CN106005395B - The inclining rotary mechanism of wing can be hidden in - Google Patents
The inclining rotary mechanism of wing can be hidden in Download PDFInfo
- Publication number
- CN106005395B CN106005395B CN201610550104.9A CN201610550104A CN106005395B CN 106005395 B CN106005395 B CN 106005395B CN 201610550104 A CN201610550104 A CN 201610550104A CN 106005395 B CN106005395 B CN 106005395B
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- wing
- seat
- inclining rotary
- paddle
- rotary mechanism
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
A kind of inclining rotary mechanism for being hidden in wing, the inclining rotary mechanism is arranged on wing, the recycling space of inclining rotary mechanism can be accommodated there are one being reserved in the wing, the inclining rotary mechanism includes steering engine, the seat that verts, motor and folds paddle, motor and folding paddle are fixed on and vert on seat, are connected between the steering engine and the seat that verts by link mechanism.The mechanism can be used as the rotor inclining rotary mechanism of unmanned tilt rotor aircraft, and aircraft can be made to stablize the conversion realized between more rotors and fixed-wing, resistance when flying before reducing, and improve the efficiency of propulsion.
Description
Technical field
The present invention relates to tilt rotor aircraft technical fields, in particular relate to a kind of inclining rotary mechanism for being hidden in wing.
Background technology
Tilt rotor aircraft is a kind of aircraft of unique properties, it can be hovered, vertically as the more gyroplanes of tradition
Landing, can also as propeller fixed wing aircraft high speed cruise flight.The aircraft has VTOL, hovering, low latitude
The ability of flight, high-performance cruise and voyage farther out, can quickly go up to the air in more complicated landform, environment, complete compared with long distance
From aerial mission, specific function can be played in battle reconnaissance and rescue and relief work, had broad application prospects.
For current most of tilt rotor aircrafts during verting, the blade of high-speed rotation will equal winged difference with aircraft
Larger component is generated on direction, causes aspect unstable.And much tilt rotor aircrafts are in flat winged state, the electricity of tail portion
Machine is stalled and is not verted, and is thus generated larger air drag in flat fly, is influenced air mileage and flying speed.
Invention content
The present invention provides a kind of inclining rotary mechanism for being hidden in wing.The mechanism can be as unmanned tilt rotor aircraft
Rotor inclining rotary mechanism uses, and aircraft can be made to stablize the conversion realized between more rotors and fixed-wing, when flying before reducing
Resistance improves the efficiency of propulsion.
The technical scheme is that：
A kind of inclining rotary mechanism for being hidden in wing, the inclining rotary mechanism are arranged on wing, are reserved in the wing
One recycling space that can accommodate inclining rotary mechanism, the inclining rotary mechanism include steering engine, the seat that verts, motor and fold paddle, electricity
Machine and folding paddle are fixed on and vert on seat, are connected between the steering engine and the seat that verts by link mechanism；
When motor driving folds paddle rotation, steering engine can drive link mechanism and then drive vert seat so that vert seat around
Rotary shaft rotation on wing, motor and folding paddle vert therewith, realize the control of tilt angle；
When folding paddle and collapsing, steering engine can drive link mechanism and then drive vert seat, make inclining rotary mechanism whole in connecting rod
The drive of mechanism, which has a down dip, to be turned to be recycled to recycling space in wing.
Further, it is a feature of the present invention that the motor is fixedly mounted on the bottom for the seat that verts, paddle installation is folded
On motor shaft, motor shaft directly drives folding paddle.
Further, it is a feature of the present invention that the link mechanism includes connecting rod and distant arm, the output terminal of steering engine connects
Rocking arm, rocking arm connection connecting rod, connecting rod connect the seat that verts, and after steering engine receives control signal, the rotation of servos control rocking arm passes through company
Bar pulls the seat that verts to be rotated around rotary shaft, and motor and folding paddle vert therewith.
Further, it is a feature of the present invention that the outer wall that verts be designed as it is streamlined.
Further, it is a feature of the present invention that inclining rotary mechanism is recycled to after recycling space, verts outside an outer wall and wing
Shell matches.
The inclining rotary mechanism for being hidden in wing based on above-mentioned offer, the present invention also provides be equipped with this to be hidden in wing
Inclining rotary mechanism aircraft, specially a kind of thrust type tilt rotor aircraft, including fuselage, wing, tail-rotor system, undercarriage with
And dynamical system, an inclining rotary mechanism that can be hidden in wing, and the machine are separately installed on the wing of the fuselage both sides
The recycling space of the inclining rotary mechanism can be accommodated there are one being reserved respectively in the wing of body both sides.
Further, two inclining rotary mechanisms that can be hidden in wing line centered on fuselage axis is left and right symmetrically arranged in machine
On the wing of body both sides.
