CN104787329A - Lifting single bodies for vertical landing gear with fixed wings - Google Patents
Lifting single bodies for vertical landing gear with fixed wings Download PDFInfo
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- CN104787329A CN104787329A CN201510175535.7A CN201510175535A CN104787329A CN 104787329 A CN104787329 A CN 104787329A CN 201510175535 A CN201510175535 A CN 201510175535A CN 104787329 A CN104787329 A CN 104787329A
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- wing
- cylindrical barrel
- wings
- fixed wings
- fixed
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Abstract
The invention discloses lifting single bodies for a vertical landing gear with fixed wings. Each lifting single body includes a cylindrical barrel (1), air outlets (2), rotors (3), wings (4), end plates (8), wing drive wheels (9) and rotor drive wheels (10). Two lifting single bodies with the same structures are arranged in parallel or coaxially to form the vertical landing gear with the fixed wings; each lifting single body has the characteristics that two fixed wings with two adjustable attack angles are mounted on each lifting single body, and the high-speed airflow generating lifting force comes from a centrifugal fan rotating at a high speed; the wingspan directions of the fixed wings are consistent with that of the axis of the centrifugal fan; the front edges of the wings are placed at the strip-shaped air outlets which are positioned at the highest and lowest positions of the cross section of the centrifugal fan and extend in the tangential directions. The lifting single bodies for the vertical landing gear with fixed wings have the benefits that the high-speed airflow blowing through the fixed wings is centralized, so that the average lifting force on a unit area of the wings is increased.
Description
Technical field
Have a vertical takeoff and landing (VTOL) device for fixed-wing, to be equipped with the adjustable fixed wing of the angle of attack for feature, but the high velocity air producing lift comes from the centrifugal blower of High Rotation Speed.Belong to the aircraft circles that can take off vertically or land.
Background technology
Research and the production of omniplane have obtained mirable achievement, and the military field of converging in sophisticated technology is exhibited one's skill to the full, but do not stop people to the exploration of new vertical take-off and landing device.
Pertinent literature indicates: the quality factor of existing Rotor Helicopter rotor are lower, and waste of power is larger.In fact, because multiple rotor is connected with main shaft with radial, cause the speed of each point in each rotor spanwise in the linear distribution being initial point with zero, and square being directly proportional of profile lift and speed, therefore the average lift on wing unit area must be very high.And the approach improved, have with regard to wing formula vertical takeoff and landing (VTOL) device with regard to what produce lift based on wing theory, universal method is exactly by blower fan generation high velocity air.
Chinese patent " Novel flight and aircraft " (application number: 201010611386.1, applicant: Dong Shugong etc.) disclose a kind of method, allow the artificial high velocity air produced all flow through the upper surface of fuselage below wing and wing simultaneously, then flow to rear.
Chinese patent " helicopter without rotors " (Authorization Notice No.: CN2714420Y, patentee: Tangshan Datang Power Machinery Co., Ltd.) disclose and a kind ofly comprise half construction of wind tunnel be made up of left and right sides air baffle, built-in one or more groups by (axial flow) fan and the girdle wing group that forms with some fins.
Chinese patent " omniplane and assembly thereof " (application number: 87105599, applicant: Kimberley. Wei Er. Sa Delia (Australia)) disclose and comprise one and have the fuselage being fixedly connected with wing, one is rotatably installed in turbo-propeller in wing and the many groups of pilot blades for controlling air-flow direction be arranged in above or below turbo-propeller ...
The weak point of said structure is: the limited area that the round exit of half-headed long and narrow formula half construction of wind tunnel and prerotator will cause the high velocity air of discharging inswept, and fixed-wing spread is open, prolongation, cause again the high velocity air of blowing over fixed-wing to be concentrated not, to blow overtaking journey long, the fin being arranged in back is in by the air-flow of front a slice disturbance, and lift will sharply decline; Thus the average lift on wing unit area still can not be very high.
Summary of the invention
The object of the present invention is to provide a kind of lift monomer with the vertical takeoff and landing (VTOL) device of fixed-wing.
