CN205022861U - VTOL fixed wing aircraft - Google Patents
VTOL fixed wing aircraft Download PDFInfo
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- CN205022861U CN205022861U CN201520681912.XU CN201520681912U CN205022861U CN 205022861 U CN205022861 U CN 205022861U CN 201520681912 U CN201520681912 U CN 201520681912U CN 205022861 U CN205022861 U CN 205022861U
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- 230000007246 mechanism Effects 0.000 claims abstract description 18
- 238000009434 installation Methods 0.000 claims description 15
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 abstract description 2
- 238000006073 displacement reaction Methods 0.000 abstract 1
- 238000005096 rolling process Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 241000566150 Pandion haliaetus Species 0.000 description 5
- 241001538365 Accipiter nisus Species 0.000 description 2
- 230000001028 anti-proliverative effect Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000035899 viability Effects 0.000 description 1
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Abstract
A VTOL fixed wing aircraft, including fuselage, fin with have the power device of the mechanism of verting, the power device that has a mechanism of verting is including fixed pitch screw, engine, engine compartment, slipstream rudder, wing, tilting wing and steering wheel, the engine mounting in engine compartment, the output shaft of fixed pitch screw and engine, fixed connection is on engine compartment for tilting wing one end, the rotatable connection of the other end on the wing, slipstream rudder swing joint on the tilting wing, steering engine driving the slipstream rudder, the power device symmetry that has the mechanism of verting sets up in the fuselage both sides, and for the wing level sets up, the fuselage head is equipped with the through -hole, establishes the ducted fan in the through -hole. The utility model discloses the size of aircraft rotor and aircraft is less, and saves complicated auto -bank unit and cycle displacement device, and simple structure has reduced the degree of difficulty of trim and flight control's complexity, and system reliability is high, with low costs.
Description
Technical field
The utility model 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.
Utility model content
Based on this, the utility model 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 described in the utility model has the following advantages and beneficial effect:
1, aircraft described in the utility model, 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 described in the utility model, 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 described in the utility model, 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 described in the utility model, 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 described in the utility model.
Fig. 2 is the structural representation that vertical takeoff and landing Fixed Wing AirVehicle described in the utility model puts down when flying state.
Fig. 3 is that the driving engine of vertical takeoff and landing Fixed Wing AirVehicle described in the utility model 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 utility model is described further.
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 preferred implementation of the present utility model, protection domain of the present utility model be not only confined to above-described embodiment, all technical schemes belonged under the utility model thinking all belong to protection domain of the present utility model.It should be pointed out that for those skilled in the art, in the some improvement do not departed under the utility model principle prerequisite and polishing, protection domain of the present utility model should be considered as.
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 |
|---|---|---|---|
| CN201520681912.XU CN205022861U (en) | 2015-09-06 | 2015-09-06 | VTOL fixed wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520681912.XU CN205022861U (en) | 2015-09-06 | 2015-09-06 | VTOL fixed wing aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN205022861U true CN205022861U (en) | 2016-02-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520681912.XU Expired - Fee Related CN205022861U (en) | 2015-09-06 | 2015-09-06 | VTOL fixed wing aircraft |
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| CN (1) | CN205022861U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109080824A (en) * | 2018-08-24 | 2018-12-25 | 中国民航大学 | A kind of Fixed Wing AirVehicle with tilted propeller |
| WO2019007101A1 (en) * | 2017-07-06 | 2019-01-10 | 深圳市道通智能航空技术有限公司 | Flight vehicle, tilt driving mechanism and control method therefor |
| CN109466763A (en) * | 2018-12-05 | 2019-03-15 | 湖南大学 | An aircraft with retractable rotors and a flight method |
| CN109606672A (en) * | 2017-10-04 | 2019-04-12 | 贝尔直升机德事隆公司 | Tilting rotor formula aircraft with the rear rotor that can be verted downwards |
| CN109649649A (en) * | 2019-01-21 | 2019-04-19 | 合肥工业大学 | Tiltrotor aircraft |
| CN112093030A (en) * | 2020-10-21 | 2020-12-18 | 北京云圣智能科技有限责任公司 | Tandem wing tilt rotor aircraft and aircraft manufacturing method |
| US10894600B2 (en) | 2017-07-06 | 2021-01-19 | Autel Robotics Co., Ltd. | Aircraft, tilt driving mechanism and control method thereof |
| CN113753230A (en) * | 2021-10-11 | 2021-12-07 | 广东汇天航空航天科技有限公司 | Aircraft, wing subassembly and hovercar |
-
2015
- 2015-09-06 CN CN201520681912.XU patent/CN205022861U/en not_active Expired - Fee Related
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019007101A1 (en) * | 2017-07-06 | 2019-01-10 | 深圳市道通智能航空技术有限公司 | Flight vehicle, tilt driving mechanism and control method therefor |
| US10894600B2 (en) | 2017-07-06 | 2021-01-19 | Autel Robotics Co., Ltd. | Aircraft, tilt driving mechanism and control method thereof |
| CN109606672A (en) * | 2017-10-04 | 2019-04-12 | 贝尔直升机德事隆公司 | Tilting rotor formula aircraft with the rear rotor that can be verted downwards |
| CN109606672B (en) * | 2017-10-04 | 2022-05-03 | 德事隆创新公司 | Tilt rotor aircraft with a downwardly tiltable rear rotor |
| CN109080824A (en) * | 2018-08-24 | 2018-12-25 | 中国民航大学 | A kind of Fixed Wing AirVehicle with tilted propeller |
| CN109466763A (en) * | 2018-12-05 | 2019-03-15 | 湖南大学 | An aircraft with retractable rotors and a flight method |
| CN109466763B (en) * | 2018-12-05 | 2021-06-25 | 湖南大学 | An aircraft with retractable rotors and a flight method |
| CN109649649A (en) * | 2019-01-21 | 2019-04-19 | 合肥工业大学 | Tiltrotor aircraft |
| CN109649649B (en) * | 2019-01-21 | 2021-08-20 | 合肥工业大学 | tilt-rotor aircraft |
| CN112093030A (en) * | 2020-10-21 | 2020-12-18 | 北京云圣智能科技有限责任公司 | Tandem wing tilt rotor aircraft and aircraft manufacturing method |
| CN113753230A (en) * | 2021-10-11 | 2021-12-07 | 广东汇天航空航天科技有限公司 | Aircraft, wing subassembly and hovercar |
| CN113753230B (en) * | 2021-10-11 | 2023-08-18 | 广东汇天航空航天科技有限公司 | Aircraft, wing assembly and aerocar |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| 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: 20160210 Termination date: 20170906 |