CN118479028B - A variable thickness wing - Google Patents
A variable thickness wingInfo
- Publication number
- CN118479028B CN118479028B CN202410649382.4A CN202410649382A CN118479028B CN 118479028 B CN118479028 B CN 118479028B CN 202410649382 A CN202410649382 A CN 202410649382A CN 118479028 B CN118479028 B CN 118479028B
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- CN
- China
- Prior art keywords
- flap
- thickness
- wing
- section
- power input
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Classifications
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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
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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
- B64C3/44—Varying camber
- B64C3/48—Varying camber by relatively-movable parts of wing structures
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
- B64C3/50—Varying camber by leading or trailing edge flaps
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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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Abstract
本发明公开了一种变厚度机翼，涉及变形机翼技术领域，包括机翼外框、动力输入模块、厚度变形模块和襟翼变形模块，动力输入模块安装于机翼外框内，且动力输入模块的输出端分别连接厚度变形模块和襟翼变形模块，厚度变形模块靠近机翼外框的前缘设置，且厚度变形模块安装于机翼外框的两侧，且厚度变形模块能够在动力输入模块的带动下对机翼外框的厚度调节，襟翼变形模块的一端延伸至连接机翼外框的后缘襟翼，且襟翼变形模块能够在动力输入模块的带动下对后缘襟翼的角度调节。本发明整体结构简单、易于操作，且控制精度高。
The present invention discloses a variable thickness wing, which relates to the technical field of deformable wings. The wing comprises a wing frame, a power input module, a thickness deformation module, and a flap deformation module. The power input module is installed within the wing frame, and the output end of the power input module is connected to the thickness deformation module and the flap deformation module, respectively. The thickness deformation module is arranged near the leading edge of the wing frame, and the thickness deformation module is installed on both sides of the wing frame. The thickness deformation module can adjust the thickness of the wing frame under the drive of the power input module. One end of the flap deformation module extends to the trailing edge flap connected to the wing frame, and the flap deformation module can adjust the angle of the trailing edge flap under the drive of the power input module. The present invention has a simple overall structure, is easy to operate, and has high control accuracy.
Description
Technical Field
The invention relates to the technical field of deformed wings, in particular to a variable-thickness wing.
Background
Wings are the primary components of an aircraft that generate lift, and the size and shape of the wings have a significant impact on the aerodynamic condition and handling of the aircraft. In most cases, the combination of ailerons, elevators and rudders is the entire control surface required for a low power aircraft. However, with the development of aeronautics, new types of wings with flaps and slats added are developed, and the aerodynamic characteristics of the aircraft are affected by the auxiliary control surfaces on these wings by changing the shape of the wings. The variable-thickness wing changes the section shape of the wing profile of the wing by a driving mechanism built in the cabin on the basis of using the trailing edge flap so as to achieve the aim of changing the aerodynamic characteristics of the aircraft. The design enables the wing to change in thickness and shape without the aid of a leading edge slat, and the wing surface remains smooth during deformation, so that aerodynamic interference caused by deformation is reduced. However, the existing design structure is too complex, the control precision is low, and the popularization and the use are difficult.
Disclosure of Invention
The invention aims to provide a variable-thickness wing, which solves the problems of the prior art, and has the advantages of simple integral structure, easy operation and high control precision.
In order to achieve the above object, the present invention provides the following solutions:
The invention provides a variable-thickness wing, which comprises a wing outer frame, a power input module, a thickness deformation module and a flap deformation module, wherein the power input module is arranged in the wing outer frame, the output end of the power input module is respectively connected with the thickness deformation module and the flap deformation module, the thickness deformation module is arranged close to the front edge of the wing outer frame, the thickness deformation module is arranged on two sides of the wing outer frame, the thickness deformation module can regulate the thickness of the wing outer frame under the driving of the power input module, one end of the flap deformation module extends to a trailing edge flap connected with the wing outer frame, and the flap deformation module can regulate the angle of the trailing edge flap under the driving of the power input module.
