CN111169620A - Telescopic wing mechanism with slotted flap and continuously variable wingspan - Google Patents

Abstract

The invention discloses a telescopic wing mechanism with a slotted flap and a continuously variable wingspan. Comprises an inner section main wing; an outer section main wing; the middle section main wing is nested between the inner section main wing and the outer section main wing; inner, middle and outer flaps respectively connected with the inner, middle and outer main wings; the first linear motor and the second linear motor are respectively used for driving the outer section main wing, the middle section main wing and the outer section main wing to move along the spanwise direction; the inner, middle and outer sections of flaps control the steering engine; one end of the front beam and the back beam of the inner section wing is connected with the fuselage, and the other end of the front beam and the back beam of the middle section wing are inserted. The front beam and the back beam of the outer section wing are inserted into the front beam and the back beam of the middle section wing. The middle section flaps are nested between the inner and outer section flaps. The front and rear beams of each section of wing are arranged in parallel along the unfolding direction, the main wings of the three sections of wings stretch and move along the front and rear beam directions, and meanwhile, the three sections of flaps are driven to stretch and move. The telescopic positioning is realized by a locking mechanism in the linear motor. The flap is controlled to be retracted and extended through the three steering engines. The aerodynamic loads of the wing are transferred from the skin to the spar via the ribs.

Description

Telescopic wing mechanism with slotted flap and continuously variable wingspan

Technical Field

The invention belongs to the field of aircraft design and technology, and particularly relates to a telescopic wing structure which is applied to a fixed wing aircraft and is provided with a slotted flap and a continuously variable wingspan.

Background

Most of the traditional aircrafts adopt a single wing aerodynamic layout to meet the aerodynamic requirements under the working conditions of main tasks of the aircrafts. However, some aircraft may be required to meet multi-mission conditions (e.g., high cruise speed and low cruise speed). At this time, the wings with single aerodynamic layout cannot meet the design requirements of the aircraft. There is a need for a wing design that can be varied in aerodynamic profile to meet different speed requirements depending on the mission requirements. For the flight working condition of low Mach number (the speed is less than 300 km/h), the extension length of the wing is changed, and meanwhile, the wing section camber is changed by putting down the slotted flap, so that the airplane can better adapt to the flight working condition, the aerodynamic efficiency is improved, and the oil consumption is reduced.

The wings are fully extended when the aircraft is taking off, thereby providing maximum lift and reducing lift-induced drag; while the flap portion is lowered to further increase the lift coefficient of the wing. Therefore, the takeoff attack angle is reduced at the same takeoff speed, and the parasitic resistance caused by the increase of the attack angle of the airplane body is reduced.

When the aircraft is cruising at a low-speed task, the wings are completely extended out and the flaps are completely retracted, so that the induced resistance and the airfoil resistance of the wings are reduced, and the low-speed aerodynamic performance of the wings is improved.

When the aircraft is cruising at high speed, the wings are fully retracted and the flaps are fully retracted to reduce the wetted area of the wings, thereby reducing frictional resistance.

The wings are fully extended when the aircraft is landing to provide maximum lift, reducing the speed required when the aircraft is landing, while the flaps are fully lowered to provide a maximum lift coefficient, further reducing the speed required when the aircraft is landing.

When the wings on the two sides have different span lengths, the rolling moment caused by the asymmetry of the left and right lifting forces can be convenient for the horizontal direction control of the aircraft.

Disclosure of Invention

In order to achieve the functions, the invention provides a three-level rectangular telescopic wing structure with flaps, which is suitable for low-Mach number (the speed is less than 300 km/h) flight conditions.

