CN106628168A - Novel tilt rotor aircraft - Google Patents
Novel tilt rotor aircraft Download PDFInfo
- Publication number
- CN106628168A CN106628168A CN201611075940.2A CN201611075940A CN106628168A CN 106628168 A CN106628168 A CN 106628168A CN 201611075940 A CN201611075940 A CN 201611075940A CN 106628168 A CN106628168 A CN 106628168A
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- Prior art keywords
- wing
- aircraft
- rotor
- motor
- nacelle
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a novel tilt rotor aircraft, which consists of an aircraft body, airfoils, a horizontal fin, a vertical fin, ailerons, an elevating rudder, a yaw rudder, a motor, rotor wings, a tilting mechanism, a landing gear, a power supply system and an operating system. The tilt rotor aircraft can realize tilting on the whole airfoils by using servo motors and lead screws; the horizontal fin adopts the same structure form and the same tilting mode as the airfoils; in addition, through control program, the fins and the airfoils can simultaneously tilt; a nacelle is arranged in each of the airfoils and the horizontal fin, and is used for installing a driving motor. The design scheme has the advantages that the aircraft can switch the flight mode between the rotor flight mode and the fixed wing flight mode, so that the vertical take-off and landing and hovering capabilities of a helicopter are realized; the fast cruising capability of a fixed wing propeller-driven aircraft is also realized. The novel tilt rotor aircraft using the design can realize take-off and landing in a narrow and small place and can fast fly to reach the flight destination, so that the novel tilt rotor aircraft using the design has very wide application prospects.
Description
Technical field
The present invention relates to a kind of aircraft with slant rotor, particularly a kind of wing of a large amount of use carbon fibre composites
And the VTOL aircraft that empennage can vert.
Background technology
Due to tilt rotor aircraft can VTOL, hovering as helicopter, again can be as fixed-wing screw
The equally quick cruising flight of aircraft, with efficiency high, speed is fast, voyage is remote the characteristics of.Therefore tiltrotor flies have extensive
With prospect, many countries, enterprise, individual are developing various types of tiltrotors.Famous V-22 " the fishes for having the U.S.
Hawk ", the VTOL tilting rotor wing unmanned aerial vehicle " black panther " of space flight scientific ＆ technical corporation of Israel production.
Existing tilt rotor aircraft mostly using verting to engine nacelle by the way of realizing verting, wing and
The bindiny mechanism of nacelle will be extremely complex with the design of inclining rotary mechanism, and has very high requirement to structural strength, therefore can cause
The increase of construction weight.Realize verting by the way of making wing integrally overturn, greatly simplify inclining rotary mechanism and tie with wing
The complexity and design difficulty of structure.
The content of the invention
The present invention relates to a kind of aircraft with slant rotor, it by fuselage, wing, tailplane, vertical tail, motor,
Rotor, nacelle, aileron, rudder, elevator, undercarriage, inclining rotary mechanism, electric power system, control system composition.Wing is installed on
Middle fuselage top, tailplane is installed on afterbody, and vertical tail is installed on tailplane middle part.While straight wing,
Tailplane adopts special connected mode with fuselage so as to overall to realize turning over by control inclining rotary mechanism.Vertically
Empennage is connected firmly with tailplane, and vertical tail verts together with tailplane when verting.The battery of electric power system is placed in fuselage
Intersegmental part, control box is placed in inside nosing, is risen and fallen and is placed on belly.Nacelle is fixed on straight wing and tailplane
On, motor is installed in nacelle.Inclining rotary mechanism is installed in fuselage, can be pushed away by this form of servomotor drive leading screw
The motivation wing is verted with tailplane.
Straight wing can be wing using high lift-drag ratio with tailplane but be not limited to this kind of wing.
Fuselage is mainly used in bearing load and containing component, using carbon fibre composite or other materials.
The beam of wing can be made up of two carbon pipes, undertake wing major part moment of flexure and shear stress.Rib can be navigated by high intensity
Cavity foam and carbon fiber sheet are constituted, and play a part of to maintain wing aerodynamic profile, and undertake fraction shear stress to answer with partly cutting
Power.Wing can transmit the load of wing with fuselage junction using rib and reinforcing frame is strengthened.Nacelle is used for fixed drive electricity
Machine, and transmit the load of motor.
Undercarriage can adopt tricycle layout, be installed on belly.
Dynamical system can be made up of 4 motors, but be not limited to 4, be respectively arranged in nacelle, and battery is then placed in machine
Inside body.
Wing adopts particular design with the junction of fuselage, enables wing integrally to vert backward, and guarantees the reasonable of load
Transmission.
Compared with most of tiltrotor design, the design has the characteristics of reliability is high, weight is little.
In sum, the design is conducive to the reliability that the design complexity for simplifying inclining rotary mechanism is verted with raising
Property.Therefore the tilting rotor wing unmanned aerial vehicle of this type will have very big development prospect.
