixed bracket, the synchronous transmission mechanism is used for converting the rotating torque on the symmetry plane of the fuselage into the bilateral synchronous rotating torque in the spanwise direction of the wings; the continuous telescopic mechanism is located in the wing and can drive the wing to complete the continuous variable-elongation action. Variable-elongation mechanism action and aileron steering engine wiring spaces are reserved in the inner side wings; the inner wing inserting piece is a connecting piece of the synchronous transmission mechanism and the inner side wing; the outer wing and the inner wing skin are nested and can continuously translate and slide along the wing spanwise direction under the action of a driving force. The extension lengths of the wings on the two sides can be accurately and synchronously changed according to flight mission requirements, the aerodynamic efficiency of the aircraft in different flight stages is effectively improved, and the risk of flight attitude imbalance caused by asynchronous wing extension length changes is reduced.

Description

Technical Field

[0001] The invention relates to the field of unmanned aerial vehicles, and in particular to a variant wing structure capable of synchronously and continuously varying the length of the wing. Background Art

[0002] With the development of aviation technology, the requirements for aircraft performance are becoming increasingly diverse. In different flight mission phases, such as take-off, cruising, and landing, there are different requirements for the lift-to-drag ratio of the aircraft, and adjusting the wing span is a direct way to change the lift-to-drag ratio. For example, in the cruising phase, wing extension can increase the lift coefficient, allowing the aircraft to maintain flight at a lower output power; when performing high-speed turns and other maneuvers, appropriately shortening the wing span can reduce the aircraft's moment of inertia, allowing the aircraft to change its flight attitude more agilely. The traditional fixed wing structure cannot meet the requirements of such dynamic changes.

[0003] Existing wing span-changing technologies mostly use gear rack mechanisms or crank rocker mechanisms, which have many shortcomings in terms of synchronization, reliability, and structural complexity. For example, both the connecting rod type and the folding type span-changing technologies require precise design and assembly. The numerous connecting rods and joints increase the complexity of the system, making it difficult to ensure the synchronous movement of the left and right wings, which can easily lead to uneven lift distribution in different areas of the wing, and then additional rolling torque will cause the aircraft to produce unexpected rolling motion, and may even enter a dangerous spiral state. In addition, the complex aerodynamic forces and structural deformations generated by the asynchronous changes in the wings may exceed the design expectations of the flight control system, resulting in misjudgment or response lag in the control system, further affecting the navigation safety of the aircraft. Summary of the invention

[0004] In order to solve the above problems, the present invention provides a variant wing structure capable of synchronously and continuously changing the span.

[0005] The present invention provides a variant wing structure capable of synchronously and continuously varying the length of the wing, which adopts the following technical solution: A variant wing structure capable of synchronously and continuously changing the length of the wing, comprising a fixing frame, wing structures arranged on both sides of the fixing frame, and a synchronous transmission mechanism for driving the wing structures on both sides to synchronously extend and retract; The wing structure comprises an inner wing and an outer wing, the outer wing is nested with the inner wing skin, and a continuous telescopic mechanism for driving the outer wing to continuously translate along the wing span is arranged in the inner wing; The continuous telescopic mechanism comprises a threaded guide rod, a linear actuator, a support pipe and a linear actuator; the threaded guide rod is connected to a synchronous transmission mechanism and driven by the synchronous transmission mechanism to rotate around the wing span axis; the linear actuator is fixedly connected to the support pipe and can be driven by the threaded guide rod to perform a translational motion; one end of the support pipe is connected to the outer wing end plate of the outer wing, and the threaded guide rod can rotate to drive the outer wing end plate to translate together with the outer wing; The synchronous transmission mechanism includes a power source, a transmission connecting rod, a driving bevel gear, two driven bevel gears, a driven transmission shaft and a bearing component; the power source is connected to the driving bevel gear through the transmission connecting rod, the two driven bevel gears are symmetrically arranged and both mesh with the driving bevel gear; one end of the driven transmission shaft is connected to the driven bevel gear, and the other end is connected to the threaded guide rod.

[0006] As a preferred embodiment of the present invention, the driven transmission shaft and the threaded guide rod are connected via a universal joint coupling.

