CN105083550A - Fixed-wing aircraft realizing vertical take-off and landing - Google Patents
Fixed-wing aircraft realizing vertical take-off and landing Download PDFInfo
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- CN105083550A CN105083550A CN201510561114.8A CN201510561114A CN105083550A CN 105083550 A CN105083550 A CN 105083550A CN 201510561114 A CN201510561114 A CN 201510561114A CN 105083550 A CN105083550 A CN 105083550A
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- 238000009434 installation Methods 0.000 claims description 14
- 230000000737 periodic Effects 0.000 abstract 1
- 238000005096 rolling process Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 6
- 241000566150 Pandion haliaetus Species 0.000 description 5
- 241001538365 Accipiter nisus Species 0.000 description 2
- 230000001028 anti-proliferant Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000035899 viability Effects 0.000 description 1
Abstract
The invention provides a fixed-wing aircraft realizing vertical take-off and landing. The fixed-wing aircraft comprises an aircraft body, a tail and power devices provided with tilting mechanisms, wherein each power device provided with the tilting mechanism comprises a fixed-pitch propeller, an engine, an engine cabin, a slipstream rudder, a wing, a tilting wing and a steering engine, the engine is mounted in the engine cabin, the fixed-pitch propeller is connected with an output shaft of the engine, one end of the tilting wing is fixedly connected onto the engine cabin, the other end is rotationally mounted onto the wing, the slipstream rudder is movably connected onto the tilting wing, and the steering engine drives the slipstream rudder; the power devices provided with the tilting mechanisms are symmetrically arranged on two sides of the aircraft body, the wings are horizontally arranged, a through hole is formed in the head of the aircraft body, and a ducted fan is arranged in the through hole. The size of the aircraft rotor wings and the aircraft is smaller, a complex automatic tilting device and a periodic pitch-variable device are omitted, the structure is simple, the trim difficulty and flight control system complexity are reduced, the system reliability is high, and the cost is low.
Description
Technical field
The present invention relates to aircraft field, particularly a kind of vertical takeoff and landing Fixed Wing AirVehicle.
Background technology
Since 21 century, increasing aircraft development business has invested the fixed wing aircraft of vertical takeoff and landing sight, this kind of aircraft has the function similar to helicopter, do not need by runway just energy vertical and landing takeoff, aloft can be verted by power from floating state unlike, this kind of aircraft and flatly fly to accelerate and be transitioned into the offline mode of fixed-wing.
At present, practical vertical takeoff and landing fixed wing aircraft mainly AV-8 sparrow hawk formula fighter plane, V-22 osprey tilt rotor aircraft, F-35 opportunity of combat.What AV-8 sparrow hawk formula opportunity of combat adopted is flying horse driving engine, and jet engine basis have employed the rotatable thrust vectoring scheme of ejector exhaust pipe, and in actual use, this type aircraft often occurs integrity problem, is also referred to as " widow's aircraft ".V-22 osprey formula tiltrotor is a tiltrotor manufactured by American Bell Incorporated and Boeing's collaborated design, is also a medium transport aircraft.It realizes the conversion of rotor between vertical and horizontal direction by two lifting airscrews of tilting wing two ends wing tip, thus more ideally the feature of helicopter and fixed wing aircraft is combined together.Under vertical takeoff and landing state, two rotor thrust directions, perpendicular to ground, utilize auto-bank unit to keep the attitude stabilization of body longitudinal direction.V-22 osprey had both had the ability of pure helicopter vertical takeoff and landing and hovering, had again the ability of the high speed cruise flight of turboprop, was a kind of dual-use new high-tech product.At present, it is mainly used in military requirement, and can give battleficld command official and more select and greater flexibility.It does not need special airport and runway, easy to maintenance, and viability is strong, is specially adapted to carry out special operations, greatly can improve military personnel and deliver, deploy troops on garrison duty, hostile takedown, the speed of the action such as disaster relief.
But because V-22 osprey have employed two lifting airscrews, under vertical takeoff and landing pattern, rotor needs auto-bank unit to control the stable of attitude of flight vehicle, add the difficulty of control, and blade adopts feathering device, too increases cost; And osprey is under vertical takeoff and landing pattern, the positive top blast of rotor slip-stream, on aerofoil surface, causes very large pressure drag loss, and forces wing to increase structural strength, and then cause Flight Vehicle Structure weight to increase, reduce the performance of aircraft.
Summary of the invention
Based on this, the invention provides that a kind of volume is little, the simple vertical takeoff and landing Fixed Wing AirVehicle of structure.
The concrete technical scheme solved the problems of the technologies described above is as follows:
A kind of vertical takeoff and landing Fixed Wing AirVehicle, comprise fuselage, empennage and the engine installation with inclining rotary mechanism, the described engine installation with inclining rotary mechanism comprises fixedpiston screw propeller, driving engine, machinery space, slip-stream rudder, wing, tilting wing and steering wheel, driving engine is installed in machinery space, fixedpiston screw propeller is connected with the output shaft of driving engine, tilting wing one end is fixedly connected on machinery space, the other end is rotating to be connected on wing, slip-stream rudder is movably connected on tilting wing, slip-stream rudder described in servo driving, the described engine installation with inclining rotary mechanism is symmetricly set in fuselage both sides, and be horizontally disposed with for wing, described fuselage head is provided with through hole, ducted fan is established in through hole, a lift is upwards provided for giving vertical takeoff and landing Fixed Wing AirVehicle.
Wherein, described slip-stream rudderpost connects or is hingedly coupled to the end of tilting wing, and is positioned at the one end away from described fixedpiston screw propeller.
Wherein, also comprise rotating shaft, rotating shaft one end is rotating to be connected on wing, and the other end is fixedly connected on tilting wing.
Wherein, the length of described wing is the 35%-55% of fixedpiston diameter of propeller.
Wherein, described wing comprises host wing and wing flap, and wing flap is movably connected on the side of host wing, and host wing is rotationally connected with on tilting wing.
Wherein, described wing flap is articulated with the side of host wing.
Wherein, the diameter of described ducted fan is the 30%-40% of fuselage maximum width.
Wherein, the quantity of the described engine installation with inclining rotary mechanism is 2.
Wherein, described empennage is T-shaped empennage.
Vertical takeoff and landing Fixed Wing AirVehicle tool of the present invention has the following advantages and beneficial effect:
1, aircraft of the present invention, adopt preposition ducted fan and the engine installation with inclining rotary mechanism, it considerably reduces the size of rotor and vertical takeoff and landing Fixed Wing AirVehicle, eliminate complicated auto-bank unit and feathering device simultaneously, structure is simple, reduce the difficulty of trim and the complexity of flight control system, improve the reliability of system, decrease manufacturing cost; This aircraft has vertical takeoff and landing function, can not take off by runway and land, and can play very large effect, also can be used as the Small General Aircraft towards civil aviaton market in navigation, mapping, patrol, transport, warning.
2, aircraft of the present invention, when the state of aircraft vertical landing, the engine installation with inclining rotary mechanism of fuselage both sides, rotate to the direction of engine axis perpendicular to horizontal surface, fixed pitch screw propeller upwards provides lift, and preposition ducted fan starts, and provides a part of lift, and the luffing of aircraft is changed by the change of ducted fan rotating speed, realize aircraft pitch trim; Vert in process at driving engine, changed the pulling force of both sides screw propeller by the rotating speed controlling fuselage both sides driving engine, to control the motion of aircraft rolling, its rolling movement is stablized; Controlled the motion in vehicle yaw direction by the deflection of slip-stream rudder, and it is stable to make it go off course; When engine rotation to forward flat fly position time, slip-stream rudder can replace aileron, air flow deflector is made by differential, produce the rolling moment of aircraft, control the rolling movement of aircraft, make like this wing can adopt large-area wing flap, in landing process, better anti-proliferative effect is played to aircraft, considerably increase the lift coefficient of aircraft, be conducive to aircraft when taking off and reach flat quickly and fly state.
3, aircraft of the present invention, also adopt T-shaped empennage, Fixed Wing AirVehicle realizing while can keep the floating state of vertical takeoff and landing reposefully, can make the driving engine of aircraft in the process that the state of flying is verted forward, keep aspect to stablize, and aircraft finally can be entered, and fixed-wing is flat flies state.
4, aircraft of the present invention, under vertical takeoff and landing state, because fixedpiston screw propeller produces downward wind all in the scope of tilting wing, downward wind can not be there is again in the position of wing, thus make wing only bear fixedpiston screw propeller generation pulling force upwards, and the resistance produced under need not going to bear wind direction again, significantly reduce the resistance loss that wing produces fixedpiston prop-blast, thus the wind making fixedpiston screw propeller produce all is utilized, improve the output efficiency of fixedpiston propeller power.
Accompanying drawing explanation
Fig. 1 is the structural representation of vertical takeoff and landing Fixed Wing AirVehicle of the present invention.
Fig. 2 is the structural representation that vertical takeoff and landing Fixed Wing AirVehicle of the present invention puts down when flying state.
Fig. 3 is that the driving engine of vertical takeoff and landing Fixed Wing AirVehicle of the present invention verts to horizontal by structural representation when 45 °.
Accompanying drawing explanation
1, fuselage; 2, tilting wing; 3, machinery space; 4, fixedpiston screw propeller; 5, host wing; 6, wing flap; 7, ducted fan; 8, empennage; 9, tailplane; 10, vertical tail; 11, Fuselage connection; 12, slip-stream rudder.
Detailed description of the invention
Below with reference to specific embodiment, the present invention will be further described.
Embodiment 1
Vertical takeoff and landing Fixed Wing AirVehicle described in the present embodiment, see Fig. 1-3, it comprises fuselage 1, empennage 8 and 2 engine installations with inclining rotary mechanism, the described engine installation with inclining rotary mechanism comprises fixedpiston screw propeller 4, driving engine (not shown in FIG.), slip-stream rudder 12, wing, tilting wing 2, machinery space 3 and steering wheel (not shown in FIG.), driving engine is installed in machinery space 3, fixedpiston screw propeller 4 is connected with the output shaft of driving engine, tilting wing 2 one end is fixedly connected on machinery space 3, the other end is rotating to be connected on wing, slip-stream rudder 12 is movably connected on tilting wing 2, slip-stream rudder 12 described in servo driving, the described engine installation with inclining rotary mechanism is symmetricly set in fuselage 1 both sides, and be connected on fuselage 1 by connecting portion, and be horizontally disposed with for wing, described fuselage 1 head is provided with through hole, ducted fan 7 is established in through hole, a lift is upwards provided for giving vertical takeoff and landing Fixed Wing AirVehicle.
In a particular embodiment, described slip-stream rudder 12 axle connects or is hingedly coupled to the end of tilting wing 2, and is positioned at the one end away from described fixedpiston screw propeller 4.
In a particular embodiment, also comprise rotating shaft, rotating shaft one end is rotating to be connected on wing, and the other end is fixedly connected on tilting wing 2.
In a particular embodiment, described wing comprises host wing 5 and wing flap 6, and wing flap 6 is movably connected on the side of host wing 5, and host wing 5 is rotationally connected with on tilting wing 2.
In a particular embodiment, the diameter of described ducted fan 7 is the 30%-40% of fuselage 1 maximum width.
When the state of aircraft vertical landing, the engine installation with inclining rotary mechanism of fuselage 1 both sides, rotate to the direction of engine axis perpendicular to horizontal surface, fixed pitch screw propeller upwards provides lift, preposition ducted fan 7 starts, a part of lift is provided, and changes the luffing of aircraft by the change of ducted fan 7 rotating speed, realize aircraft pitch trim; Vert in process at driving engine, changed the pulling force of both sides screw propeller by the rotating speed controlling fuselage 1 both sides driving engine, to control the motion of aircraft rolling, its rolling movement is stablized; Controlled the motion in vehicle yaw direction by the deflection of slip-stream rudder 12, and it is stable to make it go off course; When engine rotation to forward flat fly position time, slip-stream rudder 12 can replace aileron, air flow deflector is made by differential, produce the rolling moment of aircraft, control the rolling movement of aircraft, make like this wing to adopt large-area wing flap 6, in landing process, better anti-proliferative effect is played to aircraft, considerably increase the lift coefficient of aircraft, be conducive to aircraft when taking off and reach flat quickly and fly state.T-shaped empennage 8 (namely comprising tailplane 10 and vertical tail 9) is adopted in the present embodiment, Fixed Wing AirVehicle realizing while can keep the floating state of vertical takeoff and landing reposefully, can make the driving engine of aircraft in the process that the state of flying is verted forward, keep aspect to stablize, and aircraft finally can be entered, and fixed-wing is flat flies state.
In a particular embodiment, the length of described wing is the 35%-55% of fixedpiston screw propeller 4 diameter.
Preferably, the length of described wing is the 40%-50% of fixedpiston screw propeller 4 diameter.
More have choosing, the length of described wing is the 40%-45% of fixedpiston screw propeller 4 diameter.
In a particular embodiment, the described engine installation with inclining rotary mechanism also comprises rotating shaft, and rotating shaft one end is rotating to be connected on wing, and the other end is fixedly connected on tilting wing 2.
Below be only the preferred embodiment of the present invention, protection scope of the present invention be not only confined to above-described embodiment, all technical schemes belonged under thinking of the present invention all belong to protection scope of the present invention.It should be pointed out that for those skilled in the art, some improvement without departing from the principles of the present invention and polishing, should be considered as protection scope of the present invention.
Claims (9)
1. a vertical takeoff and landing Fixed Wing AirVehicle, it is characterized in that, comprise fuselage, empennage and the engine installation with inclining rotary mechanism, the described engine installation with inclining rotary mechanism comprises fixedpiston screw propeller, driving engine, machinery space, slip-stream rudder, wing, tilting wing and steering wheel, driving engine is installed in machinery space, fixedpiston screw propeller is connected with the output shaft of driving engine, tilting wing one end is fixedly connected on machinery space, the other end is rotating to be connected on wing, slip-stream rudder is movably connected on tilting wing, slip-stream rudder described in servo driving, the described engine installation with inclining rotary mechanism is symmetricly set in fuselage both sides, and be horizontally disposed with for wing, described fuselage head is provided with through hole, ducted fan is established in through hole, a lift is upwards provided for giving vertical takeoff and landing Fixed Wing AirVehicle.
2. vertical takeoff and landing Fixed Wing AirVehicle according to claim 1, is characterized in that, described slip-stream rudderpost connects or is hingedly coupled to the end of tilting wing, and is positioned at the one end away from described fixedpiston screw propeller.
3. vertical takeoff and landing Fixed Wing AirVehicle according to claim 2, is characterized in that, also comprise rotating shaft, and rotating shaft one end is rotating to be connected on wing, and the other end is fixedly connected on tilting wing.
4. the vertical takeoff and landing Fixed Wing AirVehicle according to any one of claim 1-3, is characterized in that, the length of described wing is the 35%-55% of fixedpiston diameter of propeller.
5. the vertical takeoff and landing Fixed Wing AirVehicle according to any one of claim 1-3, it is characterized in that, described wing comprises host wing and wing flap, wing flap is movably connected on the side of host wing, and host wing is rotationally connected with on tilting wing.
6. vertical takeoff and landing Fixed Wing AirVehicle according to claim 5, is characterized in that, described wing flap is articulated with the side of host wing.
7. the vertical takeoff and landing Fixed Wing AirVehicle according to any one of claim 1-3, is characterized in that, the diameter of described ducted fan is the 30%-40% of fuselage maximum width.
8. the vertical takeoff and landing Fixed Wing AirVehicle according to any one of claim 1-3, is characterized in that, the quantity of the described engine installation with inclining rotary mechanism is 2.
9. the vertical takeoff and landing Fixed Wing AirVehicle according to any one of claim 1-3, is characterized in that, described empennage is T-shaped empennage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510561114.8A CN105083550A (en) | 2015-09-06 | 2015-09-06 | Fixed-wing aircraft realizing vertical take-off and landing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510561114.8A CN105083550A (en) | 2015-09-06 | 2015-09-06 | Fixed-wing aircraft realizing vertical take-off and landing |
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| Publication Number | Publication Date |
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| CN105083550A true CN105083550A (en) | 2015-11-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510561114.8A Pending CN105083550A (en) | 2015-09-06 | 2015-09-06 | Fixed-wing aircraft realizing vertical take-off and landing |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516100A (en) * | 2016-09-11 | 2017-03-22 | 珠海市磐石电子科技有限公司 | Vertical takeoff and landing aircraft |
| CN106864755A (en) * | 2015-12-11 | 2017-06-20 | 中国航空工业集团公司成都飞机设计研究所 | It is a kind of not only can Horizontal Take-off and Landing but also can VTOL aircraft layout |
| CN111332465A (en) * | 2019-12-09 | 2020-06-26 | 湖北航天飞行器研究所 | Propeller and ducted fan combined type tilt rotor unmanned aerial vehicle and flight mode |
| CN113044212A (en) * | 2019-12-26 | 2021-06-29 | 中国科学院沈阳自动化研究所 | Medium-sized tilt rotor unmanned aerial vehicle |
-
2015
- 2015-09-06 CN CN201510561114.8A patent/CN105083550A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106864755A (en) * | 2015-12-11 | 2017-06-20 | 中国航空工业集团公司成都飞机设计研究所 | It is a kind of not only can Horizontal Take-off and Landing but also can VTOL aircraft layout |
| CN106516100A (en) * | 2016-09-11 | 2017-03-22 | 珠海市磐石电子科技有限公司 | Vertical takeoff and landing aircraft |
| CN111332465A (en) * | 2019-12-09 | 2020-06-26 | 湖北航天飞行器研究所 | Propeller and ducted fan combined type tilt rotor unmanned aerial vehicle and flight mode |
| CN111332465B (en) * | 2019-12-09 | 2022-01-21 | 湖北航天飞行器研究所 | Propeller and ducted fan combined type tilt rotor unmanned aerial vehicle and flight mode |
| CN113044212A (en) * | 2019-12-26 | 2021-06-29 | 中国科学院沈阳自动化研究所 | Medium-sized tilt rotor unmanned aerial vehicle |
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Address after: 410205 Hunan province Changsha High-tech Development Zone Lugu Road No. 627 sea science and Technology Industrial Park B-1 building accelerator production workshop 902 Applicant after: HUNAN AIRTOPS INTELLIGENT TECHNOLOGY CO., LTD. Address before: 410205 Hunan province Changsha City Lugu high tech Development Zone, Road No. 627 new Changhai Lugu B-2 center building workshop 3 floor of No. 303 Applicant before: CHANGSHA HONGLANG AUTOMATION TECHNOLOGY CO., LTD. |
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Application publication date: 20151125 |
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