CN109278983A - A kind of change buzzard-type wing and canard clutch mechanism and its working method - Google Patents
A kind of change buzzard-type wing and canard clutch mechanism and its working method Download PDFInfo
- Publication number
- CN109278983A CN109278983A CN201811421446.6A CN201811421446A CN109278983A CN 109278983 A CN109278983 A CN 109278983A CN 201811421446 A CN201811421446 A CN 201811421446A CN 109278983 A CN109278983 A CN 109278983A
- Authority
- CN
- China
- Prior art keywords
- buzzard
- type wing
- wing
- canard
- spar
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
A kind of change buzzard-type wing and canard clutch mechanism and its working method, are related to the wing structure technical field of aircraft；The technical issues of forming interference can be streamed to wing and fuselage by solving the gap stream between canard and complete buzzard-type wing, specifically include canard and buzzard-type wing；Canard and buzzard-type wing are separately positioned on the two sides of fuselage, and buzzard-type wing is arranged in canard front end, and for the wingtip side wall surface of buzzard-type wing along tangential setting spar, the wingtip side wall surface of buzzard-type wing is coated with flexible covering structure；Flexible covering inside configuration is additionally provided with drive system, and drive system drive wing sill bolt moves the smooth continuous modification of flexible covering structure；The present invention drives drive wing sill bolt to move the smooth continuous modification of flexible covering structure by the way that flexible covering structure is arranged in buzzard-type wing outer end by drive system；The shape of buzzard-type wing is changed shape by the driving of spar, and then changes the spacing of buzzard-type wing and canard, the final seamless overlap joint for realizing the two.
Description
Technical field
The present invention relates to the wing structure technical field of aircraft more particularly to a kind of change buzzard-type wing and canard clutch mechanism and
Its working method.
Background technique
Morphing aircraft can enable aircraft to adapt in real time more by the outer shape of partly or wholly change of flight device
Kind mission requirements, and efficiency and best performance are kept in a variety of flight environment of vehicle, riding comfort is improved, operating cost is reduced and makes an uproar
The environment of sound influences.In aeronautical technology development process, variant designs thought is constantly embodied, but is only limitted to wing or some portions
The position change of part.
Change is plunderred wing morphing aircraft and is plunderred by the way that wing is front/rear, effectively can optimize aircraft according to task and environmental change in real time
Lift resistance ratio, pneumatic efficiency, flying speed and mobility are the important research directions of new concept morphing aircraft；Especially sweepforward
Wing morphing aircraft due to material and construction applications progress so that its aeroelastic divergence problem is resolved, because of it
Potential aeroperformance gain recent domestic proposes many buzzard-type wing variations, including when supersonic speed aerofoil is complete
Sweepforward and canard are fused into the big dalta wing of class.But it is flowed in the gap in such variations between canard and complete buzzard-type wing
Wing and fuselage can be streamed to form interference, there is no reliable and effective canard and buzzard-type wing clutch mechanism at present, so that the program
Pneumatic gain have a greatly reduced quality.
Summary of the invention
The present invention overcomes above-mentioned the deficiencies in the prior art, a kind of change buzzard-type wing and canard clutch mechanism and its work are provided
Make method.The present invention drives drive wing sill bolt to move institute by the way that flexible covering structure is arranged in buzzard-type wing outer end by drive system
State the smooth continuous modification of flexible covering structure；The shape of buzzard-type wing by spar driving change shape, and then change buzzard-type wing with
The spacing of canard, the final seamless overlap joint for realizing the two.
Technical solution of the present invention:
A kind of change buzzard-type wing and canard clutch mechanism, including canard and buzzard-type wing；The canard and buzzard-type wing are respectively set
In the two sides of fuselage, the buzzard-type wing is arranged in canard front end, and the wingtip side wall surface of the buzzard-type wing is along tangential setting spar, institute
The wingtip side wall surface for stating buzzard-type wing is coated with flexible covering structure；The flexible covering inside configuration is additionally provided with drive system,
The drive system drive wing sill bolt moves the smooth continuous modification of flexible covering structure.
