CN110920865A - Telescopic wing structure with continuously variable wingspan - Google Patents
Telescopic wing structure with continuously variable wingspan Download PDFInfo
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- CN110920865A CN110920865A CN201911279921.5A CN201911279921A CN110920865A CN 110920865 A CN110920865 A CN 110920865A CN 201911279921 A CN201911279921 A CN 201911279921A CN 110920865 A CN110920865 A CN 110920865A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/54—Varying in area
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Abstract
本发明公开了一种翼展连续可变的伸缩机翼机构。由内段翼、外段翼、嵌套在内段翼、外段翼之间的中段翼、分别用于驱动外段翼、内段翼沿展向运动的第一直线电机、第二直线电机组成；内段翼前梁和后梁一端与机身连接，另一端插入中段翼的前梁与后梁。外段翼前梁与后梁插入中段翼的前梁与后梁。各段机翼的前后梁均平行放置，三段机翼均沿前后梁方向进行伸缩运动。通过固定在中段翼上的直线电机，实现外段翼相对中段翼的伸缩运动；实现外段翼和中段翼整体相对于内段翼的伸缩运动。伸缩定位由直线电机内锁止机构实现。三段翼均采用NACA2412翼型，机翼的气动载荷由蒙皮经翼肋传递至梁。伸缩变形时内段翼和外段翼蒙皮环套在中段蒙皮上。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 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
Technical Field
The invention belongs to the field of aircraft design and technology, and particularly relates to a telescopic wing structure with a continuously variable wingspan, which is applied to a fixed-wing aircraft.
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. The wings are fully extended when the aircraft is cruising at take-off, landing, and low speed tasks to provide maximum lift and reduce lift drag, and fully retracted when the aircraft is cruising at high speed to reduce wetted area to reduce frictional drag.
Disclosure of Invention
In order to achieve the functions, the invention provides a three-level rectangular telescopic wing suitable for low-Mach number (the speed is 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, a first linear motor and a second linear motor which are respectively used for driving the outer section wing and the inner section wing to move along the spanwise direction; the inner section wing, the outer section wing and the middle section wing are all composed of a plurality of wing ribs, an inter-rib plate fixed among the wing ribs, a front beam and a rear beam fixedly connected with the wing ribs and a skin fixed outside the wing ribs; wherein the front beam and the rear beam of the inner section wing extend to the outside of the inner section wing; the front beam of the middle wing comprises an inner front beam and an outer front beam which are arranged side by side, and the rear beam of the middle 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 section wing and the outer section wing are cylindrical wing spars, the front beam and the rear beam of the middle section wing are cylindrical hollow pipes, and the outer diameter of each cylindrical wing spar is matched with the inner diameter of each cylindrical hollow pipe; 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 in the middle wing side by side. Three-section interblade loads are conducted by the internal structure. The front and rear outer wing spars of the middle wing are cylindrical hollow tubes, the inner wing is cylindrical, 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 wing. The outer diameter of the cylindrical wing beam of the inner section wing is slightly smaller than the inner diameter of the front and rear outer wing beams of the middle section wing, so that the inner section wing and the middle section wing do not move relatively in the X direction (front and rear) and the Z direction (up and down direction) and can slide freely in the Y direction (left and right direction).
Similarly, the front and rear inner wing spars of the middle wing are cylindrical hollow tubes, the outer wing is cylindrical, one end of each wing spar extends to the outermost wing rib of the outer wing, and the other end of each wing spar is sleeved into the front and rear inner wing spars of the middle wing. The outer diameter of the cylindrical wing beam of the outer section wing is slightly smaller than the inner diameter of the front and rear inner wing beams of the middle section wing, so that the outer section wing and the middle section wing do not move relatively in the X direction (front and rear) and the Z direction (up and down direction) and can slide freely in the Y direction (left and right direction).
When no air flows to the deformation, the skins do not bear and transmit the loads among three sections of wings, and when the wings bend and deform under aerodynamic force, the skins are in contact with each other to bear part of the loads. But the main load is taken by the spar.
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 two schemes:
(1) first linear electric motor and the crisscross placement of second linear electric motor are in middle section 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 by adopting the vertical staggered arrangement, so that the adverse effect on the wing telescopic ratio due to the existence of the driving mechanism is eliminated, and the wing telescopic ratio is maximized;
(2) front-back beam, outer front-back beam, interior back-back beam in the middle section wing, outer back-back 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 wing can bear aerodynamic load on the one hand, and on the other hand, the wing can be free from being locked 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;
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 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 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 limiting of the motion of the three 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;
(3) the skins of the three wings are mutually independent and are respectively fixedly connected with respective internal mechanisms, the inner wing skin and the middle wing skin as well as the middle wing skin and the outer wing skin can freely slide when the wings stretch, and friction force may exist between the skins when the wings are in pneumatic deformation. There is no other constraint between the skins other than friction.
(4) The invention provides a wing which can change the aerodynamic shape according to the requirement of a flight mission and give consideration to different speed requirements, and the wing is completely extended out when the aircraft takes off, lands and patrols at a low-speed mission so as to provide the maximum lift force and reduce the lift resistance, and the wing is completely retracted so as to reduce the infiltration area when the aircraft patrols at a high speed so as to reduce the friction resistance.
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 inner and middle section skins of a wing;
in the figure, an inner wing 1, a middle wing 2, an outer wing 3, an inner wing front beam 4, an inner wing back beam 5, a middle wing outer front beam 6A, a middle wing outer back beam 6B, a middle wing inner front beam 7A, a middle wing inner back beam 7B, an outer wing front beam 8, an outer wing back 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 outermost rib 18B, middle wing ribs 19A, 19B, an inner wing inter-rib laminate 20, a middle wing inter-laminate 21, an outer wing inter-rib laminate 22, motor fixing blocks 31A, 31B, 31C, 31D, and an outer wing motor fixing block 32.
Detailed Description
The invention aims to provide a set of mechanism capable of changing the span length of an aircraft wing, so that an aircraft provided with the wing has good high-speed and low-speed performances. The detailed description is described with reference to the accompanying drawings and fig. 1-5.
The wing is a three-level telescopic wing mechanism and comprises an inner section wing 1, a middle section wing 2, an outer section wing 3, a second linear motor 11 and a first linear motor 10, wherein the second linear motor 11 and the first linear motor are respectively used for driving the inner section wing 1 and the outer section wing 3 to move along the spanwise direction. The three sections of wings are all composed of a plurality of wing ribs, an inter-rib plate fixed among the wing ribs, a front beam and a back beam fixedly connected with the wing ribs and a skin fixed on the outer sides of the wing ribs, wherein the inner section wing 1, the outer section wing 3 and the middle section wing 2 are all composed of a plurality of wing ribs, an inter-rib plate fixed among the wing ribs, a front beam and a back beam fixedly connected with the. Wherein the front beam and the rear beam of the inner section wing 1 extend to the outside of the inner section wing 1; the three-segment wing is described in detail below with reference to fig. 1:
as shown in fig. 1 and 2, the specific internal structure of the inner wing 1 includes ribs (17A and 17B), an inner rib interlayer plate 20, an inner front wing beam 4, and an inner rear wing beam 5, the inner rib interlayer plate 20 is fixed between the inner wing ribs, and the inner front wing beam 4 and the inner rear wing beam 5 are fixedly connected to the inner wing ribs, respectively; the components are fixedly connected with each other by means of gluing and fastening to form the inner wing box. The inner section wing front beam 4 and the inner section wing rear beam 5 extend to the outside of the inner section wing 1 and are used for connecting a fuselage; the inner wing 1 is further provided with a motor fixing block 30 for fixedly connecting with the first linear motor 10.
Similarly, the specific internal structure of the outer panel wing 3 includes the rib 18A and 18B, the outer panel rib intermediate floor 22, the outer panel front spar 8, the outer panel rear spar 9, and the motor fixing block 32. The outer section wing rib interlayer plate 22 is positioned between the outer section wing ribs, the outer section wing front beam 8 and the outer section wing rear beam 9 are fixedly connected with the outer section wing ribs respectively, and the components are fixedly connected with each other through gluing and fastening piece connection to form an outer section wing box. And a motor fixing block 32 is further arranged in the outer section wing 3 and is fixedly connected with the second linear motor 11.
The specific internal structure of the mid-section wing 2 includes wing ribs (19A and 19B), a mid-section wing rib interlayer plate 21 fixed between the mid-section wing ribs, mid-section wing front beams (6A and 7A) fixedly connected to the mid-section wing ribs, mid-section wing rear beams (6B and 7B), and a plurality of motor fixing blocks (31A, 31B, 31C, 31D). The components are fixedly connected with each other by means of gluing and fastening to form a midsection wing box. 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.
Wherein, interior section wing front-axle beam 4, interior section wing back-axle beam 5, exterior section wing front-axle beam 8 and exterior section wing back-axle beam 9 all adopt cylindrical wing spar, middle section wing front-axle beam (6A and 7A), middle section wing back-axle beam (6B and 7B) adopt cylindrical hollow tube, the external diameter of cylindrical wing spar and the internal diameter cooperation of cylindrical hollow tube, make interior section wing front-axle beam 4 and interior section wing back-axle beam 5 can insert middle section wing outer front-axle beam 6A and middle section wing outer back-axle beam 6B respectively, exterior section wing front-axle beam 8, exterior section wing back-axle beam 9 can insert middle section wing inner front-axle beam 7A and middle section wing inner back-axle beam 7B respectively. In addition, the lengths of the inner-section wing front beam 4 and the inner-section wing rear beam 5 are greater than the lengths of the inner-section wing box and the inner-section wing skin, and the lengths of the outer-section wing front beam 8 and the outer-section wing rear beam 9 are greater than the lengths of the outer-section wing box and the outer-section wing skin, so that the sufficient overlapping parts of the connection parts of the inner-section wing 1 and the middle-section wing 2, and the connection parts of the outer-section wing 3 and the middle-section wing 2 are still ensured under the condition that the wings are completely unfolded, the connection rigidity of the front beam and the rear beam is ensured, and the wing spars are prevented from being mutually clamped when the wings are retracted under the condition that the wings are completely unfolded, so that the middle-section wing 2 can freely slide relative to the inner-section.
In addition, the first linear motor 10 and the second linear motor 11 are arranged inside the middle blade 2 in a staggered manner in the span-wise direction by a plurality of motor fixing blocks (31A, 31B, 31C, 31D). The middle wing 2 can move relative to the inner wing 1 and the outer wing 3 relative to the middle wing 2 by controlling the first linear motor 10 and the second linear motor 11 to move, and when the motors are static, a self-locking mechanism in the linear motors ensures that the span-wise length of the linear motors is kept unchanged. 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 wing 3 relative to the middle section wing 2 and telescopic motion of the middle section wing 2 relative to the inner section wing 1.
The extension and contraction movement of the outer wing section 3 relative to the middle wing section 2 is realized by the extension and contraction movement of the first linear motor 10. The specific implementation scheme is that a driving mechanism section of the first linear motor 10 is fixed on the middle wing 2 along the span direction, and the telescopic motion of a motor push rod can be only carried out along the span direction of the machine. 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, 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. The wing beam and the electric push rod are mutually matched, so that the outer section wing 3 can freely move along the spanwise direction, and the movement of other directions is inhibited. The speed of the outer wing 3 is equal to the speed of the first linear motor 10.
Similarly, the telescopic motion of the middle wing section 2 relative to the inner wing section 1 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 middle wing along the extending direction, and the telescopic motion of the motor can only be carried out along the extending 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, 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 electric push rod, the middle section wing 2 can freely move along the spanwise direction, and the movement in other directions is restrained. The stretching speed of the middle wing 2 is equal to the stretching speed of the second linear motor 11.
The two linear motors move independently, and can move respectively or simultaneously. When only the first linear motor 10 is moved, only the outer blade 3 is moved in a telescopic manner. When only the second linear motor 11 moves, the middle wing 2 and the outer wing 3 do not move relatively, and the whole moves in a telescopic way relative to the inner wing 1.
The inner section wing skin 16 is fixedly connected with the inner section wing box in a gluing mode. The middle wing skin 12 is fixedly connected with the middle wing box in a gluing mode. The outer section 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-section wing are all NACA2412, but are not limited thereto. Wherein the outer section wing skin 14 and the inner section wing skin 16 are the same size, and the middle section wing skin 12 has a slightly smaller airfoil profile.