The telescopic wing structure comprises an inner section main wing, an outer section main wing, a middle section main wing nested between the inner section main wing and the outer section main wing, an inner section flap hinged with the rear edge of the inner section main wing, and an outer section flap hinged with the rear edge of the outer section main wing; the middle wing flap is nested between the inner wing flap and the outer wing flap and hinged with the rear edge of the middle main wing, the first linear motor is used for driving the outer main wing to move along the spanwise direction, and the second linear motor is used for driving the outer main wing and the middle main wing to move together along the spanwise direction and is respectively composed of a first steering engine, a second steering engine and a third steering engine which are used for controlling the deflection of the inner wing flap, the middle wing flap and the outer wing flap; the inner section main wing, the outer section main wing and the middle section main wing are all composed of a plurality of wing ribs, inter-rib plates fixed among the wing ribs, a front beam and a rear beam fixedly connected with the wing ribs and skins fixed on the outer sides of the wing ribs; wherein the front beam and the rear beam of the inner section main wing extend to the outside of the inner section main wing; the front beam of the middle section main wing comprises an inner front beam and an outer front beam which are arranged side by side, and the rear beam of the middle section main wing comprises an inner rear beam and an outer rear beam which are arranged side by side; the front beam and the rear beam of the inner main wing and the outer main wing are cylindrical wing beams, the front beam and the rear beam of the middle main wing are cylindrical hollow tubes, and the outer diameter of each cylindrical wing beam is matched with the inner diameter of each cylindrical hollow tube; the front beam and the rear beam of the inner section main wing and the outer section main wing are respectively sleeved in the front beam and the rear beam of the middle section main wing. The first linear motor and the second linear motor are arranged in the middle section main wing side by side. Three-section interblade loads are conducted by the internal structure. The front and rear outer wing spars of the middle section main wing are cylindrical hollow pipes, the inner section main wing is cylindrical wing spars, one end of each wing spar is connected with the fuselage, and the other end of each wing spar is sleeved in the front and rear outer cylindrical wing spars of the middle section main wing. The outer diameter of the cylindrical wing beam of the inner section main wing is slightly smaller than the inner diameters of the front and rear outer wing beams of the middle section main wing, so that the inner section main wing and the middle section main wing do not move relatively in the X direction (front and rear) and the Z direction (up and down direction) and can freely slide in the Y direction (left and right direction).

Similarly, the outer main wing section adopts a cylindrical wing beam, one end of the wing beam extends to the outermost wing rib of the outer main wing section, and the other end of the wing beam is sleeved into the front and rear inner wing beams of the middle main wing section. The outer diameter of the cylindrical wing beam of the outer section main wing is slightly smaller than the inner diameter of the front and rear inner wing beams of the middle section main wing, so that the outer section main wing and the middle section main wing do not move relatively in the X direction (front and rear) and the Z direction (up and down direction) and can freely slide in the Y direction (left and right direction).

Furthermore, the inner flap, the middle flap and the outer flap are made of rigid skins and hinged with the trailing edges of the inner main wing, the middle main wing and the outer main wing respectively. Wherein one hinged arm of the hinged mechanism is fixed on the main wing back beam, and the other hinged arm is connected with the front edge skin of the flap. The three sections of flaps are connected with the main wing in a hinged mode. Each pair of main wing and flap has no relative motion in the span-wise direction, and when the main wing does telescopic motion, the flap does telescopic motion along with the main wing. The flap can freely rotate around the hinge axis within a certain range on the vertical spanwise plane.

Further, the articulated arm on the inner flap is located at the position where the flap is close to the wing root; the articulated arm on the middle section wing flap is positioned in the middle of the wing flap; the hinged arm on the outer segment flap is located at the position where the flap is close to the wing tip. The articulated arms on the three main wings are positioned at corresponding positions in the main spanwise direction. The design ensures that the three sections of main wings and flap skins are not interfered by the articulated arms when sliding and can freely slide. In the three-segment flap, the middle-segment flap is longer, can still be respectively inserted into the inner-segment flap and the outer-segment flap when being completely extended, and has enough contact length, thereby ensuring the connection rigidity of the flap (as shown in figure 1).

Furthermore, a first steering engine, a second steering engine and a third steering engine are respectively fixed in the inner section main wing, the middle section main wing and the outer section main wing, and the inner section wing flap, the middle section wing flap and the outer section wing flap are respectively connected with the first steering engine, the second steering engine and the third steering engine through connecting rods. The motion of the steering engine is transmitted to the flap through the connecting rod. The deflection angle of the flap is controlled by controlling the deflection angle of the steering engine. The deflection positioning of the flap is realized by locking the deflection angle of the steering engine.

When no air flows to the deformation, the main wing skins do not bear and transmit the loads among the three main wings, and when the wings bend and deform under aerodynamic force, the main wing skins are contacted with each other to bear part of the loads. But the main load is taken by the spar. The no-air-to-deformation flap wing skins do not bear and transmit loads among three sections of flaps, when the flaps are under aerodynamic force, the flap loads are transmitted to the main wing back beam through the hinge mechanisms, and the adjacent flap skins are in mutual contact and have partial force transmission. The main load is still transferred by the hinge mechanism and the steering engine link.

