CN205633014U - Folding wing vertical take -off and landing aircraft - Google Patents
Folding wing vertical take -off and landing aircraft Download PDFInfo
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- CN205633014U CN205633014U CN201620486533.XU CN201620486533U CN205633014U CN 205633014 U CN205633014 U CN 205633014U CN 201620486533 U CN201620486533 U CN 201620486533U CN 205633014 U CN205633014 U CN 205633014U
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Abstract
The utility model discloses a folding wing vertical take -off and landing aircraft, including fuselage, the folding wing of the folding wing in a left side and the right side, is connected first replicate mechanism and the second mechanism that replicates between the folding wing in a left side and the folding wing in the right side and the fuselage, the mechanism is replicateed to first replicate mechanism and second makes the folding wing in a left side and the right wing of folding transfer to two stations for the fuselage: fuselage, the left folding wing of the wing and the right side of folding are on same water flat line, and perhaps the folding wing of the wing and the right side is folded to the the same of fuselage or not equidirectional certain angle of turning back in a left side. The utility model discloses folding the wing when the VTOL, making aircraft overall structure more compact, the focus is stable, stability when improving the VTOL, expand the wing when air travel, it is the same with traditional fixed -wing aircraft, flight time's resistance reduces to patrol.
Description
Technical field
This utility model relates to aviation aircraft field, particularly relates to a kind of wing folding vertical
Straight landing aircraft.
Background technology
Applicant once proposed a kind of based on round trip flight Ore-controlling Role in patent CN201520326361.5
Fixed structure formula VTOL aircraft, this aircraft uses round trip flight Ore-controlling Role to control, can be at many rotors
Freely change between pattern and fixed-wing pattern: in the takeoff and landing stage, use many rotors mould
Formula realizes VTOL；Mission phase aloft, uses fixed-wing pattern to realize high-performance cruise.
This aircraft has fixed wing airplane and the performance of many gyroplanes and advantage concurrently.
Above-mentioned fixed structure formula VTOL aircraft based on round trip flight Ore-controlling Role, one of its feature is
Can directly use traditional aircaft configuration, it is not necessary to the electromotor change axle construction that configuration is complicated,
Do not interfere with the layout of machine internal load and equipment.But, traditional aircaft configuration is in order to reduce sky
The resistance of middle flight, is designed to greatly streamlined, and the aircraft of such as flying wing structure is exactly at fuselage
Left and right sides arranges a pair huge wing, the open both sides extending in fuselage of wing, the weight of wing
Even with fuselage quite or heavier, the aircraft of this flying wing structure is when carrying out VTOL for amount
Head is perpendicular to ground, the distribution of weight of whole aircraft on fuselage and wing, crank,
The stability problem of VTOL is bigger.
Utility model content
In view of the above problems, this utility model provides a kind of folded wing VTOL aircraft, should
Wing-folding can be got up by aircraft when VTOL, makes overall structure the compactest, improves
The stability of VTOL, and during flight aloft, wing is launched, reduce cruise drag.
For reaching above-mentioned purpose, embodiment of the present utility model adopts the following technical scheme that
A kind of folded wing VTOL aircraft, including fuselage, the left folding wing and the right folding wing,
It is connected between the described left folding wing and the right folding wing and fuselage and has the first turning mechanism and second to turn back
Mechanism, described first turning mechanism and the second turning mechanism can make the described left folding wing and right folding
The wing is transferred to two stations relative to fuselage: at the first station, described fuselage, the left folding wing and
The right folding wing is in the same horizontal line；In the second station, the described left folding wing and right folding flapwise
Turn back certain angle in the identical or different direction of fuselage.
According to an aspect of the present utility model, described aircraft is provided with multiple electromotor, institute
The installation site stating electromotor meets: at the second station, the plurality of electromotor is in vertical direction
On common center of gravity coincide with the center of gravity of airplane.
According to an aspect of the present utility model, described engine bottom is provided with support seat.
According to an aspect of the present utility model, the described left folding wing and the rear fate of the right folding wing
The movable elevon having elevator and aileron function concurrently is not installed.
According to an aspect of the present utility model, the head of described fuselage is provided with detection system.
The advantage that this utility model is implemented:
On the one hand, wing-folding, when VTOL, can be got up by this utility model, makes to fly
Machine overall structure is the compactest, steadily of centre of gravity, improves stability during VTOL；
On the other hand, during this utility model flight aloft, can launch to get up by wing, and
Tradition fixed wing airplane is the same, reduces resistance during cruise.
Accompanying drawing explanation
In order to be illustrated more clearly that the technical scheme in this utility model embodiment, below will be to reality
Execute the required accompanying drawing used in example to be briefly described, it should be apparent that, in describing below
Accompanying drawing is only embodiments more of the present utility model, for those of ordinary skill in the art,
On the premise of not paying creative work, it is also possible to obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is a kind of preferred embodiment of this utility model axonometric chart in VTOL state.
