Airfoil structure and aircraft

Abstract

The utility model relates to the field of aircrafts, aims to solve the problem that a control surface of a known aircraft is heavy or inconvenient to disassemble and assemble, and provides an airfoil structure and an aircraft. The airfoil structure comprises an airfoil body, a control surface, a driving assembly and two rotary connecting mechanisms. And the control plane is arranged on one side of the airfoil body. The two rotary connecting mechanisms are arranged in the length direction of the control surface in a spaced mode. And the control surface is rotatably connected to the rear edge of the airfoil body through the two rotary connecting mechanisms. The driving assembly comprises a steering engine and a transmission mechanism. The steering engine is installed on the airfoil body. The transmission mechanism is in transmission connection between the steering engine and the control plane and used for driving the control plane to rotate relative to the airfoil body. The position, connected with the control plane, of the transmission mechanism is located between the two rotary connecting mechanisms. The utility model has the beneficial effects that the control surface is light in weight and convenient to disassemble and assemble.

Description

Technical Field

[0001] The present application relates to the field of aircraft, and more particularly, to a wing surface structure and an aircraft. Background Art

[0002] For known aircraft, such as electric vertical take-off and landing (eVTOL) aircraft, the control surfaces (such as ailerons) are installed in a form of being mounted through left and right end faces or coaxial mounting, which has problems of relatively large weight or inconvenient disassembly and assembly. Summary of the Utility Model

[0003] The present application provides a wing surface structure and an aircraft to solve the problems of relatively large weight or inconvenient disassembly and assembly of the control surfaces of known aircraft.

[0004] In a first aspect, the present application provides a wing surface structure, which includes a wing surface body, a control surface, and two rotational connection mechanisms. The control surface is disposed on one side of the wing surface body. The two rotational connection mechanisms are spaced along the length direction of the control surface; the control surface is rotatably connected to the trailing edge of the wing surface body through the two rotational connection mechanisms. The drive assembly includes a servo motor and a transmission mechanism; the servo motor is installed on the wing surface body; the transmission mechanism is drivingly connected between the servo motor and the control surface for driving the control surface to rotate relative to the wing surface body; the position where the transmission mechanism connects to the control surface is located between the two rotational connection mechanisms.

[0005] In the wing surface structure of the present application, the two rotational connection mechanisms are respectively spaced along the length direction of the control surface to rotatably suspend the control surface on one side of the wing surface body. Compared with the form of rotatably installing through a coaxial shaft, it is lighter in weight and easier to disassemble and assemble. At the same time, this suspension method of the control surface combined with the setting of the transmission mechanism enables more direct and stable load transfer.

[0006] In a possible implementation, the wing surface body is a main wing, and the control surface is an aileron. The main wing includes a main beam, a rear beam, a rear rib plate, a lower main wing skin, and an upper main wing skin. The rear rib plate is connected between the main beam and the rear beam; the upper main wing skin covers the upper surfaces of the main beam and the rear beam, and the lower main wing skin covers the lower surfaces of the main beam and the rear beam, and an internal space is defined between the lower main wing skin and the upper main wing skin; a through hole communicating with the internal space is provided on the lower main wing skin. The servo motor is disposed in the internal space and fixedly installed on the rear rib plate; the transmission mechanism includes a servo motor rocker arm, a connecting rod, and a control horn. One end of the servo motor rocker arm is connected to the output rotating shaft of the servo motor, and the other end extends out of the lower main wing skin through the through hole; one end of the control horn is fixedly connected to the control surface, and the other end extends in a direction away from the control surface; the connecting rod is located outside the lower main wing skin, and one end of the connecting rod is rotatably connected to the end of the servo motor rocker arm away from the main wing, and the other end is rotatably connected to the end of the control horn away from the control surface.

[0007] In a possible implementation, the main wing further includes a fairing cover. The fairing cover is detachably disposed on the through-hole, and the fairing cover defines a channel groove located below the lower skin of the main wing. The channel groove extends along the front-rear direction of the main wing, and one end of the channel groove communicates with the internal space, and the other end opens towards the side of the control surface. After the servo rocker arm passes through the through-hole, it enters the channel groove, and the connecting rod extends out of the opening of the channel groove along the channel groove and then is connected to the control angle.

[0008] In a possible implementation, the fairing cover includes a cover plate and a protruding surrounding wall, and the protruding surrounding wall protrudes outward from the cover plate to define the channel groove.

[0009] In a possible implementation, the connecting rod includes a rod body and two rod heads, and the two rod heads are respectively threadedly connected to both ends of the rod body so that the length of the connecting rod is adjustable. One of the rod heads is drivingly connected to the servo rocker arm, and the other rod head is drivingly connected to the control angle.

