CN103523220A - Rotatable stepped arrangement multi-flank volute power vertical takeoff and landing airplane - Google Patents
Rotatable stepped arrangement multi-flank volute power vertical takeoff and landing airplane Download PDFInfo
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- CN103523220A CN103523220A CN201310514269.7A CN201310514269A CN103523220A CN 103523220 A CN103523220 A CN 103523220A CN 201310514269 A CN201310514269 A CN 201310514269A CN 103523220 A CN103523220 A CN 103523220A
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- 230000002787 reinforcement Effects 0.000 claims description 134
- 230000002146 bilateral effect Effects 0.000 claims description 12
- 238000002347 injection Methods 0.000 claims description 12
- 239000007924 injection Substances 0.000 claims description 12
- 238000009434 installation Methods 0.000 claims description 8
- 230000009194 climbing Effects 0.000 claims description 6
- 239000007921 spray Substances 0.000 claims description 4
- 230000009189 diving Effects 0.000 claims description 3
- 230000010006 flight Effects 0.000 claims description 3
- 238000005096 rolling process Methods 0.000 claims description 3
- 238000007514 turning Methods 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 1
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Abstract
The invention relates to a rotatable stepped arrangement multi-flank volute power vertical takeoff and landing airplane, which includes three rows of symmetrically mounted wings in stepped arrangement on two sides of a fuselage, two or more front volute air cushion boosting propellers symmetrically mounted at one ends of one row or multiple rows of wings away from the fuselage, and two rear volute air cushion boosting propellers symmetrically mounted on both sides of the fuselage near the tail. The airplane is characterized in that: three rows of wings in stepped arrangement are symmetrically mounted on two sides of the fuselage, the front row of wings are closest to the handpiece and is nearest to the cockpit and the airplane back, the middle row of wings are below the front row of wings and close to the fuselage middle part, and the rear row of wings are below the middle row of wings and close to the fuselage rear part. The front edges of the middle row of wings are in the vicinity of the perpendicular lines of the front row wings' rear edges, and the front edges of the rear row of wings are in the vicinity of the perpendicular lines of the middle row wings' rear edges. The middle part of each row of wings is equipped with a shaft in connection with the fuselage, the wings can make forward or backward rotation around the shaft.
Description
Technical field
The present invention relates to rotatable many flanks of ladder row volute power vertical take-off and landing aircraft (VTOL aircraft), belong to science and technology of aviation field.
Background technology
The research and development of modern aircraft are advanced by leaps and bounds, but all these aircraft all cannot be accomplished can take off vertically freely in atmosphere, aerial high-speed flight, Britain once produced the aircraft that can take off vertically, but its landing will consume 40% fuel, affect widely flying distance and the flight time of this aircraft, so Britain does not re-use this class aircraft yet now, and the F-35 of the U.S. will lose all weapons that carry to comprise guided missile etc. when landing, this will cause huge waste and likely cause inconceivable disaster; The present invention utilizes in uncle minister in ancient times's Wei patent " 201310448764. 2 volute air cushion reinforcement propelling unit " near air nozzle, to form the method that " air cushion " improves jet reaction thrust efficiency, and the lift that wing gradient array is produced to improve its wing, thereby make this aircraft vertical takeoff and landing and high-speed flight freely.
Summary of the invention
Rotatable many flanks of the ladder row volute power vertical take-off and landing aircraft (VTOL aircraft) that the object of this invention is to provide a kind of vertical takeoff and landing freely and high-speed flight.
