CN103192990A - Vertical/short take-off and landing flying wing layout aircraft - Google Patents
Vertical/short take-off and landing flying wing layout aircraft Download PDFInfo
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- CN103192990A CN103192990A CN2013101284171A CN201310128417A CN103192990A CN 103192990 A CN103192990 A CN 103192990A CN 2013101284171 A CN2013101284171 A CN 2013101284171A CN 201310128417 A CN201310128417 A CN 201310128417A CN 103192990 A CN103192990 A CN 103192990A
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Abstract
The invention provides a flying wing layout aircraft which comprises an aircraft body (1), aircraft wings (2), ailerons, an elevator (5) and double vertical fins (4), wherein the aircraft body (1) and the aircraft wings (2) are integrated; the ailerons (3) are positioned on the outer sections of the aircraft wings (2), and are used for rolling control in level flight; the elevator (5) is positioned at the rearmost part of the aircraft body (1), and is used for pitching control in level flight; and the dual vertical fins (4) are positioned at the rear part of the aircraft body (1), and are used for enhancing the flight direction safety in level flight. The flying wing layout aircraft provided by the invention has the advantages that the aircraft body integration technique inherits the excellent pneumatic property of the flying wings, and larger internal space is provided; the weight distribution is more reasonable, and the structure is lighter, so that the load and the voyage are increased; front air screws which are arranged in an engine and tilt and rear air screws which are fixed and can be accommodated in the vertical fins achieve the capability of vertical/short take-off and landing, and the interference to the whole pneumatic appearance of the aircraft is lowered greatly; and the connection shaft design among engines greatly improves the reliability of a dynamic system, avoids the dangerous situation of invalidity after taking off, and guarantees the flight safety in vertical/short take-off and landing.
Description
Technical field
But the present invention relates to a kind of flying wing aircraft of short distance/vertical takeoff and landing, belong to fixed wing aircraft design field in the aviation aircraft.
Background technology
Because excellent pneumatic and structural weight characteristic, good stealthy performance and bigger inner space, in military domain, the flying wing type layout has obtained ripe application, as U.S. B-2 ghost stealth bomber, and the many unmanned battles of researching and developing in various countries or investigation aircraft have all adopted the flying wing type layout at present, make the flying wing type layout become the research focus in military aircraft field.
But in the General Aviation field, the flying wing type layout is not used widely, and major cause is stability that conventional flying wing type layout is intrinsic and the unfavorable factor on the road-holding property.These unfavorable factors further cause its takeoff and landing performance relatively poor, and the landing ground run distance is long, and is higher to site requirements.Unfavorable factor in the manipulation has strengthened the requirement to aviator's level on the one hand, has also increased the workload of aviator in the landing mission that takes off on the other hand greatly, has reduced the reliability of flight, and this has just further limited the application of this layout.
Summary of the invention
The present invention is directed to above-described defective, designed a kind of novel all-wing aircraft layout aircraft.This layout adopts novel power arrangement design, can realize short distance/vertical takeoff and landing.
Plane figure of the present invention is conventional all-wing aircraft layout, wide fuselage, and swept back wing, wing body merges, and afterbody is two vertical tails arranged side by side.The lifting force of wings body design that wide fuselage and wing body merge makes this layout have excellent aerodynamic characteristic.Wing sweepback and twin vertical fin have guaranteed good horizontal survey stability.Its vertical fin is divided into two parts up and down, and the upper part area does not have movable part more greatly, is fixed fin, and the lower part area is less, is all movable rudder face.
In order to have the vertical takeoff and landing ability, in the arranged around of fuselage four screw propellers, by two engine drives.Wherein, wing the place ahead, each screw propeller of fuselage both sides, fuselage afterbody respectively is equipped with a screw propeller between vertical fin and the following rudder face.Be reply engine off problem, two each and every one driving engines link by axle, avoid the single-shot inefficacy and cause lift or the moment sudden change.Lift-over control during vertical takeoff and landing realizes that by the displacement of two screw propellers in wing the place ahead the spacing of these two screw propellers is far away, and control ability is stronger, and course control is then realized by the deflection of the movable rudder face that is positioned at two screw propeller belows of tail.
Two propeller disks in wing the place ahead can vert, during vertical takeoff and landing, and the card level, it is downward that screw propeller promotes air-flow, produces lift upwards.During horizontal flight, card provides pulling force forward perpendicular to aircraft plane.During short take-off and landing (STOL), the angle of inclination of card are between between the two, and concrete numerical value depends on the actual conditions of flying field.The screw propeller of afterbody can be accommodated in the vertical fin when off working state, effectively reduces the flat resistance that flies.