An important performance index of a telescopic wing is the wing expansion ratio (i.e. the area of the wing fully extended divided by the area of the wing retracted), and a larger expansion ratio means that the wing has a stronger ability to adapt to different flight conditions. The large expansion ratio is realized by the following three schemes:

(1) first linear electric motor and the crisscross placement of second linear electric motor are in middle section main wing inner structure:

since the linear motor requires a drive mechanism to be disposed in the motor shaft, its extension stroke is always smaller than its own length. The driving mechanism sections and the telescopic stroke sections of the two motors are mutually overlapped in the wing chord direction, so that the adverse effect on the wing expansion ratio due to the existence of the driving mechanisms is eliminated, and the expansion ratio of the wing is maximized;

(2) front-axle beam, outer front-axle beam, interior back-axle beam in the middle section main wing, outer back-axle beam adopts staggered arrangement respectively:

when the wing is completely extended, the spars of the inner section, the middle section and the outer section need to be overlapped sufficiently, so that the main wing can bear the aerodynamic load on one hand, and on the other hand, the main wing does not have the phenomenon of locking in the maximum extension state and can still be retracted freely. Therefore, the front and rear wing spars of the middle wing adopt a staggered layout design, the design ensures that the inner and outer wing spars have no mutual interference (as shown in figure 4) when the wing is completely retracted, and the inner and outer wing spars and the middle wing spar still have enough contact length (as shown in figure 2) when the wing is completely unfolded, so that the connection strength is ensured;

(3) reasonable articulated arm position arrangement of main wing and flap:

the design ensures that the hinge mechanism of the flap can not block the relative sliding of the flap skin when the flap moves telescopically along with the main wing, and the end surface of the flap skin still keeps a sufficient distance with the hinge mechanism when the flap retracts completely.

The invention has the beneficial effects that:

(1) the telescopic wing provided by the invention can be stretched in the unfolding direction, the wing spars of the three sections of wings are nested with each other in pairs, the movement of the wings in the X direction (front and back) and the Z direction (up and down direction) is restrained, and the movement of the wings in the Y direction (left and right direction) is not restrained. The spars of the three-section wing do not generate any other force in the Y direction (left-right direction) except for a small frictional force. The three wings do not move relatively in the X and Z directions and can freely slide in the Y direction (left and right directions);

(2) the flaps of the three sections of wings are fixed with the main wing in a hinged mode, so that the three sections of flaps are restrained from moving relative to the main wing in the Y direction (the spanwise direction), and meanwhile, the flaps can freely rotate in a certain range in a plane vertical to the spanwise direction. The movement mode accords with the working condition of the flap;

(3) the telescopic control of the wings is realized through two linear motors respectively, and the linear motors perform telescopic motion along the Y direction so as to control the telescopic motion of the wings. The two linear motors are mutually independent and respectively control the telescopic motion of the middle section wing and the outer section wing. The motion of the outer section wings is decoupled from the middle and inner section wings. When the upper linear motor moves, only the outer section wing moves. When the upper linear motor is static, the middle section wing and the outer section wing are relatively static. When the lower linear motor moves, the middle section wing and the outer section wing move together. The limitation of the motion of the three main wings along the unfolding direction (Y direction) is realized by a locking mechanism in the linear motor, and the wings do not move when the motor is static;

(4) the telescopic motion of the flaps is synchronous with the telescopic motion of the main wings, and the relative motion between the three sections of flaps and the corresponding main wings along the span direction is limited in a hinged mode. When the main wing moves in a telescopic way, the flap moves in a telescopic way along with the main wing. When the main wings are static, the limiting of the motion of the three main wings along the unfolding direction (Y direction) is realized by a locking mechanism in the linear motor. The three sections of flaps realize the limit of motion along the unfolding direction (Y direction) through the hinge mechanisms fixedly connected with the main wing and the flaps respectively;

(5) the folding and unfolding motion of the flap is realized by three steering engines fixed on the main wing. The three steering engines are respectively connected with the three sections of flaps through three connecting rods. The angle of the flap can be controlled by controlling the angle of the steering engine. The three steering engines can move synchronously so as to control the overall retraction of the three flaps, and the rotation of the three steering engines can also be differential so as to control the differential motion of the retraction angles of the three sections of flaps along the unfolding direction;

(6) the skins of the three sections of main wings are mutually independent and are respectively fixedly connected with respective internal mechanisms, the inner section main wing skin and the middle section main wing skin as well as the middle section main wing skin and the outer section main wing skin can freely slide when the wings stretch, and when the wings are in pneumatic deformation, friction force may exist between the skins. There is no other constraint between the skins except for friction;

(7) the skins of the three sections of flaps are mutually independent and are respectively fixedly connected with respective internal mechanisms, the inner section flap skin and the middle section flap skin as well as the middle section flap skin and the outer section flap skin can freely slide when the wing stretches, and friction force possibly exists between the skins when the wing is in pneumatic deformation. There is no other constraint between the skins except for friction;

(8) the invention provides a wing which can change the aerodynamic shape according to the requirement of a flight task and meet different speed requirements. The wings are fully extended during takeoff of the aircraft to provide maximum lift and reduce lift drag. Meanwhile, the wing flap part is put down to further increase the lift coefficient of the wing, so that the takeoff attack angle is reduced at the same takeoff speed, and the parasitic resistance caused by the increase of the attack angle of the airplane body is reduced. When the aircraft is cruising at a low-speed task, the wings are completely extended out and the flaps are completely retracted, so that the induced resistance and the airfoil resistance of the wings are reduced, and the low-speed aerodynamic performance of the wings is improved. When the aircraft is cruising at high speed, the wings are fully retracted and the flaps are fully retracted to reduce the wetted area of the wings, thereby reducing frictional resistance. The wings are fully extended when the aircraft is landing to provide maximum lift, reducing the speed required when the aircraft is landing, while the flaps are fully lowered to provide a maximum lift coefficient, further reducing the speed required when the aircraft is landing.

(9) When the wings on the two sides have different span lengths, the rolling moment caused by the asymmetry of the left and right lifting forces can be convenient for the horizontal direction control of the aircraft.

Drawings

FIG. 1 is a three-view illustration of a design airfoil of the present invention, wherein a is a top view, b is a left side view, and c is a front view;

FIG. 2 is a schematic view of the mechanism of the present invention when the wing is fully extended;

FIG. 3 is a schematic view of the mechanism of the present invention designed to retract the wing section;

FIG. 4 is a schematic view of the mechanism of the present invention designed to fully retract the wings;

FIG. 5 is a three-dimensional view and a side view of the present invention relating to the outer and middle section skins of a wing;

FIG. 6 is a schematic view of the present invention relating to the hinge connection of the main wing and the outer flap of the outer section of the wing and the retraction and extension of the flap, wherein a is a schematic view of the mechanism when the flap is fully retracted, and b is a schematic view of the mechanism when the flap is fully put down;

in the figure, an inner main wing 1A, a middle main wing 2A, an outer main wing 3A, an inner flap 1B, a middle flap 2B, an outer flap 3B, an inner front wing beam 4, an inner rear wing beam 5, a middle outer front wing beam 6A, a middle outer rear wing beam 6B, a middle inner front wing beam 7A, a middle inner rear wing beam 7B, an outer front wing beam 8, an outer rear wing beam 9, a first linear motor 10, a second linear motor 11, a middle wing skin 12, an outer wing skin 14, outer wing ribs 15A, 15B, an inner wing skin 16, inner wing ribs 17A, 17B, an outer wing rib 18B, middle wing ribs 19A, 19B, an inner rib interlayer plate 20, a middle rib interlayer plate 21, an outer wing interlayer plate 22, a first steering engine 23, a second steering engine 24, a third steering engine 25, a first connecting rod 26, a second connecting rod 27, a third steering engine 28, a steering engine 28, Motor fixing blocks 31A, 31B, 31C, 31D, an outer wing motor fixing block 32, an inner wing hinge arm 41, a middle wing hinge arm 42, and an outer wing hinge arm 43.

Detailed Description

The invention aims to provide a set of mechanism for changing the span length of the aircraft through telescopic motion and changing the camber of an airfoil profile through retracting and extending a flap, so that the aircraft provided with the airfoil has good high-speed and low-speed performances. The detailed description is described with reference to the accompanying drawings and fig. 1-6.

