CN202848022U - Telescopic wing mechanism with changeable elongation and area - Google Patents
Telescopic wing mechanism with changeable elongation and area Download PDFInfo
- Publication number
- CN202848022U CN202848022U CN 201220504857 CN201220504857U CN202848022U CN 202848022 U CN202848022 U CN 202848022U CN 201220504857 CN201220504857 CN 201220504857 CN 201220504857 U CN201220504857 U CN 201220504857U CN 202848022 U CN202848022 U CN 202848022U
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- wing
- telescopic
- gear
- motor
- slide block
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Abstract
The utility model relates to a telescopic wing mechanism with changeable elongation and area, wherein a telescopic wing comprises an inner swing and an outer swing capable of making a telescopic action in the inner swing. The telescopic wing mechanism is characterized in that the whole mechanism comprises a motor (5), and supporting, force transferring, buffering and locking mechanisms which are in bilateral symmetry by taking a mechanism body as a reference and include two groups of guide rails (2), sliding blocks (9), end locking blocks (8), two groups of fan-shaped gears (3 and 6) and one group of diamond telescopic mechanisms (4), wherein hinges are mounted at both ends of each diamond telescopic mechanism (4); one end of each diamond telescopic mechanism is connected to each fan-shaped gear (6) at the root part of the outer swing through a connecting rod while the other end of each diamond telescopic mechanism is connected to each fan-shaped gear (3) at the root part of the outer swing, so that the telescopic mechanisms are driven to deform under the rotation of the gears; the motor (5) is mounted at the root part of the inner swing; one gear at the root part of the inner swing is mounted on an output shaft of the motor (5); the guide rails (2) are arranged at the front edge and the rear edge of the inner swing; the end locking blocks (8) are mounted on the outer sides of the guide rails (2); the sliding blocks (9) fixed on the outer swing are positioned in the guide rails; and the sliding blocks (9) are clamped through the end locking blocks (8) after the telescopic mechanisms stretch properly.
Description
Technical field
The utility model belongs to the unmanned plane technical field, is used for design and becomes profile unmanned plane structure.
Background technology
As raw MAT'L, majority utilizes the bending of flexible wing or torsional deflection to produce compressed-air control power to early stage aircraft, such as Lai Te brother's First motor plane with the little timber of density, cloth and metal filament.
Along with the raising of air speed and load-carrying capacity, the wing and primary control surface replace the rigidity requirement of aircaft configuration so that flexible wing is fixed.For the driving efficiency that improves aircraft, adapt to different flight environment of vehicle and different aerial missions, people have designed the rigid deformation structure, comprise that fly control, wing sweeping angle realization short take-off and landing (STOL) and supersonic speed of control surface deflection cruise etc.But rigid deformation structure bulky complex is especially for variable swept back wing mechanism, because weight increases and the income that distortion brings has almost been offset in the reliability reduction.
The proposition of the development of sensor, Drive technology and intellectual material structuring concept is for the aircraft of variable geometry has brought new dawn.Replace the articulated traditional, pneumatic function unit of mechanism with seamless, smooth continuously pneumatic control component, can avoid effectively that traditional chain lever system weight is large, hinge arrangement fatiguability, road-holding property and the manoevreability problems such as not bery ideal and 1ift-drag ratio be little, directly rely on wing to be out of shape to change aerodynamic force and carry out flight control, can significantly improve the air operated control performance of aircraft.But this wing distortion yardstick based on the self adaptation pneumatic structure is little, just to the fixed type wing to a certain extent replenish and perfect, can't satisfy the demand of the full spatial domain of following unmanned plane, All Speed Range far away.
Therefore, meet pneumatic load bearing requirements, satisfy the need of large scale geometry deformation, lightweight construction, the excellent wing deformation mechanism of controller performance are the following keys that becomes profile unmanned plane structure design.
The utility model content
The technical matters that the utility model solves is: overcome the deficiencies in the prior art, the telescopic wing mechanism that provide that a kind of load-carrying capacity is strong, the distortion yardstick is large, structure light wt, control becomes length and area efficiently.
Technical solution of the present utility model is: a kind of telescopic wing mechanism that becomes length and area, and described telescopic wing is comprised of inner wing and the outer wing that can stretch in inner wing; Mechanism comprises motor and with the symmetrical support of fuselage, power transmission, buffering catch gear; Described support, power transmission, buffering catch gear comprise two groups of guide rails, slide block and terminal latch segment, two groups of quadrant gears, one group of rhombus telescoping mechanism;
Hinge is installed at the two ends of rhombus telescoping mechanism, and an end is connected on the outer wing root quadrant gear by connecting rod, and the other end is connected on the inner wing root quadrant gear by connecting rod, rotates by gear and drives the distortion of rhombus telescoping mechanism; Motor is installed in the whole diamonding mechanism plane of symmetry, the inner wing root is installed on the output shaft of motor near the quadrant gear of the diamonding mechanism plane of symmetry, the inner wing front and rear edge arranges guide rail, terminal latch segment is installed in the guide rail outside, the slide block that is fixed on the outer wing places guide rail, blocks slide block by terminal latch segment after full extension is opened.