Preferably, the wing frame comprises an arc-shaped section, a plane section, an inclined plane section, a connecting section and a trailing edge flap, wherein the upper end of the arc-shaped section is used for being connected with the thickness deformation module, the lower end of the arc-shaped section is connected with one end of the plane section in an integrated manner, the other end of the plane section is connected with one end of the connecting section in an integrated manner, the other end of the connecting section is connected with the lower end face of the inclined plane section in an integrated manner, one end of the inclined plane section extends towards a direction close to the trailing edge flap, the other end of the inclined plane section extends towards a direction far away from the trailing edge flap, one end of the trailing edge flap is connected to the connecting section, and the other end of the trailing edge flap extends towards a direction far away from the connecting section.
Preferably, the trailing edge flap comprises a flap front section and a flap wing tip, two connecting protrusions are arranged at one end of the flap front section, the connecting protrusions located at the lower part are rotationally connected to the lower end face of the plane section, the connecting protrusions located at the upper part are rotationally connected to the flap deformation module, the other end of the flap front section is rotationally connected with one end of the flap wing tip, the other end of the flap wing tip is a free end, and one end, far away from the free end, of the flap wing tip is rotationally connected with the tail end of the flap deformation module.
Preferably, the power input module comprises a driving motor and two power input gears which are both arranged in the groove of the upper end face of the plane section, the two power input gears are symmetrically arranged on two sides in the wing outer frame, and the two power input gears are both driven by the driving motor.
Preferably, the thickness deformation modules are two groups, the two groups of thickness deformation modules are symmetrically arranged and are respectively connected with different power input gears, the thickness deformation modules comprise a thickness driving toothed bar, a first connecting rod, an airfoil front bar and an airfoil rear bar, the gear part of the thickness driving toothed bar is meshed with the power input gears, the straight bar part of the thickness driving toothed bar is rotationally connected with the lower end of the first connecting bar, the straight bar part of the thickness driving toothed bar is parallel to the plane section before thickening, the upper end of the first connecting bar is rotationally connected with the lower end of the airfoil rear bar, the upper end of the first connecting bar is inclined towards the direction close to the trailing edge flap, the airfoil rear bar comprises an arc connecting bar and a straight connecting bar, one end of the arc connecting bar is rotationally connected with the first connecting bar, the other end of the straight connecting bar is rotationally connected with one end of the inclined plane section, an arc hole is formed in the arc connecting bar, the lower end of the airfoil front bar is rotationally connected with one end of the airfoil section, and the upper end of the airfoil section is in the arc front bar is in the arc front of the arc connecting bar.
Preferably, a front wing plate is installed between the two airfoil front rods, a rear wing plate is installed between the two airfoil rear rods, one side of the front wing plate is rotationally connected with the arc-shaped section, the other side of the front wing plate is rotationally connected with one side of the rear wing plate, and the other side of the rear wing plate is rotationally connected with the inclined surface section.
Preferably, a pin is fixed at one end of the airfoil front rod, and the pin is slidably connected in the arc-shaped hole.
Preferably, the flap deformation module comprises a flap driving toothed bar, a second connecting rod and a third connecting rod, wherein a gear part of the flap driving toothed bar is meshed with the power input gear, a straight rod part of the flap driving toothed bar is rotationally connected with the upper end of the second connecting rod, the straight rod part of the flap driving toothed bar is parallel to the plane section before the flap changes the angle, the lower end of the second connecting rod is rotationally connected with one end of the front section of the flap, the upper end of the third connecting rod is rotationally connected with the lower end face of the plane section, the lower end of the third connecting rod is rotationally connected with the lower end face of the wing tip of the flap, and a connecting point of the third connecting rod and the wing tip of the flap is far away from the free end of the wing tip of the flap.