The wing is a three-stage telescopic wing mechanism, and each section of wing comprises a main wing and a flap. Specifically comprises an inner section main wing 1A; an outer-section main wing 3A; a middle main wing 2A nested between the inner main wing 1A and the outer main wing 3A; an inner flap 1B hinged to the inner main wing 1A; an outer flap 3B hinged to the outer main wing 3A; a middle flap 2B which is nested between the inner flap 1B and the outer flap 3B and is hinged with the middle main wing 2A; a first linear motor 10 for driving the outer main wing 3A, the outer main wing 3A and the middle main wing 2A to move in the span-wise direction; a second linear motor 11; a first steering engine 23 for controlling the deflection of the inner flap 1B through a connecting rod; a second steering engine 24 for controlling the deflection of the middle section flap 2B through a connecting rod; a third steering engine 25 and the like which control the deflection of the outer segment flap 3B through a connecting rod.

The inner main wing 1A, the middle main wing 2A and the outer main wing 3A are all composed of wing ribs, inter-rib plates fixed among the wing ribs, front beams and rear beams fixedly connected with the wing ribs, main wing skins fixed on the outer sides of the wing ribs in a surrounding mode, and hinged arms connected with the rear beams. Wherein, the front beam and the rear beam of the inner main wing 1A extend to the outside of the inner main wing 1A to be connected with the fuselage. The inner section flap 1B, the middle section flap 2B and the outer section flap 3B are all composed of skins and hinged arms fixedly connected with the skins. The three flaps are hinged to the main wing by means of hinge arms (see fig. 6). The following detailed description of the three-segment wing structure is made with reference to the accompanying drawings:

as shown in fig. 1 and 2, the specific internal structure of the inner main wing 1A includes ribs (17A and 17B), an inner rib interlayer plate 20, an inner front wing beam 4, an inner rear wing beam 5, and an inner hinge arm 41, the inner rib interlayer plate 20 is fixed between the inner ribs, the inner front wing beam 4 and the inner rear wing beam 5 are respectively fixedly connected to the inner ribs, and the inner hinge arm 41 is fixedly connected to the inner rear wing beam 5; the components are fixedly connected with each other by means of gluing and fastening to form the 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 for connecting a fuselage, and the inner wing hinged arm 41 extends out of the rear edge of the inner wing skin and is connected with an inner wing flap 1B; a motor fixing block 30 is also arranged in the inner section main wing 1A and is used for fixing the first linear motor 10; the inner segment flap 1B mainly comprises a skin and a flap hinge arm, and the hinge arm is hinged with an inner segment main wing hinge arm 41; the inner wing flap is simultaneously connected with an inner wing rudder machine connecting rod 26 and is connected with a first steering engine 23 through a steering engine connecting rod 26, the swinging of the steering engine is transmitted to the wing flap through the connecting rod, so that the purpose of controlling the wing flap to be folded and unfolded is achieved, and the angle positioning mechanism of the steering engine realizes the function of positioning the folding and unfolding angle of the wing flap.

Similarly, the concrete internal structure of the outer main wing 3 includes ribs (18A and 18B), an outer rib intermediate floor 22, an outer wing front beam 8, an outer wing rear beam 9, and an outer wing hinge arm 43, the outer rib intermediate floor 22 is fixed between the outer wing ribs, the outer wing front beam 8 and the outer wing rear beam 9 are respectively fixedly connected with the outer wing ribs, and the outer wing hinge arm 43 is fixedly connected with the outer wing rear beam 9; the components are fixedly connected with each other by means of gluing and fastening to form the inner wing box. The outer wing hinged arm 41 extends out of the rear edge of the outer wing skin and is connected with an outer wing flap 3B; a motor fixing block 32 is further arranged in the outer section main wing 3A and used for fixing the second linear motor 11; the outer segment flap 3B mainly comprises a skin and flap articulated arm which is articulated with an outer segment main wing articulated arm 43; the outer wing flap is connected with the outer wing rudder machine connecting rod 28 at the same time, and is connected with the third steering engine 25 through the steering engine connecting rod 28, and the swing of the steering engine is transmitted to the wing flap through the connecting rod, so that the purpose of controlling the wing flap to be folded and unfolded is achieved, and the angle positioning mechanism of the steering engine realizes the function of positioning the folding and unfolding angle of the wing flap.