[0010] In a possible implementation, the control surface is an aileron. The aileron has an aileron beam and an aileron skin, and the aileron beam is supported inside the aileron skin. A control angle connection seat is connected to the inner side of the aileron beam, and the control angle is fixedly connected to the control angle connection seat.

[0011] In a possible implementation, the main wing includes an upper skin of the main wing and a lower skin of the main wing. The aileron skin includes an upper aileron skin and a lower aileron skin, and the upper aileron skin and the lower aileron skin respectively cover the upper and lower sides of the aileron beam. The upper aileron skin includes a first large surface section and a first arc section, and the lower aileron skin includes a second large surface section and a second arc section. There is a first gap between the first large surface section and the upper skin of the main wing, and there is a second gap between the second large surface section and the lower skin of the main wing. The first arc section is an arc centered on the rotation axis of the aileron relative to the main wing, and the first arc section is arc-transitionally connected to one end of the first large surface section close to the upper skin of the main wing. The second arc section is an arc centered on the rotation axis of the aileron relative to the main wing, and the second arc section is arc-transitionally connected to one end of the second large surface section close to the lower skin of the main wing.

[0012] In a possible implementation, a first cut groove is provided at the position of the first arc section corresponding to the rotation connection mechanism, and a second cut groove is provided at the position of the second arc section corresponding to the rotation connection mechanism. The cutting depth of the second cut groove is greater than that of the first cut groove.

[0013] In a possible implementation, the connection position E of the control angle and the control surface is located on the side of the rotation center A of the control surface relative to the wing body away from the rotation center B of the servo rocker arm, and the control angle is obliquely connected between the connection position E and the connecting rod.

[0014] In a possible implementation, the rudder angle includes a connecting plate, a first inclined section, and a second inclined section; the connecting plate is laminated and connected to the lower surface of the control surface, the first inclined section is connected to the connecting plate and inclines towards the side close to the steering gear rocker arm; the second inclined section is connected to the first inclined section and inclines towards the side close to the steering gear rocker arm.

[0015] In a possible implementation, the two rotational connection mechanisms are respectively located at positions where the distances from the two ends of the length direction of the control surface to the control surface are 1 / 4 of the length of the control surface. The position where the transmission mechanism connects to the control surface is located at the midpoint of the length of the control surface.

[0016] In a second aspect, the present application provides an aircraft, which includes a fuselage and the aforementioned wing surface structure, and the wing surface structure is connected to the fuselage. Description of the Drawings

[0017] To more clearly illustrate the technical solutions of the embodiments of the present application, the drawings in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present application, and therefore should not be regarded as limiting the scope. For those of ordinary skill in the art, other related drawings can also be obtained based on these drawings without creative efforts.

[0018] Figure 1 Is a three-dimensional view of the aircraft of the embodiment of the present application;

[0019] Figure 2 Is Figure 1 A bottom view of a wing surface structure of the aircraft;

[0020] Figure 3 Is Figure 2 A three-dimensional view of the wing surface structure, where the lower skin of the main wing of the wing surface structure faces upward and is represented by a dotted line for perspective;

[0021] Figure 4 Is Figure 3 An enlarged view of part I of;

[0022] Figure 5 Is Figure 2 A three-dimensional view of the wing surface structure, where the upper skin of the main wing of the wing surface structure faces upward and is represented by a dotted line for perspective;

[0023] Figure 6 Is Figure 3 An exploded view of a part of the wing surface structure of;

[0024] Figure 7 Is Figure 6 A partial enlarged view of;

[0025] Figure 8 Is Figure 5 An enlarged view of part II of;

[0026] Figure 9 is a perspective view of the rotational connection mechanism in the embodiment of the present application;

[0027] Figure 10 is Figure 9 a sectional view of;

[0028] Figure 11 is Figure 8 a partially enlarged view of;

[0029] Figure 12 is a sectional view of the wing surface structure in the embodiment of the present application in a plane perpendicular to the length direction of the aileron;

[0030] Figure 13 is Figure 2 a schematic structural view of the wing surface structure with the aileron of the wing surface rotated by a certain angle relative to the main wing;

[0031] Figure 14 is Figure 12 a schematic diagram of the transmission principle of the wing surface structure;

[0032] Figure 15 is a schematic diagram of the transmission principle of a pair of proportional wing surface structures;

[0033] Figure 16 is a schematic diagram of the transmission principle of another pair of proportional wing surface structures.

