CN111907694A - Wing trailing edge and wing with variable camber - Google Patents

Abstract

The invention provides a variable camber trailing edge and a wing that can realize continuous bending of the trailing edge of the wing. The flexible hinge of the wing rib and the rear sub-rib, the flexible hinge includes a first cross leaf and a second cross leaf, and the first cross leaf and the second cross leaf are in the front and rear directions of the trailing edge of the wing according to the space cross line way to configure. The trailing edge of the wing in the present invention adopts a segmented structure, and adjacent sub-ribs are connected by flexible hinges, which has the advantages of strong flexibility, simple structure and light weight.

Description

A variable camber trailing edge and wing

technical field

The invention belongs to the technical field of aerospace equipment, and in particular relates to a wing trailing edge and a wing with variable camber based on a flexible hinge to realize continuous bending of the trailing edge of the wing.

Background technique

The wing is the provider of aircraft lift and an important component that determines the flight capability of the aircraft. Its main function is to generate aerodynamic lift and ensure the aircraft performance and maneuverability under all flight conditions specified by the technical requirements. The traditional fixed rigid wing uses flaps, leading edge slats, etc. as the wing lift device, which improves the aerodynamic performance of the aircraft by changing the camber and shape of the wing section. However, in the design of traditional wings, only considering the optimal performance in a specific flight situation, it is difficult to meet the flight conditions of multiple missions; on the other hand, when the traditional rigid wing is deformed, it will inevitably produce Abrupt changes in gaps and curvature disrupt the continuity of the wing surface, which degrades the aerodynamic characteristics of the aircraft.

Chinese patent 201410359555.5 discloses a wing trailing edge with variable camber for an aircraft wing. The aircraft wing includes a middle part of the wing with invariable camber, and the middle part of the wing includes a main beam; the trailing edge of the wing with variable camber includes A rear beam, a plurality of groups of trailing edge rod group structures arranged in parallel, and a trailing edge driving mechanism; the rear beam is connected to the rear end of the main beam; the trailing edge driving mechanism includes a rocker driven by a driving device, one end of the rocker is rotatably connected to the rear beam, The other end of the rod is rotatably connected to the trailing edge rod group structure; the trailing edge rod group structure is a plane rod group structure based on a 5R closed-loop unit, which has one degree of freedom; wherein, each group of trailing edge rod group structures includes pairs of Multiple pairs of 5R closed-loop units, multiple networking triangle units, one terminal 4R closed-loop unit and one terminal triangle unit; each pair of 5R closed-loop units includes an upper 5R closed-loop unit and a lower 5R closed-loop unit; The combination of multiple planar 5R closed-loop units and multiple networked triangular units realizes the change of trailing edge camber.

SUMMARY OF THE INVENTION

The invention provides a wing trailing edge and a wing with variable camber that can realize continuous bending of the trailing edge of the wing. The trailing edge of the wing adopts a segmented structure, and adjacent sub-ribs are connected by flexible hinges. It has the advantages of strong flexibility, simple structure and light weight.

The technical scheme of the present invention is:

A variable-camber trailing edge of a wing at least includes a front sub-rib, a rear sub-rib, a flexible hinge connecting the front sub-rib and the rear sub-rib, and the flexible hinge includes a first cross spring, a second cross spring The first cross-reed and the second cross-reed are arranged in a space cross-line manner in the front-rear direction of the trailing edge of the wing.

According to another specific embodiment of the present invention, the front sub-rib is provided with a front arc-shaped connecting portion facing the rear, and the rear sub-rib is provided with a rear arc-shaped connecting portion facing forward, wherein the first cross spring The front end of the first cross spring is arranged on the front arc connecting part, the rear end of the first cross spring is arranged on the rear arc connecting part, the front end of the second cross spring is arranged on the front arc connecting part, and the rear end of the second cross spring is arranged on the front arc connecting part. at the rear arc connection.

According to another specific embodiment of the present invention, the front and rear ends of the first cross spring have first arc connecting ears respectively matching the arcs of the front arc connecting part and the rear arc connecting part, and the second cross spring The front and rear ends of the sheet are provided with second arc-shaped connecting ears respectively matching the radians of the front arc-shaped connecting portion and the rear arc-shaped connecting portion.

