CN101870355A - Coaxial double-rotary wing and tilt wing aircraft - Google Patents
Coaxial double-rotary wing and tilt wing aircraft Download PDFInfo
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- CN101870355A CN101870355A CN 201010190834 CN201010190834A CN101870355A CN 101870355 A CN101870355 A CN 101870355A CN 201010190834 CN201010190834 CN 201010190834 CN 201010190834 A CN201010190834 A CN 201010190834A CN 101870355 A CN101870355 A CN 101870355A
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Abstract
The invention relates to a coaxial double-rotary wing and tilt wing aircraft. An outer shaft of an aircraft body is connected with a door type outer deflecting bracket; double rigid coaxial rotary wings are installed on the top of the bracket; a main wing of the aircraft is installed on the outer side of the bracket; an engine is installed above the root of an aerofoil and connected with the double rigid coaxial rotary wings at the top ends by a rotating shaft in the bracket; and the door type outer deflecting bracket together with the aerofoil and the engine can integrally deflect. The invention has the characteristics of high speed and remote voyage like a fixed wing aircraft and can be safely and stably lifted and hovered vertically like a helicopter. A brand new flight control way by adopting the door type outer deflecting bracket to directly change the directions of the rotary wings and adopting the aerofoil and a wing flap to change downwash airflow for controlling a flight attitude avoids a complex flight control system of the traditional helicopter and a tilt wing aircraft.
Description
Affiliated technical field
The present invention relates to a kind of aircraft, can also can fly with the stable vertical or sliding race of the short range landing of helicopter mode with fixed wing aircraft mode fast speed heavy.Significantly improve the ability of carrier adaptation different task.
Background technology
At present, known tilt-wing aircraft is mostly taked the transport plane body as U.S. V-22 both at home and abroad, by the whole deflection of engine nacelle, drive that fuselage both sides rotor is done vertical takeoff and landing or fixed-wing is flat flies, possessed short distance, vertically played ability, the aerial advantage of flight fast.
But lifting aircraft flight just because of adopt the both sides rotor, its stability can not show a candle to the helicopter of taking a rotor shaft, and existing tilt-wing aircraft is big from being converted to by rotor lift by airfoil lift manipulation control difficulty, and machinery is complicated, single-engine flight ability shortcoming, safety is not high, cost an arm and a leg, the while aircraft is wing and meeting stop portions rotor air-flow when taking off, loss part engine power, be unfavorable for the raising of fuel efficiency, influenced capacity weight and voyage.
These very important defectives cause tilt-wing aircraft to be difficult to a large amount of equipments as pure helicopter, use flexibly, drop into practical manned tilt-wing aircraft at present, and the V-22 series of U.S. army is also only arranged.
And the flight control system of existing helicopter is all very complicated, cycle is apart from control system, always apart from the technical barrier that can't avoid during control system, anti-torsion control system all are pure helicopter design, this causes aircraft machinery complicated, and the Maintenance and Repair work capacity is bigger, and use cost is higher.
Simultaneously existing helicopter since when high-speed flight the forward momentum of helicopter can increase air velocity by advancing blade, reduce the speed of retreating blade simultaneously, the speed of screw blade in high-speed operation just may reach hyprsonic, and the cooresponding screw blade of opposite side is in the rim condition of stall, and this maximum speed that has limited pure helicopter can only be about 300 kilometers/hour.
Summary of the invention
Defectives such as, technology not high at existing tilt-wing aircraft poor stability, safety is responsible for, operation easier is big, cost an arm and a leg the invention provides a kind of high flight stability, and can melt fixed wing aircraft and the helicopter advantage is a kind of aircraft of one.It had both had the fast and voyage characteristics far away of fixed wing aircraft speed, can and hover as safe, the stable vertical takeoff and landing of helicopter again, and in brand new flicon mode, simplify the flight control system of conventional helicopters and tilt-wing aircraft complexity.
The technical solution adopted for the present invention to solve the technical problems is:
For possessing the fixed-wing of change flight performance, the present invention has adopted the outer gate-type driving engine deflection support of body, in similar common outer setting of going straight up to airframe the one door type outer support, the top dress rigid coaxial bispin wing of support, driving engine and large-scale fixed-wing are installed on the outside of portal support, and driving engine is connected with the rigid coaxial bispin wing of cantilever tip by the transmission shaft in the support.Portal support bottom axle is connected in manned body both sides near near the center of gravity.Whole flying power system, most of flight control system are all separated with the aircraft main body, and rely on rotating shaft under the situation that does not change the airframe attitude, to realize the change of rotor system lead.In the helicopter flight pattern: portal support is perpendicular to fuselage, and the rigid coaxial bispin wing produces gas washing stream down, supports hang and vertical takeoff and landing.During big load short take-off and landing (STOL): the portal support certain angle that turns forward, the rigid coaxial bispin wing produces air-flow to the back lower place, and rotor pulling aircraft is made short take-off and landing (STOL).When needing the high-speed flight of fixed-wing offline mode after taking off: portal support keeps flat forward, and is parallel with body, and the rigid coaxial bispin wing produces pulling force to the dead ahead, and fixedly aerofoil produces buoyancy and lifts aircraft under high-speed situation, and aircraft is done the high speed horizontal flight.