The specific internal structure of the middle main wing 2A includes wing ribs (19A and 19B), a middle wing rib interlayer plate 21 fixed between the wing ribs, middle wing front beams (6A and 7A) fixedly connected to the wing ribs, middle wing rear beams (6B and 7B), a middle wing hinge arm 42, and a plurality of motor fixing blocks (31A, 31B, 31C, 31D). Wherein, the middle section wing front beam includes the front beam 7A in the middle section wing and the front beam 6A outside the middle section wing that arrange side by side, and the middle section wing back beam includes the back beam 7B in the middle section wing and the back beam 6B outside the middle section wing that arrange side by side. The middle wing rib interlayer plate 21 is fixed between the middle wing ribs, and the components are mutually and fixedly connected through gluing and fastening pieces to form a middle wing box. The midspan wing articulated arm 42 extends out of the rear edge of the midspan wing skin and is connected with a midspan flap 2B; the midspan flap 2B mainly comprises a skin and flap articulated arm, and the articulated arm is articulated with a midspan main wing articulated arm 42; the middle wing flap is connected with a middle wing rudder machine connecting rod 27 simultaneously, and is connected with a second steering engine 24 through a steering engine connecting rod 27, the swing of the steering engine is transmitted to the wing flap through the connecting rod, so that the purpose of controlling the wing flap to be folded and unfolded is achieved, and the angle positioning mechanism of the steering engine realizes the function of wing flap folding and unfolding angle positioning.

In the three-section wing, an inner section main wing front beam 4, an inner section main wing rear beam 5, an outer section main wing front beam 8 and an outer section main wing rear beam 9 all adopt cylindrical wing spars, a middle section main wing front beam (6A and 7A) and a middle section main wing rear beam (6B and 7B) adopt cylindrical hollow tubes, and the outer diameter of each cylindrical wing spar is matched with the inner diameter of each cylindrical hollow tube, so that the inner section main wing front beam 4 and the inner section main wing rear beam 5 can be respectively inserted into the middle section main wing outer front beam 6A and the middle section wing outer rear beam 6B, and the outer section main wing front beam 8 and the outer section main wing rear beam 9 can be respectively inserted into the middle section main wing inner front beam 7A and the middle section main wing inner rear beam 7B. In addition, the length of the inner section main wing front beam 4 and the length of the inner section main wing rear beam 5 are larger than the length of the inner section wing box and the length of the inner section main wing skin, the length of the outer section main wing front beam 8 and the length of the outer section main wing rear beam 9 are larger than the length of the outer section wing box and the length of the outer section main wing skin, so that the sufficient overlapping parts of the connection parts of the inner section main wing 1A and the middle section main wing 2A, the outer section main wing 3A and the middle section main wing 2A are still provided under the condition that the wings are completely unfolded, the connection rigidity of the front beam and the rear beam is ensured, the wing spars are prevented from being mutually clamped when the wings are retracted under the condition that the wings are completely unfolded, and the middle section main wing 2A can freely slide relative to the inner section main wing 1A and the outer section main wing 3A along the unfolding direction.

In addition, the first linear motor 10 and the second linear motor 11 are arranged inside the middle main wing 2A in a staggered manner in the span-wise direction by a plurality of motor fixing blocks (31A, 31B, 31C, 31D). The middle-section main wing 2A can move relative to the inner-section main wing 1A and the outer-section main wing 3A can move relative to the middle-section main wing 2A by controlling the first linear motor 10 and the second linear motor 11 to move, and when the motors are static, the span-wise length of the motor is kept unchanged by a self-locking mechanism in the linear motor. Since the linear motor requires a drive mechanism to be disposed in the motor shaft, its extension stroke is always smaller than its own length. The driving mechanism sections and the telescopic stroke sections of the two motors are mutually overlapped by adopting the parallel arrangement, so that the adverse effect on the telescopic ratio of the wings caused by the existence of the driving mechanisms is eliminated, and the telescopic ratio of the wings is maximized. The two linear motors are fixedly connected with the middle wing box through the motor fixing blocks, and the two motors do not move mutually.

As shown in fig. 2-4, fig. 2 is a schematic view of a mechanism when the wing is fully extended, fig. 3 is a schematic view of a mechanism when the wing is partially retracted, and fig. 4 is a schematic view of a mechanism when the wing is fully retracted. The specific telescopic motion of the wing comprises two parts, namely telescopic motion of the outer section main wing 3A relative to the middle section main wing 2A and telescopic motion of the middle section main wing 2A relative to the inner section main wing 1A. As shown in fig. 6, fig. 6(a) is a schematic view of the mechanism when the flap is fully retracted, and fig. 6(b) is a schematic view of the mechanism when the flap is fully lowered. The motion of the flap comprises the rotation of the flap around a hinged shaft under the driving of the steering engine and the stretching motion along the unfolding direction when the corresponding hinged main wing stretches out and draws back.