The object of the present invention is achieved like this: comprise cylindrical barrel 1, exhaust outlet 2, rotor 3, wing 4, end plate 8, wing drive wheel 9 and rotor drive wheel 10; Wherein, two exhaust outlets 2 and two panels wing 4 are in antisymmetrical state; As the cylindrical barrel 1 of centrifugal blower shell, its two ends are fixed with the end plate 8 being with circular induction opening; Two rotors 3 with sweepback vane rotate in cylindrical barrel 1 by the bearing seat on end plate 8 axis and rotor drive wheel 10; The extreme higher position of cylindrical barrel 1 and extreme lower position respectively install the exhaust outlet 2 that a rectangular cylinder is used as centrifugal blower, the generatrix direction of cylindrical barrel 1 described in the long edge of its transversal surface, and described rectangular cylinder should stretch along the tangential direction of circular cross section; Respectively install a slice wing 4 at each exhaust outlet 2 place, its leading edge in the face of exhaust outlet 2, and realizes small size rotation by the rotating shaft at two ends, bearing seat and wing drive wheel 9.
The vertical takeoff and landing (VTOL) device with fixed-wing is made up of side by side or coaxially two lift monomers, each lift monomer comes from the centrifugal blower of High Rotation Speed for feature with the high velocity air of fixed wing and generation lift that two adjustable angles of attack are housed, fixed wing spanwise is consistent with the major axes orientation of centrifugal blower, and the leading edge of wing is in the highest and extreme lower position of centrifugal blower transversal surface and the bar shaped exhaust outlet place of tangentially stretching.Its beneficial effect is: the high velocity air of blowing over fixed-wing is concentrated, and improves the average lift on wing unit area.
A kind of lift monomer with the vertical takeoff and landing (VTOL) device of fixed-wing comprises two exhaust outlets and two panels wing that are in antisymmetrical state; As the cylindrical barrel of centrifugal blower shell, its two ends are fixed with the end plate being with circular induction opening, and two rotors with sweepback vane rotate in described chamber by the bearing seat be packed on described end plate axis and rotor drive wheel; The extreme higher position of each described chamber and extreme lower position respectively install the exhaust outlet that a rectangular cylinder is used as centrifugal blower, the generatrix direction of cylindrical barrel described in the long edge of rectangular cross section, and described rectangular cylinder stretches along the tangential direction of the highs and lows of centrifugal blower shell circular cross section, smooth and easy to guarantee centrifugal blower exhaust stream; Respectively install a slice wing at two described exhaust outlet places, the leading edge of wing in the face of exhaust outlet, and realizes slightly rotating, to adjust the angle of attack of wing by the rotating shaft at wing two ends, the bearing seat at described end plate place and wing drive wheel.
Lift monomer described in two can form vertical takeoff and landing (VTOL) device side by side or coaxially.
During installation arranged side by side, the lift monomer described in two is symmetrical in longitudinal vertical plane of symmetry of carrier (i.e. aircraft), the axis of two rotors and the longitudinal axis parallel of carrier; In order to ensure the conservation of angular momentum of vertical takeoff and landing (VTOL) device and carrier thereof, turning to of two rotors is contrary; The wing of two tops occupies inner side, and the fixed-wing of two belows occupies outside; Or the wing of two tops occupies outside, and the fixed-wing of two belows occupies inner side; To guarantee that vertical takeoff and landing (VTOL) device and the stressed of carrier thereof are in state of equilibrium.
When longitudinally installing, the lift monomer described in two is coaxially installed in longitudinal vertical plane of symmetry of carrier (i.e. aircraft); Turning to of two described rotors still needs on the contrary; Four exhaust outlets and wing antisymmetry are in longitudinal vertical plane of symmetry of carrier.
The present invention only provides the power of aircraft ascending, descending; And the power that aircraft carrier moves ahead need be considered separately, and vertical takeoff and landing (VTOL) device rotor rotates and the propulsion source of wing angle of attack change also need from aircraft carrier and by the transmission device of routine.
Accompanying drawing explanation
A kind of horizontal cross-sectional schematic of lift monomer with the vertical takeoff and landing (VTOL) device of fixed-wing of Fig. 1.
Horizontal cross-sectional schematic when the lift monomer of Fig. 2 two discharges side by side.
The downward cutaway view of rotor axis horizontal surface is crossed when the lift monomer coaxial line of Fig. 3 two discharges.
When the lift monomer coaxial line of Fig. 4 two discharges, A-A is to cross-sectional schematic.
Detailed description of the invention
Provide the preferred embodiments of the present invention below and be illustrated by reference to the accompanying drawings.
As shown in Figure 1, a kind of lift monomer with the vertical takeoff and landing (VTOL) device of fixed-wing comprises cylindrical barrel 1, exhaust outlet 2, rotor 3, wing 4, carrier 5, wing rotating shaft 6, end plate 8, wing drive wheel 9 and rotor drive wheel 10; Wherein, as the cylindrical barrel 1 of centrifugal blower shell, its two ends are fixed with the end plate 8 being with circular induction opening; Rotor 3 with sweepback vane rotates in cylindrical barrel 1 by the bearing seat be packed on end plate 8 axis and rotor drive wheel 10; Extreme higher position in cylindrical barrel 1 and extreme lower position respectively install the exhaust outlet 2 that a rectangular cylinder is used as centrifugal blower, the generatrix direction of cylindrical barrel 1 described in the long edge of rectangular cross section, and described rectangular cylinder should stretch along the tangential direction of the circular cross section highs and lows of cylindrical barrel 1, smooth and easy to guarantee centrifugal blower exhaust stream.Respectively install a slice wing 4 at two exhaust outlet 2 places, the leading edge of wing 4 in the face of exhaust outlet 2, and realizes small size rotation, to adjust the angle of attack of wing 4 by the rotating shaft at wing 4 two ends, the bearing seat at end plate 8 place and wing drive wheel 9.As can be seen from the figure two exhaust outlets 2 and two panels wing 4 are in antisymmetrical state.
As shown in Figure 2, the lift monomer described in two forms vertical takeoff and landing (VTOL) device side by side, is symmetrical in longitudinal vertical plane of symmetry of carrier (i.e. aircraft) 5; The axis of two rotors 3 and carrier 5 longitudinal axis parallel; In order to ensure the conservation of angular momentum of vertical takeoff and landing (VTOL) device and carrier 5 thereof, turning to of two rotors 3 is contrary; The wing 4 of two tops occupies inner side, and the wing 4 of two belows occupies outside; Or the wing 4 of two tops occupies outside, and the wing 4 of two belows occupies inner side; To guarantee that vertical takeoff and landing (VTOL) device and carrier 5 the stressed of (i.e. aircraft) thereof are in state of equilibrium.
As shown in Figure 3,4, the lift monomer described in two coaxially forms vertical takeoff and landing (VTOL) device, and the axis of two rotors 3 is positioned at longitudinal vertical plane of symmetry of carrier 5 and turns to contrary; The wing 4 of two tops and the wing 4 difference antisymmetry of two belows are in longitudinal vertical plane of symmetry of carrier 5.Be the downward cutaway view of rotor 3 axis due to this figure therefore failed the position of two wings 4 that top is shown, and two of below wings 4 are in antisymmetrical state.
Described vertical takeoff and landing (VTOL) device only provides the power of aircraft ascending, descending; And the power that aircraft carrier moves ahead need be considered separately, and vertical takeoff and landing (VTOL) device rotor rotates and the propulsion source of wing angle of attack change also need from aircraft carrier and by the transmission device of routine.
Its beneficial effect is: the high velocity air of blowing over fixed-wing is concentrated, and improves the average lift on wing unit area.
Claims (1)
1. there is a lift monomer for the vertical takeoff and landing (VTOL) device of fixed-wing, it is characterized in that: comprise cylindrical barrel (1), exhaust outlet (2), rotor (3), wing (4), end plate (8), wing drive wheel (9) and rotor drive wheel (10); Wherein, two exhaust outlets (2) and two panels wing (4) are in antisymmetrical state; As the cylindrical barrel (1) of centrifugal blower shell, its two ends are fixed with the end plate (8) being with circular induction opening; Two rotors with sweepback vane (3) rotate in cylindrical barrel (1) by the bearing seat on end plate (8) axis and rotor drive wheel (10); The extreme higher position of cylindrical barrel (1) and extreme lower position respectively install the exhaust outlet (2) that a rectangular cylinder is used as centrifugal blower, the generatrix direction of cylindrical barrel (1) described in the long edge of its transversal surface, and described rectangular cylinder should stretch along the tangential direction of circular cross section; Respectively install a slice wing (4) at each exhaust outlet (2) place, its leading edge in the face of exhaust outlet (2), and realizes slightly rotating by the rotating shaft at two ends, bearing seat and wing drive wheel (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510175535.7A CN104787329B (en) | 2013-07-26 | 2013-07-26 | Lifting single bodies for vertical landing gear with fixed wings |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510175535.7A CN104787329B (en) | 2013-07-26 | 2013-07-26 | Lifting single bodies for vertical landing gear with fixed wings |
| CN201310319776.5A CN103407572B (en) | 2013-07-26 | 2013-07-26 | A kind of vertical takeoff and landing (VTOL) device with fixed-wing |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310319776.5A Division CN103407572B (en) | 2013-07-26 | 2013-07-26 | A kind of vertical takeoff and landing (VTOL) device with fixed-wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104787329A true CN104787329A (en) | 2015-07-22 |
| CN104787329B CN104787329B (en) | 2017-01-25 |
Family
ID=49600636
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510175535.7A Active CN104787329B (en) | 2013-07-26 | 2013-07-26 | Lifting single bodies for vertical landing gear with fixed wings |
| CN201310319776.5A Expired - Fee Related CN103407572B (en) | 2013-07-26 | 2013-07-26 | A kind of vertical takeoff and landing (VTOL) device with fixed-wing |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310319776.5A Expired - Fee Related CN103407572B (en) | 2013-07-26 | 2013-07-26 | A kind of vertical takeoff and landing (VTOL) device with fixed-wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN104787329B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017121116A1 (en) * | 2016-01-14 | 2017-07-20 | 王佐良 | Engine for vertically taking off or landing with airfoil lift |
| CN108860628A (en) * | 2018-05-04 | 2018-11-23 | 黄冠达 | Roll wing centrifugal power equipment in semiclosed angle of sweep |
| RU2805891C1 (en) * | 2023-04-03 | 2023-10-24 | Альберт Георгиевич Битуев | Unmanned aerial vehicle for vtol |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103863562A (en) * | 2014-03-29 | 2014-06-18 | 郑全逸 | Vertical-lifting device with combined propellers |
| RU208771U1 (en) * | 2021-10-18 | 2022-01-12 | Игорь Сергеевич Ковалев | Device for creating lifting force |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6270036B1 (en) * | 1997-01-24 | 2001-08-07 | Charles S. Lowe, Jr. | Blown air lift generating rotating airfoil aircraft |
| CN1559817A (en) * | 2004-03-03 | 2005-01-05 | 博 陈 | Two-purpose automobile convertible into aircraft |
| CN101003302A (en) * | 2007-01-02 | 2007-07-25 | 杨旭 | An aviation aircraft |
| CN101020503A (en) * | 2007-03-12 | 2007-08-22 | 哈尔滨工程大学 | Hinged wing type lift force generator |
| US20090084907A1 (en) * | 2006-03-01 | 2009-04-02 | Urban Aeronautics Ltd. | Ground Effect Vanes Arrangement |
| CN102548842A (en) * | 2009-07-06 | 2012-07-04 | 艾希尔有限公司 | Craft and method for assembling craft with controlled spin |
-
2013
- 2013-07-26 CN CN201510175535.7A patent/CN104787329B/en active Active
- 2013-07-26 CN CN201310319776.5A patent/CN103407572B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6270036B1 (en) * | 1997-01-24 | 2001-08-07 | Charles S. Lowe, Jr. | Blown air lift generating rotating airfoil aircraft |
| CN1559817A (en) * | 2004-03-03 | 2005-01-05 | 博 陈 | Two-purpose automobile convertible into aircraft |
| US20090084907A1 (en) * | 2006-03-01 | 2009-04-02 | Urban Aeronautics Ltd. | Ground Effect Vanes Arrangement |
| CN101003302A (en) * | 2007-01-02 | 2007-07-25 | 杨旭 | An aviation aircraft |
| CN101020503A (en) * | 2007-03-12 | 2007-08-22 | 哈尔滨工程大学 | Hinged wing type lift force generator |
| CN102548842A (en) * | 2009-07-06 | 2012-07-04 | 艾希尔有限公司 | Craft and method for assembling craft with controlled spin |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017121116A1 (en) * | 2016-01-14 | 2017-07-20 | 王佐良 | Engine for vertically taking off or landing with airfoil lift |
| CN108860628A (en) * | 2018-05-04 | 2018-11-23 | 黄冠达 | Roll wing centrifugal power equipment in semiclosed angle of sweep |
| RU2805891C1 (en) * | 2023-04-03 | 2023-10-24 | Альберт Георгиевич Битуев | Unmanned aerial vehicle for vtol |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104787329B (en) | 2017-01-25 |
| CN103407572A (en) | 2013-11-27 |
| CN103407572B (en) | 2015-09-30 |
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| C14 | Grant of patent or utility model | ||
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