[0007] As a preferred embodiment of the present invention, a variable swept shaft is also provided on the fixed frame, the variable swept shaft is connected to the fixed frame via a bearing, a plug-in connector is provided on the variable swept shaft, the inner wing includes an inner wing plug-in, the inner wing plug-in is fixed to the plug-in connector, and a bearing matching the driven transmission shaft is also provided on the plug-in connector.

[0008] As a preferred embodiment of the present invention, the heights of the plug-in connectors of the wing structure on both sides of the fixing frame are different.

[0009] As a preferred embodiment of the present invention, a guide rod bearing fixing piece is also installed on the inner wing plug-in unit, and the guide rod bearing fixing piece is positioned and matched with the threaded guide rod.

[0010] As a preferred embodiment of the present invention, the continuous telescopic mechanism also includes a translation slider, which is arranged in the supporting tube and is rotatably connected to the threaded guide rod. The envelope surface size of the translation slider is smaller than the sliding space after the supporting tube is assembled. An external threaded bearing is also arranged on the translation slider, and the outer ring of the bearing maintains a tangent positional relationship with the surface of the sliding space.

[0011] As a preferred embodiment of the present invention, it also includes an aileron, which is installed at the trailing edge of the outer wing and is connected to the aileron servo.

[0012] As a preferred embodiment of the present invention, an aileron servo installation space is provided inside the outer wing end plate, the aileron servo is arranged in the aileron servo installation space, the aileron servo is connected to the aileron through an aileron connecting rod mechanism, and controls the aileron rudder deflection.

[0013] In summary, the present invention includes at least one of the following beneficial technical effects: 1. The present invention uses a power source to provide a rotational torque with equal rotation speed for the left and right wings through a highly accurate synchronous transmission mechanism, effectively avoiding the risk of flight attitude imbalance caused by asynchronous changes in wing span, effectively ensuring the stability of the aircraft's flight attitude, and significantly improving flight safety; at the same time, the synchronous transmission mechanism uses a driving bevel gear to mesh with two symmetrical driven bevel gears. When the wings need to be folded, the folding direction is exactly the direction in which the two driven bevel gears are disconnected from the driving bevel gear, and the synchronous transmission mechanism will not affect the folding of the wings.

[0014] 2. By setting a universal joint coupling, the height difference of the wings on both sides can be compensated, and the additional harmful vibration and unnecessary torque caused by the assembly accuracy problem when the mechanism is in action can be reduced, which is beneficial to the precise control of the aircraft's attitude stability. The design of the universal joint coupling can also make the wing structure staggered in the upper and lower height directions, which is convenient for wing folding and reduces the space after the wing is folded.

[0015] 3. In terms of lightweight structural design, the present invention makes full use of the internal space of the fuselage and wings, and the variant mechanism ensures that it can work normally and coordinate with each other in a suitable connection mode. At the same time, the design has a certain impact resistance and spatial redundancy, which can ensure the reasonable distribution and transfer of the aircraft's load. According to the actual fuselage space and mission requirements, the design can be developed into a variant aircraft configuration that integrates folding sweep and variable span, which is in line with the evolution trend of aircraft multi-mission adaptability.

[0016] 4. By building the continuous telescopic mechanism into the internal space of the wing, the change of the wing span can be controlled on the one hand, and its supporting pipe can be used as a load-bearing component to provide support for the outer wing and bear the main aerodynamic load on the other hand. The mechanism uses a threaded guide rod as a driving component, which can achieve smooth and precise control of the wing span, thereby adapting to the differentiated needs of the wing span in different flight environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of a variant wing assembly capable of synchronously and continuously changing the length of the wing according to the present invention.

[0018] Figure 2 It is a schematic diagram of the three-dimensional structure of the variant wing of the present invention that can synchronously and continuously change the length.

[0019] Figure 3 It is a top view of the assembly of the synchronous transmission mechanism of the present invention.

[0020] Figure 4 It is a front view of the assembly of the synchronous transmission mechanism of the present invention.

[0021] Figure 5 It is a schematic diagram of the assembly of the continuous telescopic mechanism of the present invention.

[0022] Figure 6 It is a schematic diagram of the inner wing root range assembly of the present invention.

[0023] Figure 7 It is a schematic diagram of the guide rod slider partial assembly of the present invention.