The telescopic motion of the outer main wing section 3A relative to the middle main wing section 2A is realized by the telescopic motion of the first linear motor 10. The specific implementation scheme is that a driving mechanism section of a first linear motor 10 is fixed on a main wing 2A of the middle section in the span direction and is constrained by a nested structure of front and rear beams of the wing, and the telescopic motion of a motor push rod can only be carried out in the span direction of the wing. The motor push rod is fixedly connected with the inner structure of the outer section main wing 1A through a motor fixing block 32. The spar and the motor push rod are matched with each other, so that the outer section main wing 3A can freely move in the spanwise direction, and the movement in other directions is restrained. The speed of the outer main wing 3 is equal to the speed of the first linear motor 10. The outer flap 3B is articulated to the outer main wing 3A by an articulated arm. The outer flap 3B has no relative movement with the outer main wing 3A in the span-wise direction, and the flap can freely rotate about the hinge axis in a plane perpendicular to the span-wise direction. On the other hand, the flap is connected with the steering engine through a steering engine connecting rod, and the purpose of controlling the folding and unfolding angle of the flap is achieved by controlling the angle of the steering engine.

Similarly, the telescopic motion of the middle main wing 2A relative to the inner main wing 1A is realized by the telescopic motion 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 main wing of the middle section along the extending direction, and the telescopic motion of the motor can only be carried out along the extending direction. The motor push rod is fixedly connected with the inner structure of the inner section main wing 1A through the fixing block 30. On the other hand, the wing has only freedom of movement in the span-wise direction due to the constraint of the front and rear spars of the wing. Through the matching of the wing beam and the motor push rod, the middle section main wing 2A can freely move along the spanwise direction, and the movement of other directions is inhibited. The stretching speed of the middle section main wing 2A is equal to the stretching speed of the second linear motor 11. The inner segment flap 1B is hinged with the inner segment main wing 1A through a hinged arm. The inner flap 1B and the inner main wing 1A have no relative movement in the span-wise direction, and the flap can rotate freely around the hinge axis on the plane vertical to the span-wise direction. On the other hand, the flap is connected with the steering engine through a steering engine connecting rod, and the purpose of controlling the folding and unfolding angle of the flap is achieved by controlling the angle of the steering engine.

The midspan flap 2B is hinged with the midspan main wing 2A through a hinged arm. The midspan flap 2B has no relative movement with the midspan flap 2A in the spanwise direction, whereas the flap is free to rotate about the hinge axis in a plane perpendicular to the spanwise direction. On the other hand, the flap is connected with the steering engine through a steering engine connecting rod, and the purpose of controlling the folding and unfolding angle of the flap is achieved by controlling the angle of the steering engine.

The three sections of wing flaps all do telescopic motion along with the main wing. The middle section flap 2B is nested in the inner section flap 1B and the outer section flap 3B, and during telescopic motion, the middle section flap is inserted into skins of the inner section flap and the outer section flap. As shown in FIG. 1, when the wing is fully deployed, the three flaps are still nested within each other without falling out. There is no geometric interference between the flaps when the wing is fully retracted. Wherein the cross section of the inner segment flap 1B is the same as that of the outer segment flap 3B, and the cross section of the middle segment flap 2B is slightly smaller. There are enough geometrical gaps between the inner and middle sections and between the outer and middle sections. When the wing is completely extended, the flap skins still have enough contact length, so that the skins are prevented from being mutually clamped. So that the wings can still slide freely between the flap skins in the fully extended state.

The two linear motors move independently, and can move respectively or simultaneously. When only the first linear motor 10 moves, only the outer-section main wing 3A makes the telescopic movement. When only the second linear motor 11 moves, the middle main wing 2A and the outer main wing 3A do not move relatively, and the whole moves in a telescopic manner relative to the inner main wing 1A.

The inner section main wing skin 16 is fixedly connected with the inner section wing box in a gluing mode. The middle section main wing skin 12 is fixedly connected with the middle section wing box in a gluing mode. The outer section main wing skin 14 is fixedly connected with the outer section wing box in a gluing mode. The skin is sufficiently rigid to maintain its shape under aerodynamic loading.