Compared with the prior art, the invention has the following technical effects:
According to the variable-thickness wing provided by the invention, the power input module is arranged in the wing frame, the wing frame plays a role of connecting the thickness deformation module and the flap deformation module and integrally supporting, the output end of the power input module is respectively connected with the thickness deformation module and the flap deformation module, the power output by the power input module is further respectively distributed between the thickness deformation module and the flap deformation module, then the corresponding deformation function is realized by the two parts of mechanisms, the thickness deformation module is arranged close to the front edge of the wing frame, the thickness deformation module is arranged on two sides of the wing frame, the thickness deformation module can regulate the thickness of the wing frame under the driving of the power input module, one end of the flap deformation module extends to a trailing edge flap connected with the wing frame, the flap deformation module can regulate the angle of the trailing edge under the driving of the power input module, the integral structure is simple, the manufacturing and the maintenance are convenient, and meanwhile, the control of the deformation state can be realized by changing the rotation angle of the power input gear of the power input module and the flap driving bar of the missing teeth, and the flap driving bar of the power input module and the wing with the missing teeth are positioned at different meshing positions, and the control states can be realized, and the wing tooth edge can be precisely designed, and the wing is well designed to be in a unified way.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a structure of a variable thickness wing provided by the invention before deformation;
FIG. 2 is a front view of FIG. 1;
FIG. 3 is a schematic view of the structure of the variable thickness wing provided by the invention in a maximum deformation state;
FIG. 4 is a schematic view of FIG. 3 at another angle;
FIG. 5 is a front view of FIG. 3;
FIG. 6 is a front view of a variable thickness airfoil according to the present invention in an intermediate deformed state;
FIG. 7 is a schematic view of the structure of the thickness deformation module and flap deformation module of the present invention;
FIG. 8 is a schematic view of the structure of a thickness deformation module, a flap deformation module and a trailing edge flap of the present invention;
In the figure, the blade comprises a 1-arc section, a 2-plane section, a 3-inclined plane section, a 4-connecting section, a 5-power input gear, a 6-thickness driving toothed bar, a 7-first connecting rod, an 8-airfoil rear bar, a 9-flap driving toothed bar, a 10-second connecting rod, a 11-third connecting rod, a 12-airfoil front bar, a 13-flap wing tip, a 14-flap front section, a 15-front wing plate and a 16-rear wing plate.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a variable-thickness wing, which solves the problems existing in the prior art, and has the advantages of simple integral structure, easy operation and high control precision.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
As shown in fig. 1-8, the present embodiment provides a variable thickness wing, including a wing frame, a power input module, a thickness deformation module and a flap deformation module, the power input module is installed in the wing frame, the wing frame plays a role of connecting the thickness deformation module and the flap deformation module, and integral support, the output end of the power input module is respectively connected with the thickness deformation module and the flap deformation module, and then the power output by the power input module is respectively distributed to the thickness deformation module and the flap deformation module, and then the two parts of mechanisms realize corresponding deformation functions, the thickness deformation module is close to the front edge of the wing frame, and the thickness deformation module is installed at two sides of the wing frame, and the thickness deformation module can adjust the thickness of the wing frame under the driving of the power input module, one end of the flap deformation module extends to the rear edge flap connected with the wing frame, and the flap deformation module can adjust the angle of the rear edge under the driving of the power input module, and the whole structure is simple, and convenient to manufacture and maintenance, simultaneously, by changing the rotation angle of the power input module, the power input gear 5 and the flap deformation gear 9 of the flap deformation module, and the flap deformation gear 5 are not in the same design, and the gear deformation state is realized, and the flap deformation is different from the position of the wing frame, and the wing deformation is well, and the wing deformation state is well designed.
Specifically, the wing frame includes arc section 1, plane section 2, inclined plane section 3, linkage segment 4 and trailing edge flap, the upper end of arc section 1 is used for connecting thickness deformation module, the lower extreme of arc section 1 is connected with the one end integrated into one piece of plane section 2, arc section 1 plays the effect of connecting thickness deformation module, the other end and the one end integrated into one piece of linkage segment 4 of plane section 2 are connected, the other end and the lower terminal surface integrated into one piece of inclined plane section 3 of linkage segment 4 are connected, the one end of inclined plane section 3 extends to the direction that is close to the trailing edge flap, the other end of inclined plane section 3 extends to the direction that keeps away from the trailing edge flap, the one end of trailing edge flap is connected on linkage segment 4, the other end of trailing edge flap extends to the direction that keeps away from the linkage segment 4, form the whole frame construction of thickness variation flap, improve supporting stability.
The trailing edge flap comprises a flap front section 14 and a flap wing tip 13, two connecting protrusions are arranged at one end of the flap front section 14, the connecting protrusions located at the lower portion are rotationally connected to the lower end face of the plane section 2, the connecting protrusions located at the upper portion are rotationally connected to the flap deformation module, further, the angle adjustment can be achieved through rotation under the driving of the flap deformation module, the other end of the flap front section 14 is rotationally connected with one end of the flap wing tip 13, the other end of the flap wing tip 13 is a free end, one end, far away from the free end, of the flap wing tip 13 is rotationally connected with the tail end of the flap deformation module, the flap wing tip 13 can change angles along with the action of the flap deformation module, and meanwhile, the flap wing tip 13 and the action of the flap front section 14 can be achieved simultaneously.
The power input module comprises a driving motor and two power input gears 5 which are both arranged in the groove of the upper end face of the plane section 2, the two power input gears 5 are symmetrically arranged on two sides in the wing outer frame, and the two power input gears 5 are both driven by the driving motor, so that power is provided.
The thickness deformation modules are two groups, the two groups of thickness deformation modules are symmetrically arranged and are respectively connected with different power input gears 5, the thickness deformation modules comprise a thickness driving toothed bar 6, a first connecting bar 7, an airfoil front bar 12 and an airfoil rear bar 8, the gear parts of the thickness driving toothed bar 6 are meshed with the power input gears 5 and can rotate under the driving of the power input gears 5, the straight bar parts of the thickness driving toothed bar 6 are rotationally connected with the lower ends of the first connecting bars 7, the straight bar parts of the thickness driving toothed bar 6 before thickness change are parallel to the plane section 2, the upper ends of the first connecting bars 7 are rotationally connected with the lower ends of the airfoil rear bars 8, the upper ends of the first connecting bars 7 are inclined towards the direction close to a trailing edge flap, the airfoil rear bars 8 comprise arc connecting bars and straight connecting bars, one ends of the arc connecting bars are rotationally connected with one ends of the straight connecting bars, the other ends of the straight connecting bars are rotationally connected with one ends of the inclined plane section 3, arc holes are formed in the arc connecting bars, the lower ends of the airfoil front bars 12 are rotationally connected with one ends of the arc section 1, and the upper ends of the airfoil front bars 12 are movably connected with the arc front bars 12. When the driving motor drives the power input gear 5 to rotate, the gear part of the thickness driving toothed bar 6 is meshed with the periphery of the power input gear 5, so that the power input gear 5 drives the thickness driving toothed bar 6 to rotate, one end, far away from the power input gear 5, of the thickness driving toothed bar 6 is enabled to rotate upwards, the first connecting bar 7 is driven to rotate and move, meanwhile, the first connecting bar 7 drives the wing surface rear bar 8 to move upwards, the moving direction and the moving stroke of the wing surface rear bar 8 are limited through the cooperation of one end of the wing surface front bar 12 and the arc hole until one end of the wing surface front bar 12 contacts with one end, far away from a trailing edge flap, of the arc hole, and at the moment, the wing surface rear bar 8 drives one end of the wing surface front bar 12 to rotate upwards, so that wing thickness change is achieved.
A front wing plate 15 is arranged between the two wing surface front rods 12, a rear wing plate 16 is arranged between the two wing surface rear rods 8, one side of the front wing plate 15 is rotationally connected with the arc-shaped section 1, the other side of the front wing plate 15 is rotationally connected with one side of the rear wing plate 16, and the other side of the rear wing plate 16 is rotationally connected with the inclined surface section 3.
One end of the airfoil front rod 12 is fixed with a pin, the pin is slidably connected in the arc hole, limiting of the airfoil rear rod 8 is achieved through matching of the arc hole and the pin, and the airfoil rear rod 8 drives the airfoil front rod 12 to rotate.
