CN101844619A - Tiltrotor aircraft - Google Patents
Tiltrotor aircraft Download PDFInfo
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- CN101844619A CN101844619A CN200910048457A CN200910048457A CN101844619A CN 101844619 A CN101844619 A CN 101844619A CN 200910048457 A CN200910048457 A CN 200910048457A CN 200910048457 A CN200910048457 A CN 200910048457A CN 101844619 A CN101844619 A CN 101844619A
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Abstract
The invention relates to a tiltrotor aircraft, which comprises a body, a pair of wings positioned on two sides of the body, ailerons positioned on the wings and emages arranged on the tail part of the body. The pair of wings is both provided with an engine; each engine is connected with a propeller; the wings are rotatably connected to the body; the engines are fixed on the wings; and the rear part of each propeller corresponding to the wing is respectively provided with a horizontal tilt wing, a vertical stable wing and a vertical resistance plate. Compared with the prior art, the tiltrotor aircraft is simple, safe and reliable to realize without depending on a complex mechanical and electronic system; the engines are fixedly connected relatively to the wings, the wings can rotate relatively to the body, the wings and the engines tilt together in the takeoff and landing process, the rotor surface is always vertical to the wing surface under any working condition, and the wing surface cannot obstruct airflow from the propellers, so that the pneumatic efficiency of the engine is improved; and the engines are positioned at the root of the wings so as to effectively reduce the requirement on the strength of the wings and facilitate reducing weight.
Description
Technical field
The present invention relates to aircraft, particularly relate to a kind of tilt rotor aircraft.
Background technology
Tiltrotor is a kind of course of new aircraft that the advantage of fixed wing aircraft and helicopter is combined together, has the people to be called " half-breed " in the air visually.Compare with helicopter, the tiltrotor voyage is far away, speed of a ship or plane height.Compare with fixed wing aircraft, tilting rotor function vertical takeoff and landing is low to site requirements.
U.S. military secret V-22 " osprey " is the tiltrotor of at present real place in operation.The fuselage of V-22, wing and ordinary fixed wing aircraft are similar substantially, and different is that the airscrew engine that is positioned at the wing two ends can be rotated up and down, and the rotor angle of attack is controlled, can realize the function that vertical takeoff and landing and fixed-wing cruise.The performance of the design of its novelty, excellence and broad Applicable scope have left a deep impression to the people.Though V-22 has various preceences, and be equipped with advanced mechanical-electronic system, because its landing process complexity is difficult to control, some technology does not reach a standard fully, is that accident is frequent between its used life, and a lot of fatal crasses' tragedy once took place.Its deficiency is mainly reflected in several aspects:
At first be or not strict symmetry attached to the collar vortex on the aerofoil of both sides, be subject to the influence of environmental conditions, the motion of collar vortex itself is instability also.Especially when aircraft be in the decline state, during near ground, existing collar vortex and propeller race bounce ground and the new collar vortex mutual induction that produces on the wing, might produce beyond thought non-equilibrium phenomena.At this moment, aviator's manipulation has mistake slightly or reacts too late, is easy to cause air crash.
When next was the v-22 vertical takeoff and landing, because screw propeller (rotor) is positioned at the wing tip top of wing, the downwash that the propeller rotor produces had quite a few can beat upper surface at main wing, has stopped the air-flow that slip-stream moves downward.When needs propeller rotor produced big powered lift, this layout will be paid the cost of certain negative lift, reduces effective lift.
Driving engine is positioned at the two ends of wing besides, is verting and accurate positioning fixedly the time in order to guarantee driving engine, and wing must have enough rigidity and intensity to come controlled deformation.Therefore its main wing wing tip must design generouslyer, and the area that keeps out the wind the when weight that has so promptly increased wing has increased landing has again played the result who has increased complete machine weight, reduced lift.
Summary of the invention
Technical matters to be solved by this invention is exactly to provide a kind of simple and safe failure-free tilt rotor aircraft for the defective that overcomes above-mentioned prior art existence.
Purpose of the present invention can be achieved through the following technical solutions: a kind of tilt rotor aircraft, comprise fuselage, a pair of wing of fuselage both sides, the empennage that is positioned at the aileron on the wing and is located at afterbody of being positioned at, be equipped with driving engine on the described a pair of wing, be connected with a screw propeller on each driving engine, it is characterized in that, described wing is rotationally connected with on the fuselage, described driving engine is fixed on the wing, and the cooresponding wing of each rear propeller place is equipped with the wing that verts, a vertical stabilizer and a vertical flaps of a level.
Described driving engine is fixed in the root of wing.
The described wing that verts comprises the wing body that verts of two levels, and these two wing bodies that vert are located at the trailing edge place of wing.
Described stabilizer is located at two and is verted between the wing body, and this stabilizer comprises two stabilizer bodies, and described two stabilizer body vertical summetry are located at the two sides of wing.