Described terminal latch segment is the trench structure that the end is not sealed, and an end is that big opening end, an end are the osculum end, and slide block enters at the osculum end from big opening end and blocks.
The utility model beneficial effect compared with prior art is:
(1) the utility model can satisfy the strength and stiffness requirement by adopting guide rail-slide block to support and power transmission, can guarantee again the flexible fore and aft motion of long stroke of outer wing, has realized that load-carrying capacity is strong, the distortion yardstick is large.
(2) the utility model can reduce number of drives by adopting a motor and two groups of symmetrical synchronizer gears and rhombus enlarger to drive and transmission, has realized structure light wt.
(3) the utility model can solve both sides wing stationary problem by adopting a motor and two groups of symmetrical synchronizer gears and rhombus enlarger to drive and transmission, and reduces the complexity of control system, has realized that control is efficient.
Description of drawings
Fig. 1, Fig. 2 are expansion of the present utility model and contraction state;
Fig. 3 is guide rail of the present utility model, slide block and catch gear relative position scheme drawing;
Fig. 4 is buffering of the present utility model and locking mechanism scheme drawing;
Fig. 5 is slide block scheme drawing of the present utility model;
Fig. 6 is overall assembling scheme drawing of the present utility model.
The specific embodiment
Below in conjunction with accompanying drawing the technical solution of the utility model is described further:
Variable geometry aircraft according to the layout of the different change of flight devices of aerial mission, has reached the perfect matching of aeroperformance and aerial mission in flight course.
Present embodiment is a kind of telescopic wing deformation mechanism that becomes length and area, shown in Fig. 1,2,6, for convenience, has omitted wing mechanism and attaching parts among the figure.Described telescopic wing is comprised of inner wing and the outer wing 1 that can stretch in inner wing; Mechanism comprises motor 5 and with the symmetrical support of fuselage, power transmission, buffering catch gear; Described support, power transmission, buffering catch gear comprise two groups of guide rails 2, slide block 8 and terminal latch segment 9 (relative position as shown in Figure 3), two groups of quadrant gears 3,6, one group of rhombus telescoping mechanism 4.
Hinge is installed at the two ends of rhombus telescoping mechanism 4, and an end is hinged on the outer wing root, and the other end is hinged on the deformation mechanism driver train of fuselage interior, and installing connecting rods is the flexible power transmission of wing by quadrant gear 3,6 also between the hinge of every end; Motor 5 is installed in deformation mechanism plane of symmetry position, one of them gear is installed on the output shaft of motor 5 in the deformation mechanism, the inner wing front and rear edge arranges guide rail 2, terminal latch segment 8 is installed in guide rail 2 outsides, the slide block 9 that is fixed on the outer wing places guide rail 2 (as shown in Figure 5), full extension is blocked slide block 9 by terminal latch segment 8 after opening, and guide rail 2 itself and wing structure are connected, and inboardly is connected connection with the fuselage frame.
In the flight course, when the needs wing carries out dilatation, motor 5 driven wheels 3, to hinge place connecting rod, connecting rod drives rhombus telescoping mechanism 4, and then driven gear 6 by gear engagement power transmission, and the gear driven outer wing realizes that the exhibition of telescopic wing is to flexible.
In order to alleviate the complexity of distressed structure weight and control system, adopt single propulsion source to drive the both sides outer wing and realize synchronization telescope, for load-carrying capacity, kinematic accuracy and the stability of strengthening rhombus telescoping mechanism 4, hinge and quadrant gear 3,6 are adopted in rhombus telescoping mechanism two ends.The connecting rod at two hinge places of main wing root is realized being synchronized with the movement by gear engagement, and the connecting rod by one of them hinge place of motor-driven rotates to drive whole mechanism and carries out dilatation.When outer wing stretches fully, in order to prevent shake and to consume motor power, adopt guide rail end latch segment 8 to block the mode of slide block 9, lean on the friction force of the conical surface that driving and the driving system of distressed structure is locked.Terminal latch segment 8 is illustrated in figure 4 as the trench structure that the end is not sealed, and an end is that big opening end, an end are the osculum end, and slide block 9 enters at the osculum end from big opening end and blocks.
After the telescopic wing parts leave main wing, outer wing will be subject to the effect of aerodynamic force and aerodynamic torque.Especially the moment of flexure and the torque influence that cause with aerodynamic lift and aerodynamic lift in the suffered aerodynamic loading of outer wing are the most remarkable, the suffered aerodynamic loading of outer wing is by being delivered on the guide rail 2 with the fixed slide block 9 of outer wing support, then be delivered on the fuselage rib frame 7 by guide rail 2, have comparatively complicated interaction between slide block 9 and the guide rail 2.