Fig. 2 is a kind of preferred embodiment of this utility model top view in VTOL state.
Fig. 3 is the axonometric chart of this utility model a kind of preferred embodiment cruising condition aloft.
Fig. 4 is the top view of this utility model a kind of preferred embodiment cruising condition aloft.
Description of reference numerals: 1-fuselage；The 2-left folding wing；The 3-right folding wing；4-first turns back
Mechanism；5-the second turning mechanism；6-elevon；7-electromotor；8-supports seat；9-detects
System.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, in this utility model embodiment
Technical scheme be clearly and completely described, it is clear that described embodiment be only this
The a part of embodiment of utility model rather than whole embodiments.Based in this utility model
Embodiment, those of ordinary skill in the art are obtained under not making creative work premise
Every other embodiment, broadly falls into the scope of this utility model protection.
As shown in Figure 1 to 4, aircraft based on flying wing structure in this utility model structure, bag
Include fuselage 1, the left folding wing 2 and the right folding wing 3.The left folding wing 2 is by the first turning mechanism 4
Being connected with fuselage 1, the right folding wing 3 is connected with fuselage 1 by the second turning mechanism 5, left folding
The folded wing 2 and the right folding wing 3 are typically designed as seamlessly transitting, with guarantee with the junction of fuselage 1
Overall streamlined of aircraft.The trailing edge of the left folding wing 2 and the right folding wing 3 is separately installed with movably
Elevon 6, elevon 6 has the function of elevator and aileron concurrently.It is provided with many on aircraft
Individual electromotor 7, is to be provided with four electromotors 7 in the present embodiment, and two of which is arranged on fuselage
On 1, another two is separately mounted on the left folding wing 2 and the right folding wing 3, and four electromotors 7 exist
It is arranged symmetrically with on aircraft.The afterbody of electromotor 7 is provided with support seat 8, supports the work of seat 8
With keeping aircraft steady when being present ground.The head of fuselage 1 is provided with detection system 9, is used for regarding
Frequency gathers.
In the VTOL stage, as depicted in figs. 1 and 2, the first turning mechanism 4 and the second folding
Rotation mechanism 5 makes the left folding wing 2 and the right folding wing 3 turn back certain angle to the equidirectional of fuselage 1
Degree, in the present embodiment, the left folding wing 2 is identical with the angle of turning back of the right folding wing 3, is
90 degree.See the most in vertical direction, although aircaft configuration is not centrosymmetric, but four
The common center of gravity of electromotor 7 overlaps with the center of gravity of aircraft, and aircraft can be made the most vertical
Landing.
Cruising phase aloft, as shown in Figure 3 and Figure 4, the first turning mechanism 4 and the second folding
Rotation mechanism 5 make the left folding wing 2 and the right folding wing 3 turn back to fuselage 1 holding level, now
Aircraft enters cruising phase, aircraft horizontal flight.About VTOL and the aerial flat switching flown
Control, can be found in another part patent CN201510257836.4 of the applicant " based on round trip flight control
The fixed structure formula VTOL aircraft of system and control method thereof ".
Note: first, the installation site of the electromotor shown in the accompanying drawing of above-described embodiment is only
Reference scheme, the restriction of not all to this utility model schemes.Such as the peace of electromotor
For holding position, it is also possible to four electromotors are arranged on the left folding wing and the right folding wing two-by-two,
As long as ensure to turn back, in vertical direction, the common center of gravity of electromotor overlaps with the center of gravity of aircraft i.e.
Can, it is ensured that the stationarity of flight.
Second, turning back of the left folding wing shown in the accompanying drawing of above-described embodiment and the right folding wing
Angle is also only reference scheme, the restriction of not all to this utility model schemes.Such as left folding
The folded wing and the right folding wing can be turned back to the different directions of fuselage, and it is " Z " font that complete machine is bowed when seeing
Type, and the angle that both turn back can differ, as long as ensure to turn back, in vertical direction
The common center of gravity of electromotor overlaps with the center of gravity of aircraft, it is ensured that the stationarity of flight.
The above, detailed description of the invention the most of the present utility model, but guarantor of the present utility model
The scope of protecting is not limited thereto, and any those skilled in the art is at this utility model
In disclosed technical scope, the change that can readily occur in or replacement, all should contain in this practicality new
Within the protection domain of type.Therefore, protection domain of the present utility model should be with described claim
Protection domain be as the criterion.
Claims (5)
1. a folded wing VTOL aircraft, it is characterised in that include fuselage, left folding
The wing and the right folding wing, be connected between the described left folding wing and the right folding wing and fuselage and have first to turn back
Mechanism and the second turning mechanism, described first turning mechanism and the second turning mechanism can make a described left side
Folding wings and the right folding wing are transferred to two stations relative to fuselage: at the first station, described machine
Body, the left folding wing and the right folding wing are in the same horizontal line；In the second station, described left folding
Turn back certain angle in the identical or different direction of the wing and right folding flapwise fuselage.