Described flaps comprises four plate bodys, and described four plate bodys are symmetrically set in the both sides of driving engine in twos.
Described empennage comprises symmetrically arranged two tailplanes and a vertical tail, and described vertical tail is located between two tailplanes.
Compared with prior art, the present invention has the following advantages:
1, set up a pair of wing that verts, a pair of stabilizer and a pair of flaps in the back of driving engine, the process of verting is all controlled by these three pairs of rudder faces, and is not fixed against the complicated mechanical electronic system, and implementation procedure is simple, safety, reliable;
2, the relative wing of driving engine is affixed, and the relative fuselage of wing is rotatable, verts together at landing process wing and driving engine, all is perpendicular to the wing face at any operating mode backspin aerofoil, and the wing face can not stop oar air-flow formation, can improve the pneumatic efficiency of driving engine;
3, driving engine is positioned at the wing root, can effectively reduce the requirement to wing intensity, makes things convenient for loss of weight.
Description of drawings
Fig. 1 is a structural representation of the present invention;
Fig. 2 is the take off structural representation of operating mode of the present invention;
The structural representation of Fig. 3 during for cruising condition of the present invention.
The specific embodiment
The invention will be further described below in conjunction with accompanying drawing.
As shown in Figure 1, a kind of tilt rotor aircraft, comprise fuselage 1, a pair of wing 2 of fuselage both sides, the empennage that is positioned at the aileron 3 on the wing 2 and is located at afterbody of being positioned at, be equipped with driving engine 4 on the described a pair of wing 2, be connected with a screw propeller 5 on each driving engine 4, described wing 2 is rotationally connected with on the fuselage 1, described driving engine 4 is fixed on the wing 2, and each cooresponding wing place, screw propeller 5 rears is equipped with the vertical stabilizer 7 and the vertical flaps 8 of the wing 6, of verting of a level.
Described driving engine 4 is fixed in the root of wing 2; The described wing 6 that verts comprises the wing body 60 that verts of two levels, and these two wing bodies 60 that vert are located at the trailing edge place of wing 2; Described stabilizer 7 is located at two and is verted between the wing body 60, and this stabilizer 7 comprises two stabilizer bodies 70, and described two stabilizer body 70 vertical summetry are located at the two sides of wing 2; Described flaps 8 comprises four plate bodys 80, and described four plate bodys 80 are symmetrically set in the both sides of driving engine 4 in twos; Described empennage comprises symmetrically arranged two tailplanes 9 and a vertical tail 10, and described vertical tail 10 is located between two tailplanes 9.
Driving engine of the present invention is fixed on the wing, and can rotate between wing and the fuselage.Driving engine is set up the wing that verts of a pair of level, a pair of vertical stabilizer and a pair of flaps near the wing root on the wing of rear propeller, rely on these two pairs of aerofoils and flaps to come the attitude of aircraft is controlled when taking off.Enable the vertical takeoff and landing pattern when taking off, driving engine and wing all are in plumbness, take off finish after, aircraft switches to cruise mode, driving engine and wing inclined forward jointly and turn 90 degrees this moment, entered cruise mode.
When taking off as Fig. 2, driving engine and wing all are in plumbness, propellerpiston is parallel to horizontal surface, at this time screw propeller provides lift, along with lift increases gradually, aircraft is by vertical pull-up, at this time the control of the attitude of aircraft by the wing that verts, flaps and stabilizer finish, tailplane and vertical tail are inoperative this moment.Three rotational freedoms: face upward the action of bowing by the wing synchro control of verting, it is stable by the flaps synchro control to roll, and coursekeeping is by the wing differentiating control of verting.Three translation freedoms: break away by stabilizer control, move forward and backward by the flaps differentiating control, lifting is then controlled by engine power.
As Fig. 3, take off and transfer to when cruising, the wing that verts is bowed to full-helm, the relative fuselage of wing begins to vert forward, the pulling force of screw propeller is by gradually becoming level vertically upward forward at this moment, and aircraft begins toward preacceleration, and wing begins to provide lift, the lift of screw propeller is substituted by lifting force of wings gradually, and aircraft entered cruise mode after whole process was finished.
During cruising flight, wing and fuselage relative position are locked, and the wing that verts, flaps and stabilizer reset, and quit work.Aspect is by aileron, tailplane and vertical tail control, and this moment, the aircraft mode was identical with the ordinary fixed wing aircraft.
During vertical landing, aircraft enters the landing pattern.Wing and the release of fuselage relative position, the wing that verts, flaps and stabilizer are started working.The wing that verts is faced upward to full-helm, the relative fuselage of wing begins to vert backward, this moment, the pulling force of screw propeller was gradually become forward vertically upward by level, aircraft reduces speed now, wing provides lift to reduce gradually, lifting force of wings is substituted by the lift of screw propeller gradually, and aircraft began to descend final landing after whole process was finished.
Claims (6)
1. tilt rotor aircraft, comprise fuselage, a pair of wing of fuselage both sides, the empennage that is positioned at the aileron on the wing and is located at afterbody of being positioned at, be equipped with driving engine on the described a pair of wing, be connected with a screw propeller on each driving engine, it is characterized in that, described wing is rotationally connected with on the fuselage, and described driving engine is fixed on the wing, and the cooresponding wing of each rear propeller place is equipped with the wing that verts, a vertical stabilizer and a vertical flaps of a level.
2. a kind of tilt rotor aircraft according to claim 1 is characterized in that described driving engine is fixed in the root of wing.
3. a kind of tilt rotor aircraft according to claim 1 is characterized in that, the described wing that verts comprises the wing body that verts of two levels, and these two wing bodies that vert are located at the trailing edge place of wing.
4. a kind of tilt rotor aircraft according to claim 3 is characterized in that, described stabilizer is located at two and is verted between the wing body, and this stabilizer comprises two stabilizer bodies, and described two stabilizer body vertical summetry are located at the two sides of wing.
5. a kind of tilt rotor aircraft according to claim 4 is characterized in that, described flaps comprises four plate bodys, and described four plate bodys are symmetrically set in the both sides of driving engine in twos.
6. according to claim 2 or 4 described a kind of tilt rotor aircrafts, it is characterized in that described empennage comprises symmetrically arranged two tailplanes and a vertical tail, described vertical tail is located between two tailplanes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910048457A CN101844619A (en) | 2009-03-27 | 2009-03-27 | Tiltrotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910048457A CN101844619A (en) | 2009-03-27 | 2009-03-27 | Tiltrotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101844619A true CN101844619A (en) | 2010-09-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910048457A Pending CN101844619A (en) | 2009-03-27 | 2009-03-27 | Tiltrotor aircraft |
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| Country | Link |
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| CN (1) | CN101844619A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103241376A (en) * | 2012-02-01 | 2013-08-14 | 北京安翔动力科技有限公司 | Vector power vertical takeoff and landing aircraft and vector power system thereof |
| JP2014037219A (en) * | 2012-08-16 | 2014-02-27 | Masaaki Arai | Vertical take-off and landing aircraft |
| CN103979103A (en) * | 2014-06-03 | 2014-08-13 | 杭州策引东机电有限公司 | Tilt rotor airplane with novel structure |
| CN104276277A (en) * | 2013-12-16 | 2015-01-14 | 江富余 | Fixed-wing propeller flying wing provided with front wing and capable of moving up and down vertically |
| WO2015064767A1 (en) * | 2013-10-30 | 2015-05-07 | 優章 荒井 | Vertical take-off and landing flight vehicle |
| CN106864729A (en) * | 2017-03-19 | 2017-06-20 | 袁新友 | A kind of double airfoil type VTOL aircraft |
| CN109080815A (en) * | 2018-07-20 | 2018-12-25 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of unmanned plane |
| CN114148511A (en) * | 2020-09-07 | 2022-03-08 | 曹卓荣 | Helicopter with rotatable cockpit |
-
2009
- 2009-03-27 CN CN200910048457A patent/CN101844619A/en active Pending
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103241376A (en) * | 2012-02-01 | 2013-08-14 | 北京安翔动力科技有限公司 | Vector power vertical takeoff and landing aircraft and vector power system thereof |
| JP2014037219A (en) * | 2012-08-16 | 2014-02-27 | Masaaki Arai | Vertical take-off and landing aircraft |
| WO2015064767A1 (en) * | 2013-10-30 | 2015-05-07 | 優章 荒井 | Vertical take-off and landing flight vehicle |
| JP5943289B2 (en) * | 2013-10-30 | 2016-07-05 | 優章 荒井 | Vertical takeoff and landing vehicle |
| JP2016172556A (en) * | 2013-10-30 | 2016-09-29 | 優章 荒井 | Vertical takeoff and landing flying body |
| JP2016172557A (en) * | 2013-10-30 | 2016-09-29 | 優章 荒井 | Vertical takeoff and landing flying body |
| CN104276277A (en) * | 2013-12-16 | 2015-01-14 | 江富余 | Fixed-wing propeller flying wing provided with front wing and capable of moving up and down vertically |
| CN103979103A (en) * | 2014-06-03 | 2014-08-13 | 杭州策引东机电有限公司 | Tilt rotor airplane with novel structure |
| CN106864729A (en) * | 2017-03-19 | 2017-06-20 | 袁新友 | A kind of double airfoil type VTOL aircraft |
| CN109080815A (en) * | 2018-07-20 | 2018-12-25 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of unmanned plane |
| CN109080815B (en) * | 2018-07-20 | 2021-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle |
| CN114148511A (en) * | 2020-09-07 | 2022-03-08 | 曹卓荣 | Helicopter with rotatable cockpit |
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| PB01 | Publication | ||
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
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Application publication date: 20100929 |