[0024] Figure 8 It is a schematic diagram of the assembly of the wing of the present invention when it is in an unextended state.

[0025] Fig. 9 It is a schematic diagram of the assembly of the wing of the present invention when it is in a fully extended state.

[0026] Among them: 1-inner wing, 2-outer wing, 3-aileron, 4-fixing frame, 5-outer wing end plate, 11-power source, 12-transmission connecting rod, 13-active transmission shaft, 14-driven transmission shaft, 15-plug-in connector, 16-universal joint coupling, 17-variable swept shaft, 18-active bevel gear, 19-driven bevel gear, 21-inner wing plug-in, 22-threaded guide rod, 23-linear actuator, 24-support pipe fitting, 25-guide rod bearing fixing part, 26-aileron servo, 31-guide rod bearing retaining ring, 32-translation slider, 33-external threaded bearing, 34-guide rod end face fixing screw. DETAILED DESCRIPTION

[0027] The following is combined with Figure 1-9 The present invention is described in further detail.

[0028] like Figures 1 to 9 As shown, this embodiment discloses a variant wing structure capable of synchronously and continuously changing the length, including a fixing frame 4, wing structures arranged on both sides of the fixing frame 4, and a synchronous transmission mechanism for driving the wing structures on both sides to synchronously extend and retract.

[0029] The wing structure includes an inner wing 1 and an outer wing 2. The outer wing 2 and the inner wing 1 are nested in the skin. The inner wing 1 is fixed relative to the fuselage. In this embodiment, two variable sweep shafts 17 are also arranged on the fixing frame 4, and a plug-in connector 15 is arranged on the variable sweep shaft 17. The inner wing 1 includes an inner wing plug-in 21, and the inner wing plug-in 21 is fixedly connected to the plug-in connector 15, so that the inner wing 1 is fixedly installed. The variable sweep shaft 17 is connected to the fixing frame 4 through a bearing, and the wing structure can rotate with the variable sweep shaft 17, so as to realize the folding of the wing structure. In this embodiment, the heights of the plug-in connectors 15 of the wing structure on both sides of the fixing frame 4 are different. In this way, when the wing structure needs to be folded, the two wing structures after folding are staggered in the height direction, that is, in the axial direction of the variable sweep shaft 17, so that the space after folding is smaller.

[0030] Reference Figure 5A continuous telescopic mechanism for driving the outer wing to continuously translate along the wing span is provided in the inner wing 1. The continuous telescopic mechanism includes a threaded guide rod 22, a linear actuator 23, a support pipe 24, and a guide rod bearing fixing member 25. The inner wing plug-in 21 is fixedly connected to the plug-in connector 15, and the threaded guide rod 22 and the linear actuator 23 are threadedly matched. Under the guidance of the guide rod thread lead angle, the linear actuator 23 can convert the rotational motion of the threaded guide rod 22 into linear motion. The support pipe 24 is placed in the reserved rectangular space inside the inner wing 1, with one side fixedly connected to the linear actuator 23 and the other side fixedly connected to the outer wing end plate 5. When the transmission mechanism drives the threaded guide rod 22 to rotate, the support pipe 24 can be driven by the linear actuator 23 to translate and slide smoothly along a preset trajectory in the inner space of the inner wing 1.

[0031] Reference Figure 5 and Figure 7 , a translation slider 32 is arranged on the side of the threaded guide rod 22 away from the plug-in connector 15, and the translation slider 32 is arranged in the support pipe 24 and is rotatably connected with the threaded guide rod 22. In this embodiment, a guide rod bearing installation position is designed at the translation slider 32, and the connection with the threaded guide rod 22 is completed with the cooperation of the guide rod bearing end face retaining ring 31 and the guide rod end face fixing screw 34, which does not affect the rotation of the guide rod. The envelope size of the translation slider 32 is smaller than the sliding space after the support pipe 24 is assembled, and 4 external threaded bearings 33 are installed. The outer ring of the bearing maintains a tangent position relationship with the surface of the sliding space, which can assist the translation slider 32 to slide smoothly in this space, increase the passability of the telescopic mechanism when performing variable extension action, and effectively avoid the mechanism operation failure caused by mechanical interference or jamming. At the same time, the support pipe 24 provides circumferential positioning for the guide rod bearing, which can ensure that the threaded guide rod 22 rotates along the predetermined axis and does not interfere with the translation action of the support pipe 24.

[0032] When the wing is in the extended state, the support tube 24 becomes the main load-bearing component due to its excellent structural mechanical properties, used to bear the aerodynamic load generated by the outer wing 2. The outer contour line of the outer wing end plate 5 is completely consistent with the airfoil of the inner wing 1. It is installed inside the outer wing 2 at a position away from the fuselage, and can slide in translation along the wing span under the drive of the support tube 24. The continuous telescopic mechanism adopts the form of nesting of the inner and outer wings, with the threaded guide rod 22 as the main driving component. The inner wing 1 is fixed relative to the fuselage, and the outer wing 2 adjusts the wing span by sliding relative to the inner wing 1. The threaded guide rod 22 is driven by a synchronous transmission mechanism. The synchronous drive mechanism can simultaneously drive the threaded guide rods 22 in the two wing structures to rotate synchronously, so that the two wing structures can be retracted or unfolded synchronously.

[0033] In this embodiment, the wing structure further includes an aileron 3, which is mounted at the trailing edge of the outer wing 2, and is connected to an aileron servo 26. An installation space for the aileron servo 26 is designed inside the outer wing end plate 5, and the aileron servo 26 is arranged in the aileron servo installation space, and the aileron servo 26 is connected to the aileron 3 through an aileron linkage mechanism. The aileron 3 rudder deflection is controlled by driving the aileron linkage mechanism, thereby controlling the aircraft attitude.

[0034] Reference Figure 3 and Figure 4 The synchronous transmission mechanism includes a power source 11, a transmission connecting rod 12, a driving transmission shaft 13, a driving bevel gear 18, two driven bevel gears 19, a driven transmission shaft 14 and a bearing component. The power source 11 is connected to the driving transmission shaft 13 through the transmission connecting rod 12, the driving transmission shaft 13 is connected to the driving bevel gear 27, the two driven bevel gears 19 are symmetrically arranged and both mesh with the driving bevel gear 18; one end of the driven transmission shaft 14 is connected to the driven bevel gear 28, and the other end is connected to the threaded guide rod 22 through the universal joint coupling 16. The universal joint coupling 16 is located in the inner envelope space of the inner wing plug-in 21, and can transfer the rotation of the driven transmission shaft 14 to the rotation of the threaded guide rod 22, thereby establishing an effective power link from the power source 11 to the telescopic wing drive. Since the two wing structures are installed at a certain distance in the height direction, the heights of the threaded guide rods 22 in the two continuous telescopic mechanisms are different. Therefore, the height deviation of the telescopic wings on both sides can be compensated by the universal joint coupling 16 to avoid additional stress, vibration and other adverse phenomena caused by the height difference.

[0035] In this embodiment, the power source 11 adopts a motor, and the driving bevel gear 27 is driven to rotate by the rotation of the power source 11 (motor). The driving bevel gear 18 is meshed with the two driven bevel gears 19, thereby driving the driven transmission shaft 14 to rotate. The fixing member 4 provides support positioning and bearing installation positions for various components in the synchronous transmission mechanism. The driven transmission shaft 14 rotates, and the power is transmitted to the threaded guide rod 22 through the universal joint coupling 16. The threaded guide rod 22 rotates and then drives the continuous telescopic mechanism to move the outer wing 2 on the inner wing 1, and realize the expansion and contraction of the wing. A bearing that matches the driven transmission shaft 14 is also provided on the plug-in connector 15, which is used for positioning and installing the driven transmission shaft 14. It is conducive to ensuring that the bevel gears can be accurately meshed to transmit a stable torque. The guide rod bearing fixture 25 is installed in the rectangular space of the inner wing plug-in 21, which does not affect the assembly of the plug-in and the inner wing 2. At the same time, it can locate the rotation axis position of the threaded guide rod 22. The guide rod bearing fixture 25 can reduce the vibration of the threaded guide rod caused by the rotation of the universal joint coupling.