Further, the drive system includes spar, slide roller, reset spring, actuator and fixed mounting；It is described
The inside of the buzzard-type wing side wall is arranged in fixing seat frame, is provided with two groups of peaces disposed in parallel on the fixed mounting upper surface
Vertical plate is filled, the corresponding position of installation riser described in two groups is machined with inclined mobile chute respectively, and every two position is corresponding
It is respectively arranged with one group of slide roller in mobile chute, is respectively arranged with one group of rolling bearing on each slide roller, two
Connection is fixed by the connecting rod between the group rolling bearing, two rolling bearings pass through pull rod and the fixed company of spar respectively
It connecing, one end of rolling bearing and actuator that left end is arranged in connects, and the other end and executor support of the actuator are hinged,
The executor support is fixed at the left end of the fixed mounting, and the rolling bearing and one group of reset spring of right end is arranged in
It is fixedly connected, the other end of the reset spring, which is fixed at, to be resetted on mounting plate, and the reset mounting plate is fixed at
On the fixed mounting.
A kind of working method becoming buzzard-type wing and canard clutch mechanism, this method comprises the following steps:
Step a: the driving of spar: actuator driving slide roller moves in inclined mobile chute, by actuator edge
The tangential horizontal movement of wing is converted into perpendicular to tangential vertical movement,
Step b: the extension of buzzard-type wing: the wingtip side wall of buzzard-type wing is opened up by spar drives edge wing to Forward, and sweepforward is changed
Contour of flange；
Step c: the overlap joint of buzzard-type wing and canard: the shape of buzzard-type wing is changed shape by the driving of spar, and then before change
The spacing of the wing and canard is plunderred, the final seamless overlap joint for realizing the two.
The present invention has the advantages that compared with the existing technology
The present invention overlaps canard and buzzard-type wing wingtip side wall aerofoil, so that two aerofoils are seamless to be fused into the big triangle of class
The wing can improve the supersonic velocity pneumatic performance of buzzard-type wing variant aircraft, give full play to the advance of buzzard-type wing variant aircraft；It completes several
The structural system structure of what change in shape is simple, compact, efficient, and it is convenient to design for specific buzzard-type wing morphing aircraft；
The present invention drives drive wing sill bolt to move institute by the way that flexible covering structure is arranged in buzzard-type wing outer end by drive system
State the smooth continuous modification of flexible covering structure；The shape of buzzard-type wing by spar driving change shape, and then change buzzard-type wing with
The spacing of canard, the final seamless overlap joint for realizing the two.
Detailed description of the invention
Fig. 1 is that buzzard-type wing variant of the invention is laid out complete sweepforward state schematic layout pattern；
Fig. 2 is change buzzard-type wing and canard clutch mechanism operation front and back contrast schematic diagram of the invention；
Fig. 3 is drive system axonometric drawing one of the invention；
Fig. 4 is drive system axonometric drawing two of the invention；
Fig. 5 is the connection relationship diagram of two slide rollers of the invention.
1- canard in figure；2- buzzard-type wing；3- wingtip side wall surface；4- drive system；5- spar；6- pull rod；7- slide roller；
8- mobile chute；9- reset spring；10- actuator；11- fixes mounting；12- rolling bearing.
Specific embodiment
Below with reference to attached drawing, the present invention is described in detail.
Show in conjunction with Fig. 1-Fig. 5, a kind of change buzzard-type wing and canard clutch mechanism disclosed in the present embodiment, including canard 1 and before
Plunder the wing 2；The canard 1 and buzzard-type wing 2 are separately positioned on the two sides of fuselage, and the setting of buzzard-type wing 2 is described in 1 front end of canard
The wingtip side wall surface 3 of buzzard-type wing 2 is coated with flexible covering knot along tangential setting spar 5, the wingtip side wall surface 3 of the buzzard-type wing 2
Structure；The flexible covering inside configuration is additionally provided with drive system 4, and the drive system 4 drives spar 5 to drive the flexible illiteracy
The smooth continuous modification of skin structure.
Specifically, the drive system 4 includes spar 5, slide roller 7, reset spring 9, actuator 10 and fixed mounting
11；The wingtip side wall surface 3 of the buzzard-type wing 2 is arranged in the fixed mounting 11, is provided on fixed 11 upper surface of mounting
Two groups of installation risers disposed in parallel, the corresponding position of installation riser described in two groups are machined with inclined mobile chute 8 respectively,
It is respectively arranged with one group of slide roller 7 in the corresponding mobile chute 8 in every two position, is set respectively on each slide roller 7
It is equipped with one group of rolling bearing 12, connection, two rolling bearings are fixed by the connecting rod between rolling bearing 12 described in two groups
12 are fixedly connected by pull rod 6 with spar 5 respectively, and the rolling bearing 12 that left end is arranged in is connect with one end of actuator 10, institute
The other end and 10 bracket of actuator for stating actuator 10 are hinged, and 10 bracket of actuator is fixed at the fixed mounting 11
Left end, the rolling bearing 12 that right end is arranged in is fixedly connected with one group of reset spring 9, and the other end of the reset spring 9 is solid
On resetting mounting plate, the reset mounting plate is fixed on the fixed mounting 11 for fixed setting.
