CN109606629A - Aircraft - Google Patents
Aircraft Download PDFInfo
- Publication number
- CN109606629A CN109606629A CN201811336203.2A CN201811336203A CN109606629A CN 109606629 A CN109606629 A CN 109606629A CN 201811336203 A CN201811336203 A CN 201811336203A CN 109606629 A CN109606629 A CN 109606629A
- Authority
- CN
- China
- Prior art keywords
- hinge
- fuselage
- fixed
- main plane
- wing
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/40—Varying angle of sweep
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/08—Aircraft not otherwise provided for having multiple wings
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of aircraft.The aircraft includes: fuselage, wing, and wing includes the main plane and a pair of preceding secondary aerofoil slightly of a pair of of sweepback；Main plane is connected with time aerofoil by joining wing hinge；Main plane is connect with fuselage by preceding hinge；It include sliding block and slide-driving device on fuselage, control sliding driving device driving sliding block moves forward and backward；Secondary aerofoil is connect with sliding block by rear hinge；Sliding block by sliding driving device driving can sliding back and forth along fuselage, to change the angle between main plane and secondary aerofoil and fuselage.The present invention has the transformable function of angle between wing and fuselage, have when obtain the technical effect that optimum pneumatic rises resistance efficiency.
Description
Technical field
The present invention relates to technical field of aerospace, more particularly, to a kind of aircraft.
Background technique
Angle between the wing and fuselage of conventional aircraft immobilizes.Such as the aircraft of low-speed operations, in order to obtain
Bigger lift, and the form for using wing vertical with fuselage；Such as the aircraft of high-speed flight, in order to reduce the resistance of wing,
And use the form of smaller angle between wing and fuselage；But in entire flight course, speed does not immobilize aircraft
, the changeless flight of angle in entire speed interval, under specific speed only therein, between wing and fuselage
Device could obtain good pneumatic liter resistance efficiency.
Through applicants have found that: extremely complex deformation device is mounted on wing and machine by certain fighter planes or bomber
Body connecting portion drives the angle of wing and fuselage to change by it.There are deformation device installation spaces for this aircraft
The problems such as narrow, deformation device complexity is high, loaded serious.
Summary of the invention
In consideration of it, at least one problem in solve the above-mentioned problems, the present invention provide a kind of aircraft.
A kind of aircraft, comprising:
Fuselage, wing,
Wing includes the main plane and a pair of preceding secondary aerofoil slightly of a pair of of sweepback；
Main plane is connected with time aerofoil by joining wing hinge；
Main plane is connect with fuselage by preceding hinge；
On fuselage include sliding block and slide-driving device,
Control sliding driving device driving sliding block moves forward and backward；
Secondary aerofoil is connect with sliding block by rear hinge,
Sliding block by sliding driving device driving can sliding back and forth along fuselage, to change main plane and secondary aerofoil and fuselage
Between angle.
Thus following technical effect may be implemented in the embodiment of the present invention:
1) present invention realizes wing setting continuous variable.
2) present invention drives sliding block to move forward and backward by sliding driving device, to realize the angle between wing and fuselage
Variation, drive form are simple, reliable.
3) sliding driving device of the invention is mounted on fuselage, and the space of installation is open, is avoided and is connected in Wing-Body Configurations
The small space limitation of place's installation driving device is connect, installation, the maintenance of whole device are more convenient.
4) the box-like layout airfoil formula for the variable sweepback that the present invention uses, wing setting, which not only may be implemented, can be changed,
Bigger lift can also be provided compared to traditional monolithic wing.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, will make below to required in the embodiment of the present invention
Attached drawing is briefly described, it is therefore apparent that drawings described below is only some embodiments of the present invention, for this
For the technical staff in field, without creative efforts, it can also be obtained according to these attached drawings other attached
Figure.
The schematic diagram of aircraft when Fig. 1 is the wing and fuselage angle maximum of one embodiment of the invention；
The schematic diagram of aircraft when Fig. 2 is the wing and fuselage angle minimum of one embodiment of the invention；
Fig. 3 is the main plane of one embodiment of the invention and the connection schematic diagram of time aerofoil；
Fig. 4 is the main plane of one embodiment of the invention and the connection schematic diagram of time aerofoil；
Fig. 5 is the main plane of one embodiment of the invention and the connection schematic diagram of fuselage；
Fig. 6 is the secondary aerofoil of one embodiment of the invention and the connection schematic diagram of fuselage.
Wherein, 1- fuselage, 2- wing, 4- main plane, 5- aerofoil, 8- sliding block, 10- slide-driving device, 601- first
Hinge sleeve, 602- first fixed bulb, the first fixing axle of 603-, 601 '-second hinge sets, 602 '-the second fixed bulbs,
Hinge fixing axle, 101- card slot, 901- before 603 '-the second fixing axles, 701- axle sleeve, 702- upper stopper, 703- lower stopper, 704-
Hinge fixing axle after hinge lower stopper, 904- after hinge upper stopper, 903- after hinge shaft sleeve, 902- afterwards.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described.Obviously, described embodiment is
A part of the embodiment of the present invention, rather than whole embodiments.Based on the embodiments of the present invention, those skilled in the art
Without making creative work, every other embodiment obtained, shall fall within the protection scope of the present invention.