The midsection wing skin 12 may be nested within the inner section wing skin 16 with sufficient geometric clearance between the two skins as shown in FIG. 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 (1)
1. A telescopic wing with a continuously variable wing span is characterized by comprising an inner section wing (1), an outer section wing (3), a middle section wing (2) nested between the inner section wing (1) and the outer section wing (3), a first linear motor (10) and a second linear motor (11), wherein the first linear motor (10) and the second linear motor are respectively used for driving the outer section wing (3) and the inner section wing (1) to move along the spanwise direction; the inner section wing (1), the outer section wing (3) and the middle section wing (2) are all composed of a plurality of ribs, inter-rib plates fixed among the ribs, front beams and rear beams 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 wing (1) extend to the outside of the inner section wing (1). The front beam of the middle wing (2) comprises an inner front beam and an outer front beam which are arranged side by side, and the rear beam of the middle wing (2) 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 wing (1) and the outer section wing (3) are cylindrical wing spars, the front beam and the back beam of the middle section wing (2) are cylindrical hollow tubes, and the outer diameters of the cylindrical wing spars are matched with the inner diameters of the cylindrical hollow tubes. The front beam and the rear beam of the inner section wing (1) and the outer section wing (3) are respectively sleeved in the front beam and the rear beam of the middle section wing (2). The first linear motor (10) and the second linear motor (11) are arranged in the middle wing (2) in parallel from front to back.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911279921.5A CN110920865B (en) | 2019-12-13 | 2019-12-13 | A retractable wing structure with continuously variable wingspan |
| PCT/CN2020/093063 WO2021114578A1 (en) | 2019-12-13 | 2020-05-29 | Telescopic wing structure with continuously variable wingspan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911279921.5A CN110920865B (en) | 2019-12-13 | 2019-12-13 | A retractable wing structure with continuously variable wingspan |
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| Publication Number | Publication Date |
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| CN110920865A true CN110920865A (en) | 2020-03-27 |
| CN110920865B CN110920865B (en) | 2020-07-31 |
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| CN201911279921.5A Active CN110920865B (en) | 2019-12-13 | 2019-12-13 | A retractable wing structure with continuously variable wingspan |
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| WO (1) | WO2021114578A1 (en) |
Cited By (5)
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| CN111688913A (en) * | 2020-05-26 | 2020-09-22 | 哈尔滨工业大学 | Dual-drive wing with variable span length and up-down dihedral angle |
| WO2021114578A1 (en) * | 2019-12-13 | 2021-06-17 | 浙江大学 | Telescopic wing structure with continuously variable wingspan |
| CN114537645A (en) * | 2021-12-31 | 2022-05-27 | 中国航天空气动力技术研究院 | Stable unmanned aerial vehicle telescopic wing structure |
| CN114735197A (en) * | 2022-04-19 | 2022-07-12 | 清华大学 | Fixed locking mechanism for foldable wings |
| CN115416839A (en) * | 2022-09-06 | 2022-12-02 | 中国空间技术研究院 | A Bidirectional Expanding Mechanism for Folding Wings with Skin Support Structure |
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| CN113636065B (en) * | 2021-08-12 | 2024-10-01 | 郑州航空工业管理学院 | Deformed wing device and unmanned aerial vehicle |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021114578A1 (en) * | 2019-12-13 | 2021-06-17 | 浙江大学 | Telescopic wing structure with continuously variable wingspan |
| CN111688913A (en) * | 2020-05-26 | 2020-09-22 | 哈尔滨工业大学 | Dual-drive wing with variable span length and up-down dihedral angle |
| CN111688913B (en) * | 2020-05-26 | 2023-02-17 | 哈尔滨工业大学 | A wing with double drive, variable length and dihedral angle |
| CN114537645A (en) * | 2021-12-31 | 2022-05-27 | 中国航天空气动力技术研究院 | Stable unmanned aerial vehicle telescopic wing structure |
| CN114735197A (en) * | 2022-04-19 | 2022-07-12 | 清华大学 | Fixed locking mechanism for foldable wings |
| CN115416839A (en) * | 2022-09-06 | 2022-12-02 | 中国空间技术研究院 | A Bidirectional Expanding Mechanism for Folding Wings with Skin Support Structure |
| CN115416839B (en) * | 2022-09-06 | 2025-01-28 | 中国空间技术研究院 | A two-way unfolding mechanism for a folding wing with a skin support structure |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2021114578A1 (en) | 2021-06-17 |
| CN110920865B (en) | 2020-07-31 |
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