[0034] Description of main component symbols:

[0035] Aircraft 100

[0036] Fuselage 110

[0037] Wing surface structures 120, 120a, 120b

[0038] Wing 120c

[0039] Tail wing 120d

[0040] Wing surface body 121

[0041] Control surface 122

[0042] Main wing 10

[0043] Front beam 11

[0044] Main beam 12

[0045] Rear beam 13

[0046] Front rib plate 14

[0047] Rear rib plate 15

[0048] Lower skin of the main wing 16

[0049] Upper skin of main wing 17

[0050] Fairing cover 18

[0051] Cover plate 18a

[0052] Protruding bulkhead 18b

[0053] Aileron 30

[0054] Aileron beam 31

[0055] Aileron skin 32

[0056] Upper aileron skin 321

[0057] Lower aileron skin 322

[0058] First large surface segment 321a

[0059] First arc segment 321b

[0060] Second large surface segment 322a

[0061] Second arc segment 322b

[0062] Rudder angle connection seat 33

[0063] Drive assembly 50

[0064] Servo 51

[0065] Output rotating shaft 51a

[0066] Transmission mechanism 52

[0067] Servo rocker arm 53

[0068] Connecting rod 54

[0069] Rod body 54a

[0070] Rod head 54b

[0071] Adjusting nut 54c

[0072] Lock washer 54d

[0073] Rudder angle 55

[0074] Connecting plate 55a

[0075] First inclined segment 55b

[0076] Second inclined segment 55c

[0077] Hinge pin 56a

[0078] Nut 56b

[0079] Split pin 56c

[0080] Rotating connection mechanism 70

[0081] Rotating seat 71

[0082] Rotating frame 72

[0083] Connecting bolt 73

[0084] Spherical plain bearing 74

[0085] Bushing 75

[0086] Internal space Q1

[0087] Penetration port K1

[0088] Avoidance groove C1

[0089] First cut groove C11

[0090] Second cut groove C12

[0091] First gap f1

[0092] Second gap f2

[0093] Channel groove C2

[0094] Reference position W1

[0095] Deflection position W2

[0096] First rotation axis L1

[0097] Second rotation axis L2

[0098] Horizontal middle plane P1 Detailed implementation mode

[0099] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments.

[0100] It should be noted that when an element is referred to as being "fixed to" another element, it can be directly on the other element or there may also be an intermediate element. When an element is considered to be "connected" to another element, it can be directly connected to the other element or there may be an intermediate element at the same time. When an element is considered to be "disposed on" another element, it can be directly disposed on the other element or there may be an intermediate element at the same time. The terms "vertical", "horizontal", "left", "right" and similar expressions used herein are for illustrative purposes only.

[0101] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terms used in the specification of this application are for the purpose of describing specific embodiments only and are not intended to limit this application. The term "and / or" as used herein includes any and all combinations of one or more of the related listed items.

[0102] Some embodiments of this application will be described in detail. Without conflict, the following embodiments and the features in the embodiments can be combined with each other.

[0103] Embodiment

[0104] Refer to Figure 1 , this embodiment provides an aircraft 100, and the aircraft 100 takes an eVTOL aircraft as an example.

[0105] Refer to Figure 1 and Figure 2 , the aircraft 100 includes a fuselage 110 and an airfoil structure 120. Among them, the airfoil structure 120 (such as a wing 120c or a tail 120d) includes an airfoil body 121 and a control surface 122, and the control surface 122 can be controlled to deflect a certain angle relative to the airfoil body 121 to control the flight attitude of the aircraft 100.

[0106] For example, when the airfoil structure 120 is a wing 120c, its airfoil body 121 is the main wing 10, and its control surface 122 can be an aileron 30, a spoiler, a flap, etc. There are two wings 120c, and the two wings 120c are respectively connected to both sides of the fuselage 110 of the aircraft 100.

[0107] The tail 120d is connected to the tail of the fuselage 110. The control surface of the tail 120d can be a rudder, an elevator, etc.

[0108] Refer to in conjunction with Figure 2 , the airfoil structure 120 (such as a wing 120c) includes a main wing 10, an aileron 30 and a drive assembly 50. The aileron 30 is rotatably connected to one side of the main wing 10, for example, rotatably connected to the trailing edge of the main wing 10. The drive assembly 50 is installed on the main wing 10 and is drivingly connected to the aileron 30 to drive the aileron 30 to rotate relative to the main wing 10 to adjust the overall shape of the airfoil structure 120, and further adjust the flight position and attitude of the aircraft 100.