A kind of working method becoming buzzard-type wing and canard clutch mechanism, this method comprises the following steps:
Step a: the driving of spar 5: actuator 10 drives slide roller 7 to move in inclined mobile chute 8, by actuation
Device 10 is converted into along the tangential horizontal movement of wing perpendicular to tangential vertical movement,
Step b: the extension of buzzard-type wing 2: the wingtip side wall surface 3 of buzzard-type wing 2 is opened up by 5 drives edge wing of spar to Forward, is changed
Become 2 shape of buzzard-type wing；
Step c: the overlap joint of buzzard-type wing 2 and canard 1: 3 shape of wingtip side wall surface of buzzard-type wing 2 is changed by the driving of spar 5
Shape, and then change the spacing of buzzard-type wing 2 and canard 1, the final seamless overlap joint for realizing the two.
Above embodiments are exemplary description of this patent, do not limit its protection scope, those skilled in the art
Member can also be changed its part, as long as it does not exceed the essence of this patent, within the protection scope of the present patent.
Claims (3)
1. a kind of change buzzard-type wing and canard clutch mechanism, including canard (1) and buzzard-type wing (2)；It is characterized by: the canard
(1) and buzzard-type wing (2) is separately positioned on the two sides of fuselage, and the buzzard-type wing (2) is arranged in canard (1) front end, the buzzard-type wing
(2) wingtip side wall surface (3) coats flexible illiteracy along tangential setting spar (5), the wingtip side wall surface (3) of the buzzard-type wing (2)
Skin structure；The flexible covering inside configuration is additionally provided with drive system (4), and drive system (4) driving spar (5) drives
The smooth continuous modification of flexible covering structure.
2. a kind of change buzzard-type wing according to claim 1 and canard clutch mechanism, which is characterized in that the drive system
It (4) include spar (5), slide roller (7), reset spring (9), actuator (10) and fixation mounting (11)；The fixed mounting
(11) the wingtip side wall surface (3) in the buzzard-type wing (2) is set, be provided on fixed mounting (11) upper surface two groups it is parallel
The installation riser of setting, the corresponding position of installation riser described in two groups are machined with inclined mobile chute (8), every two respectively
It is respectively arranged with one group of slide roller (7) in the corresponding mobile chute in position (8), is set respectively on each slide roller (7)
It is equipped with one group of rolling bearing (12), connection, two rollings are fixed by the connecting rod between rolling bearing described in two groups (12)
Bearing (12) is fixedly connected by pull rod (6) with spar (5) respectively, and rolling bearing (12) and actuator (10) of left end are arranged in
One end connection, the other end and actuator (10) bracket of the actuator (10) are hinged, and actuator (10) bracket is fixed
The rolling bearing (12) that right end is arranged in the left end of the fixed mounting (11) and the fixed company of one group of reset spring (9) are set
It connects, the other end of the reset spring (9), which is fixed at, to be resetted on mounting plate, and the reset mounting plate is fixed at described
On fixed mounting (11).
3. a kind of working method using a kind of change buzzard-type wing and canard clutch mechanism described in as claimed in claim 1 or 22, feature exist
In this method comprises the following steps:
Step a: the driving of spar (5): actuator (10) driving slide roller (7) is moved in inclined mobile chute (8), will
Actuator (10) is converted into along the tangential horizontal movement of wing perpendicular to tangential vertical movement,
Step b: the extension of buzzard-type wing (2): the wingtip side wall surface (3) of buzzard-type wing (2) is opened up forward by spar (5) drives edge wing
It moves, changes buzzard-type wing (2) shape；
Step c: the overlap joint of buzzard-type wing (2) and canard (1): drive of wingtip side wall surface (3) shape of buzzard-type wing (2) by spar (5)
It is dynamic to change shape, and then change the spacing of buzzard-type wing (2) and canard (1), the seamless overlap joint of both final realizations.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811421446.6A CN109278983B (en) | 2018-11-26 | 2018-11-26 | Front-sweep wing-changing and duck wing overlapping mechanism and working method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811421446.6A CN109278983B (en) | 2018-11-26 | 2018-11-26 | Front-sweep wing-changing and duck wing overlapping mechanism and working method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109278983A true CN109278983A (en) | 2019-01-29 |
| CN109278983B CN109278983B (en) | 2023-09-29 |
Family
ID=65173262
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811421446.6A Active CN109278983B (en) | 2018-11-26 | 2018-11-26 | Front-sweep wing-changing and duck wing overlapping mechanism and working method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109278983B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979682A (en) * | 2019-12-30 | 2020-04-10 | 西北工业大学 | Variable-area duck-type forward-swept wing variant aircraft |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101271485B1 (en) * | 2011-12-23 | 2013-06-05 | 한국항공우주연구원 | Morphing wing of air vehicle |
| CA2793044A1 (en) * | 2011-12-12 | 2013-06-12 | The Boeing Company | Wing variable camber trailing edge tip |
| CN103231795A (en) * | 2013-04-12 | 2013-08-07 | 成都飞机设计研究所 | Corporate aircraft engine upper placement and front swept wing duck type layout |
| CN203255353U (en) * | 2013-05-16 | 2013-10-30 | 柴睿 | Variable-sweep wing of aircraft |
| CN203740120U (en) * | 2014-03-31 | 2014-07-30 | 冯加伟 | Aerodynamic structure of morphing aircraft with wide flight envelope |
| CN108190005A (en) * | 2016-12-08 | 2018-06-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of aerofoil fusion type edge strip |
-
2018
- 2018-11-26 CN CN201811421446.6A patent/CN109278983B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2793044A1 (en) * | 2011-12-12 | 2013-06-12 | The Boeing Company | Wing variable camber trailing edge tip |
| KR101271485B1 (en) * | 2011-12-23 | 2013-06-05 | 한국항공우주연구원 | Morphing wing of air vehicle |
| CN103231795A (en) * | 2013-04-12 | 2013-08-07 | 成都飞机设计研究所 | Corporate aircraft engine upper placement and front swept wing duck type layout |
| CN203255353U (en) * | 2013-05-16 | 2013-10-30 | 柴睿 | Variable-sweep wing of aircraft |
| CN203740120U (en) * | 2014-03-31 | 2014-07-30 | 冯加伟 | Aerodynamic structure of morphing aircraft with wide flight envelope |
| CN108190005A (en) * | 2016-12-08 | 2018-06-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of aerofoil fusion type edge strip |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979682A (en) * | 2019-12-30 | 2020-04-10 | 西北工业大学 | Variable-area duck-type forward-swept wing variant aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109278983B (en) | 2023-09-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102458988B (en) | There is the aircraft of the box-like wing structure of λ | |
| CN102282070B (en) | Horizontal stabilising surface of an aircraft | |
| EP3034393B1 (en) | Trailing edge device with bell crank mechanism | |
| US10889365B2 (en) | Auxiliary support system for a flap of an aircraft wing | |
| US9580168B2 (en) | Cove lip door slaved to trailing edge control device | |
| EP2060769A2 (en) | Thrust reverser | |
| US7416155B2 (en) | Canard position and dihedral for boom reduction and pitch/directional control | |
| CN206664929U (en) | A kind of culvert type oil moves single rotor unmanned aircraft | |
| EP3309059A1 (en) | Aircraft wings, aircraft, and related methods | |
| CN110979682A (en) | Variable-area duck-type forward-swept wing variant aircraft | |
| WO1995011159A1 (en) | Aircraft flight control system | |
| CN111348178A (en) | Variable camber wing leading edge flexible skin structure and design method thereof | |
| CN103204238A (en) | Jet rudder surface control system, aircraft using same, and method for controlling aircraft | |
| CN109278983A (en) | A kind of change buzzard-type wing and canard clutch mechanism and its working method | |
| CN102114911B (en) | Pulley type structure high lift device for dual-arc sliding rail | |
| CN102963521A (en) | Central wing of horizontal tail of civil airplane | |
| CN209097008U (en) | A kind of change buzzard-type wing and canard clutch mechanism | |
| CN108296290B (en) | A kind of processing method and aluminium alloy rolling apparatus of skin panel | |
| CN110116802A (en) | A kind of big loading small-sized unmanned aircraft of high universalizable | |
| US20130256451A1 (en) | Aircraft having at least two aircraft fuselages and a first wing arrangement with at least two wing sections that are not connected to each other | |
| CN205256672U (en) | Manpower drive fixed -wing aircraft | |
| CN105438466B (en) | A kind of manpower driving fixed wing aircraft | |
| US20050045764A1 (en) | Canard position and dihedral for boom reduction and pitch/directional control | |
| CN203294308U (en) | Jet rudder control system and aircraft using control system | |
| US3575363A (en) | Horizontal tail for aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |