CN203958617U - Butterfly list duct tiltrotor aircraft - Google Patents
Butterfly list duct tiltrotor aircraft Download PDFInfo
- Publication number
- CN203958617U CN203958617U CN201420351843.1U CN201420351843U CN203958617U CN 203958617 U CN203958617 U CN 203958617U CN 201420351843 U CN201420351843 U CN 201420351843U CN 203958617 U CN203958617 U CN 203958617U
- Authority
- CN
- China
- Prior art keywords
- aircraft
- main
- main cabin
- duct
- cabin
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Toys (AREA)
Abstract
A kind of butterfly list duct tiltrotor aircraft, it is characterized in that it is mainly made up of aircraft skin (1), the main cabin of aircraft (2) and yaw rudder (4), aircraft skin (1) is sleeved on the main cabin of aircraft (2), between the two by ball bearing of main shaft (3) location, the centre hole of aircraft skin (1) is provided with internally toothed annulus (1-2), internally toothed annulus (1-2) is meshed with driven wheel, and driven wheel drives by auxiliary turboaxle motor (2-2) is installed; In main cabin (2), geometric centre place is provided with tilting rotor sustainer, main engine (2-4); The bottom in main cabin is provided with alighting gear (2-6).The utility model can vertical takeoff and landing, can make aircraft flight speed, and 1ift-drag ratio is higher, and load carrying ability is large, and stealth is good, and flight stability is high, is difficult for being subject to the impact of air-flow.Practical, can be dual-use.
Description
Technical field
The utility model relates to a kind of aviation aircraft, especially a kind of profile is butterfly, fuselage is double-deck, centre is single channel, and use the aircraft of tilting rotor driving engine, specifically a kind of new multi-purpose butterfly list duct tiltrotor aircraft that can be used as large aircraft and unmanned plane application.
Background technology
Along with the fast development of aviation industry, aircraft is more and more advanced, and the kind of aircraft is also more and more various.But at present mainly taking fixed wing aircraft and autogyro as main, but the plane track that most of fixed wing aircraft need to be longer, can not vertical takeoff and landing and hovering, and there are several root problems because having used screw propeller in autogyro.First, autogyro easily causes sonic boom phenomenon because of front blade awing, and the reason that rear blade easily produces stall phenomenon causes flying speed slower.And because the reason that screw propeller moves air-flow from top to bottom, helicopter cabin can not be excessive, also limit the load carrying ability of autogyro simultaneously.The today becoming more and more important at Defence business, the solution of above problem is also more and more necessary.For above deficiency, the utility model can effectively overcome the above problems to a certain extent.
Summary of the invention
The purpose of this utility model is can not vertical takeoff and landing and hovering for most of fixed wing aircraft, autogyro speed, volume, the problem limited with load carrying ability, designing one can vertical takeoff and landing, and speed and volume aspect effectively increase, and 1ift-drag ratio is higher, the good butterfly list of stealth duct tiltrotor aircraft.
The technical solution of the utility model is:
A kind of butterfly list duct tiltrotor aircraft, it is characterized in that it is mainly by aircraft skin 1, the main cabin 2 of aircraft and yaw rudder 4 form in relative rotation, aircraft skin 1 is sleeved on the main cabin 2 of aircraft, between the two by ball bearing of main shaft 3 location motions for the relative rotation, the centre hole of aircraft skin 1 is provided with internally toothed annulus 1-2, internally toothed annulus 1-2 is meshed with the driven wheel being arranged in main cabin 2, and driven wheel is driven by the auxiliary turboaxle motor 2-2 that is arranged on 2 inside, main cabin; In main cabin, 2 geometric centre places are provided with tilting rotor sustainer, main engine 2-4, are connected with screw propeller 2-5 on sustainer, main engine 2-4; The bottom in main cabin is provided with alighting gear 2-6; Yaw rudder 4 is by the strut bar 4-2 extending out in duct, stable rudder face 4-3, direction rudder face 4-4 composition.
Described tilting rotor sustainer, main engine 2-4 is arranged in main cabin 2 by cantilever 2-3.Sustainer, main engine tilt angle is unfixing, and maximum is no more than 70 degree; The cantilever 2-3 quantity that connects sustainer, main engine 2-4 and the main cabin of aircraft body 2-1 is unfixing.
The head 4-1 of described strut bar 4-2 is provided with photoelectric probe and pitot.
Yaw rudder 4 is inverted V-shaped and is installed on aircraft bottom.
Described aircraft skin 1 upper surface radian is greater than lower surface radian to make aircraft in the time flying forward, and the wing that aircraft cabin body can be equivalent to fixed wing aircraft produces lift.。
The beneficial effects of the utility model:
The structure of this aircraft takes full advantage of aerodynamics, and 1ift-drag ratio is higher.Aircraft has adopted the aerodynamic arrangement of butterfly, and the shell 1 upper surface radian of aircraft is greater than lower surface radian, and in the time flying forward, aircraft cabin body can be equivalent to the wing of fixed wing aircraft, can produce lift like this.In the middle of aircraft, adopt the layout of single duct, and use tilting rotor driving engine.The air-flow that screw propeller is produced all flows through from centre, has increased power, has reduced air-flow resistance.In the time that aircraft is normaled cruise, incoming flow flows backward along aircraft lower house, in the time flowing through duct, can form one deck air cushion simultaneously.Accelerated by sustainer, main engine by duct oblique after action of high-speed airflow on air cushion, can produce certain lift, principle is similar to ground effect vehicle.The utility model can vertical takeoff and landing, can make aircraft have the flying speed higher than pure helicopter, and cabin volumes is large, and load carrying ability is larger, and stealth is good, and flight stability is high, is difficult for being subject to the impact of air-flow.Practical, can be dual-use.
Brief description of the drawings
Fig. 1 is the sectional drawing of overlooking of aircraft skin 1.
Fig. 2 is the sectional drawing of overlooking of the main cabin of aircraft body 2-1.
Fig. 3 is that the master of aircraft looks sectional drawing.
Fig. 4 is the lateral plan of aircraft.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is further described.
As Figure 1-4.
A kind of butterfly list duct tiltrotor aircraft, it is mainly by aircraft skin 1 in relative rotation, and the main cabin 2 of aircraft and yaw rudder 4 form.Aircraft skin 1 is sleeved on the main cabin 2 of aircraft.Ball bearing of main shaft 3 between aircraft skin and main cabin ensures relatively rotating between shell and main cabin.As shown in Figure 1, aircraft skin 1 is mainly made up of the gear 1-2 of interior lower end on aircraft skin face 1-1 and shell.As shown in Figure 2, tilting rotor sustainer, main engine 2-4 is positioned at aircraft and overlooks face geometric centre, is installed on the body 2-1 of the main cabin of aircraft by cantilever 2-3.Sustainer, main engine 2-4 drives rotor 2-5 rotation to produce lift upwards while normally work, aircraft can upwards be flown, simultaneously tilting rotor sustainer, main engine 2-4 can before and after the certain angle that verts, aircraft can be flown forward and backward.Two the symmetrical main cabin of aircraft body 2-1 lower parts that are installed on of auxiliary turbine engine 2-2 built-in type.Two auxiliary turboaxle motor 2-2 can drive aircraft skin 1 backwards rotation by gear 1-2, with the counter torque of this balance sustainer, main engine 2-4.The size that simultaneously can change by controlling the rotation of auxiliary turboaxle motor 2-2 counter torque rotates aircraft entirety, can reach left with right-hand turning to object.The shell 1 upper surface radian of aircraft is greater than lower surface radian, and in the time flying forward, aircraft cabin body can be equivalent to the wing of fixed wing aircraft, can produce lift like this.The alighting gear of aircraft is positioned at aircraft duct inner bottom part, as shown in Figure 3.Yaw rudder 4 is inverted V-shaped and is installed on the front bottom of aircraft, and yaw rudder 4 is by the strut bar 4-2 extending out in duct, stable rudder face 4-3, and direction rudder face 4-4 forms, and as shown in Figure 4, a pair of inverted V-shaped yaw rudder can be controlled pitching and the left and right turn of aircraft simultaneously.
operation logic of the present utility model
When aircraft takeoff, tilting rotor sustainer, main engine and two auxiliary turboaxle motor 2-2 work simultaneously, and sustainer, main engine drives screw propeller rotation, thereby generation lift, aircraft is upwards flown, and auxiliary turboaxle motor rotates by gear set drive shell, with the counter torque of balance sustainer, main engine.Now aircraft power consumption is larger.When aircraft rises to certain altitude, vert by flight control computer control sustainer, main engine, aircraft is flown forward.Aircraft skin serves as wing and produces lift, ensures aircraft normal flight.
When aircraft is normaled cruise, sustainer, main engine tilt angle is larger, and the air-flow that screw propeller produces all flows through from centre, has increased power, has reduced air-flow resistance, and aircraft flight speed is very fast, and the lift that aircraft skin produces is also larger.Aircraft front incoming flow flows backward along aircraft lower house simultaneously, in the time flowing through duct, can form one deck air cushion.Accelerated by sustainer, main engine by duct oblique after action of high-speed airflow on air cushion, can produce certain lift, principle is similar to ground effect vehicle.Now the horizontal moment of sustainer, main engine is very little, so the power of auxiliary engine is also very little, overall power is also very little.Because the turning effort of shell can cause aircraft port wingtip and right flank point to produce a speed poor in the time flying forward, so it is poor to produce a lift on the aerofoil of left and right.Moment in the poor and sustainer, main engine vertical direction of lift on the aerofoil of left and right is carried out balance by rotational stabilization and the flight control computer direction of operating rudder of aircraft skin.
In the time that aircraft lands, sustainer, main engine and auxiliary engine are reduced to takeoff condition.Owing to adopting the design of single duct, now may produce a certain amount of ring of eddy.
The utility model does not relate to partly all prior aries that maybe can adopt same as the prior art to be realized.
Claims (5)
1. a butterfly list duct tiltrotor aircraft, it is characterized in that it is mainly by aircraft skin (1) in relative rotation, the main cabin of aircraft (2) and yaw rudder (4) composition, aircraft skin (1) is sleeved on the main cabin of aircraft (2), between the two by ball bearing of main shaft (3) location motion for the relative rotation, the centre hole of aircraft skin (1) is provided with internally toothed annulus (1-2), internally toothed annulus (1-2) is meshed with the driven wheel being arranged in main cabin (2), driven wheel drives by being arranged on the inner auxiliary turboaxle motor (2-2) in main cabin (2), in main cabin (2), geometric centre place is provided with tilting rotor sustainer, main engine (2-4), is connected with screw propeller (2-5) on sustainer, main engine (2-4), the bottom in main cabin is provided with alighting gear (2-6), yaw rudder (4) is by the strut bar extending out in duct (4-2), stable rudder face (4-3), direction rudder face (4-4) composition.
2. butterfly list duct tiltrotor aircraft according to claim 1, is characterized in that described tilting rotor sustainer, main engine (2-4) is arranged in main cabin (2) by cantilever (2-3).
3. butterfly list duct tiltrotor aircraft according to claim 1, is characterized in that the head (4-1) of described strut bar (4-2) is provided with photoelectric probe and pitot.
4. butterfly list duct tiltrotor aircraft according to claim 1, is characterized in that yaw rudder (4) is inverted V-shaped and is installed on aircraft bottom.
