CN108928471A - Variable tail rotor high-speed aircraft - Google Patents
Variable tail rotor high-speed aircraft Download PDFInfo
- Publication number
- CN108928471A CN108928471A CN201810914868.0A CN201810914868A CN108928471A CN 108928471 A CN108928471 A CN 108928471A CN 201810914868 A CN201810914868 A CN 201810914868A CN 108928471 A CN108928471 A CN 108928471A
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- China
- Prior art keywords
- tail rotor
- rotor
- tail
- fuselage
- variable
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- Pending
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- 230000005540 biological transmission Effects 0.000 claims abstract description 11
- 230000001360 synchronised effect Effects 0.000 claims description 3
- 230000006870 function Effects 0.000 abstract description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of variable tail rotor high-speed aircrafts, including fuselage, power mechanism, transmission mechanism, main rotor, tail rotor, manipulation and control unit, the tail rotor is mounted in the rotary shaft perpendicular to fuselage, the rotating shaft terminal is mounted on afterbody, servo motor is additionally provided in afterbody, the servo motor can drive rotary shaft to rotate around middle line, and the power mechanism is distributed by transmission mechanism to main rotor and tail rotor by transfer case.The tail rotor direction-agile of variable tail rotor high-speed aircraft of the invention changes, tail rotor is towards fuselage side when taking off, it functions as helicopter tail rotor, and power mechanism drives main rotor and tail rotor simultaneously, provides lift by main rotor, after lift-off, the direction of adjustable tail rotor backward, provides thrust by tail rotor, VTOL both may be implemented, high-speed flight can be realized again, and structure is simple, safety is good.
Description
Technical field
The present invention relates to technical field of aerospace, specially a kind of variable tail rotor high-speed aircraft.
Background technique
Helicopter is widely applied to the multiple fields such as transport, patrol, tourism, rescue, mainly by body and lift, dynamic
Power, the transmission composition such as three digest journals and onboard flight equipment.The lift system of single rotor formula helicopter includes main rotor and tail
Paddle, main rotor provide lift, and helicopter is lifted support in the sky, and tail-rotor is used to balance reaction torque and carries out course behaviour to helicopter
It is vertical.The direction of the tail-rotor of existing helicopter is all fixed immutable.
Gyroplane be it is a kind of using it is preceding winged when relative wind blow autorotation to generate the rotary wing aircraft of lift.Rotation
The rotor of wing machine is not connected with engine driving system, engine not instead of to drive rotor to provide lift as gyroplane,
During gyroplane flies, rotor wing rotation is blown by front air-flow and generates lift, its forward force is promoted by driven by engine
Device directly provides.
Existing rotor craft have the characteristics that it is respective, helicopter can VTOL, speed is slow；Gyroplane safety
It is good, but be unable to VTOL, cannot hover；Fixed-wing speed is fast, also needs runway；Deflector vane, which can be taken into account, has hung down and high speed
But figure is huge, and structure is complicated.
Summary of the invention
The present invention is directed to above-mentioned problems of the prior art, improves, provides in the foundation structure of helicopter
One kind can VTOL, high speed, safety is good, the simple aircraft of structure.
The technical solution adopted by the invention is as follows: a kind of variable tail rotor high-speed aircraft, including fuselage, power mechanism,
Transmission mechanism, main rotor, tail rotor, manipulation and control unit, the tail rotor is mounted in the rotary shaft perpendicular to fuselage, described
Rotating shaft terminal is mounted on afterbody, is additionally provided with servo motor in afterbody, the servo motor can drive rotary shaft
It is rotated around middle line, the power mechanism is distributed by transmission mechanism to main rotor and tail rotor by transfer case.
It further, further include duct, the tail rotor is mounted in duct, and duct and rotation axis connection can be with tail rotors
Synchronous rotary.
Further, the manipulation and control unit can control transfer case to disconnect the power transmission with main rotor.
Further, the tail portion of the fuselage is equipped with tailplane and vertical tail.
Beneficial effects of the present invention are as follows: the tail rotor direction-agile of variable tail rotor high-speed aircraft of the invention changes,
Tail rotor functions as helicopter tail rotor towards fuselage side when taking off, and power mechanism drives main rotor and tailspin simultaneously
The wing provides lift by main rotor, and after lift-off, the direction that can adjust tail rotor backward, provides thrust by tail rotor, both can be real
Existing VTOL, and can realize high-speed flight, structure is simple, safety is good.
Detailed description of the invention
Fig. 1-Fig. 2 is the variable tail rotor high-speed aircraft different flight state schematic diagram of the present invention.
Specific embodiment
To facilitate the understanding of the present invention, the present invention is made below in conjunction with Figure of description and preferred embodiment more complete
Face meticulously describes, but the protection scope of the present invention is not limited to the following specific embodiments.
As shown in Figure 1 and Figure 2, a kind of variable tail rotor high-speed aircraft of the invention, including fuselage 1, power mechanism, biography
Motivation structure, main rotor 2, tail rotor 3, manipulation and control unit, the tail rotor 3 are mounted in the rotary shaft 4 perpendicular to fuselage, institute
It states 4 both ends of rotary shaft and is mounted on afterbody, be additionally provided with servo motor in afterbody, the servo motor can drive rotation
Axis 4 is rotated around middle line, is externally provided with duct 5 in tail rotor 3, duct 5 is connect with rotary shaft 4 can be with 3 synchronous rotary of tail rotor.It is described
Power mechanism is distributed by transmission mechanism to main rotor 2 and tail rotor 3 by transfer case, and manipulation and control unit can control transfer case disconnected
The power transmission with main rotor is opened, the tail portion of the fuselage is equipped with tailplane and vertical tail.