Whole mechanism shrinks identical with spreading principle, can realize continuous modification.
The utility model not detailed description is technology as well known to those skilled in the art.
Claims (2)
1. telescopic wing mechanism that becomes length and area, described telescopic wing is comprised of inner wing and the outer wing that can stretch in inner wing; It is characterized in that: mechanism comprises motor (5) and with the symmetrical support of fuselage, power transmission, buffering catch gear; Described support, power transmission, buffering catch gear comprise two groups of guide rails (2), slide block (9) and terminal latch segment (8), two groups of quadrant gears, one group of rhombus telescoping mechanism (4);
Hinge is installed at the two ends of rhombus telescoping mechanism (4), and an end is connected on the outer wing root quadrant gear by connecting rod, and the other end is connected on the inner wing root quadrant gear by connecting rod, rotates by gear and drives rhombus telescoping mechanism (4) distortion; Motor (5) is installed in the whole diamonding mechanism plane of symmetry, the inner wing root is installed on the output shaft of motor (5) near the quadrant gear of the diamonding mechanism plane of symmetry, the inner wing front and rear edge arranges guide rail (2), terminal latch segment (8) is installed in guide rail (2) outside, be fixed on and block slide block (9) by terminal latch segment (8) after slide block (9) on the outer wing places guide rail, full extension to open.
2. a kind of telescopic wing mechanism that becomes length and area according to claim 1, it is characterized in that: the trench structure that described terminal latch segment (8) does not seal for the end, one end is that big opening end, an end are the osculum end, and slide block (9) enters at the osculum end from big opening end and blocks.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220504857 CN202848022U (en) | 2012-09-29 | 2012-09-29 | Telescopic wing mechanism with changeable elongation and area |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220504857 CN202848022U (en) | 2012-09-29 | 2012-09-29 | Telescopic wing mechanism with changeable elongation and area |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202848022U true CN202848022U (en) | 2013-04-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220504857 Expired - Fee Related CN202848022U (en) | 2012-09-29 | 2012-09-29 | Telescopic wing mechanism with changeable elongation and area |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202848022U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105277077A (en) * | 2014-07-25 | 2016-01-27 | 南京理工大学 | Intelligent flexible wing of terminal sensing ammunition |
| CN106628117A (en) * | 2016-12-30 | 2017-05-10 | 西安科技大学 | High-speed controllable telescopic wing |
| CN107795810A (en) * | 2017-11-13 | 2018-03-13 | 梁兆寇 | Rotatable television stand convenient to height-adjusting |
| CN107914864A (en) * | 2017-11-01 | 2018-04-17 | 成都飞亚航空设备应用研究所有限公司 | Aircraft wing rotates jack and its accommodation method |
| CN108248826A (en) * | 2016-12-29 | 2018-07-06 | 北京卓翼智能科技有限公司 | A kind of telescopic wing mechanism, telescopic method and include its aircraft |
| CN112977879A (en) * | 2021-04-01 | 2021-06-18 | 中国航天空气动力技术研究院 | Aeroelastic test platform |
| CN114313256A (en) * | 2022-02-18 | 2022-04-12 | 上海力鸿航空科技有限公司 | Bird-like folding wing mechanism |
-
2012
- 2012-09-29 CN CN 201220504857 patent/CN202848022U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105277077A (en) * | 2014-07-25 | 2016-01-27 | 南京理工大学 | Intelligent flexible wing of terminal sensing ammunition |
| CN108248826A (en) * | 2016-12-29 | 2018-07-06 | 北京卓翼智能科技有限公司 | A kind of telescopic wing mechanism, telescopic method and include its aircraft |
| CN106628117A (en) * | 2016-12-30 | 2017-05-10 | 西安科技大学 | High-speed controllable telescopic wing |
| CN106628117B (en) * | 2016-12-30 | 2023-02-24 | 西安科技大学 | High-speed controllable telescopic wing |
| CN107914864A (en) * | 2017-11-01 | 2018-04-17 | 成都飞亚航空设备应用研究所有限公司 | Aircraft wing rotates jack and its accommodation method |
| CN107795810A (en) * | 2017-11-13 | 2018-03-13 | 梁兆寇 | Rotatable television stand convenient to height-adjusting |
| CN112977879A (en) * | 2021-04-01 | 2021-06-18 | 中国航天空气动力技术研究院 | Aeroelastic test platform |
| CN114313256A (en) * | 2022-02-18 | 2022-04-12 | 上海力鸿航空科技有限公司 | Bird-like folding wing mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130403 Termination date: 20150929 |
|
| EXPY | Termination of patent right or utility model |