The skins of the three wings are mutually overlapped. Preferably, the airfoil sections of the skins of the three main wings are all NACA2412, and the airfoil section of the flap is NACA0012, but the invention is not limited thereto. Wherein the outer section main wing skin 14 and the inner section wing skin 16 are the same size, and the middle section main wing skin 12 has a slightly smaller airfoil profile.

The mid-section main wing skin 12 may be nested within the inner section main wing skin 16 with sufficient geometric clearance between the two skins as shown in figure 5. When the wing is completely extended out, the two sections of skins still have enough contact length, so that the skins are prevented from being mutually clamped. So that the wing is still free to slide between the skins in the fully extended condition.

Similarly, the midspan wing skin 12 may be nested within the outer section wing skin 14 with sufficient geometric clearance between the two sections. When the wing is completely extended out, the two sections of skins still have enough contact length, so that the skins are prevented from being mutually clamped. So that the wing is still free to slide between the skins in the fully extended condition.

Claims (4)

1. The telescopic wing with the slotted wing flaps and the continuously variable wing span is characterized by comprising an inner-section main wing (1A), an outer-section main wing (3A), a middle-section main wing (2A) nested between the inner-section main wing (1A) and the outer-section main wing (3A), an inner-section wing flap (1B) connected with the rear edge of the inner-section main wing (1A) through a hinge, an outer-section wing flap (3B) connected with the rear edge of the outer-section main wing (3A) through a hinge, a middle-section wing flap (2B) connected with the rear edge of the middle-section main wing (2A) through a hinge and nested between the inner-section wing flap (1B) and the outer-section wing flap (3B), a first linear motor (10) used for driving the outer-section main wing (3A) to move in the span direction, a second linear motor (11) used for driving the middle-section main wing flap (2A) and the outer-section main wing (3A) to move in the span direction simultaneously, and a first, The first steering engine (23), the second steering engine (24) and the third steering engine (25) that middle section flap (2B), outer section flap (3B) deflected are constituteed. The inner section main wing (1A), the outer section main wing (3A) and the middle section main wing (2A) are all composed of a plurality of ribs, inter-rib plates fixed among the ribs, a front beam and a back beam fixedly connected with the ribs and skins fixed on the outer sides of the ribs; wherein the front beam and the rear beam of the inner section main wing (1A) extend to the outside of the inner section main wing (1A); the front beam of the middle section main wing (2A) comprises an inner front beam and an outer front beam which are arranged side by side, and the rear beam of the middle section main wing (2A) comprises an inner rear beam and an outer rear beam which are arranged side by side; the front beam and the back beam of the inner section main wing (1A) and the outer section main wing (3A) are cylindrical wing spars, the front beam and the back beam of the middle section main wing (2A) are cylindrical hollow tubes, and the outer diameter of each cylindrical wing spar is matched with the inner diameter of each cylindrical hollow tube; the front beam and the rear beam of the inner section main wing (1A) and the outer section main wing (3A) are respectively sleeved in the front beam and the rear beam of the middle section main wing (2A). The first linear motor (10) and the second linear motor (11) are arranged in the middle section main wing (2A) in parallel from front to back.

2. The retractable wing with slotted flaps and continuously variable wingspan according to claim 1, characterized in that the inner flap (1B), the middle flap (2B) and the outer flap (3B) are made of rigid skins and hinged to the trailing edges of the inner main wing (1A), the middle main wing (2A) and the outer main wing (3A), respectively.

3. The continuously variable wingspan telescopic wing with slotted flaps according to claim 2 is characterized in that the hinge mechanism of the midspan main wing (2A) and the midspan flaps (2B) is arranged in the middle, the hinge mechanism of the outer main wing (3A) and the outer flaps (3A) is arranged at the wing tip, and the hinge mechanism of the inner main wing (1A) and the inner flaps (1B) is arranged at the wing root.

4. The telescopic wing with the slotted flaps and the continuously variable wingspan according to claim 1 is characterized in that a first steering engine (23), a second steering engine (24) and a third steering engine (25) are respectively fixed in an inner section main wing (1A), a middle section main wing (2A) and an outer section main wing (3A), and an inner section flap (1B), a middle section flap (2B) and an outer section flap (3B) are respectively connected with the first steering engine (23), the second steering engine (24) and the third steering engine (25) through connecting rods.

Images