[0109] Optionally, the aileron 30 is rotatably connected to one side of the main wing 10 close to the aileron 30, i.e., the position of the trailing edge of the main wing 10, through two rotating connection mechanisms 70, and the two rotating connection mechanisms 70 are arranged at intervals along the length direction of the aileron 30. The connection point between the drive assembly 50 and the aileron 30 is located between the two rotating mechanisms. Figure 2 As shown in FIG. 1 , the connection point between the drive assembly 50 and the aileron 30 is located at or approximately at the midpoint of the length direction of the aileron 30, and the load transmission is more direct and stable. The two rotating connection mechanisms 70 are respectively located at the midpoint of the line connecting the two end points in the length direction of the aileron 30 and the connection point between the drive assembly 50 and the aileron 30, that is, the two rotating connection mechanisms 70 are respectively located at 1 / 4 of the length of the aileron 30, so that the rotating connection mechanisms 70 can be loaded more evenly and the load transmission is more direct.

[0110] See also Figures 2 - 4 In this embodiment, the driving assembly 50 includes a steering gear 51 and a transmission mechanism 52. The steering gear 51 is installed on the main wing 10. The transmission mechanism 52 is connected between the steering gear 51 and the aileron 30 to drive the aileron 30 to rotate relative to the main wing 10.

[0111] The transmission mechanism 52 includes a steering gear rocker arm 53, a connecting rod 54 and a rudder angle 55. One end of the steering gear rocker arm 53 is connected to the output shaft 51a of the steering gear 51, and the other end thereof extends in a direction away from the main wing 10. One end of the rudder angle 55 is fixedly connected to the aileron 30, and the other end thereof extends in a direction away from the aileron 30. One end of the connecting rod 54 is rotationally connected to one end of the steering gear rocker arm 53 away from the main wing 10, and the other end thereof is rotationally connected to one end of the rudder angle 55 away from the aileron 30. In this way, when the steering gear 51 rotates, the steering gear rocker arm 53 can be driven to swing, and the swing of the steering gear rocker arm 53 will drive the aileron 30 to rotate relative to the main wing 10 through the connecting rod 54 and the rudder angle 55.

[0112] See also Figure 5 and Figure 4 In this embodiment, the main wing 10 includes a front beam 11, a main beam 12, a rear beam 13, a front rib 14, a rear rib 15, a main wing lower skin 16 and a main wing upper skin 17. The front beam 11, the main beam 12 and the rear beam 13 are arranged in sequence, and the front rib 14 is vertically connected between the main beam 12 and the front beam 11; the rear rib 15 is vertically connected between the main beam 12 and the rear beam 13. The main wing upper skin 17 is covered on the upper surfaces of the front beam 11, the main beam 12 and the rear beam 13; the main wing lower skin 16 is covered on the lower surfaces of the front beam 11, the main beam 12 and the rear beam 13.

[0113] The lower main wing skin 16 and the upper main wing skin 17 of the main wing 10 enclose an internal space Q1, and a through-hole K1 is provided in the lower main wing skin 16 of the main wing 10, and the through-hole K1 communicates with the internal space Q1. The servo 51 is arranged in the internal space Q1 and fixedly connected to the rear rib 15, and the servo rocker arm 53 extends out of the lower main wing skin 16 from the through-hole K1. The connecting rod 54 is also located outside the lower main wing skin 16 and will not interfere with the lower main wing skin 16 during movement. This embodiment fully utilizes the rear rib 15 of the main wing 10 to install the servo 51 without the need to additionally provide a bracket for installing the servo 51, which is beneficial to reducing the weight of the wing structure 120; at the same time, the servo rocker arm 53 extends out of the lower main wing skin 16 from the through-hole K1, so that the servo rocker arm 53 has a larger length and is not limited by the height dimension of the main wing 10, resulting in a larger output force arm of the servo 51 and a larger output torque of the servo 51. Or rather, for the required driving torque of the aileron 30, due to the larger force arm, a servo 51 with a smaller size and / or lower cost can be used, which is convenient for servo 51 selection and cost savings, and at this time, the force transmitted by the connecting rod 54 is smaller, thereby improving the stability of the entire mechanism.