Description of the drawings
Fig. 1 is the placement scheme schematic diagram of tilting rotor wing unmanned aerial vehicle of the present invention；
Fig. 2 is the schematic diagram of tilting rotor wing unmanned aerial vehicle VTOL state of the present invention；
Fig. 3,4 be tilting rotor wing unmanned aerial vehicle level flight condition of the present invention schematic diagram；
Fig. 5 is the part leading screw schematic diagram that mainly verts of tilting rotor wing unmanned aerial vehicle of the present invention；
Specific embodiment
Below in conjunction with drawings and Examples, the invention will be further described.
The present invention is a kind of aircraft with slant rotor, referring to Fig. 1, mainly by fuselage (1), straight wing (2), horizontal tail
The wing (3), vertical tail (4) composition.Fuselage ring mainly can be made up of aluminum frame, aluminum reinforcing frame, aluminum stringer, fuselage skin
Carbon fibre material can be adopted, the ability that fuselage bears load is strengthened while reducing weight.Install in fuselage control box, battery,
Servomotor, leading screw, belly installs undercarriage.Straight wing is connected by central wing box with fuselage, and primary structure can be by
Two carbon pipes play beam action, and rib can be bonded by high intensity aviation foam and carbon fiber board, and wing is installed at nacelle
Ribs then can be bonded with foam using thicker carbon fiber board, and the reinforcement being located at the central wing box in the middle part of wing
Rib then can be made using metal, and wing cover equally may also be employed carbon fibre material and make.Tailplane can be adopted with vertical tail
Made with similar version and material, when both make, be made as an entirety.
Referring to Fig. 2, when the tilting rotor wing unmanned aerial vehicle VTOL and hovering of the present invention, in wing and tailplane
Duan Houyuan is connected with fuselage, and both stage casing leading edges are connected by inclining rotary mechanism with fuselage.Vertical tail is connected firmly with tailplane,
Vert together with tailplane when verting.Therefore wing is more special with the attachment structure of fuselage, and wing stage casing is Chong Die with fuselage
The trailing edge at place is connected the ribs of wing central authorities wing box with the reinforcing frame at fuselage by axle, bearing, and the center of leading edge
Place is then connected by rotating shaft with leading screw.
Referring to Fig. 5, inclining rotary mechanism mainly can be made up of servomotor, leading screw, and the inclining rotary mechanism has simple structure, stable
Property high, lightweight feature, but be not limited only to this kind of mode.
The core of the present invention is that its special vert mode and inclining rotary mechanism, but the invention is not limited in this kind of reality
Apply mode, if the various changes and deformation to the present invention are without departing from the scope of the invention, still fall within the present invention claim and
Within the scope of equivalent technology.
Claims (8)
1. a kind of aircraft with slant rotor, by fuselage (1), wing (2), tailplane (3), vertical tail (4), aileron (5),
Elevator (6), rudder (7), rotor (8), nacelle (9), motor, undercarriage, inclining rotary mechanism, electric power system composition；Wing (2)
Installed in the top in fuselage (1) stage casing, shoulder-wing configuration, and wing are constituted by machines such as ribs, reinforcing frame, rotating shaft, leading screws
While structure reaches wing (2) and is connected with fuselage (1), straight wing (2) can be made integrally to be flipped up；Tailplane (3) with
Wing (2) is wing using identical, is installed on afterbody, connects firmly in vertical tail (4) and tailplane (3) structure；In machine
The middle part at the wing (2) two ends is respectively provided with nacelle (9), and nacelle is each on motor to install a secondary rotor (8) built with motor；Horizontal tail
The wing (3) adopts the layout similar to wing (2), and at the two ends of empennage nacelle (9) is provided with, and nacelle (9) is built with motor, level
Empennage (3) can integrally be flipped up again by identical inclining rotary mechanism.
2. it is according to claim 1 it is a kind of can tilting rotor aircraft, it is characterised in that：The aircraft with slant rotor
Vert by whole wing (2) with tailplane (3) while verted realizing, its motor by nacelle (9) with
Wing is connected firmly.
3. according to claim 1,2 it is a kind of can tilting rotor aircraft, it is characterised in that：Tailplane (3) with it is vertical
Empennage (4) is connected firmly in structure, and while tailplane (3) verts, vertical tail (4) will vert together.
4. according to claim 1, it is characterised in that：The rotor verts the inclining rotary mechanism of unmanned plane can be by servomotor and silk
Thick stick constitutes but is not limited to this kind of form.
5. according to claim 1, it is characterised in that：Motor on wing (2) is installed on the nacelle (9) of the middle side part of wing two
Interior, the motor of tailplane (3) is then installed in the nacelle (9) of wing both side ends, but motor arrangements are not limited to this kind of form,
Motor number is also not necessarily limited to four.
6. according to claim 1, it is characterised in that：The design of rotor (8), make rotor can meet aircraft vertical landing,
The performance requirement of hovering, can meet aircraft and put down winged performance requirement again.
