CN110920865B - A retractable wing structure with continuously variable wingspan - Google Patents

Abstract

The invention discloses a telescopic wing mechanism with a continuously variable wingspan. It consists of an inner section wing, an outer section wing, a middle section wing nested between the inner section wing and the outer section wing, a first linear motor and a second linear motor respectively used to drive the outer section wing and the inner section wing to move in the spanwise direction. The motor is composed; one end of the front spar and the rear spar of the inner wing is connected with the fuselage, and the other end is inserted into the front spar and the rear spar of the middle wing. The front spar and the rear spar of the outer section wing are inserted into the front spar and the rear spar of the middle section wing. The front and rear beams of each section of the wing are placed in parallel, and the three sections of the wings are all telescopic along the direction of the front and rear beams. The telescopic movement of the outer section wing relative to the middle section wing is realized through the linear motor fixed on the middle section wing; the telescopic movement of the outer section wing and the middle section wing is realized relative to the inner section wing. The telescopic positioning is realized by the internal locking mechanism of the linear motor. The three sections of the wing all use the NACA2412 airfoil, and the aerodynamic load of the wing is transmitted from the skin to the spar through the rib. During telescopic deformation, the inner and outer wing skins are looped over the middle skin.

Description

A retractable wing structure with continuously variable wingspan

technical field

The invention belongs to the field of aircraft design and technology, and in particular relates to a telescopic wing structure with a continuously variable wingspan applied to a fixed-wing aircraft.

Background technique

Most traditional aircraft use a single wing aerodynamic layout to meet the aerodynamic requirements of their main mission conditions. However, some aircraft need to meet multi-mission conditions (such as taking into account both high-speed cruise control and low-speed mission cruise). At this time, the wing with a single aerodynamic layout can no longer meet the requirements of this type of aircraft design. This requires a wing design that can change its aerodynamic shape according to the requirements of the flight mission and take into account different speed requirements. When the aircraft is taking off, landing, and cruising at low speeds, the wings are fully extended to provide maximum lift and reduce lift drag. When the aircraft is cruising at high speeds, the wings are fully retracted to reduce the wetting area, thereby reducing frictional drag.

SUMMARY OF THE INVENTION

In order to achieve the above functions, the present invention proposes a three-stage rectangular telescopic wing suitable for low Mach number (speed less than 300 km/h) flight conditions.

The telescopic wing structure consists of an inner section wing, an outer section wing, a middle section wing nested between the inner section wing and the outer section wing, and a first straight line for driving the outer section wing and the inner section wing to move in the span direction respectively. The motor and the second linear motor are composed; the inner section wing, outer section wing and middle section wing are all composed of a plurality of ribs, intercostal laminates fixed between the ribs, front beams and rear beams fixed with the ribs, The skin fixed on the outer side of the wing rib is composed of the front spar and the rear spar of the inner section wing extending to the outside of the inner section wing; the front spar of the middle section wing includes the inner front spar and the outer front spar arranged side by side, and the rear spar of the middle section wing includes The inner rear spar and outer rear spar are arranged side by side; the front and rear spar of the inner and outer wings are cylindrical spar, the front and rear spar of the middle wing are cylindrical hollow tubes, and the outer diameter of the cylindrical spar It is matched with the inner diameter of the cylindrical hollow tube; the front beam and the rear beam of the inner section wing and the outer section wing are respectively sleeved in the front beam and the rear beam of the middle section wing. The first linear motor and the second linear motor are arranged side by side in the mid-section wing. The three-section interwing loads are conducted by the internal structure. The front and rear outer spar of the mid-section wing are made of cylindrical hollow tubes, and the inner section of the wing is made of cylindrical spar. The outer diameter of the cylindrical spar of the inner wing is slightly smaller than the inner diameter of the front and rear outer spar of the middle wing to ensure that the inner wing and the middle wing have no relative movement in the X direction (front and rear) and Z direction (up and down direction), while in the Y direction ( Left and right directions) slide freely.