The tail rotor direction-agile of variable tail rotor high-speed aircraft of the invention changes, and tail rotor is towards fuselage side when taking off
Face (as shown in Figure 1) functions as helicopter tail rotor, and power mechanism drives main rotor and tail rotor simultaneously, by main rotor
Lift is provided, after lift-off, the direction that can adjust tail rotor backward (as shown in Figure 2), provides thrust by tail rotor.
With the help of the introduction present in aforementioned specification and relevant drawings, those skilled in the art in the invention will
It will recognize that many modifications and other embodiments of the invention.It will consequently be understood that the present invention is not limited to disclosed specific realities
Scheme is applied, modification and other embodiments are to be considered as included in scope of the appended claims.Although spy is used herein
Determine term, they are only used with generic and descriptive sense, rather than limitation.
Claims (4)
1. variable tail rotor high-speed aircraft, including fuselage, power mechanism, transmission mechanism, main rotor, tail rotor, manipulation and control
Unit, it is characterised in that: the tail rotor is mounted in the rotary shaft perpendicular to fuselage, and the rotating shaft terminal is mounted on fuselage
Tail portion is additionally provided with servo motor in afterbody, and the servo motor can drive rotary shaft to rotate around middle line, the engine
Structure is distributed by transmission mechanism to main rotor and tail rotor by transfer case.
2. variable tail rotor high-speed aircraft as described in claim 1, it is characterised in that: it further include duct, the tail rotor
It is mounted in duct, duct and rotation axis connection can be with tail rotor synchronous rotaries.
3. variable tail rotor high-speed aircraft as described in claim 1, it is characterised in that: the manipulation and control unit is controllable
Transfer case disconnects the power transmission with main rotor.
4. variable tail rotor high-speed aircraft as claimed in any one of claims 1-3, it is characterised in that: the tail of the fuselage
Portion is equipped with tailplane and vertical tail.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810914868.0A CN108928471A (en) | 2018-08-13 | 2018-08-13 | Variable tail rotor high-speed aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810914868.0A CN108928471A (en) | 2018-08-13 | 2018-08-13 | Variable tail rotor high-speed aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108928471A true CN108928471A (en) | 2018-12-04 |
Family
ID=64445223
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810914868.0A Pending CN108928471A (en) | 2018-08-13 | 2018-08-13 | Variable tail rotor high-speed aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108928471A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114302847A (en) * | 2019-09-20 | 2022-04-08 | 株式会社爱隆未来 | Flying body |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06171597A (en) * | 1992-05-29 | 1994-06-21 | Toru Fujii | Vertical jet rocket aircraft |
| CN2439400Y (en) * | 2000-09-08 | 2001-07-18 | 韩秀文 | Helicopter with wings |
| KR20030049796A (en) * | 2001-12-17 | 2003-06-25 | 한국항공우주연구원 | Three-Fan Lifted Vertical Take-off and Landing Aircraft |
| RU70220U1 (en) * | 2007-09-28 | 2008-01-20 | Московский авиационный институт (государственный технический университет) | AUTO FAT |
| CN203005744U (en) * | 2012-10-30 | 2013-06-19 | 武卫平 | Tilt rotor helicopter |
| US20160200430A1 (en) * | 2014-05-23 | 2016-07-14 | Bell Helicopter Textron Inc. | Tail Rotor Actuation System |
| CN206520752U (en) * | 2016-12-01 | 2017-09-26 | 及兰平 | Double mode rotary wing aircraft based on folding wing |
| CN208947593U (en) * | 2018-08-13 | 2019-06-07 | 湘潭市湘盾道路交通设施建设维护有限责任公司 | Variable tail rotor high-speed aircraft |
-
2018
- 2018-08-13 CN CN201810914868.0A patent/CN108928471A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06171597A (en) * | 1992-05-29 | 1994-06-21 | Toru Fujii | Vertical jet rocket aircraft |
| CN2439400Y (en) * | 2000-09-08 | 2001-07-18 | 韩秀文 | Helicopter with wings |
| KR20030049796A (en) * | 2001-12-17 | 2003-06-25 | 한국항공우주연구원 | Three-Fan Lifted Vertical Take-off and Landing Aircraft |
| RU70220U1 (en) * | 2007-09-28 | 2008-01-20 | Московский авиационный институт (государственный технический университет) | AUTO FAT |
| CN203005744U (en) * | 2012-10-30 | 2013-06-19 | 武卫平 | Tilt rotor helicopter |
| US20160200430A1 (en) * | 2014-05-23 | 2016-07-14 | Bell Helicopter Textron Inc. | Tail Rotor Actuation System |
| CN206520752U (en) * | 2016-12-01 | 2017-09-26 | 及兰平 | Double mode rotary wing aircraft based on folding wing |
| CN208947593U (en) * | 2018-08-13 | 2019-06-07 | 湘潭市湘盾道路交通设施建设维护有限责任公司 | Variable tail rotor high-speed aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114302847A (en) * | 2019-09-20 | 2022-04-08 | 株式会社爱隆未来 | Flying body |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20200119 Address after: 411104 refrigeration workshop, No.38, Shuyuan Road, high tech Zone, Xiangtan City, Hunan Province Applicant after: Xiangtan xiangdun Intelligent Technology Co., Ltd Address before: 411100 No. 3, Majialing, Yuhu District Square Street, Xiangtan City, Hunan Province Applicant before: Xiangtan Xiangdan Road Traffic Facilities Construction and Maintenance Co., Ltd. |
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| TA01 | Transfer of patent application right |