5. butterfly list duct tiltrotor aircraft according to claim 1, it is characterized in that described aircraft skin (1) upper surface radian is greater than lower surface radian to make aircraft in the time flying forward, the wing that aircraft cabin body can be equivalent to fixed wing aircraft produces lift.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420351843.1U CN203958617U (en) | 2014-06-30 | 2014-06-30 | Butterfly list duct tiltrotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420351843.1U CN203958617U (en) | 2014-06-30 | 2014-06-30 | Butterfly list duct tiltrotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203958617U true CN203958617U (en) | 2014-11-26 |
Family
ID=51919237
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420351843.1U Expired - Fee Related CN203958617U (en) | 2014-06-30 | 2014-06-30 | Butterfly list duct tiltrotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203958617U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106477021A (en) * | 2016-11-22 | 2017-03-08 | 武汉科技大学 | Aircraft cellular-type cabin balanced controls |
| CN107685856A (en) * | 2017-05-27 | 2018-02-13 | 北京深远世宁科技有限公司 | Dish-shaped flying machine |
| CN113942638A (en) * | 2021-08-11 | 2022-01-18 | 星逻人工智能技术(上海)有限公司 | Ducted unmanned aerial vehicle achieving steering through louver and control method |
-
2014
- 2014-06-30 CN CN201420351843.1U patent/CN203958617U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106477021A (en) * | 2016-11-22 | 2017-03-08 | 武汉科技大学 | Aircraft cellular-type cabin balanced controls |
| CN107685856A (en) * | 2017-05-27 | 2018-02-13 | 北京深远世宁科技有限公司 | Dish-shaped flying machine |
| CN113942638A (en) * | 2021-08-11 | 2022-01-18 | 星逻人工智能技术(上海)有限公司 | Ducted unmanned aerial vehicle achieving steering through louver and control method |
| CN113942638B (en) * | 2021-08-11 | 2024-04-09 | 星逻人工智能技术(上海)有限公司 | Ducted unmanned aerial vehicle for realizing steering by utilizing transom and control method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107089316A (en) | Flying wing type dual-culvert vertical take-off and landing aircraft | |
| CN101423117A (en) | Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder | |
| CN105083550A (en) | Fixed-wing aircraft realizing vertical take-off and landing | |
| CN205022862U (en) | Power device and fixed wing aircraft with mechanism of verting | |
| CN106864744B (en) | Coaxial rotor variant VTOL aircraft | |
| CN205022861U (en) | VTOL fixed wing aircraft | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN105015770A (en) | Vertical take-off and landing aircraft with wing body blended with single duct | |
| CN205998126U (en) | A kind of unmanned plane during flying system | |
| CN109319110A (en) | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure | |
| CN103158856A (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
| CN105059535A (en) | Gravity trimming vertical lift aircraft | |
| CN105346715A (en) | Vertical take-off and landing unmanned plane | |
| CN103754360B (en) | One kind flying disc type gyroplane | |
| CN205469821U (en) | Perpendicular or short take off and landing fixed wing aircraft | |
| CN106828918A (en) | A kind of Three-wing-surface vertically taking off and landing flyer | |
| CN105460215A (en) | Fixed-wing air vehicle achieving vertical or short-distance take-off and landing | |
| CN204871604U (en) | Wing body fuses single duct VTOL aircraft | |
| CN105173076B (en) | A kind of vertical take-off and landing drone | |
| CN105923154A (en) | Longitudinal column type double-rotor-wing fixed wing combined vertical take-off and landing aircraft | |
| CN108622402A (en) | A kind of combined type VTOL long endurance unmanned aircraft | |
| CN107021208A (en) | The tail sitting posture VUAV and control method of a kind of utilization duct | |
| CN203958617U (en) | Butterfly list duct tiltrotor aircraft | |
| CN112027073A (en) | Combined type tilting wing longitudinal rotation double-rotor aircraft | |
| CN108569396A (en) | Combined type blended wing-body high-speed helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141126 Termination date: 20160630 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |