WO2021114578A1 - Telescopic wing structure with continuously variable wingspan - Google Patents

Abstract

A telescopic wing mechanism with continuously variable wingspan is composed of an inner wing section (1), an outer wing section (3), a middle wing section (2) nested between the inner wing section and the outer wing section, as well as a first linear motor (10) and a second linear motor (11) respectively configured to drive the outer wing section and the inner wing section to move in the span direction. One ends of a front beam (4) and a rear beam (5) of the inner wing section are connected to a fuselage, and the other ends are inserted into a front beam and a rear beam of the middle wing section. A front beam (8) and a rear beam (9) of the outer wing section are inserted into the front beam and the rear beam of the middle wing section. The front and rear beams of each section of the wing are arranged in parallel, and the three wing sections all move in the direction of the front and rear beams. By means of the linear motors fixed on the middle wing section, the telescopic movement of the outer wing section relative to the middle wing section is achieved, and the telescopic movement of the outer wing section and the middle wing section as a whole relative to the inner wing section is achieved. The telescopic positioning is achieved by internal locking mechanisms of the linear motors. The three wing sections all use NACA2412 airfoil, and the aerodynamic load of the wing is transferred from the skin to the beams by means of wing ribs. The skin of the inner wing section and the outer wing section are sleeved on the skin of the middle wing section during expansion and contraction.

Description

Telescopic wing structure with continuously variable wingspan Technical field

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

Background technique

Traditional aircraft mostly use a single wing aerodynamic layout to meet the aerodynamic requirements of their main mission conditions. However, some aircraft need to meet multi-task conditions (such as taking into account both high-speed fixed-speed cruise and low-speed mission cruise). At this time, the wing with a single aerodynamic layout can no longer meet the design requirements of this type of aircraft. 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 in take-off, landing, and low-speed mission cruising, 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 infiltration area, thereby reducing frictional resistance.

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. The motor and the second linear motor are composed; the inner wing, the outer wing and the middle wing are all composed of multiple wing ribs, intercostal slabs fixed between the wing ribs, front beams and rear beams fixedly connected to the wing ribs, The front beam and rear beam of the inner section wing extend to the outside of the inner section wing; the front beam of the middle section wing includes the inner and outer front beams arranged side by side, and the rear beam of the middle section wing includes The inner and outer rear beams are arranged side by side; the front and rear beams of the inner and outer wings are cylindrical spars, and the front and rear beams of the middle wing are cylindrical hollow tubes, 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 middle section wing. The load between the three wings is transmitted by the internal structure. The front and rear outer spars of the middle section wing use cylindrical hollow tubes, and the inner section wing adopts a cylindrical spar. One end of the spar is connected to the fuselage, and the other end is sleeved into the front and rear outer cylindrical spars of the middle section wing. The outer diameter of the cylindrical spar of the inner wing is slightly smaller than the inner diameter of the front and rear outer spars 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), but in the Y direction ( (Left and right direction) slide freely.

Similarly, the front and rear inner spars of the middle section wing use cylindrical hollow tubes, and the outer section wing adopts cylindrical spars. One end of the spar extends to the outermost rib of the outer section wing, and the other end is sleeved into the front and rear inner spars of the middle 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 wing 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), but in the Y direction ( (Left and right direction) slide freely.

When airless to deform, the skin will not bear and transmit the load between the three wings. When the wings are bent and deformed by aerodynamic force, the skin will contact each other and bear part of the load. But the main load is borne by the spar.

An important performance index of a telescopic wing is the wing extension ratio (that is, the fully expanded area of the wing divided by the area that has been retracted). The larger the extension ratio, the stronger the wing's ability to adapt to different flight conditions. The large expansion ratio in the present invention is achieved through the following two schemes:

(1) The first linear motor and the second linear motor are alternately placed in the internal structure of the middle wing:

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

(2) The inner front beam, outer front beam, inner rear beam, and outer rear beam of the middle section of the wing are arranged in a staggered manner:

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, and on the other hand, the wing can be contracted without jamming in the maximum extension state. freely. Therefore, the front and rear spars of the mid-section wing adopt a staggered layout design, which ensures that when the wing is fully retracted, the inner and outer spars do not interfere with each other (see Figure 4). When the wing is fully extended, the inner and outer spars and the middle spar 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 in the span direction, and the spars of the three wings are nested in pairs to restrict the movement of the wings in the X direction (front and rear) and Z direction (up and down directions), and not restrict the three wings Movement in the Y direction (left and right direction). The three-segment wing has no relative movement in the X and Z directions but can slide freely in the Y direction (left and right direction);

(2) The expansion and contraction control of the wing is realized by two linear motors respectively, and the linear motors expand and contract along the Y direction to control the expansion and contraction of the wing. The two linear motors are independent of each other, and respectively control the telescopic movement of the middle section wing and the outer section wing. 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 linear motor moves, the middle wing and the outer wing move together. The movement limit of the three-segment wing in the span direction (Y direction) is realized by the locking mechanism inside the linear motor, and the wing does not move when the motor is stationary;

(3) The skins of the three-segment wing are independent of each other and are fixedly connected to their respective internal mechanisms. The inner and middle wing skins and the middle and outer wing skins can slide freely when the wing is telescopic. When the wings are aerodynamically deformed, there may be friction between the skins. Except for 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 takes into account different speed requirements. When the aircraft is taking off, landing, and cruising at low speed missions, the wing of the present invention is fully extended, thereby providing Maximum lift and reduce lift drag. When the aircraft is cruising at high speed, the wing of the present invention is completely retracted to reduce the infiltration area, thereby reducing frictional resistance.

Description of the drawings

Figure 1 is three views of the wing designed according to the present invention, where a is a top view, b is a left view, and c is a front view;

Figure 2 is a schematic diagram of the mechanism when the designed wing of the present invention is fully extended;

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

Figure 4 is a schematic diagram of the mechanism when the designed wing of the present invention is fully retracted;

Figure 5 is a three-dimensional view and a side view of the inner and mid-segment skins of the wing involved in the present invention;

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

Detailed ways

The purpose of the present invention is to provide a set of mechanism that can change the wing span, so that the aircraft equipped with the wing can have good high-speed and low-speed performance. The detailed description is described with reference to the abstract drawings and FIGS. 1 to 5.

The wing is a three-stage telescopic wing mechanism, which includes 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. , The first linear motor 10. The three sections of the wing are the inner section wing 1, the outer section wing 3 and the middle section wing 2 are all composed of multiple wing ribs, intercostal slabs fixed between the wing ribs, front and rear beams fixedly connected to the wing ribs, and fixed The skin on the outside of the wing rib is composed. The front beams and rear beams of the inner wing 1 extend to the outside of the inner wing 1. The three-segment wing will be described in detail below with reference to Fig. 1:

As shown in Figures 1 and 2, the specific internal structure of the inner wing 1 includes ribs (17A and 17B), the inner wing intercostal layer 20, the inner wing front beam 4 and the inner wing rear beam 5, the inner wing The intercostal layer 20 is fixed between the inner wing ribs. The inner wing front beam 4 and the inner wing rear beam 5 are respectively fixedly connected to the inner wing ribs; these components are mutually fixed by means of glue connection and fastener connection. Connected to form an inner wing box. The inner wing front beam 4 and the inner wing rear beam 5 extend to the outside of the inner wing 1 and are used to connect the fuselage; the inner wing 1 is also provided with a motor fixing block 30 for fixing with the first linear motor 10 connection.

Similarly, the specific internal structure of the outer wing 3 includes the ribs 18A and 18B, the outer wing intercostal layer 22, the outer wing front beam 8, the outer wing rear beam 9, and the motor fixing block 32. The outer wing intercostal plate 22 is located between the outer wing ribs. The outer wing front beam 8 and the outer wing rear beam 9 are respectively fixedly connected to the outer wing ribs. These components are connected by glue and fasteners. They are mutually fixed to form an 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 middle section wing 2 includes the ribs (19A and 19B), the middle section wing intercostal plate 21 fixed between the middle section wing ribs, the middle section wing front beam (6A and 7A) fixedly connected to the middle section wing rib, and the middle section Wing rear beams (6B and 7B) and multiple motor fixing blocks (31A, 31B, 31C, 31D) and other components. By means of glue connection and fastener connection, these parts are fixedly connected to each other to form a mid-section wing box. The middle wing front beam includes a middle wing inner front beam 7A and a middle wing outer front beam 6A arranged side by side, and the middle wing rear beam includes a middle wing inner rear beam 7B and a middle wing outer rear beam 6B arranged side by side.

Among them, the inner wing front beam 4, the inner wing rear beam 5, the outer wing front beam 8 and the outer wing rear beam 9 are all cylindrical spars, the middle wing front beam (6A and 7A), the middle wing rear beam (6B and 7B) Cylindrical hollow tube is used. The outer diameter of the cylindrical spar matches the inner diameter of the cylindrical hollow tube, so that the inner wing front beam 4 and the inner wing rear beam 5 can be inserted into the middle wing outer front beam 6A and the middle section, respectively The outer wing rear beam 6B, the outer wing front beam 8 and the outer wing rear beam 9 can be inserted into the middle wing inner front beam 7A and the middle wing inner rear beam 7B, respectively. In addition, the lengths of the inner wing front beam 4 and the inner wing rear beam 5 in the present invention are greater than the lengths of the inner wing box and the inner wing skin, and the outer wing front beam 8 and the outer wing rear beam 9 are longer than the outer wing box. As well as the length of the outer wing skin, ensure that there is enough overlap between the inner wing 1 and the middle wing 2, the outer wing 3 and the middle wing 2 when the wing is fully deployed, so as to ensure the front and rear The rigidity of the beam connection also prevents the spars from jamming when the wing is fully deployed and retracts, so that the middle section wing 2 can slide freely in the spanwise direction relative to the inner section wing 1 and the outer section wing 3 relative to the inner section wing 1.

In addition, the first linear motor 10 and the second linear motor 11 are alternately arranged in the middle wing 2 in the spanwise direction through a plurality of motor fixing blocks (31A, 31B, 31C, 31D). By controlling the movement of the first linear motor 10 and the second linear motor 11, the movement of the middle section wing 2 relative to the inner section wing 1, and the outer section wing 3 relative to the middle section wing 2 can be realized. When the motor is stationary, the self-locking mechanism in the linear motor Ensure that the spanwise length of the wing remains unchanged. Since the linear motor needs to install the drive mechanism in the motor rod, its telescopic stroke is always less than its own length. By adopting the side-by-side arrangement, the driving mechanism section and the telescopic stroke section of the two motors overlap each other, thereby eliminating the adverse effect on the wing expansion ratio due to the existence of the driving mechanism, and maximizing the expansion 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 Figures 2-4, Figure 2 is a schematic diagram of the mechanism when the wing is fully extended, Figure 3 is a schematic diagram of the mechanism when the wing is partially retracted, and Figure 4 is a schematic diagram of the mechanism when the wing is fully retracted. The specific telescopic movement of the wing includes the telescopic movement of the outer wing 3 relative to the middle wing 2 and the telescopic movement of the middle wing 2 relative to the inner wing 1.

The telescopic movement of the outer wing 3 relative to the middle wing 2 is realized by the telescopic movement of the first linear motor 10. The specific implementation is that the driving mechanism section of the first linear motor 10 is fixed on the middle wing 2 along the span direction, and the telescopic movement of the motor push rod can only be performed along the span direction of the wing. The push rod of the motor is fixedly connected to the internal structure of the outer wing 1 through the motor fixing block 32. On the other hand, due to the constraints of the front and rear beams of the wing, the wing only has the freedom to move in the span direction. Through the mutual cooperation of the wing spar and the electric push rod, the outer segment wing 3 can move freely in the span direction, while the movement in other directions is restrained. The telescopic speed of the outer 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 implementation is that the driving mechanism section of the second linear motor 11 is fixed on the mid-section wing along the span direction, and the telescopic movement of the motor can only be performed along the span direction. The push rod of the motor is fixedly connected to the internal structure of the inner wing 1 through the fixed block 30. On the other hand, due to the constraints of the front and rear beams of the wing, the wing only has the freedom to move in the span direction. Through the mutual cooperation of the spar and the electric push rod, the middle section wing 2 can move freely in the span direction, while the movement in other directions is restrained. The telescopic speed of the middle 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 they can move separately or at the same time. When only the first linear motor 10 moves, only the outer segment wing 3 will make a telescopic movement. 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 section makes a telescopic movement relative to the inner section wing 1.

The inner wing skin 16 is fixedly connected to the inner wing box by means of adhesive bonding. The middle section wing skin 12 is fixedly connected to the middle section wing box by means of adhesive bonding. The outer section wing skin 14 is fixedly connected to the outer section wing box by means of adhesive bonding. The skin is rigid enough to maintain its shape under aerodynamic loads.

The skins of the three wings overlap each other. Preferably, the airfoil profile of the skin of the three-segment wing is NACA2412, but it is not limited to this. The outer wing skin 14 and the inner wing skin 16 have the same size, while the middle wing skin 12 has a slightly smaller airfoil profile.

The middle wing skin 12 can be sleeved into the inner wing skin 16, and there is a sufficient geometric gap between the two skins, as shown in FIG. 5. When the wing is fully extended, the two skins still have enough contact length to avoid mutual jamming between the skins. The wing can still slide freely between the skins in the fully extended state.

Similarly, the middle section wing skin 12 can be sleeved into the outer section wing skin 14 with sufficient geometric gap between the two sections. When the wing is fully extended, the two skins still have enough contact length to avoid mutual jamming between the skins. The wing can still slide freely between the skins in the fully extended state.

Claims (1)

A telescopic wing with continuously variable wingspan, characterized in that it consists of an inner wing (1), an outer wing (3), nested between the inner wing (1), and the outer wing (3). The middle section wing (2) is composed of a first linear motor (10) and a 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 inner section The wing (1), the outer section wing (3) and the middle section wing (2) are all composed of multiple wing ribs, intercostal plates fixed between the wing ribs, front and rear beams fixed to the wing ribs, and fixed to the wing ribs. The outer skin of the rib is composed of the front beam and the rear beam of the inner section wing (1) extending to the outside of the inner section wing (1); the front beam of the middle section wing (2) includes the inner front beam and the outer front beam arranged side by side , The rear beam of the middle section wing (2) includes the inner rear beam and the outer rear beam arranged side by side; the front and rear beams of the inner section wing (1) and the outer section wing (3) are all cylindrical spars, and the middle section wing (2) The front beam and the rear beam are cylindrical hollow tubes, and the outer diameter of the cylindrical spar matches the inner diameter of the cylindrical hollow tube; the front beam and the rear beam of the inner wing (1) and the outer wing (3) are respectively sleeved In the front and rear beams of the middle wing (2). The first linear motor (10) and the second linear motor (11) are arranged side by side in the middle section wing (2).

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