Further, there are two types of working conditions, respectively rotor state and fixed wing for the inclining rotary mechanism tool on the aircraft
State；
During rotor state, the motor driving of each inclining rotary mechanism folds paddle rotation and generates downdraught formation lift, and steering engine leads to
It crosses link mechanism and rotates the seat that verts so that rotary shaft rotation of the seat on wing of verting, motor and folding paddle vert therewith, real
The control of existing tilt angle；Aircraft is controlled by controlling the tilt angle of each motor speed for folding paddle and each inclining rotary mechanism
Posture；
During fixed-wing state, fold paddle contraction and fold, the steering engine in inclining rotary mechanism drives the seat that verts by link mechanism, makes
Whole drives in link mechanism of inclining rotary mechanism has a down dip the recycling space turn being recycled in wing.
The method have the benefit that：
The inclining rotary mechanism of the present invention can be used as the rotor inclining rotary mechanism of unmanned tilt rotor aircraft, can make to fly
Machine stablizes the conversion realized between more rotors and fixed-wing, resistance when flying before reducing, and improves the efficiency of propulsion.
This tilt rotor aircraft of the present invention is successfully realized VTOL, the conversion of rotor and fixed-wing, and have
Good stability, faster flying speed and voyage farther out.
Description of the drawings
Fig. 1 is the structure diagram one (rotor state) of inclining rotary mechanism of the present invention.
Fig. 2 is the structure diagram two (fixed-wing state) of inclining rotary mechanism of the present invention.
Fig. 3 is the structure diagram of thrust type tilt rotor aircraft of the present invention.
In figure：
1st, wing；2nd, space is recycled；3rd, steering engine；4th, vert seat；5th, motor；6th, paddle is folded；7th, connecting rod；8th, rocking arm；9th, machine
Body；10th, wing；11st, tail-rotor system；12nd, undercarriage；13rd, dynamical system
Specific embodiment
In order to which technical problem solved by the invention, technical solution and advantageous effect is more clearly understood, below in conjunction with
Accompanying drawings and embodiments, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein only to
It explains the present invention, is not intended to limit the present invention.
As shown in Figure 1 to Figure 2, a kind of inclining rotary mechanism for being hidden in wing, the inclining rotary mechanism are arranged on wing 1,
The recycling space 2 of inclining rotary mechanism can be accommodated there are one being reserved in the wing 1, the inclining rotary mechanism is including steering engine 3, vert seat
4th, motor 5 and folding paddle 6, the motor 5 are fixedly mounted on the bottom for the seat 4 that verts, and are folded paddle 6 and are mounted on motor shaft,
Motor shaft, which directly drives, folds paddle 6.It is connected between the steering engine 3 and the seat 4 that verts by link mechanism.The link mechanism includes
Connecting rod 7 and distant arm 8, the output terminal connecting rocker arm 8 of steering engine 3, rocking arm 8 connect connecting rod 7, and connecting rod 7 connects the seat 4 that verts.When steering engine 3 is received
To after control signal, steering engine 3 controls rocking arm 8 to rotate, and the seat 4 that verts is pulled to be rotated around rotary shaft by connecting rod 7, motor 5 and folding
Paddle 6 verts therewith, realizes the control of tilt angle.The movement of inclining rotary mechanism causes aspect to change.
During fixed-wing state, fold paddle and collapse, steering engine 3 can drive link mechanism and then drive vert seat 4, make the machine that verts
Whole drives in link mechanism of structure has a down dip the recycling space 2 turn being recycled in wing.The outer wall that verts is designed as streamline
Type, after inclining rotary mechanism is recycled to recycling space, the outer wall that verts is matched with wing shell, is significantly reduced resistance during flight.
The inclining rotary mechanism for being hidden in wing based on above-mentioned offer, the present invention also provides be equipped with this to be hidden in wing
Inclining rotary mechanism aircraft, specially a kind of thrust type tilt rotor aircraft, including fuselage 9, wing 10, tail-rotor system 11, rise
Frame 12 and dynamical system 13 are fallen, verting for wing can be hidden in by being separately installed with one on the wing 10 of 9 both sides of fuselage
Mechanism, two inclining rotary mechanisms that can be hidden in wing line centered on fuselage axis are left and right symmetrically arranged the machine in 9 both sides of fuselage
On the wing 10.And the recycling space 2 of the inclining rotary mechanism can be accommodated there are one being reserved respectively in the wing 10 of 9 both sides of fuselage.