[0114] In this embodiment, the main wing 10 further includes a fairing cover 18 (also shown in Figure 2 ), and the fairing cover 18 is detachably covered on the through-hole K1. It should be noted that Figure 5 the fairing cover 18 in

[0115] is represented by a dotted line and can penetrate the internal structure. Figure 2 ) The fairing cover 18 defines a channel groove C2 located below the lower main wing skin 16 (also shown in Figure 2 ), the channel groove C2 extends along the front-rear direction of the main wing 10, and one end of the channel groove C2 communicates with the internal space Q1, and the other end opens towards the aileron 30 side. After passing through the through-hole K1, the servo rocker arm 53 enters the channel groove C2, and the connecting rod 54 extends out of the opening of the channel groove C2 along the channel groove C2 and is connected to the steering angle 55. Optionally, referring to

[0116] again, Figure 5 the through-hole K1 can be provided in the area of the lower main wing skin 16 near the servo 51, and the fairing cover 18 is detachably covered on the through-hole K1. In this way, when needed, the fairing cover 18 can be removed to repair or replace the servo 51. The fairing cover 18 can also improve the aerodynamic performance of the wing structure 120 at the through-hole K1.

[0117] Optionally, the servo 51 is fixed on one side of the rear rib 15. After the output rotating shaft 51a of the servo 51 passes through the rib, the servo rocker arm 53 is connected to the other side of the rear rib 15.

[0118] See Figure 6 and Figure 7 In this embodiment, the aileron 30 has an aileron beam 31 and an aileron skin 32, and the aileron beam 31 is supported within the aileron skin 32. Optionally, the aileron beam 31 can be made of a channel-shaped metal profile (such as a channel steel or other metal profiles of the same shape), and the opening of the aileron beam 31 faces the main wing 10 side. The aileron skin 32 includes an upper aileron skin 321 and a lower aileron skin 322, and the upper aileron skin 321 and the lower aileron skin 322 respectively cover the upper and lower sides of the aileron beam 31.

[0119] A rudder angle connection seat 33 is connected to the inner side of the aileron beam 31 (i.e., the side close to the main wing 10). For example, the rudder angle connection seat 33 is fixed to the web of the aileron beam 31 and supported between the upper and lower wing plates of the aileron beam 31.

[0120] The rudder angle 55 is fixedly connected to the rudder angle connection seat 33. For example, the rudder angle 55 is stacked on the lower surface of the aileron 30 and locked and fixed together with the lower wing plate of the aileron skin 32 and the aileron beam 31 by bolts or other fasteners.

[0121] In the transmission mechanism 52 of this embodiment, optionally, the connecting rod 54 includes a rod body 54a and two rod heads 54b, and the two rod heads 54b are respectively threadedly connected to both ends of the rod body 54a so that the length of the connecting rod 54 is adjustable. Optionally, an adjusting nut 54c and a locking washer 54d are also provided at the connection between the rod body 54a and the rod heads 54b to achieve adjustment and anti-loosening effects.

[0122] Both of the two rod heads 54b can be provided with spherical plain bearings. One of the rod heads 54b is rotatably connected to the servo rocker 53 through a hinge pin 56a, and the other rod head 54b is rotatably connected to the rudder angle 55 through a hinge pin 56a. The ends of the hinge pins 56a are respectively connected to nuts 56b and split pins 56c to achieve anti-disengagement.

[0123] See also in conjunction with Figures 8 - 11 In this embodiment, an avoidance groove C1 is provided on the side of the aileron skin 32 facing the main wing 10. The avoidance groove C1 is used to allow the rotation connection mechanism 70 to extend into the aileron 30 to connect to the aileron beam 31 and avoid the rotation of the rotation connection mechanism 70. In this way, the distance between the aileron 30 and the main wing 10 can be made smaller.

[0124] Among them, the rotation connection mechanism 70 includes a rotating seat 71 and a rotating frame 72. The rotating seat 71 is installed on the side of the main wing 10 facing the aileron 30, and the rotating frame 72 is installed on the side of the aileron 30 facing the main wing 10. The rotating frame 72 is rotatably connected to the rotating seat 71, and the rotation axis is the first rotation axis L1. In this way, the aileron 30 can rotate and cooperate with the main wing 10 around the first rotation axis L1.

[0125] In this embodiment, the first rotation axis L1 is parallel to the rotation axis of the servo rocker arm 53 (defined as the second rotation axis L2, as shown in Figure 6 or Figure 7 ) to ensure the smooth rotation of the transmission mechanism 52.

[0126] Optionally, the rotating seat 71 is a double-ear suspension joint, and the rotating frame 72 is a single-ear suspension joint. The two form a single-double ear cooperation to ensure the strength and stability of the structure. The rotating seat 71 and the rotating frame 72 are rotatably connected by a connecting bolt 73. Optionally, a bushing 75 is provided between the connecting bolt 73 and the rotating seat 71, and the connecting bolt 73 and the rotating frame 72 are rotatably connected by a spherical plain bearing 74.