The feature and illustrative examples of various aspects of the invention is described more fully below.In following detailed description
In, many details are proposed, in order to provide complete understanding of the present invention.But come for those skilled in the art
It says it will be apparent that the present invention can be implemented in the case where not needing some details in these details.Below to reality
The description of example is applied just for the sake of providing and better understanding to of the invention by showing example of the invention.The present invention is never
It is limited to any specific setting and method set forth below, but covering finishes under the premise of without departing from the spirit of the present invention
Structure, method, any improvement of device, substitutions and modifications.In the the accompanying drawings and the following description, well known structure and skill is not shown
Art is unnecessary fuzzy to avoid causing to the present invention.
It should be noted that in the absence of conflict, the feature in the embodiment of the present invention and embodiment can be tied mutually
It closes, each embodiment mutually can be referred to and be quoted.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is one embodiment of invention, the schematic diagram of wing 2 and aircraft when 1 angle maximum of fuselage.
As shown in Figure 1, main plane 4 is vertical with fuselage 1, in aircraft low speed, the wing 2 of this configuration can be flight
Device provides bigger aerodynamic lift, is suitable for aircraft and flies at low speed.
The schematic diagram of aircraft when Fig. 2 is wing 2 and 1 angle minimum of fuselage.
As shown in Fig. 2, 20 degree of main plane 4 and 1 angle of fuselage, in aircraft high-speed flight, the wing 2 of this configuration can
To reduce the aerodynamic drag that aircraft is subject to, it is suitable for aircraft high-speed flight.
Fig. 3 is the connection schematic diagram of main plane 4 and time aerofoil 5.
As shown in figure 3, main plane 4 and time aerofoil 5 are connected by connection wing hinge 6, join wing hinge 6 by being fixed on main plane 4
On the fixed bulb 602 of the first fixing axle 603, first and the first axle set 601 that is fixed on time aerofoil 5 constitute, the first hinge
Chain case 601 can make circular-rotation around the first fixing axle 603 and make the spheric pendulum of a small range around the first fixed bulb 602
It is dynamic.
Fig. 4 is the connection schematic diagram of main plane 4 and time aerofoil 5.
As shown in figure 4, main plane 4 and time aerofoil 5 are connected by connection wing hinge 6, connection wing hinge 6 is by being fixed on time aerofoil 5
On the second fixing axle 603 ', the second fixed bulb 602 ' and 5 hinge sleeve 601 ' of secondary aerofoil composition being fixed on main plane 4,
Second hinge set 601 ' can make circular-rotation around the second fixing axle 603 ' and make a small range around the second fixed bulb 602 '
Spherical surface swing.
Fig. 5 is the connection schematic diagram of main plane 4 and fuselage 1.
As shown in figure 5, main plane 4 is connect with fuselage 1 by preceding hinge 7, preceding hinge 7 includes: before fixing on the fuselage 1
Hinge fixing axle 704, upper stopper 702, lower stopper 703 and the axle sleeve 701 being fixed on main plane 4, axle sleeve 701 can surround preceding hinge
Chain fixing axle 704 makees circular-rotation.
Fig. 6 is the connection schematic diagram of time aerofoil 5 and fuselage 1.
As shown in fig. 6, secondary aerofoil 5 is connect with sliding block 8 by rear hinge 9, rear hinge 9 includes: after being fixed on sliding block 8
Hinge fixing axle 904, rear hinge upper stopper 902, rear hinge lower stopper 903 and the rear hinge shaft sleeve being fixed on time aerofoil 5
901, rear hinge shaft sleeve 901 can make circular-rotation around rear hinge fixing axle 904；Sliding block 8 and slide-driving device 10, sliding block two
Side protrusion is nested in the card slot 101 fixed with fuselage, and sliding driving device 10 drives sliding block 8 along the centerline direction of fuselage 1
It moves forward and backward.
Finally it should be noted that: the above embodiments are merely illustrative of the technical solutions of the present invention, but protection of the invention
Range is not limited thereto, and anyone skilled in the art in the technical scope disclosed by the present invention, can be thought easily
It is modified or replaceed to various equivalent, these, which are modified or replaceed, should all be included within the scope of the present invention.
Claims (10)
1. a kind of aircraft characterized by comprising
Fuselage (1), wing (2),
Wing (2) includes the main plane (4) and a pair of preceding secondary aerofoil (5) slightly of a pair of of sweepback,
Main plane (4) and time aerofoil (5) pass through connection wing hinge (6) connection；
Main plane (4) is connect with fuselage (1) by preceding hinge (7)；
On fuselage (1) include sliding block (8) and slide-driving device (10),
Control sliding driving device (10) driving sliding block (8) moves forward and backward；
Secondary aerofoil (5) is connect with sliding block (8) by rear hinge (9),
Sliding block (8) by sliding driving device (10) driving can sliding back and forth along fuselage (2), to change main plane (4) and secondary
Angle between aerofoil (5) and fuselage (2).