The flap deformation module comprises a flap driving toothed bar 9, a second connecting rod 10 and a third connecting rod 11, wherein a gear part of the flap driving toothed bar 9 is meshed with the power input gear 5, a straight rod part of the flap driving toothed bar 9 is rotationally connected with the upper end of the second connecting rod 10, the straight rod part of the flap driving toothed bar 9 is parallel to the plane section 2 before the flap changes angle, the lower end of the second connecting rod 10 is rotationally connected with one end of the flap front section 14, the upper end of the third connecting rod 11 is rotationally connected with the lower end face of the plane section 2, the lower end of the third connecting rod 11 is rotationally connected with the lower end face of the flap wing tip 13, and a connecting point of the third connecting rod 11 and the flap wing tip 13 is far away from the free end of the flap wing tip 13. When the driving motor drives the power input gear 5 to rotate, the gear part of the flap driving toothed bar 9 is meshed with the periphery of the power input gear 5, so that the power input gear 5 drives the flap driving toothed bar 9 to rotate, one end, far away from the power input gear 5, of the flap driving toothed bar 9 rotates downwards (and the rotation of the flap driving toothed bar 9 and the rotation of the thickness driving toothed bar 6 are synchronously carried out), the second connecting rod 10 is driven to rotate and move, the second connecting rod 10 drives the flap front section 14 to rotate and adjust the angle, meanwhile, due to the matched connection of the flap front section 14 and the flap tip 13 and the arrangement of the third connecting rod 11, when the second connecting rod 10 drives the flap front section 14 to rotate, the third connecting rod 11 drives the flap tip 13 to rotate under the driving of the flap front section 14, so that the flap tip 13 rotates relative to the flap front section 14 and also rotates along with the flap front section 14, the rear edge is integrally designed to be a two-end-type lowering wing, and finally, the angle adjustment of the flap on the rear edge is realized, and the wing is integrally deformed in a coordinated manner.
When the wing is regulated, the power input gear 5 and each driving toothed bar can be positioned at different meshing positions by changing the rotation angle of the output shaft of the driving motor, so that the accurate control of the whole deformation state can be realized, and the trailing edge flap and the variable-thickness wing are combined, thereby realizing uniform driving.
The principles and embodiments of the present invention have been described in detail with reference to specific examples, which are provided herein to facilitate understanding of the principles and embodiments of the present invention and to provide further advantages and practical applications for those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (5)
1. The variable-thickness wing is characterized by comprising a wing outer frame, a power input module, a thickness deformation module and a flap deformation module, wherein the power input module is arranged in the wing outer frame, the output end of the power input module is respectively connected with the thickness deformation module and the flap deformation module, the thickness deformation module is arranged close to the front edge of the wing outer frame, the thickness deformation module is arranged on two sides of the wing outer frame, the thickness deformation module can regulate the thickness of the wing outer frame under the drive of the power input module, one end of the flap deformation module extends to a trailing edge flap connected with the wing outer frame, and the flap deformation module can regulate the angle of the trailing edge flap under the drive of the power input module;
The wing outer frame comprises an arc-shaped section, a plane section, an inclined plane section, a connecting section and a trailing edge flap, wherein the upper end of the arc-shaped section is used for being connected with the thickness deformation module, the lower end of the arc-shaped section is integrally connected with one end of the plane section, the other end of the plane section is integrally connected with one end of the connecting section, the other end of the connecting section is integrally connected with the lower end face of the inclined plane section, one end of the inclined plane section extends towards the direction close to the trailing edge flap, the other end of the inclined plane section extends towards the direction far away from the trailing edge flap, one end of the trailing edge flap is connected to the connecting section, and the other end of the trailing edge flap extends towards the direction far away from the connecting section;
The power input module comprises a driving motor and two power input gears which are both arranged in a groove on the upper end surface of the plane section, the two power input gears are symmetrically arranged on two sides in the wing outer frame, and the two power input gears are both driven by the driving motor;
The thickness deformation modules are two groups, the two groups of thickness deformation modules are symmetrically arranged and are respectively connected with different power input gears, each thickness deformation module comprises a thickness driving toothed bar, a first connecting rod, an airfoil front rod and an airfoil rear rod, the gear parts of the thickness driving toothed bars are meshed with the power input gears, the straight rod parts of the thickness driving toothed bars are rotationally connected with the lower ends of the first connecting rods, the straight rod parts of the thickness driving toothed bars are parallel to the plane sections before thickening, the upper ends of the first connecting rods are rotationally connected with the lower ends of the airfoil rear rods, the upper ends of the first connecting rods are inclined towards the direction close to the trailing edge flaps, each airfoil rear rod comprises an arc connecting rod and a straight connecting rod, one ends of the arc connecting rods are rotationally connected with the first connecting rods, the other ends of the arc connecting rods are integrally formed with one ends of the straight connecting rods, one ends of the inclined surface sections are rotationally connected with the lower ends of the airfoil front rods, one ends of the airfoil front rods are rotationally connected with the lower ends of the airfoil front rods, and the upper ends of the airfoil front rods are in front ends of the arc connecting rods.