There are two types of working conditions, respectively rotor state and fixed-wing state for inclining rotary mechanism tool on the aircraft；
During rotor state, the motor driving of each inclining rotary mechanism folds paddle rotation and generates downdraught formation lift, and steering engine leads to
It crosses link mechanism and rotates the seat that verts so that rotary shaft rotation of the seat on wing of verting, motor and folding paddle vert therewith, real
The control of existing tilt angle；Aircraft is controlled by controlling the tilt angle of each motor speed for folding paddle and each inclining rotary mechanism
Posture；
During fixed-wing state, fold paddle contraction and fold, the steering engine in inclining rotary mechanism drives the seat that verts by link mechanism, makes
Whole drives in link mechanism of inclining rotary mechanism has a down dip the recycling space turn being recycled in wing.
The above is only the preferred embodiment of the present invention, and protection scope of the present invention is not limited merely to above-mentioned implementation
Example, all technical solutions belonged under thinking of the present invention all belong to the scope of protection of the present invention.It should propose, for the art
Those of ordinary skill for, improvements and modifications without departing from the principles of the present invention, these improvements and modifications should also regard
For protection scope of the present invention.
Claims (7)
1. a kind of inclining rotary mechanism for being hidden in wing, which is characterized in that the inclining rotary mechanism is arranged on wing, the wing
Interior reserved there are one the recycling space that can accommodate inclining rotary mechanism, the inclining rotary mechanism includes steering engine, the seat that verts, motor and folding
Folded paddle, motor and folding paddle are fixed on and vert on seat, and the motor is fixedly mounted on the bottom for the seat that verts, and fold paddle installation
On motor shaft, motor shaft directly drives folding paddle；It is connected between the steering engine and the seat that verts by link mechanism；
When motor driving folds paddle rotation, steering engine can drive link mechanism and then drive vert seat so that the seat that verts is around wing
On a rotary shaft rotation, motor and fold paddle vert therewith, realize the control of tilt angle；
When folding paddle and collapsing, steering engine can drive link mechanism and then drive vert seat, make inclining rotary mechanism whole in link mechanism
Drive have a down dip and turn to be recycled to recycling space in wing.
2. the inclining rotary mechanism according to claim 1 for being hidden in wing, which is characterized in that the link mechanism includes connecting
Bar and rocking arm, the output terminal connecting rocker arm of steering engine, rocking arm connection connecting rod, connecting rod connects the seat that verts, when steering engine receives control signal
Afterwards, servos control rocking arm rotates, and the seat that verts is pulled to be rotated around rotary shaft by connecting rod, and motor and folding paddle vert therewith.
3. the inclining rotary mechanism according to claim 2 for being hidden in wing, which is characterized in that an outer wall design of verting
It is streamlined.
4. according to the inclining rotary mechanism for being hidden in wing described in claim 1,2 or 3, which is characterized in that inclining rotary mechanism recycles
To recycling space, the outer wall that verts is matched with wing shell.
5. a kind of thrust type tilt rotor aircraft, including fuselage, wing, tail-rotor system, undercarriage and dynamical system, feature
It is, an inclining rotary mechanism that can be hidden in wing, and the fuselage both sides is separately installed on the wing of the fuselage both sides
Wing in reserved respectively there are one the recycling space of the inclining rotary mechanism can be accommodated, the inclining rotary mechanism includes steering engine, verts
Seat, motor and folding paddle, motor and folding paddle are fixed on and vert on seat, and the motor is fixedly mounted on the bottom for the seat that verts
On, it folds paddle and is mounted on motor shaft, motor shaft directly drives folding paddle；Pass through link mechanism between the steering engine and the seat that verts
Connection；
When motor driving folds paddle rotation, steering engine can drive link mechanism and then drive vert seat so that the seat that verts is around wing
On a rotary shaft rotation, motor and fold paddle vert therewith, realize the control of tilt angle；
When folding paddle and collapsing, steering engine can drive link mechanism and then drive vert seat, make inclining rotary mechanism whole in link mechanism
Drive have a down dip and turn to be recycled to recycling space in wing.
6. thrust type tilt rotor aircraft according to claim 5, it is characterised in that：Two can be hidden in verting for wing
Mechanism line centered on fuselage axis is left and right symmetrically arranged on the wing of fuselage both sides.