Similarly, cylindrical hollow tubes are used for the front and rear inner spar of the mid-section wing, and cylindrical spar is used for the outer section wing. The outer diameter of the cylindrical spar of the outer wing is slightly smaller than the inner diameter of the front and rear inner spar of the middle wing to ensure that the outer wing and the middle wing have no relative movement in the X direction (front and rear) and Z direction (up and down direction), while in the Y direction ( Left and right directions) slide freely.

When there is no air to deform, the skin does not bear and transmit the load between the three sections of the wing. When the wing is deformed by aerodynamic bending, the skin will contact each other and bear part of the load. But the main load is carried by the spars.

An important performance indicator of a telescopic wing is the wing telescopic ratio (that is, the area of the wing that is fully deployed divided by the area that is fully retracted). The larger the telescopic ratio, the stronger the ability of the wing to adapt to different flight conditions. In the present invention, the large expansion ratio is realized through the following two schemes:

(1) The first linear motor and the second linear motor are staggered in the inner structure of the mid-section wing:

Since linear motors require a drive mechanism inside the motor rod, their telescopic travel is always less than their own length. The upper and lower staggered arrangement adopted in the present invention, the driving mechanism section of the two motors and the telescopic stroke section overlap each other in the chordwise direction of the wing, thereby eliminating the adverse effect on the expansion ratio of the wing due to the existence of the driving mechanism, and maximizing the wing the expansion ratio;

(2) The inner front beam, outer front beam, inner rear beam, and outer rear beam of the mid-section wing are staggered respectively:

When fully extended, the inner, middle and outer spars need to have sufficient overlap. On the one hand, the wing can bear the aerodynamic load; freely. Therefore, the front and rear spar of the mid-section wing are designed with a staggered layout, which ensures that when the wing is fully retracted, the inner and outer spar will not interfere with each other (as shown in Figure 4). There is still enough contact length (as shown in Figure 2) to ensure the connection strength;

The beneficial effects of the present invention are:

(1) The telescopic wing in the present invention expands and contracts along the span, and the spars of the three-section wings are nested in pairs, constraining the movements in the X-direction (front and rear) and Z-direction (up-down direction) of the wing, and does not constrain the three-section wings Movement in the Y direction (left and right). The three-section wings have no relative movement in the X and Z directions and can slide freely in the Y direction (left and right directions);

(2) The telescoping control of the wing is realized by two linear motors respectively, and the linear motor moves telescopically along the Y direction, thereby controlling the telescoping of the wing. The two linear motors are independent of each other and control the telescopic movement of the middle wing and the outer wing respectively. The movement of the outer wing is not coupled with the middle wing and the inner wing. When the upper linear motor moves, only the outer wing moves. When the upper linear motor is stationary, the middle wing and the outer wing are relatively stationary. When the lower linear motor moves, the middle wing and the outer wing move together. The limit of the movement of the three-section wings in the span direction (Y direction) is realized by the locking mechanism inside the linear motor, and the wings do not move when the motor is stationary;

(3) The skins of the three-section wings are independent of each other and are respectively fixed to their respective internal mechanisms. When the wing is retracted, the inner and middle wing skins, as well as the middle and outer wing skins can slide freely. There may be friction between the skins when the wing is aerodynamically deformed. Apart from friction, there are no other constraints between the skins.

(4) The present invention provides a wing that can change its aerodynamic shape according to the requirements of the flight mission and take into account different speed requirements. To maximize lift and reduce lift drag, when the aircraft is cruising at high speed, the wings of the present invention are fully retracted to reduce the wetted area, thereby reducing frictional drag.

