CN103171764A - Perpendicular/short-distance lifting warplane with two retractable rotor wings - Google Patents
Perpendicular/short-distance lifting warplane with two retractable rotor wings Download PDFInfo
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- CN103171764A CN103171764A CN2013101097762A CN201310109776A CN103171764A CN 103171764 A CN103171764 A CN 103171764A CN 2013101097762 A CN2013101097762 A CN 2013101097762A CN 201310109776 A CN201310109776 A CN 201310109776A CN 103171764 A CN103171764 A CN 103171764A
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Abstract
The invention discloses a perpendicular/short-distance lifting warplane with two retractable rotor wings. Besides components of the common warplane, the perpendicular/short-distance lifting warplane is provided with the rotor wings (1), a vector tail spraying port (3), a transmission mechanism (4), a speed reduction and clutch mechanism (5), a supporting truss (7), a rotating shaft (6) arranged at a joint of the supporting truss (7) and a plane body, rotor wing bins (8) arranged on two sides of the plane body, cabin doors (9) of the rotor wing bins (8), and a slippage flow rudder (10), so that the warplane can work under one out of a perpendicular lifting mode, a short-distance lifting mode and a patrolling mode. In the perpendicular lifting mode, the rotor wings are outwards expanded, and the vector tail spraying port is downwards deflected by 90 degrees; power is supplied to the rotor wings through the speed reduction and clutch mechanism; the power of a turbofan engine is rationally distributed to the rotor wings and the vector tail spraying port, so that the lifting force is produced jointly by the rotor wings and the vector tail spraying port; in the short-distance lifting mode, the vector tail spraying port produces forwards thrust; in the patrolling mode, the speed reduction and clutch mechanism stops supplying power to the rotor wings; the supporting truss, the slippage flow rudder and the rotor wings are collected into the rotor wing bin through the rotating shaft; and the cabin doors are closed, so that the original attractive pneumatic appearance of the warplane can be kept.
Description
Technical field
But the present invention relates to a kind of fighter plane of V/STOL, belong to fixed wing aircraft design field in aviation aircraft.
Background technology
Vertical takeoff and landing and short take-off and landing (STOL) technology be as one of cutting edge technology of fighter plane development, in recent decades the development along with the improvement of thrust vectoring system.Compare and can only carry out the fighter plane of CTOL, the fighter plane with V/STOL ability has following many advantages:
1. little to the dependence on airport, can be on the airport of breakage, simple and crude air strip landing, in case of necessity even can be in highway, roof, vacant lot landing, viability improves greatly.
2. be more suitable for being deployed on aircraft carrier, can thering is no landing on the aircraft carrier of ejector, can increase the carrier aircraft quantity of aircraft carrier simultaneously.
3. have hover capabilities, be more suitable for carrying out special assignment.
Because fighter plane adopts whirlpool spray or fanjet more, adopt F402-RR-406 type fanjet as Britain " sparrow hawk " formula, these two kinds of driving engines are in the inefficiency of hovering phase, cause the hovering phase consumption of fuel huge, thereby have a strong impact on voyage, and the bullet-loading capacity when adopting vertical takeoff and landing is restricted.
Summary of the invention
The present invention is conceived to have vertically and the design of the fighter plane of short take-off and landing (STOL) (V/STOL) ability.Before the center of gravity of fighter plane, two rotors are arranged in the fuselage both sides, with the transmission of power of driving engine to rotor, make rotor directly produce lift, change the fanjet thrust direction by the deflection vector nozzle simultaneously, change all or part of thrust into lift, and common enough lift and the balancing torque of producing of rotor, realize the V/STOL under the control of vertical direction direct force, make aircraft have simultaneously the ability of vertical and short take-off and landing (STOL).
In the cruising phase of fighter plane, rotor can be closed in the rotor cabin of fuselage side, thereby not affect the whole aeroperformance of aircraft.
According to an aspect of the present invention, a kind of fighter plane that possesses the V/STOL ability is provided, it is except each assembly of common fighter plane, also add: the hatch door in rotor, vector tail nozzle, transmission device, deceleration-engaging and disengaging gear, sub-truss, the turning cylinder that is arranged on sub-truss 7 and fuselage junction, the rotor cabin that is arranged on the fuselage both sides, rotor cabin, be connected in the slip-stream rudder on sub-truss, thereby make described fight function in vertical takeoff and landing mode, short take-off and landing (STOL) mode and the work under one of three kinds of different operation modes of mode of cruising.
According to an aspect of the present invention, a kind of fighter plane that possesses the ability of V/STOL is provided, it is except each assembly of common fighter plane, also add: the hatch door in rotor, vector tail nozzle, transmission device, deceleration-engaging and disengaging gear, sub-truss, the turning cylinder that is arranged on sub-truss and fuselage junction, the rotor cabin that is arranged on the fuselage both sides, rotor cabin, be connected in the slip-stream rudder on sub-truss, thereby make described fight function in vertical takeoff and landing mode, short take-off and landing (STOL) mode and the work under one of three kinds of different operation modes of mode of cruising.
Description of drawings
Fig. 1 is the diagrammatic top view of fighter plane according to an embodiment of the invention.
Fig. 2 is the diagrammatic elevation view of fighter plane embodiment as shown in Figure 1.
Fig. 3 is the diagrammatic side view of fighter plane embodiment as shown in Figure 1.
Reference numeral:
[1] rotor [2] fanjet [3] vector tail nozzle
[4] transmission device [5] deceleration, engaging and disengaging gear [6] turning cylinder
[7] sub-truss [8] rotor cabin [9] hatch door
[10] slip-stream rudder
The specific embodiment
This programme makes it to possess the ability of V/STOL by transforming on commonly used fighter plane layout basis at present.Fighter plane according to an embodiment of the invention adds and comprises rotor 1, vector tail nozzle 3, transmission device 4, deceleration-engaging and disengaging gear 5, sub-truss 7, rotor cabin 8 and slip-stream rudder 10.Concrete layout according to an embodiment of the invention is seen Fig. 1-3.
Fighter plane layout according to an embodiment of the invention is supported vertical takeoff and landing, short take-off and landing (STOL) and the three kinds of different operation modes that cruise, wherein:
-vertical takeoff and landing mode: rotor 1 outwards launches, vector tail nozzle 3 times inclined to one side 90 ° (Fig. 3), fanjet 2 provides power by deceleration-engaging and disengaging gear 5 to rotor 1, the power of fanjet 2 is reasonably allocated to rotor 1 and vector tail nozzle 3, overcome gravity by rotor 1 and the common lift that produces of vector tail nozzle 3, do not produce thrust forward.
In the vertical takeoff and landing stage:
1) by the poor roll stability of keeping of the pulling force of controlling two rotors 1.
2) keep pitching stability by the pulling force of control rotor 1 and the thrust of fanjet 2.
3) keep course stability by the horizontal direction finding deflection of controlling vector tail nozzle 3 and the slip-stream rudder 10 that is connected on sub-truss 7.
-short take-off and landing (STOL) mode: in the take-off and landing stage, rotor 1 outwards launches, rotate under the driving of fanjet 2, make rotor 1 directly produce lift, 3 times partially suitable angles of vector tail nozzle promote to produce when fighter plane is sliding to be run certain lift, and the lift that rotor 1 and fanjet 2 directly produce can replace the aerodynamic lift of part CTOL institute palpus, reduce minimum flying speed, thereby realize short take-off and landing (STOL).Usually during the CTOL of fighter plane in order to overcome nose-down pitching moment, inclined to one side on elevating rudder, therefore elevating rudder produce negative lift, but in this programme because rotor 1 produces larger nose-up pitching moment, the nose-down pitching moment that but the balance high coefficient of lift combined is taken off, produce when landing, elevating rudder can be following partially to produce positive lift force simultaneously, makes the aircraft minimum flying speed further reduce.
In the short take-off and landing (STOL) stage:
1) by the poor roll stability of keeping of the pulling force of controlling two rotors 1.
2) keep pitching stability by the pulling force of controlling rotor 1, thrust and the elevating rudder deflection of fanjet 2.
3) the slip-stream rudder 10 and the yaw rudder that are connected on sub-truss 7 by control are kept course stability.
4) jointly provide lift by the pulling force of rotor 1, part thrust and the aerodynamic force of fanjet 2.
5) provide forward thrust by fanjet 2.
-the mode of cruising: when aircraft enters cruising phase, stop providing power to rotor 1 by deceleration-engaging and disengaging gear 5, in the rotor cabin 8 of turning cylinder 6 by sub-truss 7 and fuselage junction with sub-truss 7, slip-stream rudder 10 and rotor 1 income fuselage both sides, and shut hatch door 9 to keep the original good aerodynamic configuration of fighter plane.The fighter plane of this stage the present embodiment and general fighter plane are as broad as long.
In order to make fighter plane have larger bullet-loading capacity and fuel load, can adopt short takeoff vertical landing (STO/VL).
Advantage of the present invention and effect comprise
Compare with existing fighter plane vertical takeoff and landing technology, the present invention has the following advantages:
1 added weight is light, and volume is little.Very little on the impact of the aspects such as the cruise performance of fighter plane, Stealth Fighter, manoevreability.
2 is little on the center-of-gravity position impact of aircraft.
3 is less on the impact of aircraft overall structure.
4 in the such low speed situation of V/STOL, larger rotor disk area has guaranteed that the lift efficient of rotor is in theory higher than existing pure jet-propelled vertical take off and landing fighter (as: AV-8B sparrow hawk formula fighter plane) and ducted fan assist type vertical take off and landing fighter (as F-35B), so with the part transmission of power of jet engine to large rotor, the efficient that produces lift is higher, thereby reduce oil consumption, improve lift, make fighter plane have larger bullet-loading capacity and voyage.
5 structures are comparatively simple, and the maintenance time at unit pilot time reduces greatly.
In sum, vertical and short take-off and landing (STOL) technology of the present invention is a kind of scheme of excellent combination property.
Claims (5)
1. fighter plane that possesses the ability of V/STOL, it also adds except each assembly of common fighter plane:
Rotor (1),
Vector tail nozzle (3),
Transmission device (4),
Deceleration-engaging and disengaging gear (5),
Sub-truss (7),
Be arranged on the turning cylinder (6) of sub-truss (7) and fuselage junction,
Be arranged on the rotor cabin (8) of fuselage both sides,
The hatch door (9) in rotor cabin (8),
Be connected in the slip-stream rudder (10) on sub-truss (7),
Thereby make described fight function in vertical takeoff and landing mode, short take-off and landing (STOL) mode and the work under one of three kinds of different operation modes of mode of cruising.
2. according to claim 1 fighter plane is characterized in that:
Under vertical takeoff and landing mode, rotor (1) outwards launches, lower inclined to one side 90 ° of vector tail nozzle (3), provide power by deceleration-engaging and disengaging gear (5) to rotor (1), the power of fanjet (2) is reasonably allocated to rotor (1) and vector tail nozzle (3), jointly produce lift by rotor (1) and vector tail nozzle (3) and overcome gravity, do not produce thrust forward.
3. according to claim 1 and 2 fighter plane, is characterized in that
Described fighter plane also can be operated under the short take-off and landing (STOL) mode in take-off and landing stage, under short take-off and landing (STOL) mode, rotor (1) outwards launches, rotate under the driving of fanjet (2), make rotor (1) directly produce lift, owing to producing simultaneously larger nose-up pitching moment, but the balance high coefficient of lift combined is taken off, the nose-down pitching moment that produces when landing, make aircraft can adopt larger lift coefficient to take off, land, reduce minimum flying speed.
4. according to claim 1 and 2 fighter plane, is characterized in that
Under the mode of cruising, stop providing power to rotor (1) by deceleration-engaging and disengaging gear (5), by turning cylinder (6), sub-truss (7), slip-stream rudder (10) and rotor (1) are taken in rotor cabin (8), and shut hatch door (9) to keep the original good aerodynamic configuration of fighter plane.
5. according to claim 2 fighter plane is characterized in that:
Under vertical takeoff and landing mode:
-by controlling the poor roll stability of keeping of pulling force of two rotors (1),
-keep pitching stability by the pulling force of control rotor (1) and the thrust of fanjet (2),
-keep course stability by the horizontal lateral deflection of controlling vector tail nozzle (3) and the slip-stream rudder (10) that is connected on sub-truss (7), 6, fighter plane according to claim 3, it is characterized in that:
-by the poor roll stability of keeping of the pulling force of controlling two rotors 1,
-keep pitching stability by the pulling force of controlling rotor 1, thrust and the elevating rudder deflection of fanjet 2,
-slip-stream the rudder 10 and the yaw rudder that are connected on sub-truss 7 by control kept course stability,
-jointly provide lift by the pulling force of rotor 1, part thrust and the aerodynamic force of fanjet 2,
-provide forward thrust by fanjet 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310109776.2A CN103171764B (en) | 2013-03-29 | Having can the vertical/STOL fighter plane of folding and unfolding DCB Specimen |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310109776.2A CN103171764B (en) | 2013-03-29 | Having can the vertical/STOL fighter plane of folding and unfolding DCB Specimen |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103171764A true CN103171764A (en) | 2013-06-26 |
| CN103171764B CN103171764B (en) | 2016-11-30 |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103640696A (en) * | 2013-12-05 | 2014-03-19 | 新誉集团有限公司 | Vertical touchdown type unmanned aerial vehicle and control method thereof |
| CN104554733A (en) * | 2013-10-14 | 2015-04-29 | 姜文睿 | Jet engine capable of flexibly changing angle of jet engine body relative to airframe |
| WO2017025060A1 (en) * | 2015-08-12 | 2017-02-16 | 刘十一 | Fixed-wing aircraft capable of taking off and landing vertically, and flight control method therefor |
| CN106428547A (en) * | 2015-08-12 | 2017-02-22 | 刘十 | Perpendicular take-off and landing fixed-wing aircraft with multiple automatic retractable rotors |
| 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 |
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN112793773A (en) * | 2021-04-02 | 2021-05-14 | 成都云鼎智控科技有限公司 | Vertical take-off and landing unmanned aerial vehicle and driving method thereof |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
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| DE20303024U1 (en) * | 2002-09-06 | 2003-08-14 | Hinueber Edgar V | Combination aircraft has rotor lift for telescoping of rotor power unit and makes it possible for rotor drive to be withdrawn completely from aerodynamic influence in plane flying by recessing into fuselage or to extend it from fuselage |
| CN101204991A (en) * | 2007-09-28 | 2008-06-25 | 深圳市艾特航模有限公司 | Four channel row two-bladed helicopter |
| CN101602403A (en) * | 2008-06-12 | 2009-12-16 | 张庆柳 | Vertical take-off and landing aircraft (VTOL aircraft) |
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| US3907219A (en) * | 1972-10-16 | 1975-09-23 | Jack W Pharris | High speed, long range turbo-jet aircraft |
| DE20303024U1 (en) * | 2002-09-06 | 2003-08-14 | Hinueber Edgar V | Combination aircraft has rotor lift for telescoping of rotor power unit and makes it possible for rotor drive to be withdrawn completely from aerodynamic influence in plane flying by recessing into fuselage or to extend it from fuselage |
| CN101204991A (en) * | 2007-09-28 | 2008-06-25 | 深圳市艾特航模有限公司 | Four channel row two-bladed helicopter |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554733A (en) * | 2013-10-14 | 2015-04-29 | 姜文睿 | Jet engine capable of flexibly changing angle of jet engine body relative to airframe |
| CN103640696A (en) * | 2013-12-05 | 2014-03-19 | 新誉集团有限公司 | Vertical touchdown type unmanned aerial vehicle and control method thereof |
| EP3335989A4 (en) * | 2015-08-12 | 2019-02-13 | Shanghai Fukun Aviation Technology Co., Ltd | Fixed-wing aircraft capable of taking off and landing vertically, and flight control method therefor |
| CN106428547A (en) * | 2015-08-12 | 2017-02-22 | 刘十 | Perpendicular take-off and landing fixed-wing aircraft with multiple automatic retractable rotors |
| WO2017025060A1 (en) * | 2015-08-12 | 2017-02-16 | 刘十一 | Fixed-wing aircraft capable of taking off and landing vertically, and flight control method therefor |
| AU2016305704B2 (en) * | 2015-08-12 | 2019-03-07 | Shanghai Fukun Aviation Technology Co., Ltd | Vertical take-off and landing Fixed-wing aircraft and the flight control method thereof |
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US10875658B2 (en) | 2015-09-02 | 2020-12-29 | Jetoptera, Inc. | Ejector and airfoil configurations |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN107521686A (en) * | 2017-03-31 | 2017-12-29 | 杨爱迪 | It is a kind of can VTOL structure changes aircraft |
| US11148801B2 (en) | 2017-06-27 | 2021-10-19 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN107444633A (en) * | 2017-08-04 | 2017-12-08 | 杨爱迪 | Structure changes VTOL invisbile plane |
| CN112793773A (en) * | 2021-04-02 | 2021-05-14 | 成都云鼎智控科技有限公司 | Vertical take-off and landing unmanned aerial vehicle and driving method thereof |
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Granted publication date: 20161130 Termination date: 20170329 |
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