CN103979103A - Tilt rotor airplane with novel structure - Google Patents
Tilt rotor airplane with novel structure Download PDFInfo
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- CN103979103A CN103979103A CN201410240741.7A CN201410240741A CN103979103A CN 103979103 A CN103979103 A CN 103979103A CN 201410240741 A CN201410240741 A CN 201410240741A CN 103979103 A CN103979103 A CN 103979103A
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Abstract
The invention provides a tilt rotor airplane with a novel structure. The tilt rotor airplane comprises an airplane body, a pair of framework type wings with tilt rotor surfaces, and a V-shaped empennage at the rear end of the airplane body, wherein engines are fixedly arranged on the outer sides of the framework type wings and are connected with propellers; the framework type wings and the tilt rotor surfaces tilt under the driving of a driving mechanism. During cruising, control of the tilt rotor airplane is the same as that of a general fixed wing airplane; in a vertical take-off and landing process, the wings rotate in a tilting manner relative to the airplane body and the wing surfaces rotate in a titling manner in frameworks of the wings, so that the forward flying resistance is reduced to the minimum, and the dangerous situation of advanced stall caused by a factor that the wings thoroughly lose the lifting force is avoided; a good rectification effect can be achieved on thrust air flow generated by the rotor wings; the adverse effect caused by a vortex ring in a falling process of the rotor airplane is greatly relieved.
Description
Technical field
The present invention relates to the tilt wing aircraft of a kind of aircraft, particularly a kind of new structure, belong to aviation aircraft design field.
Background technology
Tilt wing aircraft is the comprehensive and compromise of helicopter and fixed wing aircraft, has the vertical takeoff and landing function of helicopter and the feature that fixed wing aircraft voyage is far away, the speed of a ship or plane is high simultaneously.U.S. military secret V-22 " osprey " is the tilted propeller aircraft of at present real place in operation, its wing is substantially similar with fixed wing aircraft, different is that the airscrew engine that is positioned at wing two ends can be rotated up and down, and the screw propeller angle of attack is controlled, the function that can realize vertical takeoff and landing and cruise.But V-22 also has the deficiency of following several respects.
First be in the time of the downward exhaust of screw propeller, the air-flow that partly glides is subject to stopping of wing, will inevitably on main plane, form collar vortex; And the collar vortex upwards evoking can produce and disturb the normal work of screw propeller.Although the screw propeller of " osprey " is symmetrical, can not ensure to be attached to the also certain symmetry of collar vortex on the aerofoil of left and right, be subject to the impact of environmental conditions, the motion of collar vortex itself is also unstable.Especially when aircraft is in decline process, while approaching ground, on wing, existing collar vortex and screw propeller downslide air-flow bounce ground and the collar vortex mutual induction that produces, likely produce beyond thought non-equilibrium phenomena, as easy as rolling off a logly cause air crash.
When next is " osprey " vertical takeoff and landing, because screw propeller is positioned at above the wing tip of wing, the downwash flow that screw propeller produces has quite a few can beat the upper surface at main wing, has stopped the air-flow that downslide air-flow moves downward.When needs screw propeller produces larger 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, and in order to ensure that driving engine is verting and fixed type accurate positioning, wing must have enough Rigidity and strengths to control modification.The area that keeps out the wind when so not only having increased the weight of wing but also having increased landing, thus complete machine weight increased, reduce the result of lift.
Be finally osprey cruising in the conversion of vertical takeoff and landing process, the angle of screw propeller and fuselage increases to 90 ° from 0 °, and aircraft is easy to penetration depth stall condition, easily causes air crash.
Canadair CL-84 " Dynavert " is the tilt wing aircraft that has completed related system test flight, compare with " osprey ", vert the wing to driving engine, pneumatic integration ratio between blade and wing is easier to process, blade needn't be arranged in wing tip, can arrange two oars along wing in theory, four oars or more, adapt to the needs of large aircraft, but whole wing need to vert, the machine design of the junction to wing and fuselage requires very high, in the time of helicopter state, wing erects, not only before fly resistance very large, wing is also from producing lift to penetration depth stall, completely lose lift, but screw propeller downwash flow is subject to blocking of wing less, the pneumatic relation of downwash flow and wing is also more fixing.
Therefore, the design of tilt wing aircraft and the oar aircraft that verts is urgently further perfect.
Summary of the invention
The technical matters that the present invention mainly solves is to provide a kind of tilt wing aircraft of new structure, thereby overcomes the defect that above-mentioned prior art exists.