Description of drawings

Fig. 1 is three views of the design wing of the present invention, wherein a is a top view, b is a left view, and c is a front view;

Fig. 2 is the schematic diagram of the mechanism when the wings of the present invention are fully extended;

3 is a schematic diagram of the mechanism when the wing part is retracted in the design of the present invention;

4 is a schematic diagram of the mechanism when the wings are fully retracted according to the design of the present invention;

5 is a three-dimensional view and a side view of the skin of the inner section and the middle section of the wing according to the present invention;

In the figure, the inner section wing 1, the middle section wing 2, the outer section wing 3, the inner section wing front beam 4, the inner section wing rear beam 5, the middle section wing outer front beam 6A, the middle section wing outer rear beam 6B, the middle section wing inner front beam 7A, Middle wing inner rear spar 7B, outer wing front spar 8, outer wing rear spar 9, first linear motor 10, second linear motor 11, middle wing skin 12, outer wing skin 14, outer wing rib 15A, 15B, inner section wing skin 16, inner section wing ribs 17A, 17B, outermost section wing rib 18B, middle section wing ribs 19A and 19B, inner section wing inter-rib layer plate 20, middle section wing inter-rib layer Plate 21 , outer section wing inter-rib layer plate 22 , motor fixing blocks 31A, 31B, 31C, 31D, outer section wing motor fixing block 32 .

Detailed ways

The purpose of the present invention is to provide a set of mechanisms that can change the span of the wings, so that the aircraft equipped with the wings has good high-speed and low-speed performances. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS is described in conjunction with the abstract drawings and FIGS.

The wing is a three-stage telescopic wing mechanism, including an inner wing 1, a middle wing 2, an outer wing 3, and a second linear motor 11 for driving the inner wing 1 and the outer wing 3 to move in the span direction respectively. , the first linear motor 10 . The three sections of wings are all composed of a plurality of ribs, an inter-rib laminate fixed between the ribs, a front beam and a rear beam fixed with the ribs, Skin composition on the outside of the rib. The front spar and the rear spar of the inner section wing 1 extend to the outside of the inner section wing 1; the three sections of the wing are described in detail below with reference to Figure 1:

As shown in Figures 1 and 2, the specific internal structure of the inner section wing 1 includes ribs 17A and 17B, the inner section wing inter-rib laminate 20, the inner section wing front spar 4 and the inner section wing rear spar 5. The inner section wing rib The laminates 20 are fixed between the inner wing ribs, and the inner wing front spar 4 and the inner wing rear spar 5 are respectively fixed to the inner wing ribs; by means of gluing and fastener connection, these parts are fixedly connected to each other to form Inner wing box. The inner wing front spar 4 and the inner wing rear spar 5 extend to the outside of the inner wing 1 for connecting the fuselage; the inner wing 1 is also provided with a motor fixing block 30 for fixing with the first linear motor 10 connect.

Similarly, the specific internal structure of the outer section wing 3 includes the ribs 18A and 18B, the outer section wing inter-rib laminate 22 , the outer section wing front spar 8 , the outer section wing rear spar 9 and the motor fixing block 32 and other components. The outer section wing inter-rib laminate 22 is located between the outer section wing ribs, and the outer section wing front spar 8 and the outer section wing rear spar 9 are respectively connected with the outer section wing ribs. These components are connected by gluing and fasteners. They are fastened to each other to form the outer wing box. The outer segment wing 3 is also provided with a motor fixing block 32 for fixed connection with the second linear motor 11 .

The specific internal structure of the mid-section wing 2 includes the ribs 19A and 19B, the middle-section wing inter-rib laminate 21 fixed between the middle-section wing ribs, the middle-section wing front spar 6A and 7A, and the middle-section wing rear spar 6B and 7B and a plurality of motor fixing blocks 31A, 31B, 31C, 31D and other components. By means of gluing and fasteners, these parts are fastened to each other to form a mid-section wing box. The mid-section front spar includes a mid-section inner front spar 7A and a mid-section outer front spar 6A, and the middle-section rear spar includes a mid-section inner rear spar 7B and a mid-section outer rear spar 6B arranged side by side.

Among them, the inner section front spar 4, the inner section rear spar 5, the outer section front 8 and the outer section rear spar 9 all adopt cylindrical spar, the middle section front spar 6A and 7A, and the middle section rear spar 6B and 7B adopt cylindrical spar The outer diameter of the cylindrical wing spar is matched with the inner diameter of the cylindrical hollow tube, so that the inner wing front spar 4 and the inner wing rear spar 5 can be inserted into the middle wing outer front spar 6A and the middle wing outer rear spar 6B respectively. , the front spar 8 of the outer section and the rear spar 9 of the outer section can be inserted into the inner front spar 7A of the middle section and the inner rear spar 7B of the middle section respectively. In addition, in the present invention, the lengths of the inner wing front spar 4 and the inner wing rear spar 5 are greater than the lengths of the inner wing box and the inner wing skin, and the outer wing front spar 8 and the outer wing rear spar 9 are longer than the outer wing box. And the length of the outer wing skin, to ensure that the inner wing 1 and the middle wing 2, the outer wing 3 and the middle wing 2 still have enough overlap when the wings are fully deployed, so as to ensure that the front and rear The stiffness of the spar connection also prevents the spar from being stuck to each other when the wing is retracted when the wing is fully deployed, so that the middle wing 2 can slide freely with respect to the inner wing 1 and the outer wing 3 relative to the inner wing 1 in the spanwise direction.

In addition, the first linear motor 10 and the second linear motor 11 are staggered and arranged in the mid-section wing 2 in the spanwise direction through a plurality of motor fixing blocks 31A, 31B, 31C, and 31D. By controlling the movement of the first linear motor 10 and the second linear motor 11, the movement of the middle wing 2 relative to the inner wing 1 and the outer wing 3 relative to the middle wing 2 can be realized. When the motor is stationary, the self-locking mechanism in the linear motor Make sure that the spanwise length of the wings remains the same. Since linear motors require a drive mechanism inside the motor rod, their telescopic travel is always less than their own length. With side-by-side arrangement, the driving mechanism sections of the two motors and the telescopic stroke sections overlap each other, thereby eliminating the adverse effect on the expansion and contraction ratio of the wing due to the existence of the driving mechanism, and maximizing the expansion and contraction ratio of the wing. The two linear motors are fixedly connected to the middle wing box through the motor fixing block, and there is no mutual movement between the two motors.

As shown in Figure 2-4, Figure 2 is a schematic diagram of the mechanism when the wings are fully extended, Figure 3 is a schematic diagram of the mechanism when the wings are partially retracted, and Figure 4 is a schematic diagram of the mechanism when the wings are fully retracted. The specific telescopic movement of the wing includes two parts: the telescopic movement of the outer section wing 3 relative to the middle section wing 2 and the telescopic movement of the middle section wing 2 relative to the inner section wing 1 .

The telescopic movement of the outer section wing 3 relative to the middle section wing 2 is realized by the telescopic movement of the first linear motor 10 . The specific embodiment is that the driving mechanism section of the first linear motor 10 is fixed on the mid-section wing 2 in the spanwise direction, and the telescopic motion of the motor push rod can only be performed in the spanwise direction of the wing. The push rod of the motor is fixedly connected with the inner structure of the outer section wing 1 through the motor fixing block 32 . On the other hand, due to the constraints of the front and rear spar of the wing, the wing only has the freedom of movement in the spanwise direction. Through the mutual cooperation between the spar and the electric push rod, the outer section wing 3 can move freely in the spanwise direction, while the movement in other directions is restrained. The telescopic speed of the outer section wing 3 is equal to the telescopic speed of the first linear motor 10 .

Similarly, the telescopic movement of the middle section wing 2 relative to the inner section wing 1 is realized by the telescopic movement of the second linear motor 11 . The specific embodiment is that the driving mechanism section of the second linear motor 11 is fixed on the mid-section wing in the spanwise direction, and the telescopic motion of the motor can only be performed in the spanwise direction. The push rod of the motor is fixedly connected with the inner structure of the inner section wing 1 through the fixing block 30 . On the other hand, due to the constraints of the front and rear spar of the wing, the wing only has the freedom of movement in the spanwise direction. Through the mutual cooperation of the spar and the electric push rod, the mid-section wing 2 can move freely in the spanwise direction, while the movement in other directions is restrained. The telescopic speed of the mid-section wing 2 is equal to the telescopic speed of the second linear motor 11 .

The movements of the two linear motors are independent of each other, and can be moved separately or simultaneously. When only the first linear motor 10 moves, only the outer section wing 3 will perform telescopic motion. When only the second linear motor 11 moves, the middle section wing 2 and the outer section wing 3 do not move relative to each other, and the whole body performs telescopic motion relative to the inner section wing 1 .

The inner section wing skin 16 is fixedly connected to the inner section wing box by means of gluing. The mid-section wing skin 12 is fixedly connected to the mid-section wing box by means of gluing. The outer section wing skin 14 is fixedly connected with the outer section wing box by means of gluing. The skin is rigid enough to retain its shape under aerodynamic loads.

The skins of the three wings overlap each other. Preferably, the airfoil profiles of the skins of the three-section wings are all NACA2412, but not limited thereto. The outer section wing skin 14 and the inner section wing skin 16 have the same size, while the airfoil section of the middle section wing skin 12 is slightly smaller.

The middle wing skin 12 can be nested into the inner wing skin 16, and there is a sufficient geometric gap between the two skins, as shown in FIG. 5 . When the wings are fully extended, the two skins still have sufficient contact length to avoid the skins from sticking to each other. This allows the wings to slide freely between the skins when the wings are fully extended.

Similarly, the middle wing skin 12 can be nested into the outer wing skin 14 with sufficient geometric clearance between the two skins. When the wings are fully extended, the two skins still have sufficient contact length to avoid the skins from sticking to each other. This allows the wings to slide freely between the skins when the wings are fully extended.

Claims (1)

1. A telescopic wing with a continuously variable wingspan, characterized in that it consists of an inner segment wing (1), an outer segment wing (3), a nested inner segment wing (1), and an outer segment wing (3). The middle section wing (2) in between, the first linear motor (10) and the second linear motor (11) respectively used to drive the outer section wing (3) and the inner section wing (1) to move in the span direction; the The inner section wing (1), the outer section wing (3) and the middle section wing (2) are all composed of a plurality of ribs, intercostal laminates fixed between the ribs, front and rear beams fixed with the ribs, fixed The skin on the outside of the wing rib is composed; the front spar and rear spar of the inner wing (1) extend to the outside of the inner wing (1); the front spar of the middle wing (2) includes the inner front spar and the outer spar arranged side by side The front spar and the rear spar of the mid-section wing (2) include inner rear spar and outer rear spar arranged side by side; the front and rear spar of the inner-section wing (1) and the outer-section wing (3) are cylindrical spar, and the mid-section wing (2) ) of the front and rear beams are cylindrical hollow tubes, the outer diameter of the cylindrical wing spar is matched with the inner diameter of the cylindrical hollow tube; the front and rear beams of the inner section wing (1) and the outer section wing (3) are respectively sleeved It is arranged in the front beam and the rear beam of the middle wing (2); the first linear motor (10) and the second linear motor (11) are arranged side by side in the middle wing (2); the telescopic movement of the wing includes the outer wing ( 3) There are two parts, the telescopic movement relative to the middle wing (2) and the telescopic movement of the middle wing (2) relative to the inner wing (1). The telescopic motion of the linear motor (10) is realized, and the driving mechanism section of the first linear motor (10) is fixed on the mid-section wing (2) in the spanwise direction, and the push rod of the first linear motor (10) passes through the motor The fixing block (32) is fixedly connected with the internal structure of the outer section wing (3); the telescopic movement of the push rod of the first linear motor (10) makes the outer section wing (3) move in the spanwise direction of the wing; the middle section wing (2) The telescopic movement relative to the inner section wing (1) is realized by the telescopic movement of the second linear motor (11), and the driving mechanism segment of the second linear motor (11) is fixed on the middle section wing (2) in the span direction, and the second linear motor The push rod of the motor (11) is fixedly connected with the internal structure of the inner section wing (1) through the motor fixing block (30); the telescopic movement of the push rod of the second linear motor (11) makes the middle section wing (2) move along the span of the wing sports.

Images