According to another specific embodiment of the present invention, the position of the intersection of the first cross leaf and the second cross leaf is offset from the rear sub-rib, and the first cross leaf and the second cross leaf are in an X shape. shape or V shape.

According to another specific embodiment of the present invention, the first cross reed and the second cross reed are located on the left and right sides of the front sub-rib and the rear sub-rib, respectively, and the front sub-rib and the rear sub-rib are opposite each other. contact and form a rotational fit at the point of contact.

A variable camber wing, comprising a wing leading edge with an invariable camber, two or more variable camber wing trailing edges and a wing skin, wherein the wing trailing edge comprises:

N successively connected sub-ribs, where N≥2;

a flexible hinge connecting two adjacent sub-ribs; and

drive device;

The flexible hinge includes a first cross reed and a second cross reed. The first cross reed and the second cross reed are configured in the form of a space cross line in the front and rear directions of the trailing edge of the wing to connect the n-1th sub-wing respectively. Rib and nth sub-rib, where 2≤n≤N;

The drive device includes a connecting rod, a rocker and a driver. The connecting rod is fixedly connected to the sub-ribs in the trailing edges of different wings, and the driver is fixed on the leading edge of the wing. One end of the rocker is connected to the connecting rod, and the other end of the rocker is Connected with the output end of the driver, the middle part of the rocker is connected to the leading edge of the wing through a hinge point, and the driver drives the rocker to rotate around the hinge point, so that the trailing edge of the wing is driven by the connecting rod to perform a pitching and bending motion.

According to another specific embodiment of the present invention, the driver is a steering gear, an eccentric rocker arm is provided at the output end of the driver, the other end of the rocker is provided with a connecting groove, and the rocker arm is placed in the connecting groove and can be connected in the connecting groove. Swipe in.

According to another specific embodiment of the present invention, the number of sub-ribs in the trailing edge of the wing is 3-8.

According to another specific embodiment of the present invention, the wing skin is an elastic skin that can generate elastic deformation in the process of changing the camber of the trailing edge of the wing, and the wing skin is connected to the leading edge of the wing through rivets.

The present invention has the following beneficial effects:

The invention can realize the effect of continuous bending of the trailing edge of the wing, adjust the camber of the wing during flight, change aerodynamic parameters such as lift-drag ratio, and achieve better aerodynamic efficiency of the aircraft under different flight conditions.

In addition, the wing rib of the present invention adopts a segmented design and a flexible design, has a simple structure, and is light in weight, and avoids a series of problems such as hinge gap and friction force of a rigid structure.

In addition, the arc connection structure is adopted between the first cross spring and the second cross spring and the front sub-rib and the rear sub-rib in the present invention. connection effect. At the same time, the stiffness of the trailing edge of the wing can be changed by changing the first and second cross springs with different thicknesses to meet the requirements of different flight conditions of the aircraft.

In addition, the present invention has a large deformation range, the rigid drive device carries the air load, has a large carrying capacity, and at the same time has a simple structure and is easy to maintain.

The present invention will be further described in detail below in conjunction with the accompanying drawings.

Description of drawings

Fig. 1 is the structural representation of the wing of the present invention;

Fig. 2 is the schematic diagram of the present invention showing the trailing edge of the wing;

3 is a schematic diagram of the present invention showing two adjacent sub-ribs;

Fig. 4 is the exploded schematic diagram of two sub-ribs in Fig. 3;

Fig. 5 is the schematic diagram showing the drive mechanism of the present invention;

Figure 6 is a simplified schematic view of the downwardly curved trailing edge of a wing of the present invention.

Detailed ways

A variable camber wing, as shown in Figures 1-6, includes a wing leading edge 100 with a constant camber, a variable camber trailing edge 200, and a wing skin.

In this example, the wing skin (not shown in the figure) is connected with the leading edge 100 of the wing by riveting. In order to better change with the curvature of the trailing edge 200 of the wing, the wing skin adopts elastic The skin is adapted to deform when the camber of the trailing edge of the wing is changed by 200 degrees.

The trailing edge 200 of the wing includes five sub-ribs 210 connected in sequence, two adjacent sub-ribs 210 are connected by flexible hinges 220, and the five sub-ribs 210 are driven by the driving device 230 to bend upward or downward Bending, wherein, in order to adapt to the shape of the trailing edge 200 of the wing, the shapes of the five sub-ribs 210 are not exactly the same. Referring to FIGS. 1 and 2 , the first sub-rib 210a, the second sub-rib 210b, the third The sub-rib 210c, the fourth sub-rib 210d, and the fifth sub-rib 210e, wherein the first sub-rib 210a, the second sub-rib 210b, the third sub-rib 210c, and the fourth sub-rib 210d are close to present a ladder shape, the fifth sub-rib 210e is approximately triangular.

The connection structure between the third sub-rib 210c and the fourth sub-rib 210 is described in detail below:

As shown in FIGS. 3 and 4 , the flexible hinge 220 includes a first cross leaf 221 and a second cross leaf 222 . The first cross leaf 221 and the second cross leaf 222 are in the front-rear direction of the trailing edge 200 of the wing. Configured according to the space cross line.

In order to improve the degree of connection and cooperation between the first cross springs 221 and the second cross springs 222 and the third sub-rib 210c and the fourth sub-rib 210, a circular arc connection structure is adopted in this example.

The third sub-rib 210c is provided with a front arc-shaped connecting portion 211 facing rearward, the fourth sub-rib 210d is provided with a rear arc-shaped connecting portion 212 facing forward, and the front end of the first cross spring 221 is provided at (specifically For snap connection) the front arc-shaped connecting portion 211, the rear end of the first cross spring 221 is arranged on the rear arc connecting portion 212, the front end of the second cross spring 222 is arranged on the front arc connecting portion 211, and the second cross spring The rear end of the piece 222 is disposed on the rear arc connecting portion 212 .

The front and rear ends of the first cross reed 221 have first arc connecting ears 223 that match the radians of the front arc connecting portion 211 and the rear arc connecting portion 212 respectively. The ends have second arc-shaped connecting ears (similar to the first arc-shaped connecting lugs 223, not shown in the figure) that match the arcs of the front arc-shaped connecting portion 211 and the rear arc-shaped connecting portion 212 respectively.

In this example, the intersection of the first cross leaf 221 and the second cross leaf 222 is offset from the fourth sub-rib 210d. The X-shaped structure shown.

Referring to FIG. 3 again, an arrangement structure of the first cross reed 221 and the second cross reed 222 in this example is located on the left and right sides of the third sub-rib 210c and the fourth sub-rib 210d, respectively. The rib 210c and the fourth sub-rib 210d are in contact with each other and form a rotating fitting structure at the contact point. Specifically, the third sub-rib 210c is provided with a connecting angle 213, and the fourth sub-rib 210d is provided with a limiter. A position slot 214 , wherein the connecting angle 213 is placed in the position limit groove 214 and can generate rotational displacement in the position limit groove 214 .

As shown in FIG. 1 and FIG. 5 , the driving device 230 includes a connecting rod 231 , a rocker 232 , a steering gear 233 , and a rocker arm 234 .

The connecting rod 231 is fixedly connected to the sub-ribs 210 (specifically, connected to the fifth sub-rib 210) in different wing trailing edges 200, and a wing box 300 is provided on the wing leading edge 100, and the wing box 300 has a spacer The plate 310 and the fixing frame 320, the steering gear 233 is fixed on the partition 310 and located in the wing box 300, the rocker arm 234 is eccentrically arranged at the output end of the steering gear 233, one end of the rocker 232 is connected with the connecting rod 231, The other end of the rod 232 is provided with a connecting groove 232a, and the rocker arm 234 is placed in the connecting groove 232a and can slide in the connecting groove 232a. The rocker 232 can be driven to rotate about the hinge point 235 , so that the trailing edge 200 of the wing is driven to perform a downward bending motion and an upward bending motion through the connecting rod 231 .

Specifically, when the wing needs to be deformed, the steering gear 233 rotates according to the set direction, and the rocker 232 is driven to rotate around the hinge point 235 by the rocker arm 234. Since the rocker 232 and the connecting rod 231 (specifically, a carbon fiber rod) are fixed The connecting rod 231 is fixedly connected with the sub-rib 210 in the trailing edge 200 of the wing, so the rotation of the rocker 232 can drive the trailing edge 200 of the wing to move together.

Each set of the first cross springs 221 and the second cross springs 222 in the rear edge 200 of the rib constitutes a flexible hinge 220, and each flexible hinge 220 is bent under the action of the force of the driving device 230, resulting in the rear edge 200 of the rib. Bend up or down segment by segment, thus realizing the variable camber process of the wing.

Although the present invention is disclosed above with preferred embodiments, it is not intended to limit the scope of implementation of the present invention. Any person of ordinary skill in the art can make some improvements without departing from the scope of the present invention, that is, all equivalent improvements made according to the present invention should be covered by the scope of the present invention.

Claims (9)

1. The wing trailing edge with variable camber is characterized by at least comprising a front sub-wing rib, a rear sub-wing rib and a flexible hinge for connecting the front sub-wing rib and the rear sub-wing rib, wherein the flexible hinge comprises a first cross reed and a second cross reed, and the first cross reed and the second cross reed are arranged in a spatial cross line mode in the front-rear direction of the wing trailing edge.

2. The variable camber trailing edge of claim 1, wherein the leading sub-rib defines a rearwardly facing leading arcuate joint and the trailing sub-rib defines a forwardly facing trailing arcuate joint, wherein the leading end of the first cross-spring is disposed at the leading arcuate joint, the trailing end of the first cross-spring is disposed at the trailing arcuate joint, the leading end of the second cross-spring is disposed at the leading arcuate joint, and the trailing end of the second cross-spring is disposed at the trailing arcuate joint.

3. The variable camber trailing edge of claim 2, wherein said first cross spring has first curved engaging lugs at front and rear ends thereof respectively matching the camber of said front and rear curved connecting portions, and said second cross spring has second curved engaging lugs at front and rear ends thereof respectively matching the camber of said front and rear curved connecting portions.

4. The variable camber trailing edge of claim 2, wherein an intersection of the first cross spring and the second cross spring is positioned offset from the trailing subfin, the first cross spring and the second cross spring having an X-shape or a V-shape therebetween.

5. The variable camber trailing edge of claim 1, wherein the first cross reed and the second cross reed are located on the left and right sides of the leading sub-rib and the trailing sub-rib, respectively, and the leading sub-rib and the trailing sub-rib contact each other to form a running fit at the contact point.

6. A variable camber airfoil comprising a camber-invariant airfoil leading edge, two or more variable camber airfoil trailing edges, and an airfoil skin, wherein the airfoil trailing edge comprises:

n sequentially connected sub-ribs, wherein N is more than or equal to 2;

a flexible hinge connecting two adjacent sub-ribs; and

a drive device;

the flexible hinge comprises a first cross reed and a second cross reed, the first cross reed and the second cross reed are arranged in a space cross line mode in the front-back direction of the trailing edge of the wing to respectively connect the (N-1) th sub-wing rib and the (N) th sub-wing rib, wherein N is more than or equal to 2 and less than or equal to N;

the driving device comprises a connecting rod, a rocker and a driver, the connecting rod is fixedly connected with the sub-wing ribs in different wing trailing edges, the driver is fixed on the wing leading edge, one end of the rocker is connected with the connecting rod, the other end of the rocker is connected with the output end of the driver, the middle part of the rocker is connected onto the wing leading edge through a hinge joint, and the driver drives the rocker to rotate around the hinge joint so as to drive the wing trailing edges to perform pitching bending action through the connecting rod.

7. The variable camber airfoil of claim 6, wherein the actuator is a steering engine, an eccentric rocker arm is disposed at an output end of the actuator, and a connecting groove is disposed at the other end of the rocker arm, and the rocker arm is disposed in the connecting groove and is capable of sliding in the connecting groove.

8. The variable camber wing according to claim 6, wherein the number of sub-ribs in the trailing edge is 3-8.

9. The variable camber wing of claim 6, wherein the wing skin is an elastomeric skin capable of elastically deforming in response to the camber process at the trailing edge of the wing, the wing skin being attached to the leading edge of the wing by rivets.

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