2. The variable thickness wing according to claim 1, wherein the trailing edge flap comprises a flap front section and a flap tip, two connecting protrusions are arranged at one end of the flap front section, the connecting protrusions located at the lower part are rotationally connected to the lower end face of the plane section, the connecting protrusions located at the upper part are rotationally connected to the flap deformation module, the other end of the flap front section is rotationally connected with one end of the flap tip, the other end of the flap tip is a free end, and one end of the flap tip, which is far away from the free end, is rotationally connected to the tail end of the flap deformation module.
3. A variable thickness wing as set forth in claim 2 wherein a front wing plate is mounted between said two airfoil front rods and a rear wing plate is mounted between said two airfoil rear rods, one side of said front wing plate being rotatably connected to said arcuate section, the other side of said front wing plate being rotatably connected to one side of said rear wing plate, the other side of said rear wing plate being rotatably connected to said inclined section.
4. The variable thickness airfoil as set forth in claim 3, wherein a pin is secured to an end of the airfoil forward shank, the pin being slidably coupled within the arcuate bore.
5. The variable thickness wing of claim 2, wherein the flap deformation module comprises a flap drive toothed bar, a second connecting rod and a third connecting rod, a gear part of the flap drive toothed bar is meshed with the power input gear, a straight rod part of the flap drive toothed bar is rotationally connected with the upper end of the second connecting rod, the straight rod part of the flap drive toothed bar is parallel to the plane section before flap angle change, the lower end of the second connecting rod is rotationally connected with one end of the flap front section, the upper end of the third connecting rod is rotationally connected with the lower end face of the plane section, the lower end of the third connecting rod is rotationally connected with the lower end face of the flap tip, and a connection point of the third connecting rod and the flap tip is far away from the free end of the flap tip.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410649382.4A CN118479028B (en) | 2024-05-23 | 2024-05-23 | A variable thickness wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410649382.4A CN118479028B (en) | 2024-05-23 | 2024-05-23 | A variable thickness wing |
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| Publication Number | Publication Date |
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| CN118479028A CN118479028A (en) | 2024-08-13 |
| CN118479028B true CN118479028B (en) | 2025-09-05 |
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| CN202410649382.4A Active CN118479028B (en) | 2024-05-23 | 2024-05-23 | A variable thickness wing |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6000660A (en) * | 1998-01-19 | 1999-12-14 | Southwest Research Institute | Rotary beam variable stiffness wing spar |
| KR20230085460A (en) * | 2021-12-07 | 2023-06-14 | 조대기 | Morphing wing device |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4262868A (en) * | 1979-05-29 | 1981-04-21 | The Boeing Company | Three-position variable camber flap |
| CN114291249B (en) * | 2021-12-31 | 2023-08-04 | 中国飞机强度研究所 | Variable-thickness wing structure |
| CN117602061A (en) * | 2023-12-07 | 2024-02-27 | 南京航空航天大学 | A distributed drive mechanism that can achieve variable camber and thickness of the wing |
| CN117550062A (en) * | 2023-12-11 | 2024-02-13 | 北京航空航天大学 | Variable-thickness wing |
-
2024
- 2024-05-23 CN CN202410649382.4A patent/CN118479028B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6000660A (en) * | 1998-01-19 | 1999-12-14 | Southwest Research Institute | Rotary beam variable stiffness wing spar |
| KR20230085460A (en) * | 2021-12-07 | 2023-06-14 | 조대기 | Morphing wing device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN118479028A (en) | 2024-08-13 |
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