For solving above-mentioned technological deficiency, the present invention implements by following scheme: a kind of tilt wing aircraft of new structure is provided, comprises: fuselage, frame-type wing, the aerofoil that can vert, engine, screw propeller, the first driver train, the second driver train, the 3rd driver train, front spar lock, empennage.
Described frame-type wing comprises two parallel front spar and rear spar and a vertical main rib that is connected diaxon, and centered by main rib, line is rotationally connected with the both sides of described fuselage in pairs.
The rear spar of described frame-type wing and fuselage junction, be provided with the first driver train, by the driving of described driver train, can make this frame-type wing carry out backward verting between 0 ° to 90 ° with respect to fuselage.。
Described frame-type wing is provided with six aerofoils that can vert, on described aerofoil, be equipped with interplane pipe link, described aerofoil is by three, the described every limit of interplane pipe link line centered by the main rib of described wing, and symmetry is installed between the front spar and rear spar of described wing.
Main rib and the rear spar junction of described frame-type wing are provided with the second driver train, and by the driving of described driver train, the cw carrying out within the scope of 0 ° to 90 ° between aerofoil and wing that can make to vert verts.
The second described driver train, carries out mechanical connection by the wheel wing pipe link on flywheel, flywheel axle drive shaft and the frame-type leading edge of a wing of frame-type wing main rib below and the aerofoil that verts, and produces driving effect.
The 3rd described driver train is positioned at fuselage interior, is located at the below, junction of described frame-type wing front spar and fuselage, and described driver train is provided with front spar lock, completes the folding of described lock by the running of described driving.
Described engine is the symmetrical outside that is fixed at described frame-type wing respectively, is connected with the screw propeller described on each engine.
Described empennage is two, becomes V-shape to be symmetrically set in the rear end of described fuselage.
Compared with prior art, the present invention has the following advantages.
1, frame-type wing is provided with the aerofoil that can vert, according to cruising or the needs of vertical takeoff and landing, the aerofoil that can vert can be opened or be closed, under vertical takeoff and landing state, by opening the aerofoil that can vert, make aerofoil and spar angle in 90 °, fly resistance to minimum level to play before reducing, thereby avoid wing to completely lose the danger situation of lift penetration depth stall.
2, engine is affixed with respect to wing, and wing is rotatable with respect to fuselage, in vertical takeoff and landing process, wing verts together with engine, and under any circumstance, screw propeller face is all perpendicular to wing face, wing face can not form and stop screw propeller air-flow, thereby has improved the pneumatic efficiency of engine.
3, in vertical takeoff and landing process, the aerofoil that can vert becomes 90 degree angles with frame-type wing, and all aerofoils that vert are in the position that is parallel to each other, the thrust air-flow that can produce screw propeller plays good valve action, has alleviated widely the screw propeller machine adverse effect that ring of eddy causes in decline process.
Brief description of the drawings
Structural representation when accompanying drawing 1 cruises work for the present invention;
The structural representation of driver train when accompanying drawing 2 cruises work for the present invention;
Wing configuration front elevation when accompanying drawing 3 cruises work for the present invention;
Structural representation when accompanying drawing 4 is vertical takeoff and landing of the present invention;
Lateral plan when accompanying drawing 5 is vertical takeoff and landing of the present invention;
Wing configuration front elevation when accompanying drawing 6 is vertical takeoff and landing of the present invention.
Reference numeral: fuselage 1, frame-type wing 2, frame-type wing front spar 2a, frame-type wing rear spar 2b, frame-type wing main rib 2c, the aerofoil 3 that can vert, interplane pipe link 3a, engine 4, screw propeller 5, the first driver train 6, the second driver train 7, flywheel axle drive shaft 7a, flywheel 7b, wheel wing pipe link 7c, the 3rd driver train 8, front spar lock 9, empennage 10.
Detailed description of the invention
The present invention is described further for existing accompanying drawings.
As shown in accompanying drawing 1, accompanying drawing 2, a kind of tilt wing aircraft of new structure, fuselage 1, frame-type wing 2, the aerofoil 3 that can vert, engine 4, screw propeller 5, the first driver train 6, the second driver train 7, the 3rd driver train 8, front spar lock 9, empennage 10.