7. thrust type tilt rotor aircraft according to claim 6, it is characterised in that：Inclining rotary mechanism on the aircraft has
Two kinds of working conditions, respectively rotor state and fixed-wing state；
During rotor state, the motor driving of each inclining rotary mechanism folds paddle rotation and generates downdraught formation lift, and steering engine passes through company
Linkage rotates the seat that verts so that rotary shaft rotation of the seat on wing of verting, motor and folding paddle vert therewith, and realization is inclined
The control of gyration；The appearance of aircraft is controlled by controlling the tilt angle of each motor speed for folding paddle and each inclining rotary mechanism
State；
During fixed-wing state, fold paddle contraction and fold, the steering engine in inclining rotary mechanism drives the seat that verts by link mechanism, makes to vert
Whole drives in link mechanism of mechanism has a down dip the recycling space turn being recycled in wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610550104.9A CN106005395B (en) | 2016-07-13 | 2016-07-13 | The inclining rotary mechanism of wing can be hidden in |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610550104.9A CN106005395B (en) | 2016-07-13 | 2016-07-13 | The inclining rotary mechanism of wing can be hidden in |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106005395A CN106005395A (en) | 2016-10-12 |
| CN106005395B true CN106005395B (en) | 2018-07-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610550104.9A Active CN106005395B (en) | 2016-07-13 | 2016-07-13 | The inclining rotary mechanism of wing can be hidden in |
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| CN (1) | CN106005395B (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106986019B (en) * | 2017-04-17 | 2023-05-30 | 四川建筑职业技术学院 | Motor cabinet capable of changing inclination angle of rotary wing surface of multi-rotor unmanned aerial vehicle |
| CN107719659A (en) * | 2017-08-28 | 2018-02-23 | 南京达索航空科技有限公司 | A kind of VTOL fixed-wing formula aircraft |
| CN108298071A (en) * | 2018-03-14 | 2018-07-20 | 长沙市云智航科技有限公司 | A kind of more rotor flying vehicles of manned duct |
| CN108423171A (en) * | 2018-03-30 | 2018-08-21 | 天长航空技术有限公司 | Without rudder face VTOL fixed-wing unmanned plane |
| CN108750081A (en) * | 2018-06-05 | 2018-11-06 | 中国人民解放军国防科技大学 | Tilting four-rotor-wing deformable aircraft |
| CN110356550B (en) * | 2018-11-27 | 2021-08-10 | 北京京东乾石科技有限公司 | Rotor wing tilting mechanism and aircraft |
| CN109573013A (en) * | 2019-01-24 | 2019-04-05 | 猎鸢科技(厦门)有限公司 | A kind of unmanned plane and its flying method based on multi-composite type dynamical system |
| CN111516903B (en) * | 2020-05-15 | 2023-05-12 | 蜂巢航宇科技（北京）有限公司 | Tilting rotor unmanned aerial vehicle test bench |
| CN113320694B (en) * | 2021-07-13 | 2023-08-18 | 广东汇天航空航天科技有限公司 | Tilt rotor mechanism and aircraft with same |
| CN113306710B (en) * | 2021-07-28 | 2021-11-12 | 西安羚控电子科技有限公司 | Tube type launching composite wing unmanned aerial vehicle and method for realizing roll action |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2678785A (en) * | 1952-04-17 | 1954-05-18 | Northrop Aircraft Inc | Rotating blade speed brake |
| US3592412A (en) * | 1969-10-03 | 1971-07-13 | Boeing Co | Convertible aircraft |
| US3693910A (en) * | 1970-12-14 | 1972-09-26 | Angelo J Aldi | Aircraft rotor blade mechanism |
| CN101314409A (en) * | 2008-07-10 | 2008-12-03 | 周武双 | Swallow type inclined rotation rotorcraft |
| CN102126553A (en) * | 2010-01-12 | 2011-07-20 | 北京航空航天大学 | Vertically taking off and landing small unmanned aerial vehicle |
| CN102905972A (en) * | 2010-06-15 | 2013-01-30 | 贝尔直升机泰克斯特龙公司 | Method and apparatus for in-flight blade folding |
| CN205837191U (en) * | 2016-07-13 | 2016-12-28 | 中国人民解放军国防科学技术大学 | The inclining rotary mechanism of wing can be hidden in |
-
2016
- 2016-07-13 CN CN201610550104.9A patent/CN106005395B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2678785A (en) * | 1952-04-17 | 1954-05-18 | Northrop Aircraft Inc | Rotating blade speed brake |
| US3592412A (en) * | 1969-10-03 | 1971-07-13 | Boeing Co | Convertible aircraft |
| US3693910A (en) * | 1970-12-14 | 1972-09-26 | Angelo J Aldi | Aircraft rotor blade mechanism |
| CN101314409A (en) * | 2008-07-10 | 2008-12-03 | 周武双 | Swallow type inclined rotation rotorcraft |
| CN102126553A (en) * | 2010-01-12 | 2011-07-20 | 北京航空航天大学 | Vertically taking off and landing small unmanned aerial vehicle |
| CN102905972A (en) * | 2010-06-15 | 2013-01-30 | 贝尔直升机泰克斯特龙公司 | Method and apparatus for in-flight blade folding |
| CN205837191U (en) * | 2016-07-13 | 2016-12-28 | 中国人民解放军国防科学技术大学 | The inclining rotary mechanism of wing can be hidden in |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106005395A (en) | 2016-10-12 |
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