2. aircraft according to claim 1, which is characterized in that wherein:
The wing hinge (6) includes: the first fixing axle (603) being fixed on main plane (4), first fixed bulb (602),
With
The first axle set (601) being fixed on time aerofoil (5).
3. aircraft according to claim 2, which is characterized in that wherein:
First axle set (601) can make circular-rotation around the first fixing axle (603) and make around first fixed bulb (602) small
Spherical surface in range is swung.
4. aircraft according to claim 1, which is characterized in that wherein:
The wing hinge (6) includes: the second fixing axle (603 ') being fixed on time aerofoil (5), the second fixed bulb
(602 '), and
The second hinge set (601 ') being fixed on main plane (4).
5. aircraft according to claim 4, which is characterized in that wherein:
Second hinge set (601 ') can make circular-rotation around the second fixing axle (603 ') and around second fixed bulb (602 ')
The spherical surface for making a small range is swung.
6. aircraft according to claim 1, which is characterized in that wherein:
Preceding hinge (7) includes: the preceding hinge fixing axle (704) being fixed on fuselage (1), upper stopper (702), lower stopper (703),
With the axle sleeve (701) being fixed on main plane (4).
7. aircraft according to claim 6, which is characterized in that wherein:
Axle sleeve (701) can make circular-rotation around preceding hinge fixing axle (704).
8. aircraft according to claim 1, which is characterized in that wherein:
Hinge (9) includes: the rear hinge fixing axle (904) being fixed on sliding block (8), rear hinge upper stopper (902), rear hinge afterwards
Lower stopper (903), and the rear hinge shaft sleeve (901) being fixed on time aerofoil (5).
9. aircraft according to claim 8, which is characterized in that wherein:
Hinge shaft sleeve (901) can make circular-rotation around rear hinge fixing axle (904) afterwards.
10. aircraft described in any one in -9 according to claim 1, which is characterized in that wherein:
The two sides protrusion of sliding block (8) is nested in the card slot (101) fixed with fuselage, and sliding driving device (10) drives sliding block
(8) centerline direction along fuselage (1) moves forward and backward.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811336203.2A CN109606629A (en) | 2018-11-07 | 2018-11-07 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811336203.2A CN109606629A (en) | 2018-11-07 | 2018-11-07 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109606629A true CN109606629A (en) | 2019-04-12 |
Family
ID=66004110
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811336203.2A Pending CN109606629A (en) | 2018-11-07 | 2018-11-07 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109606629A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113899517A (en) * | 2021-12-06 | 2022-01-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Deformation test method for missile wing of hypersonic wind tunnel model |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6056237A (en) * | 1997-06-25 | 2000-05-02 | Woodland; Richard L. K. | Sonotube compatible unmanned aerial vehicle and system |
| CN104176237A (en) * | 2014-07-25 | 2014-12-03 | 哈尔滨工业大学深圳研究生院 | Deformable wing device and airplane applying same |
| CN104802979A (en) * | 2015-05-08 | 2015-07-29 | 重庆大学 | Multi-connecting-rod auxiliary folding mechanism with fixed sub-angle for shipborne helicopter |
| CN105818962A (en) * | 2016-06-01 | 2016-08-03 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Foldable wing extensible in wingspan |
| CN108202861A (en) * | 2016-12-16 | 2018-06-26 | 中国航天科工飞航技术研究院 | A kind of fold mechanism and its control method for aircraft |
-
2018
- 2018-11-07 CN CN201811336203.2A patent/CN109606629A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6056237A (en) * | 1997-06-25 | 2000-05-02 | Woodland; Richard L. K. | Sonotube compatible unmanned aerial vehicle and system |
| CN104176237A (en) * | 2014-07-25 | 2014-12-03 | 哈尔滨工业大学深圳研究生院 | Deformable wing device and airplane applying same |
| CN104802979A (en) * | 2015-05-08 | 2015-07-29 | 重庆大学 | Multi-connecting-rod auxiliary folding mechanism with fixed sub-angle for shipborne helicopter |
| CN105818962A (en) * | 2016-06-01 | 2016-08-03 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Foldable wing extensible in wingspan |
| CN108202861A (en) * | 2016-12-16 | 2018-06-26 | 中国航天科工飞航技术研究院 | A kind of fold mechanism and its control method for aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 大辞海编辑委员会: "《大辞海》", 31 December 2007 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113899517A (en) * | 2021-12-06 | 2022-01-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Deformation test method for missile wing of hypersonic wind tunnel model |
| CN113899517B (en) * | 2021-12-06 | 2022-02-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Deformation test method for missile wing of hypersonic wind tunnel model |
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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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190412 |
|
| RJ01 | Rejection of invention patent application after publication |