Folded wing VTOL aircraft the most according to claim 1, it is characterised in that
Being provided with multiple electromotor on described aircraft, the installation site of described electromotor meets: second
Station, the plurality of electromotor common center of gravity in vertical direction coincides with the center of gravity of airplane.
Folded wing VTOL aircraft the most according to claim 2, it is characterised in that
Described engine bottom is provided with support seat.
Folded wing VTOL aircraft the most according to claim 1, it is characterised in that
The trailing edge of the described left folding wing and the right folding wing is separately installed with and has elevator and aileron function concurrently
Movable elevon.
Folded wing VTOL aircraft the most according to claim 1, it is characterised in that
The head of described fuselage is provided with detection system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620486533.XU CN205633014U (en) | 2016-05-25 | 2016-05-25 | Folding wing vertical take -off and landing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620486533.XU CN205633014U (en) | 2016-05-25 | 2016-05-25 | Folding wing vertical take -off and landing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205633014U true CN205633014U (en) | 2016-10-12 |
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ID=57052162
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620486533.XU Active CN205633014U (en) | 2016-05-25 | 2016-05-25 | Folding wing vertical take -off and landing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205633014U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106585951A (en) * | 2016-12-09 | 2017-04-26 | 上海圣尧智能科技有限公司 | Folding structure and aircraft |
| CN106927022A (en) * | 2017-03-23 | 2017-07-07 | 清华大学 | Based on the super high-aspect-ratio aircraft for self-deploying folding wings technology |
| CN107176286A (en) * | 2017-05-16 | 2017-09-19 | 华南理工大学 | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems |
| CN108045554A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of turbofan twin vertical fin early warning plane |
| WO2018163159A1 (en) * | 2017-03-07 | 2018-09-13 | Colugo Systems Ltd | Folded wing multi rotor |
| WO2018171089A1 (en) * | 2017-03-23 | 2018-09-27 | 清华大学 | Aircraft with super high aspect ratio based on self-unfolding folding wing technology |
| WO2018236295A1 (en) * | 2017-06-21 | 2018-12-27 | Ali Turan | Easing the horizontal movement of drones |
| CN110466753A (en) * | 2019-09-09 | 2019-11-19 | 西安交通大学 | A kind of VTOL fixed-wing unmanned plane that can rapid disassembling folding and case |
-
2016
- 2016-05-25 CN CN201620486533.XU patent/CN205633014U/en active Active
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106585951A (en) * | 2016-12-09 | 2017-04-26 | 上海圣尧智能科技有限公司 | Folding structure and aircraft |
| WO2018163159A1 (en) * | 2017-03-07 | 2018-09-13 | Colugo Systems Ltd | Folded wing multi rotor |
| CN106927022A (en) * | 2017-03-23 | 2017-07-07 | 清华大学 | Based on the super high-aspect-ratio aircraft for self-deploying folding wings technology |
| WO2018171089A1 (en) * | 2017-03-23 | 2018-09-27 | 清华大学 | Aircraft with super high aspect ratio based on self-unfolding folding wing technology |
| EP3604122A4 (en) * | 2017-03-23 | 2021-01-13 | Tsinghua University | Aircraft with super high aspect ratio based on self-unfolding folding wing technology |
| CN106927022B (en) * | 2017-03-23 | 2023-08-15 | 清华大学 | Super-large aspect ratio aircraft based on self-unfolding folding wing technology |
| CN107176286A (en) * | 2017-05-16 | 2017-09-19 | 华南理工大学 | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems |
| CN107176286B (en) * | 2017-05-16 | 2023-08-22 | 华南理工大学 | Double-duct fan power system-based foldable fixed wing vertical take-off and landing unmanned aerial vehicle |
| WO2018236295A1 (en) * | 2017-06-21 | 2018-12-27 | Ali Turan | Easing the horizontal movement of drones |
| CN108045554A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of turbofan twin vertical fin early warning plane |
| CN110466753A (en) * | 2019-09-09 | 2019-11-19 | 西安交通大学 | A kind of VTOL fixed-wing unmanned plane that can rapid disassembling folding and case |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 214000 Room 411, building A1, 999 Gao Lang Dong Road, Binhu District, Wuxi, Jiangsu. Patentee after: Jiangsu digital Eagle Polytron Technologies Inc Address before: 214000 Room 411, building A1, 999 Gao Lang Dong Road, Binhu District, Wuxi, Jiangsu. Patentee before: Jiangsu numeral Accipitridae skill Development Co., Ltd |
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| CP01 | Change in the name or title of a patent holder |