According to an aspect of the present invention, provide a kind of all-wing aircraft layout aircraft, it is characterized in that comprising: fuselage and wing combine together; Be positioned at the aileron of the outer section of wing, the lift-over control when being used for flat flying; Be positioned at the elevating rudder at the rear of fuselage, the pitch control subsystem when being used for flat flying; Be positioned at the twin vertical fin at the rear of fuselage, the course stability when being used for strengthening flat flying.
Description of drawings
Fig. 1 is the plane figure scheme drawing of all-wing aircraft layout aircraft according to an embodiment of the invention.
Fig. 2 is all-wing aircraft layout aircraft power according to an embodiment of the invention system transmission scheme drawing.
Fig. 3 is that the airplane tail group of all-wing aircraft layout aircraft according to an embodiment of the invention is arranged scheme drawing.
The specific embodiment
All-wing aircraft layout aircraft according to an embodiment of the invention shown in Figure 1 comprises the fuselage that combines together (1) and wing (2), and it has excellent aeroperformance.Aileron (3) is positioned at the outer section of wing (2), the lift-over control when being used for flat flying.Elevating rudder (5) is positioned at the rear of fuselage (1), the pitch control subsystem when being used for flat flying.Twin vertical fin (4) is positioned at the rear of fuselage (1), and the course stability when being used for strengthening flat flying is without any movable rudder face.Sleeve (8) crosses fuselage (1), and is connected with the gondola (23) that is positioned at two screw propellers (7) in fuselage (1) both sides, wing (2) the place ahead.The preceding power of sending out verts by the rotation realization of sleeve (8).During horizontal flight, front propeller (7) oar dish is vertical, and front propeller (7) state provides pulling force forward as shown in Figure 2.During vertical takeoff and landing, as oar card and the aircraft plane level of Fig. 1 front propeller (7), provide thrust upwards, bear the downward gravity of aircraft jointly with the lift that the screw propeller (4) that is positioned at vertical fin (4) below produces.During short take-off and landing (STOL), between front propeller (7) deflection state flies before vertical takeoff and landing and level, thrust vectoring points to the front upper place, after screw (6) thrust still keeps up, when sliding running velocity degree acquires a certain degree, the lift that front propeller (7), after screw (6) and blended wing-body (1,2) produce is during greater than aircraft gravity, and aircraft can be liftoff.
In the shown in Figure 2 all-wing aircraft layout aircraft power according to an embodiment of the invention system, two symmetries are positioned over the piston engine (14) of fuselage interior and give first (13) with transmission of power simultaneously by first gear cluster (15), this " connecting shaft " designs the dangerous consequences that can avoid a certain power failure to bring, improves the reliability of aircraft greatly.First (13) pass to sleeve (8) interior second (10) by second gear cluster (9) with power forward, and second (10) drive the 3rd (12) by the 3rd gear cluster (11), and axle (12) drives front propellers (7) rotation.First (13) drive the 4th (17) by power-transfer clutch (16) backward, and the 4th (17) give after screw (6) by the 4th gear cluster (18), the 5th (19), the 5th gear cluster (20), the 6th (21) and the 6th gear cluster (22) with transmission of power successively.When short distance or vertical takeoff and landing, power-transfer clutch (16) tightens up, and driving engine (14) power will pass to after screw (6), and during horizontal flight, power-transfer clutch (16) unclamps, and cuts off driving engine (14) thrust and transmits backward.
The airplane tail group of all-wing aircraft layout aircraft according to an embodiment of the invention shown in Figure 3 arranges in the scheme drawing that the 6th (21) drive the screw propeller (6) that is positioned at vertical fin (4) bottom by the 6th gear cluster (22).As shown in Figure 3, when horizontal flight, tail undercarriage (6) stops operating, and is accommodated in vertical fin (4) below along air flow line, has avoided the unfavorable interference to air-flow.Rudder face (24) is arranged in the below slip-stream of screw propeller (6), can be by slip-stream being carried out the course control in the deflection realization vertical takeoff and landing process.
Advantage of the present invention and beneficial effect comprise
-wing body integration technology has been inherited the aerodynamic characteristic of all-wing aircraft excellence, and bigger inner space is provided, and weight distribution is more reasonable, and structure is lighter, is conducive to increase load and voyage.
-engine embedded, vert front propeller and the fixing and after screw that can close at vertical fin when realizing short distance/vertical takeoff and landing ability, greatly reduce the interference to the overall aircraft aerodynamic configuration.
The design of connecting shaft between the-driving engine has improved the reliability of power system greatly, avoided the dangerous situation of an inefficacy, the flight safety when having guaranteed short distance/vertical takeoff and landing.
Claims (6)
1. all-wing aircraft layout aircraft is characterized in that comprising:
Combine together fuselage (1) and wing (2),
Be positioned at the aileron (3) of the outer section of wing (2), the lift-over control when being used for flat flying,
Be positioned at the elevating rudder (5) at the rear of fuselage (1), the pitch control subsystem when being used for flat flying,
Be positioned at the twin vertical fin (4) at the rear of fuselage (1), the course stability when being used for strengthening flat flying.
2. according to the all-wing aircraft layout aircraft of claim 1, it is characterized in that further comprising:
Cross fuselage (1) sleeve (8),
Be positioned at the gondola (23) of two front propellers (7) in fuselage (1) both sides, wing (2) the place ahead, itself and described sleeve (8) are connected,
Be positioned at the after screw (6) of twin vertical fin (4) below,
Wherein
The power of described two front propellers (7) verts by the rotation realization of sleeve (8),
During horizontal flight, front propeller (7) oar dish is vertical, and pulling force forward is provided,
During vertical takeoff and landing, the oar card of front propeller (7) and aircraft plane level provide thrust upwards, and the lift that this thrust and after screw (6) produce is born the downward gravity of aircraft jointly,
During short take-off and landing (STOL), between deflection state when front propeller (7) deflection state flies before vertical takeoff and landing and level, thrust vectoring points to the front upper place, after screw (6) thrust still keeps up, when sliding running velocity degree acquires a certain degree, the lift that front propeller (7), after screw (6) and the fuselage that combines together (1) and wing (2) produce is during greater than aircraft gravity, and aircraft can be liftoff.
3. according to the all-wing aircraft layout aircraft of claim 2, it is characterized in that further:
Be positioned at the twin vertical fin (4) at rear of fuselage (1) without any movable rudder face.
4. according to the all-wing aircraft layout aircraft of claim 2 or 3, it is characterized in that further:
Symmetry is positioned over two piston engine (14) of fuselage interior,
First gear cluster (15) is used for giving first (13) with the transmission of power of two piston engine (14) simultaneously,
Described first (13) are used for by second gear cluster (9) power being passed to sleeve (8) interior second (10),
Described second gear cluster (9),
Described second (10) are used for driving the 3rd (12) by the 3rd gear cluster (11),
Described the 3rd gear cluster (11),
Described the 3rd (12) are used for driving front propeller (7) and rotate,
Power-transfer clutch (16), first (13) drive the 4th (17) by power-transfer clutch (16) backward,
Described the 4th (17) are used for giving after screw (6) by the 4th gear cluster (18), the 5th (19), the 5th gear cluster (20), the 6th (21) and the 6th gear cluster (22) with transmission of power successively,
Described the 4th gear cluster (18), the 5th (19), the 5th gear cluster (20), the 6th (21) and the 6th gear cluster (22),
Wherein
When short distance or vertical takeoff and landing, power-transfer clutch (16) tightens up, and driving engine (14) power is delivered to after screw (6),
During horizontal flight, power-transfer clutch (16) unclamps, and cuts off the transmission to after screw (6) of driving engine (14) thrust.
5. according to the all-wing aircraft layout aircraft of claim 4, it is characterized in that further:
When horizontal flight, tail undercarriage (6) stops operating, and is accommodated in vertical fin (4) below along air flow line, to avoid the unfavorable interference to air-flow.
6. according to the all-wing aircraft layout aircraft of claim 5, it is characterized in that further:
Rudder face (24) is arranged in the below slip-stream of screw propeller (6), can be by slip-stream being carried out the course control in the deflection realization vertical takeoff and landing process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310128417.1A CN103192990B (en) | 2013-04-12 | 2013-04-12 | Can Flying-wing's aircraft of short distance/vertical takeoff and landing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310128417.1A CN103192990B (en) | 2013-04-12 | 2013-04-12 | Can Flying-wing's aircraft of short distance/vertical takeoff and landing |
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| CN103192990A true CN103192990A (en) | 2013-07-10 |
| CN103192990B CN103192990B (en) | 2015-09-09 |
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| CN201310128417.1A Expired - Fee Related CN103192990B (en) | 2013-04-12 | 2013-04-12 | Can Flying-wing's aircraft of short distance/vertical takeoff and landing |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105173075A (en) * | 2015-09-10 | 2015-12-23 | 南京多零无人机技术有限公司 | Tiltable hybrid rotor-wing aircraft |
| CN105270623A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | High lift aircraft |
| CN105447249A (en) * | 2015-11-25 | 2016-03-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Static test load calculation method for engine nacelle structure |
| CN106081060A (en) * | 2016-07-05 | 2016-11-09 | 北京航空航天大学 | A kind of VTOL composite layouts unmanned plane rotor draw off gear |
| CN106741919A (en) * | 2016-12-21 | 2017-05-31 | 顺丰科技有限公司 | A kind of fixed-wing unmanned plane of VTOL |
| CN107054669A (en) * | 2017-01-20 | 2017-08-18 | 成都前沿动力科技有限公司 | A kind of unmanned plane based on vectored thrust VTOL Flying-wing |
| CN107187578A (en) * | 2017-05-18 | 2017-09-22 | 钟江汉 | A kind of Fixed Wing AirVehicle utilizes the wing structure for being vortexed lift-rising |
| CN107444633A (en) * | 2017-08-04 | 2017-12-08 | 杨爱迪 | Structure changes VTOL invisbile plane |
| CN107521686A (en) * | 2017-03-31 | 2017-12-29 | 杨爱迪 | It is a kind of can VTOL structure changes aircraft |
| CN109703758A (en) * | 2019-01-14 | 2019-05-03 | 北京空天技术研究所 | Two-way all-wing aircraft flight vehicle aerodynamic shape and design method |
| CN110104162A (en) * | 2019-04-28 | 2019-08-09 | 厦门大学 | A kind of solar energy flying wing with a variety of landing modes |
| CN110143275A (en) * | 2018-12-29 | 2019-08-20 | 上海歌尔泰克机器人有限公司 | Multi-rotor unmanned aerial vehicle |
| CN110267876A (en) * | 2017-05-08 | 2019-09-20 | 田瑜 | More rotor lift body aircrafts with tilting rotor |
| CN110871892A (en) * | 2018-09-01 | 2020-03-10 | 田瑜 | Aircraft vertical stabilizer with lift propeller and using method thereof |
| CN112537445A (en) * | 2020-12-16 | 2021-03-23 | 北京航空航天大学合肥创新研究院 | Rotor craft capable of tilting in flying wing layout |
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| CN105173075A (en) * | 2015-09-10 | 2015-12-23 | 南京多零无人机技术有限公司 | Tiltable hybrid rotor-wing aircraft |
| CN105270623A (en) * | 2015-10-30 | 2016-01-27 | 佛山市神风航空科技有限公司 | High lift aircraft |
| CN105447249B (en) * | 2015-11-25 | 2018-12-11 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of slow test load calculation method of power structure for pod |
| CN105447249A (en) * | 2015-11-25 | 2016-03-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Static test load calculation method for engine nacelle structure |
| CN106081060A (en) * | 2016-07-05 | 2016-11-09 | 北京航空航天大学 | A kind of VTOL composite layouts unmanned plane rotor draw off gear |
| CN106741919A (en) * | 2016-12-21 | 2017-05-31 | 顺丰科技有限公司 | A kind of fixed-wing unmanned plane of VTOL |
| CN107054669A (en) * | 2017-01-20 | 2017-08-18 | 成都前沿动力科技有限公司 | A kind of unmanned plane based on vectored thrust VTOL Flying-wing |
| CN107521686A (en) * | 2017-03-31 | 2017-12-29 | 杨爱迪 | It is a kind of can VTOL structure changes aircraft |
| CN110267876B (en) * | 2017-05-08 | 2024-02-02 | 上海峰飞航空科技有限公司 | Multi-rotor lifting body aircraft with tiltrotor |
| CN110267876A (en) * | 2017-05-08 | 2019-09-20 | 田瑜 | More rotor lift body aircrafts with tilting rotor |
| CN107187578A (en) * | 2017-05-18 | 2017-09-22 | 钟江汉 | A kind of Fixed Wing AirVehicle utilizes the wing structure for being vortexed lift-rising |
| CN107444633A (en) * | 2017-08-04 | 2017-12-08 | 杨爱迪 | Structure changes VTOL invisbile plane |
| CN110871892A (en) * | 2018-09-01 | 2020-03-10 | 田瑜 | Aircraft vertical stabilizer with lift propeller and using method thereof |
| CN110871892B (en) * | 2018-09-01 | 2023-06-23 | 上海峰飞航空科技有限公司 | Aircraft vertical stabilizer with lift propeller and method of use thereof |
| CN110143275B (en) * | 2018-12-29 | 2023-01-10 | 上海歌尔泰克机器人有限公司 | Multi-rotor unmanned aerial vehicle |
| CN110143275A (en) * | 2018-12-29 | 2019-08-20 | 上海歌尔泰克机器人有限公司 | Multi-rotor unmanned aerial vehicle |
| CN109703758A (en) * | 2019-01-14 | 2019-05-03 | 北京空天技术研究所 | Two-way all-wing aircraft flight vehicle aerodynamic shape and design method |
| CN110104162A (en) * | 2019-04-28 | 2019-08-09 | 厦门大学 | A kind of solar energy flying wing with a variety of landing modes |
| CN112537445A (en) * | 2020-12-16 | 2021-03-23 | 北京航空航天大学合肥创新研究院 | Rotor craft capable of tilting in flying wing layout |
| CN112537445B (en) * | 2020-12-16 | 2024-04-23 | 北京航空航天大学合肥创新研究院 | Flying wing layout tilting rotor aircraft |
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