New flicon mode:
Flicon: when aircraft will advance or retreat, directly take the outer portal support of aircraft to turn forward or recede to realize advancing and retreat, perhaps change down the gas washing current control and advance and retreat with the main wing wing flap.Gas washing stream was realized under the control of left and right directions was then taked under helicopter mode to change with main wing, wing flap, fixed-wing and plane-hop pattern downside rely on the empennage controlling party to.
Because adopt the rigid coaxial rotor also to save the anti-torsion control system of pure helicopter, simultaneously also because of brand new direction mode has been arranged, the present invention has also saved the differential heading control loop of general co-axial rotor machine.
The present invention takes simple and actv. accusation mode in a word, saves a large amount of structural weights and improves capacity weight.Also improved the reliability of aircraft.
The invention has the beneficial effects as follows:
Actv. improves the flight stability of aircraft: just the same with common heligyro aspect flight stability, avoided the phenomenon of common tilt-wing aircraft crank.
Improved the capacity weight of aircraft: under the ad eundem situation, obtain bigger load-carrying effect with the comparable helicopter of short takeoff mode, the delivery personnel, the efficient of goods and materials is higher.
Speed is faster: because awing rotor can be adjusted to horizontal direction, rotor efficient is used to promote aircraft fully and moves ahead, and must open the speed limit of helicopter, possesses the ability of high-speed flight.
Voyage is farther: because the rotor horizontal adjustment promoted fuel efficiency, under equal fuel load situation, this invention aircraft more can be obtained advantage on the voyage than similar rank helicopter and common tilt-wing aircraft, and flying speed is faster, and what fly is higher.
Easy maintenance: owing to adopted brand new flicon mode, simplified Machinery Control System, greatly reduced maintenance workload.
Safety improves: the existing tilt-wing aircraft of contrast, and this invention is effectively simple, and steadily of centre of gravity can equally with helicopter rely on the rotor escape of falling after running into mechanical breakdown.
Not high to technical requirements: according to existing helicopter technical design, existing helicopter technology can realize fully fully in the present invention.
Price is not high: because design does not need a large amount of researches of technique based on a large amount of prior aries, simultaneously because of having adopted the mode of simple and effective control, reduced overall cost yet, helped marketing.
Range of use is wide: all multiple spots that the design's aircraft has helicopter concurrently it's too late fixed wing aircraft in the use, possess civilian and military use, can easily be in little place landings such as warship deck, high building balconies, can be widely used in each department that sightseeing tour, fire rescue, first aid at sea, anti-smuggling drug law enforcement, fire-fighting, commercial transport, medical rescue, the insecticide of communicating by letter and spray insecticide eliminated destructive insects, surveyed national economy such as resource.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples.
Fig. 1 is that the present invention overlooks constructional drawing.
Fig. 2 is helicopter mode downside apparent structure figure of the present invention.
Fig. 3 is fixed-wing pattern downside apparent structure figure of the present invention.
Fig. 4 is a forward sight constructional drawing of the present invention.
Among the figure 1, the rigid coaxial bispin wing 2, gate-type extrinsic deflection support 3, host wing 4, axis of deflection 5, pitot 6, driving engine 7, wing flap 8, fuselage 9, tailplane 10, vertical tail.
The specific embodiment
In the embodiment shown in fig. 1, driving engine (6) drives the rigid coaxial bispin wing (1) rotation by the axle in the gate-type extrinsic deflection support (2), the traction aircraft flies forward, and carries out the control of lifting and direction respectively by host wing (3) and tailplane (9) vertical tail (10).
In embodiment illustrated in fig. 2, driving engine (6) drives the rigid coaxial bispin wing (1) rotation by the axle in the gate-type extrinsic deflection support (2), make aircraft overcome self gravitation, realize vertical lift, and pass through the control of host wing (3) wing flap (7) vertical tail (10) travel direction, turn forward to retreat by gate-type extrinsic deflection support (2) and control forward-reverse.
In the embodiment shown in fig. 3, driving engine (6) drives the rigid coaxial bispin wing (1) rotation by the axle in the gate-type extrinsic deflection support (2), provide aircraft preceding action edge, host wing (3) is supported aircraft weight, fixed-wing flight is carried out in vertical tail (10), tailplane (9) travel direction, lifting control.
Claims (2)
1. coaxial double-rotary wing and tilt wing aircraft, it is characterized in that: aircraft body outer shaft connects one door type extrinsic deflection support, the rigid coaxial bispin wing is installed on a top of the trellis, the aircraft main wing is installed on the support outside, engine installation is in wing root top, and gate-type extrinsic deflection support can whole deflection together with wing, driving engine.
2. coaxial double-rotary wing and tilt wing aircraft according to claim 1 is characterized in that: gate-type extrinsic deflection support changes the rotor lead and cooperates empennage to control flight attitude by the wing of installing on the support, wing flap with the needs of flying method.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010190834 CN101870355A (en) | 2010-06-03 | 2010-06-03 | Coaxial double-rotary wing and tilt wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010190834 CN101870355A (en) | 2010-06-03 | 2010-06-03 | Coaxial double-rotary wing and tilt wing aircraft |
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| Publication Number | Publication Date |
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| CN101870355A true CN101870355A (en) | 2010-10-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010190834 Pending CN101870355A (en) | 2010-06-03 | 2010-06-03 | Coaxial double-rotary wing and tilt wing aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104015925A (en) * | 2014-05-27 | 2014-09-03 | 南京航空航天大学 | Multi-purpose vertical take-off and landing unmanned aerial vehicle |
| CN109866926A (en) * | 2019-02-01 | 2019-06-11 | 东北农业大学 | VTOL fixed-wing reclining device and spinning solution |
| CN110869276A (en) * | 2017-04-27 | 2020-03-06 | 翼动力股份有限公司 | Fuselage of vertical take-off and landing |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2511025A (en) * | 1947-01-21 | 1950-06-13 | Tucker & Sons | Fixed wing aircraft convertible to a rotary wing aircraft |
| US6382556B1 (en) * | 1999-12-20 | 2002-05-07 | Roger N. C. Pham | VTOL airplane with only one tiltable prop-rotor |
| CN1556006A (en) * | 2004-01-11 | 2004-12-22 | 孟吉平 | Mechanical rotating two wing deflected ascent small airplane |
| CN101041380A (en) * | 2006-03-23 | 2007-09-26 | 李泽奇 | Inclined wing airplane and application thereof |
| WO2009102739A2 (en) * | 2008-02-13 | 2009-08-20 | Bell Helicopter Textron Inc. | Rotorcraft with variable incident wing |
| CN101618763A (en) * | 2008-07-02 | 2010-01-06 | 孙为红 | Miniature high-speed vertical-lifting self rotor aircraft |
-
2010
- 2010-06-03 CN CN 201010190834 patent/CN101870355A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2511025A (en) * | 1947-01-21 | 1950-06-13 | Tucker & Sons | Fixed wing aircraft convertible to a rotary wing aircraft |
| US6382556B1 (en) * | 1999-12-20 | 2002-05-07 | Roger N. C. Pham | VTOL airplane with only one tiltable prop-rotor |
| CN1556006A (en) * | 2004-01-11 | 2004-12-22 | 孟吉平 | Mechanical rotating two wing deflected ascent small airplane |
| CN101041380A (en) * | 2006-03-23 | 2007-09-26 | 李泽奇 | Inclined wing airplane and application thereof |
| WO2009102739A2 (en) * | 2008-02-13 | 2009-08-20 | Bell Helicopter Textron Inc. | Rotorcraft with variable incident wing |
| CN101618763A (en) * | 2008-07-02 | 2010-01-06 | 孙为红 | Miniature high-speed vertical-lifting self rotor aircraft |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104015925A (en) * | 2014-05-27 | 2014-09-03 | 南京航空航天大学 | Multi-purpose vertical take-off and landing unmanned aerial vehicle |
| CN110869276A (en) * | 2017-04-27 | 2020-03-06 | 翼动力股份有限公司 | Fuselage of vertical take-off and landing |
| CN110869276B (en) * | 2017-04-27 | 2024-05-24 | 翼动力股份有限公司 | Vertical take-off and landing fuselage |
| CN109866926A (en) * | 2019-02-01 | 2019-06-11 | 东北农业大学 | VTOL fixed-wing reclining device and spinning solution |
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Addressee: Yang Maoliang Document name: Notification to Make Formalities Rectification |
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Application publication date: 20101027 |