Rotatable many flanks of ladder row volute power vertical take-off and landing aircraft (VTOL aircraft), comprise the wing that fuselage bilateral symmetry installation three row's stageds are arranged, with at row's wing or arrange wing more, away from one end of fuselage is symmetrical, two or more front volute air cushion reinforcement propelling units are installed, and after near fuselage bilateral symmetry tail is installed two volute air cushion reinforcement propelling unit; It is characterized in that:
1, fuselage bilateral symmetry is installed the wing that three row's stageds are arranged, the front-seat the most close head of wing and nearest from driving compartment and the machine back of the body, the position of middle row's wing close waist below front-seat wing, the position of rear row's wing close fuselage afterbody below middle row's wing, the front edge of middle row's wing is near the antemarginal perpendicular line of front-seat wing, the front edge of rear row's wing is near the antemarginal perpendicular line of middle row's wing, can make like this to arrange high-speed air flow that wing upper side flows through in the past and partly blow over the upper side of middle row's wing, simultaneously, the slightly slow high-speed air flow major part of high-speed air flow that this wing upper side flows through flowing through from front-seat wing downside enters into the upper side of row's wing, thereby make the upper side density of air of middle row's wing large compared with the density of air of front-seat wing upper side, the speed that must add like this air stream of big-and-middle row's wing upper side, and air stream density and the flow velocity of the air stream density of middle row's wing downside and flow velocity and front-seat wing downside are close, this just equals to have strengthened the velocity contrast of middle row's wing upper side air stream and downside air stream, and then strengthened the lift that middle row's wing produces, in like manner, therefrom arrange high-speed air flow that wing upper side flows through and partly blow over the upper side of rear row's wing, simultaneously, therefrom arrange the upper side that the slightly slow high-speed air flow major part of high-speed air flow that this wing upper side flows through that wing downside flows through enters into rear row's wing, thereby make the upper side density of air of rear row's wing large compared with the density of air of middle row's wing upper side, must strengthen like this speed of the air stream of rear row's wing upper side, then arrange air stream density and flow velocity and the front row of wing downside, air stream density and the flow velocity of middle row's wing downside are close, this just equals to have strengthened the velocity contrast of rear row's wing upper side air stream and downside air stream, and then strengthened the lift that rear row's wing produces, the middle part of each row's wing has an axle to be connected with fuselage, wing can be done rotation forward or backward around this axle, Q:-45 °≤Q≤90 ° of its anglec of rotation, when wing is during in horizontality, its wing front edge downwards maximum rotation 45° angle, the maximum half-twist angle that can make progress is vertical to wing, when aircraft takes off vertically by land, the front edges of three row's wings rotate up 90 ° vertical to wing, open all volute air cushion reinforcement propelling unit Jet with downward flow direction and hold up aircraft and take off vertically, need to be to front upper place during oblique climbing in horizontal flight when aircraft, the wing front edge of front-seat wing or front row, middle row, rear row three row's wings rotates up certain angle, so just can make aircraft oblique flight of climbing to front upper place, need to be to front lower place during oblique underriding in horizontal flight when aircraft, the wing front edge of front-seat wing or front row, middle row, rear row three row's wings is rotated down certain angle, so just can make aircraft oblique diving flight to front lower place.
2, at a row or multi-row wing S. A., stretch out wing away from the position of fuselage end 100mm ~ 1000mm, the two or more front volute air cushion reinforcement propelling units that can independently rotate around wing S. A. of symmetrical installation, one section that stretches out wing 100mm ~ 1000mm is front volute air cushion reinforcement propelling unit pipe link, and front volute air cushion reinforcement propelling unit is not associated around this axle rotation with wing around the rotation of wing S. A., front volute air cushion reinforcement propelling unit is around P:-90 °≤Q≤90 ° of the wing S. A. anglec of rotation, be that aircraft is when level attitude, the angle of rake air nozzle of current volute air cushion reinforcement is vertically downward time, the angle of rake air nozzle of front volute air cushion reinforcement can to heading half-twist to the angle of rake air nozzle of front volute air cushion reinforcement forward horizontal-jet, to 90 ° of tail direction rotations to the angle of rake air nozzle of front volute air cushion reinforcement horizontal-jet backwards, volute air cushion reinforcement propelling unit after near fuselage bilateral symmetry tail is installed two, rear volute air cushion reinforcement propelling unit and fuselage pipe link are rear volute air cushion reinforcement propelling unit pipe link, rear volute air cushion reinforcement propelling unit can be around P:-90 °≤Q≤90 ° of the rear volute air cushion reinforcement propelling unit pipe link anglec of rotation, be that aircraft is when level attitude, when the angle of rake air nozzle of rear volute air cushion reinforcement is vertically downward time, the angle of rake air nozzle of rear volute air cushion reinforcement can be to heading half-twist to the angle of rake air nozzle of rear volute air cushion reinforcement horizontal-jet forward, to 90 ° of tail direction rotations to the angle of rake air nozzle of rear volute air cushion reinforcement horizontal-jet backwards, when current volute air cushion reinforcement propelling unit and the angle of rake air nozzle of rear volute air cushion reinforcement spray downward vertically, produce the lift that upwards holds up aircraft, current volute air cushion reinforcement propelling unit and the angle of rake air nozzle of rear volute air cushion reinforcement are during to tail direction horizontal-jet, generation is to the thrust of preacceleration, current volute air cushion reinforcement propelling unit and the angle of rake air nozzle of rear volute air cushion reinforcement be during to heading horizontal-jet, the thrust that produces backward and aircraft is slowed down.
3, the front volute air cushion reinforcement propelling unit of installing away from fuselage end at wing, must install with the central axis symmetry of fuselage, the rear volute air cushion reinforcement propelling unit that install near fuselage both sides tail, also must install with the central axis symmetry of fuselage, when front volute air cushion reinforcement propelling units of installing in these symmetries or rear volute air cushion reinforcement propelling unit symmetry are opened and make its injection direction consistent, could produce thrust in the same way, when the front volute air cushion reinforcement propelling unit of symmetry or after volute air cushion reinforcement propelling unit open simultaneously, but when its injection direction is inconsistent, can make aircraft produce the power of different directions, when the front volute air cushion reinforcement propelling unit in left side and rear volute air cushion reinforcement propelling unit are opened and are sprayed to tail direction, close one or several front volute air cushion reinforcement propelling unit and the rear volute air cushion reinforcement propelling unit on right side, other several volute air cushion reinforcement propelling unit injection directions are consistent with the volute air cushion reinforcement propelling unit injection direction on right side, at this moment, left side volute air cushion reinforcement propelling unit produces to back pressure, be greater than that the volute air cushion reinforcement propelling unit on right side produces to back pressure, aircraft to the right direction is turned, and this thrust is backward poor larger, the radius that aircraft bends to right is just less, utilize the thrust of front volute air cushion reinforcement propelling unit and the different directions that rear volute air cushion reinforcement propelling unit produces of asymmetric unlatching, can make aircraft do various turnings, rotation, the flights such as rolling.
The present invention compared with prior art has the following advantages:
1, the wing of this gradient array, relatively existing aircraft, with span area, can bring larger lift to aircraft.
2, the rotatable performance of this wing is brought better handling and larger flight alerting ability to aircraft.
Accompanying drawing explanation
Fig. 1 is the schematic side view of the embodiment of the present invention;
Fig. 2 is schematic top plan view embodiment illustrated in fig. 1.
In Fig. 1-2: 1, head 2, driving compartment 3, chaufeur 4, fuselage 5, left front volute air cushion reinforcement propelling unit 6, left front flank 7, left flank 8, left flank S. A. 9, left back flank 10, left back flank S. A. 11, ventral 12, the machine back of the body 13, left back volute air cushion reinforcement propelling unit 14, tail 15, the tail wing 16, right front flank 17, right front volute air cushion reinforcement propelling unit 18, left front volute air cushion reinforcement propelling unit pipe link 19, right flank 20, right back flank 21, left back volute air cushion reinforcement propelling unit pipe link 22, right back volute air cushion reinforcement propelling unit pipe link 23, right back volute air cushion reinforcement propelling unit.
The specific embodiment
In the embodiment shown in Fig. 1-2: rotatable many flanks of ladder row volute power vertical take-off and landing aircraft (VTOL aircraft), comprise the wing that fuselage 4 bilateral symmetry installation three row's stageds are arranged, with at row's wing or arrange wing more and away from one end of fuselage 4 is symmetrical two or more front volute air cushion reinforcement propelling units are installed, and after near two of fuselage 4 bilateral symmetry installations tail 14 volute air cushion reinforcement propelling unit, it is characterized in that: fuselage 4 bilateral symmetry are installed the wing that three row's stageds are arranged, the front-seat the most close head 1 of wing and carry on the back 12 nearest from driving compartment 2 and machine, the position at middle row's wing close fuselage 4 middle parts below front-seat wing, the position at rear row's wing close fuselage 4 rear portions below middle row's wing, the front edge of middle row's wing is near the antemarginal perpendicular line of front-seat wing, the front edge of rear row's wing is near the antemarginal perpendicular line of middle row's wing, can make like this to arrange high-speed air flow that wing upper side flows through in the past and partly blow over the upper side of middle row's wing, simultaneously, the slightly slow high-speed air flow major part of high-speed air flow that this wing upper side flows through flowing through from front-seat wing downside enters into the upper side of row's wing, thereby make the upper side density of air of middle row's wing large compared with the density of air of front-seat wing upper side, the speed that must add like this air stream of big-and-middle row's wing upper side, and air stream density and the flow velocity of the air stream density of middle row's wing downside and flow velocity and front-seat wing downside are close, this just equals to have strengthened the velocity contrast of middle row's wing upper side air stream and downside air stream, and then strengthened the lift that middle row's wing produces, in like manner, therefrom arrange high-speed air flow that wing upper side flows through and partly blow over the upper side of rear row's wing, simultaneously, therefrom arrange the upper side that the slightly slow high-speed air flow major part of high-speed air flow that this wing upper side flows through that wing downside flows through enters into rear row's wing, thereby make the upper side density of air of rear row's wing large compared with the density of air of middle row's wing upper side, must strengthen like this speed of the air stream of rear row's wing upper side, then arrange air stream density and flow velocity and the front row of wing downside, air stream density and the flow velocity of middle row's wing downside are close, this just equals to have strengthened the velocity contrast of rear row's wing upper side air stream and downside air stream, and then strengthened the lift that rear row's wing produces, the middle part of each row's wing has an axle to be connected with fuselage 4, wing can be done rotation forward or backward around this axle, Q:-45 °≤Q≤90 ° of its anglec of rotation, when wing is during in horizontality, its wing front edge downwards maximum rotation 45° angle, the maximum half-twist angle that can make progress is vertical to wing, when aircraft takes off vertically by land, the front edges of three row's wings rotate up 90 ° vertical to wing, open all volute air cushion reinforcement propelling unit Jet with downward flow direction and hold up aircraft and take off vertically, need to be to front upper place during oblique climbing in horizontal flight when aircraft, the wing front edge of front-seat wing or front row, middle row, rear row three row's wings rotates up certain angle, so just can make aircraft oblique flight of climbing to front upper place, need to be to front lower place during oblique underriding in horizontal flight when aircraft, the wing front edge of front-seat wing or front row, middle row, rear row three row's wings is rotated down certain angle, so just can make aircraft oblique diving flight to front lower place.
At a row or multi-row wing S. A., stretch out wing away from the position of fuselage 4 end 100mm ~ 1000mm, the two or more front volute air cushion reinforcement propelling units that can independently rotate around wing S. A. of symmetrical installation, one section that stretches out wing 100mm ~ 1000mm is front volute air cushion reinforcement propelling unit pipe link, and front volute air cushion reinforcement propelling unit is not associated around this axle rotation with wing around the rotation of wing S. A., front volute air cushion reinforcement propelling unit is around P:-90 °≤Q≤90 ° of the wing S. A. anglec of rotation, be that aircraft is when level attitude, the angle of rake air nozzle of current volute air cushion reinforcement is vertically downward time, the angle of rake air nozzle of front volute air cushion reinforcement can to 90 ° of head 1 direction rotations to the angle of rake air nozzle of front volute air cushion reinforcement forward horizontal-jet, to 90 ° of tail 14 direction rotations to the angle of rake air nozzle of front volute air cushion reinforcement horizontal-jet backwards, volute air cushion reinforcement propelling unit after near fuselage bilateral symmetry tail 14 is installed two, rear volute air cushion reinforcement propelling unit and fuselage 4 pipe links are rear volute air cushion reinforcement propelling unit pipe link, rear volute air cushion reinforcement propelling unit can be around P:-90 °≤Q≤90 ° of the rear volute air cushion reinforcement propelling unit pipe link anglec of rotation, be that aircraft is when level attitude, when the angle of rake air nozzle of rear volute air cushion reinforcement is vertically downward time, the angle of rake air nozzle of rear volute air cushion reinforcement can be to 90 ° of head 1 direction rotations to the angle of rake air nozzle of rear volute air cushion reinforcement horizontal-jet forward, to 90 ° of tail 14 direction rotations to the angle of rake air nozzle of rear volute air cushion reinforcement horizontal-jet backwards, when current volute air cushion reinforcement propelling unit and the angle of rake air nozzle of rear volute air cushion reinforcement spray downward vertically, produce the lift that upwards holds up aircraft, current volute air cushion reinforcement propelling unit and the angle of rake air nozzle of rear volute air cushion reinforcement are during to tail 14 direction horizontal-jet, generation is to the thrust of preacceleration, current volute air cushion reinforcement propelling unit and the angle of rake air nozzle of rear volute air cushion reinforcement be during to head 1 direction horizontal-jet, the thrust that produces backward and aircraft is slowed down.
The front volute air cushion reinforcement propelling unit of installing away from fuselage 4 ends at wing, must install with the central axis symmetry of fuselage 4, the rear volute air cushion reinforcement propelling unit that install near fuselage 4 both sides tail 14, also must install with the central axis symmetry of fuselage 4, when front volute air cushion reinforcement propelling units of installing in these symmetries or rear volute air cushion reinforcement propelling unit symmetry are opened and make its injection direction consistent, could produce thrust in the same way, when the front volute air cushion reinforcement propelling unit of symmetry or after volute air cushion reinforcement propelling unit open simultaneously, but when its injection direction is inconsistent, can make aircraft produce the power of different directions, when the front volute air cushion reinforcement propelling unit in left side and rear volute air cushion reinforcement propelling unit opened and spray to tail 14 directions, close one or several front volute air cushion reinforcement propelling unit and the rear volute air cushion reinforcement propelling unit on right side, other several volute air cushion reinforcement propelling unit injection directions are consistent with the volute air cushion reinforcement propelling unit injection direction on right side, at this moment, left side volute air cushion reinforcement propelling unit produces to back pressure, be greater than that the volute air cushion reinforcement propelling unit on right side produces to back pressure, aircraft to the right direction is turned, and this thrust is backward poor larger, the radius that aircraft bends to right is just less, utilize the thrust of front volute air cushion reinforcement propelling unit and the different directions that rear volute air cushion reinforcement propelling unit produces of asymmetric unlatching, can make aircraft do various turnings, rotation, the flights such as rolling.
?
Claims (2)
1. rotatable ladder is arranged many flanks volute power vertical take-off and landing aircraft (VTOL aircraft), comprise the wing that fuselage (4) bilateral symmetry installation three row's stageds are arranged, with at row's wing or arrange wing more and away from one end of fuselage (4) is symmetrical two or more front volute air cushion reinforcement propelling units are installed, and after near two of fuselage (4) bilateral symmetry installations tail (14) volute air cushion reinforcement propelling unit, it is characterized in that: fuselage (4) bilateral symmetry is installed the wing that three row's stageds are arranged, the front-seat the most close head of wing (1) and nearest from driving compartment (2) and the machine back of the body (12), the position at middle row's wing close fuselage (4) middle part below front-seat wing, the position at rear row's wing close fuselage (4) rear portion below middle row's wing, the front edge of middle row's wing is near the antemarginal perpendicular line of front-seat wing, the front edge of rear row's wing is near the antemarginal perpendicular line of middle row's wing, can make like this to arrange high-speed air flow that wing upper side flows through in the past and partly blow over the upper side of middle row's wing, simultaneously, the slightly slow high-speed air flow major part of high-speed air flow that this wing upper side flows through flowing through from front-seat wing downside enters into the upper side of row's wing, thereby make the upper side density of air of middle row's wing large compared with the density of air of front-seat wing upper side, the speed that must add like this air stream of big-and-middle row's wing upper side, and air stream density and the flow velocity of the air stream density of middle row's wing downside and flow velocity and front-seat wing downside are close, this just equals to have strengthened the velocity contrast of middle row's wing upper side air stream and downside air stream, and then strengthened the lift that middle row's wing produces, in like manner, therefrom arrange high-speed air flow that wing upper side flows through and partly blow over the upper side of rear row's wing, simultaneously, therefrom arrange the upper side that the slightly slow high-speed air flow major part of high-speed air flow that this wing upper side flows through that wing downside flows through enters into rear row's wing, thereby make the upper side density of air of rear row's wing large compared with the density of air of middle row's wing upper side, must strengthen like this speed of the air stream of rear row's wing upper side, then arrange air stream density and flow velocity and the front row of wing downside, air stream density and the flow velocity of middle row's wing downside are close, this just equals to have strengthened the velocity contrast of rear row's wing upper side air stream and downside air stream, and then strengthened the lift that rear row's wing produces, the middle part of each row's wing has an axle to be connected with fuselage (4), wing can be done rotation forward or backward around this axle, Q:-45 °≤Q≤90 ° of its anglec of rotation, when wing is during in horizontality, its wing front edge downwards maximum rotation 45° angle, the maximum half-twist angle that can make progress is vertical to wing, when aircraft takes off vertically by land, the front edges of three row's wings rotate up 90 ° vertical to wing, open all volute air cushion reinforcement propelling unit Jet with downward flow direction and hold up aircraft and take off vertically, need to be to front upper place during oblique climbing in horizontal flight when aircraft, the wing front edge of front-seat wing or front row, middle row, rear row three row's wings rotates up certain angle, so just can make aircraft oblique flight of climbing to front upper place, need to be to front lower place during oblique underriding in horizontal flight when aircraft, the wing front edge of front-seat wing or front row, middle row, rear row three row's wings is rotated down certain angle, so just can make aircraft oblique diving flight to front lower place, at a row or multi-row wing S. A., stretch out wing away from the position of fuselage (4) end 100mm ~ 1000mm, the two or more front volute air cushion reinforcement propelling units that can independently rotate around wing S. A. of symmetrical installation, one section that stretches out wing 100mm ~ 1000mm is front volute air cushion reinforcement propelling unit pipe link, and front volute air cushion reinforcement propelling unit is not associated around this axle rotation with wing around the rotation of wing S. A., front volute air cushion reinforcement propelling unit is around P:-90 °≤Q≤90 ° of the wing S. A. anglec of rotation, be that aircraft is when level attitude, the angle of rake air nozzle of current volute air cushion reinforcement is vertically downward time, the angle of rake air nozzle of front volute air cushion reinforcement can to 90 ° of head (1) direction rotations to the angle of rake air nozzle of front volute air cushion reinforcement forward horizontal-jet, to 90 ° of tail (14) direction rotations to the angle of rake air nozzle of front volute air cushion reinforcement horizontal-jet backwards, volute air cushion reinforcement propelling unit after near fuselage bilateral symmetry tail (14) is installed two, rear volute air cushion reinforcement propelling unit and fuselage (4) pipe link are rear volute air cushion reinforcement propelling unit pipe link, rear volute air cushion reinforcement propelling unit can be around P:-90 °≤Q≤90 ° of the rear volute air cushion reinforcement propelling unit pipe link anglec of rotation, be that aircraft is when level attitude, when the angle of rake air nozzle of rear volute air cushion reinforcement is vertically downward time, the angle of rake air nozzle of rear volute air cushion reinforcement can be to 90 ° of head (1) direction rotations to the angle of rake air nozzle of rear volute air cushion reinforcement horizontal-jet forward, to 90 ° of tail (14) direction rotations to the angle of rake air nozzle of rear volute air cushion reinforcement horizontal-jet backwards, when current volute air cushion reinforcement propelling unit and the angle of rake air nozzle of rear volute air cushion reinforcement spray downward vertically, produce the lift that upwards holds up aircraft, current volute air cushion reinforcement propelling unit and the angle of rake air nozzle of rear volute air cushion reinforcement are during to tail (14) direction horizontal-jet, generation is to the thrust of preacceleration, current volute air cushion reinforcement propelling unit and the angle of rake air nozzle of rear volute air cushion reinforcement be during to head (1) direction horizontal-jet, the thrust that produces backward and aircraft is slowed down.
2. rotatable ladder as claimed in claim 1 is arranged many flanks volute power vertical take-off and landing aircraft (VTOL aircraft), it is characterized in that: the front volute air cushion reinforcement propelling unit of installing away from fuselage (4) end at wing, must install with the central axis symmetry of fuselage (4), the rear volute air cushion reinforcement propelling unit that install near fuselage (4) both sides tail (14), also must install with the central axis symmetry of fuselage (4), when front volute air cushion reinforcement propelling units of installing in these symmetries or rear volute air cushion reinforcement propelling unit symmetry are opened and make its injection direction consistent, could produce thrust in the same way, when the front volute air cushion reinforcement propelling unit of symmetry or after volute air cushion reinforcement propelling unit open simultaneously, but when its injection direction is inconsistent, can make aircraft produce the power of different directions, when the front volute air cushion reinforcement propelling unit in left side and rear volute air cushion reinforcement propelling unit are opened and are sprayed to tail (14) direction, close one or several front volute air cushion reinforcement propelling unit and the rear volute air cushion reinforcement propelling unit on right side, other several volute air cushion reinforcement propelling unit injection directions are consistent with the volute air cushion reinforcement propelling unit injection direction on right side, at this moment, left side volute air cushion reinforcement propelling unit produces to back pressure, be greater than that the volute air cushion reinforcement propelling unit on right side produces to back pressure, aircraft to the right direction is turned, and this thrust is backward poor larger, the radius that aircraft bends to right is just less, utilize the thrust of front volute air cushion reinforcement propelling unit and the different directions that rear volute air cushion reinforcement propelling unit produces of asymmetric unlatching, can make aircraft do various turnings, rotation, the flights such as rolling.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310514269.7A CN103523220B (en) | 2013-10-28 | 2013-10-28 | Rotatable stepped arrangement multi-flank volute power vertical takeoff and landing airplane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310514269.7A CN103523220B (en) | 2013-10-28 | 2013-10-28 | Rotatable stepped arrangement multi-flank volute power vertical takeoff and landing airplane |
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| CN103523220A true CN103523220A (en) | 2014-01-22 |
| CN103523220B CN103523220B (en) | 2015-06-17 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005399A (en) * | 2015-11-18 | 2016-10-12 | 黄登 | Tilt wing aircraft |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0356541A1 (en) * | 1988-08-30 | 1990-03-07 | Karl Eickmann | Vertically taking off and landing aircraft, which flies horizontally on wings which include a pipe structure and which can be pivoted from substantially vertical to horizontal position |
| DE3830930A1 (en) * | 1988-09-12 | 1990-03-15 | Breinlich Richard Dr | Vertical take-off aircraft |
| US5823468A (en) * | 1995-10-24 | 1998-10-20 | Bothe; Hans-Jurgen | Hybrid aircraft |
| CN1907806A (en) * | 2005-08-02 | 2007-02-07 | 韩培洲 | helicopter with tilted front rotary wing |
| CN101450714A (en) * | 2007-12-05 | 2009-06-10 | 陈昌志 | Jet type helicopters |
| CN102991672A (en) * | 2012-05-18 | 2013-03-27 | 宋新民 | Variable power wing vertical short-range taking off and landing aircraft |
-
2013
- 2013-10-28 CN CN201310514269.7A patent/CN103523220B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0356541A1 (en) * | 1988-08-30 | 1990-03-07 | Karl Eickmann | Vertically taking off and landing aircraft, which flies horizontally on wings which include a pipe structure and which can be pivoted from substantially vertical to horizontal position |
| DE3830930A1 (en) * | 1988-09-12 | 1990-03-15 | Breinlich Richard Dr | Vertical take-off aircraft |
| US5823468A (en) * | 1995-10-24 | 1998-10-20 | Bothe; Hans-Jurgen | Hybrid aircraft |
| CN1907806A (en) * | 2005-08-02 | 2007-02-07 | 韩培洲 | helicopter with tilted front rotary wing |
| CN101450714A (en) * | 2007-12-05 | 2009-06-10 | 陈昌志 | Jet type helicopters |
| CN102991672A (en) * | 2012-05-18 | 2013-03-27 | 宋新民 | Variable power wing vertical short-range taking off and landing aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005399A (en) * | 2015-11-18 | 2016-10-12 | 黄登 | Tilt wing aircraft |
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| CN103523220B (en) | 2015-06-17 |
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Effective date of registration: 20180710 Address after: 226371 North four groups of Tu Shan village, Xingdong Town, Tongzhou District, Nantong, Jiangsu Patentee after: NANTONG HUAXIA AIRPLANE ENGINEERING TECHNOLOGY CO., LTD. Address before: 314408 304, room 2, 30 shallow water bay, Kashi street, Haining, Jiaxing, Zhejiang. Patentee before: Wei Boqing |