7. according to claim 1, it is characterised in that：Each motor can work independently, and both sides motor can be by differential control
Make to control the flight course of aircraft, this is conducive to the flight course of change aircraft more accurately and fast.
8. according to claim 1, it is characterised in that：The aircraft with slant rotor, can as helicopter VTOL, and
Can carry out sliding race landing as general fixed wing aircraft.And the aircraft can vertical flight mode and horizontal flight mode it
Between carry out any switching laws, greatly extend the utilization prospect of the type.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611075940.2A CN106628168A (en) | 2016-11-30 | 2016-11-30 | Novel tilt rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611075940.2A CN106628168A (en) | 2016-11-30 | 2016-11-30 | Novel tilt rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106628168A true CN106628168A (en) | 2017-05-10 |
Family
ID=58813122
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611075940.2A Pending CN106628168A (en) | 2016-11-30 | 2016-11-30 | Novel tilt rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106628168A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107028549A (en) * | 2017-05-18 | 2017-08-11 | 烟台工程职业技术学院 | A kind of glass-cleaning robot |
| CN107521661A (en) * | 2017-09-03 | 2017-12-29 | 佛山市龙远科技有限公司 | A kind of rotatable more amphibious unmanned planes of power VTOL of wing |
| CN107651164A (en) * | 2017-08-28 | 2018-02-02 | 北京航空航天大学 | A kind of wing wide-angle inclining rotary mechanism for small-sized tilting wing formula aircraft |
| CN108107902A (en) * | 2017-12-20 | 2018-06-01 | 成都纵横自动化技术有限公司 | Horizontal course attitude control method and relevant apparatus |
| CN109573006A (en) * | 2019-01-30 | 2019-04-05 | 深圳市道通智能航空技术有限公司 | A kind of tilting rotor wing unmanned aerial vehicle and its wing components |
| CN112607011A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Tilt rotor unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2306952Y (en) * | 1997-03-27 | 1999-02-10 | 黄永吉 | Double-wing aircraft capable of landing or taking-off vertically |
| CN201729271U (en) * | 2009-08-03 | 2011-02-02 | 北京航空航天大学 | Twin-propeller vertical duct controlled tiltrotor aircraft |
| CN103129737A (en) * | 2013-03-27 | 2013-06-05 | 南京傲翼伟滕自动化科技有限公司 | Inclined fixed wing unmanned plane |
| US20150298804A1 (en) * | 2013-05-22 | 2015-10-22 | Bell Helicopter Textron Inc. | Rotorcraft Flapping Lock |
| CN105564642A (en) * | 2016-03-03 | 2016-05-11 | 辽宁猎鹰航空科技有限公司 | Tilt-rotor UAV (Unmanned Aerial Vehicle) |
-
2016
- 2016-11-30 CN CN201611075940.2A patent/CN106628168A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2306952Y (en) * | 1997-03-27 | 1999-02-10 | 黄永吉 | Double-wing aircraft capable of landing or taking-off vertically |
| CN201729271U (en) * | 2009-08-03 | 2011-02-02 | 北京航空航天大学 | Twin-propeller vertical duct controlled tiltrotor aircraft |
| CN103129737A (en) * | 2013-03-27 | 2013-06-05 | 南京傲翼伟滕自动化科技有限公司 | Inclined fixed wing unmanned plane |
| US20150298804A1 (en) * | 2013-05-22 | 2015-10-22 | Bell Helicopter Textron Inc. | Rotorcraft Flapping Lock |
| CN105564642A (en) * | 2016-03-03 | 2016-05-11 | 辽宁猎鹰航空科技有限公司 | Tilt-rotor UAV (Unmanned Aerial Vehicle) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107028549A (en) * | 2017-05-18 | 2017-08-11 | 烟台工程职业技术学院 | A kind of glass-cleaning robot |
| CN107651164A (en) * | 2017-08-28 | 2018-02-02 | 北京航空航天大学 | A kind of wing wide-angle inclining rotary mechanism for small-sized tilting wing formula aircraft |
| CN107521661A (en) * | 2017-09-03 | 2017-12-29 | 佛山市龙远科技有限公司 | A kind of rotatable more amphibious unmanned planes of power VTOL of wing |
| CN108107902A (en) * | 2017-12-20 | 2018-06-01 | 成都纵横自动化技术有限公司 | Horizontal course attitude control method and relevant apparatus |
| CN108107902B (en) * | 2017-12-20 | 2021-06-18 | 成都纵横自动化技术股份有限公司 | Lateral heading attitude control method and related device |
| CN109573006A (en) * | 2019-01-30 | 2019-04-05 | 深圳市道通智能航空技术有限公司 | A kind of tilting rotor wing unmanned aerial vehicle and its wing components |
| CN109573006B (en) * | 2019-01-30 | 2024-04-12 | 深圳市道通智能航空技术股份有限公司 | Tilt rotor unmanned aerial vehicle and wing subassembly thereof |
| CN112607011A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Tilt rotor unmanned aerial vehicle |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170510 |
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