[0127] Optionally, with reference to Figure 11 and Figure 12 , the upper aileron skin 321 includes a first large surface section 321a and a first arc section 321b, and the lower aileron skin 322 includes a second large surface section 322a and a second arc section 322b. There is a first gap f1 between the first large surface section 321a and the upper main wing skin 17, and a second gap f2 between the second large surface section 322a and the lower main wing skin 16. The first arc section 321b is an arc centered on the rotation axis of the aileron 30 relative to the main wing 10, and the first arc section 321b is arc-transitionally connected to one end of the first large surface section 321a close to the upper main wing skin 17. The second arc section 322b is an arc centered on the rotation axis of the aileron 30 relative to the main wing 10, and the second arc section 322b is arc-transitionally connected to one end of the second large surface section 322a close to the lower main wing skin 16. In this way, the main wing 10 and the aileron 30 are well combined, with little impact on the aerodynamic performance of the wing surface structure 120, and the settings of the first gap f1 and the second gap f2 can avoid interference between the aileron 30 and the inner surface of the upper main wing skin 17 or the lower main wing skin 16 during rotation.

[0128] Optionally, a first cut groove C11 is provided at the position corresponding to the rotation connection mechanism 70 on the first arc section 321b, and a second cut groove C12 is provided at the position corresponding to the rotation connection mechanism 70 on the second arc section 322b. The first cut groove C11 and the second cut groove C12 together form an avoidance groove C1 for avoiding the rotation connection mechanism 70. The cutting depth of the second cut groove C12 is greater than that of the first cut groove C11. In this way, when the aileron 30 is deflected upward by 35°, the second cut groove C12 can expose enough space to facilitate the installation and disassembly of the rotation connection mechanism 70 here, and the aileron 30 is convenient to disassemble.

[0129] Refer to Figures 12 - 16 , the aileron 30 in this embodiment has a reference position W1 (such as the position shown in Figure 12 ) and a deflection position W2 (such as the position shown in Figure 13)。The aileron 30 can be driven by the servo 51 to vary between the reference position W1 and the deflected position W2. Among them Figure 13 The shown deflected position W2 where the aileron 30 is located is the upper limit position, and the aileron 30 can also be deflected downward to the lower limit position under the drive of the drive assembly 50.

[0130] Refer to Figure 12 and Figure 14 , in this embodiment, the connecting line BA between the rotation center B of the servo rocker arm 53 (coinciding with the rotation center of the servo 51) and the rotation center A of the aileron 30 relative to the main wing 10 (located on the first rotation axis L1) is located in the horizontal middle plane P1 of the main wing 10. Among them, the horizontal middle plane P1 of the main wing 10 is the plane passing through the midpoint of the main beam 12 in the height direction and the midpoint of the rear beam 13 in the height direction. The straight-line distance between the rotation center C of the servo rocker arm 53 relative to the connecting rod 54 and the rotation center B of the servo rocker arm 53 (located on the second rotation axis L2) is equal to the straight-line distance between the rotation center D of the steering angle 55 relative to the connecting rod 54 and the rotation center A of the aileron 30 relative to the main wing 10. In the state where the aileron 30 is in the reference position W1, the connecting line CB is perpendicular to the connecting line BA, and the connecting line DA is perpendicular to the connecting line BA. In the wing surface structure 120 of this embodiment, by defining that the connecting line BA is in the horizontal middle plane P1 of the main wing 10 and the connecting lines CB and DA are equal, the drive assembly 50 forms a parallel double-crank mechanism without a quick-return characteristic, which is beneficial to ensuring the stability of the aileron 30 operation. Moreover, when the drive assembly 50 is in the reference position, the pressure angle α = 0 and the transmission angle γ = 90°. Among them, the pressure angle α is the acute angle between the driving force received by the steering angle 55 and the absolute velocity direction of the force application point, the transmission angle γ is the complementary angle of the pressure angle α, γ = 90° - α, and the effective transmission force F1 = Fsinγ = Fcosα. The smaller the pressure angle α, the better the force transmission performance of the mechanism and the higher the transmission efficiency. Therefore, the drive assembly 50 of this embodiment has good force transmission performance and high transmission efficiency.

[0131] Optionally, the distance from the rotation center B to the main beam 12 is equal to the distance to the rear beam 13, that is, the servo 51 is arranged at the midpoint of the length direction of the rear rib plate 15. In this way, the arrangement of the servo 51 can be facilitated, and the force on the main wing 10 can be more balanced.

[0132] Refer to again Figure 12 , in this embodiment, the connection position E of the steering angle 55 and the aileron 30 (i.e., the position of the aforementioned steering angle connection seat 33) is located on the side of the rotation center A away from the rotation center B, and the steering angle 55 is obliquely connected between the connection position E and the rotation center D of the connecting rod 54. In this way, the steering angle 55 is supported at the connection position E of the aileron 30, and can more reliably support the aileron 30 upward and is beneficial to controlling the movement of the aileron 30.

[0133] Optionally, the rudder angle 55 includes a connecting plate 55a, a first inclined section 55b, and a second inclined section 55c; the connecting plate 55a is superposed and connected to the lower surface of the aileron 30, the first inclined section 55b is connected to the connecting plate 55a and inclined towards the side close to the servo rocker arm 53, and the second inclined section 55c is connected to the first inclined section 55b and inclined towards the side close to the servo rocker arm 53. Thus, at the reference position W1, the two conditions that the connecting line DA is perpendicular to the connecting line BA and the connecting position E is located on the side of the rotation center A away from the rotation center B can be ensured simultaneously.

[0134] Figure 15 A pair of proportional airfoil structures 120a are shown, which are different from Figure 14 the airfoil structure 120 of, in that the rotation center B is not on the horizontal middle plane P1 of the main wing 10. Thus, there is an included angle between the connecting line BA and the horizontal middle plane P1 of the main wing 10. The connecting lines CB and DA still remain equal in length and are respectively perpendicular to the connecting line BA.

[0135] Figure 15 For the shown airfoil structure 120a, its drive assembly 50 forms a parallel double-crank mechanism without a quick-return characteristic, ensuring the stability of control. Moreover, the transmission angle γ (i.e., the complementary angle of the pressure angle α) is 90°. At this time, the force transmission performance of the transmission mechanism 52 is good and the transmission efficiency is high. However, at this time, the transmission mechanism 52 has an initial angle β with the horizontal middle plane P1 of the main beam 12. Due to gravity, the transmission mechanism 52 will have a negative torque by itself, affecting the stability of transmission.

[0136] Figure 16 Another pair of proportional airfoil structures 120b are shown, which are different from Figure 14 the airfoil structure 120 of, in that the connecting lines CB and DA are not equal in length. The connecting line BA remains on the horizontal middle plane P1 of the main wing 10, and the connecting lines CB and DA still remain respectively perpendicular to the connecting line BA.

[0137] At this time, the drive assembly 50 is not a parallel double-crank mechanism and has a quick-return characteristic, reducing the stability of control, and the pressure angle α is not 0°. Thus, Figure 16 the pressure angle α not being 0° will make the force transmission performance and transmission efficiency of the transmission mechanism 52 inferior to those of Figure 14 the embodiment shown.

[0138] Therefore, in this embodiment, by simultaneously defining that the connecting line BA is on the horizontal middle plane P1 of the main wing 10, and the connecting lines CB and DA still remain equal in length and are respectively perpendicular to the connecting line BA, the airfoil structure 120 has excellent control stability, transmission performance, and transmission efficiency.

[0139] This embodiment also provides an airfoil structure assembly method for assembling the aforementioned airfoil structure 120; the airfoil structure assembly method includes:

[0140] The control surface (such as an aileron) is rotatably connected to the trailing edge of the wing structure body (such as the main wing), and the servo of the drive assembly is arranged inside the wing structure body, so that the transmission mechanism of the drive assembly is connected to the control surface. And after assembly, the drive assembly forms a parallel double crank mechanism.

[0141] The above embodiments are only used to illustrate the technical solutions of the present application rather than to limit them. Although the present application has been described in detail with reference to the above preferred embodiments, those of ordinary skill in the art should understand that the technical solutions of the present application can be modified or equivalently replaced without departing from the spirit and scope of the technical solutions of the present application.

Claims

1. A wing structure, characterized in that: include: airfoil body; A control rudder surface is arranged on one side of the wing body; Two rotating connection mechanisms, the two rotating connection mechanisms are arranged at intervals along the length direction of the control rudder surface; the control rudder surface is rotatably connected to the trailing edge of the airfoil body through the two rotating connection mechanisms; as well as, The driving assembly includes a steering gear and a transmission mechanism; the steering gear is installed on the wing body; the transmission mechanism is connected between the steering gear and the control surface to drive the control surface to rotate relative to the wing body; the position where the transmission mechanism is connected to the control surface is located between the two rotation connection mechanisms.