[0036] Through this transmission direction conversion mechanism, the transmission direction can be changed within the limited space inside the fuselage, making the structure of the entire transmission part more compact and reasonable. Since the contact process of the bevel gear tooth surface is gradually entering and exiting, the vibration and impact in the transmission process can be reduced, which is beneficial to the overall stability of the aircraft. At the same time, the driven transmission shafts 14 on the left and right sides are arranged symmetrically, and can accurately transmit power according to the designed transmission ratio, which can ensure the accuracy and consistency of the lengthening process of the wings on both sides. At the same time, when the synchronous transmission mechanism of this embodiment needs to fold the wings, the folding direction is exactly the direction in which the two driven bevel gears 19 are disconnected from the active bevel gear 18, and the synchronous transmission mechanism will not affect the folding of the wings.

[0037] The above are all preferred embodiments of the present invention, and are not intended to limit the protection scope of the present invention. Therefore, any equivalent changes made based on the structure, shape, and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A variant wing structure capable of synchronously and continuously varying the length, characterized in that: It includes a fixing frame, wing structures arranged on both sides of the fixing frame, and a synchronous transmission mechanism for driving the wing structures on both sides to synchronously extend and retract; The wing structure comprises an inner wing and an outer wing, the outer wing is nested with the inner wing skin, and a continuous telescopic mechanism for driving the outer wing to continuously translate along the wing span is arranged in the inner wing; The continuous telescopic mechanism comprises a threaded guide rod, a linear actuator, a supporting pipe and a linear actuator; The threaded guide rod is connected to the synchronous transmission mechanism, and is driven by the synchronous transmission mechanism to rotate around the wing span axis; the linear actuator is fixedly connected to the supporting pipe, and can be driven by the threaded guide rod to perform translational motion; one end of the supporting pipe is connected to the outer wing end plate of the outer wing, and the rotation of the threaded guide rod can drive the outer wing end plate to translate together with the outer wing; The synchronous transmission mechanism includes a power source, a transmission connecting rod, a driving bevel gear, two driven bevel gears, a driven transmission shaft and a bearing component; the power source is connected to the driving bevel gear through the transmission connecting rod, the two driven bevel gears are symmetrically arranged and both mesh with the driving bevel gear; one end of the driven transmission shaft is connected to the driven bevel gear, and the other end is connected to the threaded guide rod.

2. A variant wing structure capable of synchronously and continuously varying the length according to claim 1, characterized in that: The driven transmission shaft and the threaded guide rod are connected via a universal joint coupling.

3. A variant wing structure capable of synchronously and continuously varying the length according to claim 2, characterized in that: A variable swept shaft is also provided on the fixed frame, and the variable swept shaft is connected to the fixed frame through a bearing. A plug-in connector is provided on the variable swept shaft, and the inner wing includes an inner wing plug-in, and the inner wing plug-in is fixed to the plug-in connector. A bearing matching the driven transmission shaft is also provided on the plug-in connector.

4. The variant wing structure capable of synchronously and continuously varying the length according to claim 3, characterized in that: The heights of the plug-in connectors of the wing structure on both sides of the fixing frame are different.

5. The variant wing structure capable of synchronously and continuously changing the length of the wing according to claim 4, characterized in that: A guide rod bearing fixing piece is also installed on the inner wing plug-in unit, and the guide rod bearing fixing piece is positioned and matched with the threaded guide rod.

6. The variant wing structure capable of synchronously and continuously varying the length of the wing according to claim 1, characterized in that: The continuous telescopic mechanism also includes a translation slider, which is arranged in the supporting tube and is rotatably connected to the threaded guide rod. The envelope surface size of the translation slider is smaller than the sliding space after the supporting tube is assembled. An external threaded bearing is also arranged on the translation slider, and the outer ring of the bearing maintains a tangent positional relationship with the surface of the sliding space.

7. The variant wing structure capable of synchronously and continuously changing the length of the wing according to claim 1, characterized in that: It also includes ailerons, which are installed at the trailing edge of the outer wing and are connected to the aileron servo.

8. The variant wing structure capable of synchronously and continuously varying the length of the wing according to claim 7, characterized in that: An aileron servo installation space is provided inside the outer wing end plate. The aileron servo is arranged in the aileron servo installation space. The aileron servo is connected to the aileron through an aileron connecting rod mechanism to control the aileron rudder deflection.

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