CN208947593U - Variable tail rotor high-speed aircraft - Google Patents
Variable tail rotor high-speed aircraft Download PDFInfo
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- CN208947593U CN208947593U CN201821296469.4U CN201821296469U CN208947593U CN 208947593 U CN208947593 U CN 208947593U CN 201821296469 U CN201821296469 U CN 201821296469U CN 208947593 U CN208947593 U CN 208947593U
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- tail rotor
- rotor
- tail
- fuselage
- variable
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Abstract
The utility model 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 the variable tail rotor high-speed aircraft of the utility model 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 utility model 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 utility model is directed to above-mentioned problems of the prior art, improves in the foundation structure of helicopter,
There is provided one kind can VTOL, high speed, safety is good, the simple aircraft of structure.
The technical solution adopted in the utility model is as follows: a kind of variable tail rotor high-speed aircraft, including fuselage, engine
Structure, transmission mechanism, main rotor, tail rotor, manipulation and control unit, the tail rotor are mounted in the rotary shaft perpendicular to fuselage,
The rotating shaft terminal is mounted on afterbody, is additionally provided with servo motor in afterbody, the servo motor can drive rotation
Shaft is rotated around middle line, and 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.
The beneficial effects of the utility model are as follows: the tail rotor direction of the variable tail rotor high-speed aircraft of the utility model
Convertible, tail rotor functions as helicopter tail rotor towards fuselage side when taking off, and power mechanism drives main rotor simultaneously
And tail rotor, lift is provided by main rotor, after lift-off, the direction that can adjust tail rotor backward, provides thrust by tail rotor, both
VTOL may be implemented, and can realize high-speed flight, structure is simple, safety is good.
Detailed description of the invention
Fig. 1-Fig. 2 is that the utility model can be changed tail rotor high-speed aircraft different flight state schematic diagram.
Specific embodiment
For the ease of understanding the utility model, below in conjunction with Figure of description and preferred embodiment to the utility model
Work more comprehensively, meticulously describes, but the protection scope of the utility model is not limited to embodiment in detail below.
As shown in Figure 1 and Figure 2, a kind of variable tail rotor high-speed aircraft of the utility model, including fuselage 1, engine
Structure, transmission mechanism, main rotor 2, tail rotor 3, manipulation and control unit, the tail rotor 3 are mounted on the rotary shaft 4 perpendicular to fuselage
On, 4 both ends of rotary shaft are mounted on afterbody, are additionally provided with servo motor in afterbody, the servo motor can drive
Dynamic rotary shaft 4 is rotated around middle line, is externally provided with duct 5 in tail rotor 3, duct 5 can rotation synchronous with tail rotor 3 with the connection of rotary shaft 4
Turn.The power mechanism is distributed by transmission mechanism to main rotor 2 and tail rotor 3 by transfer case, and manipulation and control unit is controllable
Transfer case disconnects the power transmission with main rotor, and the tail portion of the fuselage is equipped with tailplane and vertical tail.
The tail rotor direction-agile of the variable tail rotor high-speed aircraft of the utility model changes, and tail rotor is towards machine when taking off
Body side (as shown in Figure 1) functions as helicopter tail rotor, and power mechanism drives main rotor and tail rotor simultaneously, by leading
Rotor provides lift, and 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, the technology people of the utility model fields
Member will be appreciated that many modifications and other embodiments of the utility model.It will consequently be understood that the utility model is not limited to
Disclosed specific embodiment, modification and other embodiments are to be considered as included in scope of the appended claims.Although this
Specific term is used in text, 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 |
|---|---|---|---|
| CN201821296469.4U CN208947593U (en) | 2018-08-13 | 2018-08-13 | Variable tail rotor high-speed aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821296469.4U CN208947593U (en) | 2018-08-13 | 2018-08-13 | Variable tail rotor high-speed aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208947593U true CN208947593U (en) | 2019-06-07 |
Family
ID=66733626
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821296469.4U Expired - Fee Related CN208947593U (en) | 2018-08-13 | 2018-08-13 | Variable tail rotor high-speed aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208947593U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108928471A (en) * | 2018-08-13 | 2018-12-04 | 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 |
| CN113022847A (en) * | 2021-03-11 | 2021-06-25 | 北京航空航天大学 | High-speed helicopter with vector duct tail rotor |
-
2018
- 2018-08-13 CN CN201821296469.4U patent/CN208947593U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108928471A (en) * | 2018-08-13 | 2018-12-04 | 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 |
| CN113022847A (en) * | 2021-03-11 | 2021-06-25 | 北京航空航天大学 | High-speed helicopter with vector duct tail rotor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200122 Address after: 411104 refrigeration workshop, No.38, Shuyuan Road, high tech Zone, Xiangtan City, Hunan Province Patentee after: Xiangtan xiangdun Intelligent Technology Co.,Ltd. Address before: 411100 No. 3, Majialing, Yuhu District Square Street, Xiangtan City, Hunan Province Patentee before: XIANGTAN XIANGDUN ROAD TRAFFIC FACILITIES CONSTRUCTION AND MAINTENANCE Co.,Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190607 Termination date: 20210813 |