2. The airfoil structure according to claim 1, characterized in that: The wing body is a main wing, and the control surface is an aileron; The main wing comprises a main beam, a rear beam, a rear rib, a main wing lower skin and a main wing upper skin, wherein the rear rib is connected between the main beam and the rear beam; the main wing upper skin is covered on the upper surfaces of the main beam and the rear beam, the main wing lower skin is covered on the lower surfaces of the main beam and the rear beam, and an internal space is defined between the main wing lower skin and the main wing upper skin; the main wing lower skin is provided with a through opening communicating with the internal space; The servo is arranged in the internal space and fixedly mounted on the rear rib; the transmission mechanism comprises a servo rocker arm, a connecting rod and a rudder angle, one end of the servo rocker arm is connected to the output shaft of the servo, and the other end extends out of the lower skin of the main wing from the through-hole; one end of the rudder angle is fixedly connected to the control control surface, and the other end extends in a direction away from the control control surface; the connecting rod is located outside the lower skin of the main wing, and one end of the connecting rod is rotatably connected to one end of the servo rocker arm away from the main wing, and the other end is rotatably connected to one end of the rudder angle away from the control control surface.

3. The airfoil structure according to claim 2, characterized in that: The main wing also includes a fairing cover; The fairing cover is detachably covered on the through opening, and the fairing cover defines a channel groove located below the lower skin of the main wing; The channel groove extends along the front-rear direction of the main wing, and one end of the channel groove is connected to the internal space, and the other end is open toward one side of the control control surface; The steering gear rocker arm passes through the through opening and enters the channel groove, and the connecting rod extends out of the opening of the channel groove along the channel groove and is connected to the steering angle.

4. The airfoil structure according to claim 3, characterized in that: The fairing cover includes a cover plate and a protruding surrounding wall, wherein the protruding surrounding wall protrudes outward from the cover plate to define the channel groove.

5. The airfoil structure according to claim 2, characterized in that: The connecting rod comprises a rod body and two rod heads, and the two rod heads are respectively threadedly connected to two ends of the rod body, so that the length of the connecting rod can be adjusted; One of the rod heads is transmission-connected to the steering gear rocker arm, and the other rod head is transmission-connected to the rudder angle.

6. The airfoil structure according to claim 2, characterized in that: The aileron has an aileron spar and an aileron skin, wherein the aileron spar is supported in the aileron skin; A rudder angle connection seat is connected to the inner side of the aileron beam, and the rudder angle is fixedly connected to the rudder angle connection seat.

7. The airfoil structure according to claim 6, characterized in that: The main wing comprises an upper skin of the main wing and a lower skin of the main wing; The aileron skin comprises an aileron upper skin and an aileron lower skin, and the aileron upper skin and the aileron lower skin are respectively covered on the upper and lower sides of the aileron beam; The aileron upper skin includes a first large surface segment and a first arc segment, and the aileron lower skin includes a second large surface segment and a second arc segment; There is a first gap between the first large surface segment and the main wing upper skin, and there is a second gap between the second large surface segment and the main wing lower skin; The first arc segment is an arc centered on the rotation axis of the aileron relative to the main wing, and the first arc segment is transitionally connected to an end of the first large surface segment close to the upper skin of the main wing; The second arc segment is an arc centered on the rotation axis of the aileron relative to the main wing, and the second arc segment is transitionally connected to an end of the second large surface segment close to the lower skin of the main wing.

8. The airfoil structure according to claim 7, characterized in that: A first groove is formed at a position of the first arc segment corresponding to the rotating connection mechanism, and a second groove is formed at a position of the second arc segment corresponding to the rotating connection mechanism; The cutting depth of the second groove is greater than that of the first groove.

9. The airfoil structure according to claim 2, characterized in that: The connection position E between the rudder angle and the control rudder surface is located on the side of the control rudder surface away from the rotation center B of the servo rocker arm relative to the rotation center A of the wing body, and the rudder angle is obliquely connected between the connection position E and the connecting rod.

10. The airfoil structure according to claim 9, characterized in that: The rudder angle includes a connecting plate, a first inclined section and a second inclined section; the connecting plate is overlapped and connected to the lower surface of the control rudder surface, the first inclined section is connected to the connecting plate and is inclined toward the side close to the servo rocker arm; the second inclined section is connected to the first inclined section and is inclined toward the side close to the servo rocker arm.

11. The airfoil structure according to any one of claims 1 to 10, characterized in that: The two rotating connection mechanisms are respectively located at positions at which the distances from the two ends of the control rudder surface in the length direction are 1 / 4 of the length of the control rudder surface; The position where the transmission mechanism is connected to the control surface is located at the midpoint of the length of the control surface.

12. An aircraft, characterized in that: include: body; as well as, The wing structure according to any one of claims 1 to 11, wherein the wing structure is connected to the fuselage.

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