Described frame-type wing 2 comprises two parallel front spar 2a and rear spar 2b and a vertical main rib 2c who is connected diaxon, and centered by main rib 2c, line is rotationally connected with the both sides of described fuselage 1 in pairs.Described rear spar 2a and fuselage 1 junction, be provided with the first motor 6, by the driving of described motor 6, can make this frame-type wing 2 carry out backward verting between 0 ° to 90 ° with respect to fuselage 1.Described frame-type wing 2 is provided with six aerofoils 3 that can vert, on described aerofoil 3, be equipped with interplane pipe link 7c, described aerofoil 3 is by described interplane pipe link 7c three, every limit of line centered by the main rib 2c of described wing, and symmetry is installed between the front spar 2a and rear spar 2b of described wing.The main rib 2c of described frame-type wing and rear spar 2b junction are provided with the second driver train 7, and by the driving of described driver train 7, the cw carrying out within the scope of 0 ° to 90 ° between aerofoil 3 and wing 2 that can make to vert verts.The second described driver train 7, carries out mechanical connection by the wheel wing pipe link 7c in flywheel 7b, flywheel axle drive shaft 7a and frame-type wing 2 leading edges of frame-type wing main rib 2c below with the aerofoil 3 that verts, and produces driving effect.The 3rd described driver train 8 is positioned at fuselage 1 inside, is located at the below, junction of described frame-type wing front spar 2a and fuselage 1, and described driver train 8 is provided with front spar lock 9, completes the folding of described lock 9 by the running of described driving 8.Described engine 4 is the symmetrical outside that is fixed at described frame-type wing 2 respectively, is connected with the screw propeller 5 described on each engine 4.Described empennage 10 is two, becomes V-shape to be symmetrically set in the rear end of described fuselage 1.
As shown in accompanying drawing 1, accompanying drawing 3, aircraft is in the time of cruising flight, the aerofoil that can vert is closure state on frame-type wing, wing aerofoil and fuselage surface are the level of state, front spar is locked in blocking, firmly keep cruising form thereby frame-type wing can be stablized, prevent because the lift in maneuvering flight is uprushed and deviation position.Now aircraft master mode is identical with common fixed wing aircraft.
As shown in accompanying drawing 4, accompanying drawing 5, accompanying drawing 6, aircraft transfers vertical takeoff and landing pattern to by cruise mode, and the 3rd driving mechanisms control front wing lock is unblanked, the first driver train work, rear spar on driver framework formula wing rotates, and wing starts to vert backward with respect to fuselage, until perpendicular to fuselage; Simultaneously, the second driver train work, flywheel circles around axle drive shaft under flywheel drive shaft, and flywheel is by connecting wheel wing pipe link, interplane pipe link thereon simultaneously; make to do rotating within the scope of 0-90 degree relative to frame-type wing by Pour rotor face, until perpendicular to frame-type wing.
Claims (9)
1. a tilt wing aircraft for new structure, is characterized in that, described aircraft comprises: fuselage, frame-type wing, the aerofoil that can vert, engine, screw propeller, the first driver train, the second driver train, the 3rd driver train, front spar lock, empennage.
2. the tilt wing aircraft of a kind of new structure according to claim 1, it is characterized in that, described frame-type wing comprises two parallel front spar and rear spar and a vertical main rib that is connected diaxon, and centered by main rib, line is rotationally connected with the both sides of described fuselage in pairs.
3. the tilt wing aircraft of a kind of new structure according to claim 2, it is characterized in that, the rear spar of described frame-type wing and fuselage junction, be provided with the first driver train, by the driving of described driver train, can make this frame-type wing carry out backward verting between 0 ° to 90 ° with respect to fuselage.
4. the tilt wing aircraft of a kind of new structure according to claim 2, it is characterized in that, described frame-type wing is provided with six aerofoils that can vert, on described aerofoil, be equipped with interplane pipe link, described aerofoil is by three, the described every limit of interplane pipe link line centered by the main rib of described wing, and symmetry is installed between the front spar and rear spar of described wing.
5. the tilt wing aircraft of a kind of new structure according to claim 2, it is characterized in that, main rib and the rear spar junction of described frame-type wing are provided with the second driver train, by the driving of described driver train, can make to vert and between aerofoil and wing, carry out verting within the scope of 0 ° to 90 °.
6. the tilt wing aircraft of a kind of new structure according to claim 5, it is characterized in that, the second described driver train, carry out mechanical connection by the wheel wing pipe link on flywheel, flywheel axle drive shaft and the frame-type leading edge of a wing of frame-type wing main rib below and the aerofoil that verts, make to vert aerofoil around its axle type rib rotating within the scope of frame-type wing is done 0 ° to 90 °, until perpendicular to frame-type wing.
7. the tilt wing aircraft of a kind of new structure according to claim 1, it is characterized in that, the 3rd described driver train is positioned at fuselage interior, be located at the below, junction of described frame-type wing front spar and fuselage, described driver train is provided with front spar lock, completes unblanking and locking of described front spar lock by the running of described driving.
8. the tilt wing aircraft of a kind of new structure according to claim 1, is characterized in that, described engine is the symmetrical outside that is fixed at described frame-type wing respectively, is connected with the screw propeller described on each engine.
9. the tilt wing aircraft of a kind of new structure according to claim 1, is characterized in that, described empennage is two, becomes V-shape to be symmetrically set in the rear end of described fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410240741.7A CN103979103A (en) | 2014-06-03 | 2014-06-03 | Tilt rotor airplane with novel structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410240741.7A CN103979103A (en) | 2014-06-03 | 2014-06-03 | Tilt rotor airplane with novel structure |
Publications (1)
| Publication Number | Publication Date |
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| CN103979103A true CN103979103A (en) | 2014-08-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410240741.7A Pending CN103979103A (en) | 2014-06-03 | 2014-06-03 | Tilt rotor airplane with novel structure |
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| CN (1) | CN103979103A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105197230A (en) * | 2015-10-30 | 2015-12-30 | 佛山市神风航空科技有限公司 | Aircraft provided with double rotor wings |
| CN105217029A (en) * | 2015-11-05 | 2016-01-06 | 伍卫 | Louver wing type tilt rotor aircraft |
| CN113734419A (en) * | 2021-09-07 | 2021-12-03 | 南京航空航天大学 | Wing configuration and tilt rotor aircraft |
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| CN101041380A (en) * | 2006-03-23 | 2007-09-26 | 李泽奇 | Inclined wing airplane and application thereof |
| CN101844619A (en) * | 2009-03-27 | 2010-09-29 | 同济大学 | Tiltrotor aircraft |
| CN101875399A (en) * | 2009-10-30 | 2010-11-03 | 北京航空航天大学 | Tilt rotor aircraft adopting parallel coaxial dual rotors |
| CN201729271U (en) * | 2009-08-03 | 2011-02-02 | 北京航空航天大学 | Twin-propeller vertical duct controlled tiltrotor aircraft |
| CN102627146A (en) * | 2011-02-04 | 2012-08-08 | 贝尔直升机泰克斯特龙公司 | Tilt rotor aircraft with fixed engine arrangement |
| CN203005747U (en) * | 2012-10-30 | 2013-06-19 | 武卫平 | Tilt rotor aircraft |
| CN203032936U (en) * | 2012-11-27 | 2013-07-03 | 郑博洋 | Passenger helicopter |
| 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 |
| CN103434637A (en) * | 2013-08-25 | 2013-12-11 | 西北工业大学 | Novel aerofoil by utilizing magnus effect |
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2014
- 2014-06-03 CN CN201410240741.7A patent/CN103979103A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101041380A (en) * | 2006-03-23 | 2007-09-26 | 李泽奇 | Inclined wing airplane and application thereof |
| CN101844619A (en) * | 2009-03-27 | 2010-09-29 | 同济大学 | Tiltrotor aircraft |
| CN201729271U (en) * | 2009-08-03 | 2011-02-02 | 北京航空航天大学 | Twin-propeller vertical duct controlled tiltrotor aircraft |
| CN101875399A (en) * | 2009-10-30 | 2010-11-03 | 北京航空航天大学 | Tilt rotor aircraft adopting parallel coaxial dual rotors |
| CN102627146A (en) * | 2011-02-04 | 2012-08-08 | 贝尔直升机泰克斯特龙公司 | Tilt rotor aircraft with fixed engine arrangement |
| 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 |
| CN203005747U (en) * | 2012-10-30 | 2013-06-19 | 武卫平 | Tilt rotor aircraft |
| CN203032936U (en) * | 2012-11-27 | 2013-07-03 | 郑博洋 | Passenger helicopter |
| CN103434637A (en) * | 2013-08-25 | 2013-12-11 | 西北工业大学 | Novel aerofoil by utilizing magnus effect |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105197230A (en) * | 2015-10-30 | 2015-12-30 | 佛山市神风航空科技有限公司 | Aircraft provided with double rotor wings |
| CN105217029A (en) * | 2015-11-05 | 2016-01-06 | 伍卫 | Louver wing type tilt rotor aircraft |
| CN113734419A (en) * | 2021-09-07 | 2021-12-03 | 南京航空航天大学 | Wing configuration and tilt rotor aircraft |
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Application publication date: 20140813 |