CN205366075U - VTOL formula fixed wing aircraft - Google Patents
VTOL formula fixed wing aircraft Download PDFInfo
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- CN205366075U CN205366075U CN201620145156.3U CN201620145156U CN205366075U CN 205366075 U CN205366075 U CN 205366075U CN 201620145156 U CN201620145156 U CN 201620145156U CN 205366075 U CN205366075 U CN 205366075U
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- wing
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- vtol
- fixed wing
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Abstract
The utility model relates to a VTOL formula fixed wing aircraft, including the central shell body, the central shell body is including the upside cavity of intercommunication portion of breathing in and downside cavity gas exhalation portion, and the cavity is breathed in the portion upper end and has been offered the induction port, be provided with in cavity portion of breathing in or cavity gas exhalation portion to the getter device of supplying gas in the gas exhalation portion, the outer circumference department equidistance of cavity gas exhalation portion spaced apart be equipped with with a plurality of air jets of gas exhalation portion inner chamber intercommunication, encircle and be provided with the annular wing that approaches outside the gas exhalation outside interior the thickness. This application of this application simple structure can realize the purpose in arbitrary topography VTOL. This application cost drops into lowly, is favorable to being widely used and sprays in the agricultural, environment field such as seek and visit.
Description
Technical field
The application relates to a kind of VTOL formula Fixed Wing AirVehicle.
Background technology
Along with the development of science and technology, multiple fields such as unmanned plane or small-sized manned vehicle have been applied in taking photo by plane, measure, transport, overhaul, rescue.Unmanned plane of the prior art or small-sized manned vehicle are mostly Fixed Wing AirVehicle or Multi-axis aircraft.
Fixed Wing AirVehicle arranges the wing of one or more symmetry, and propeller is set on wing, rotated the air-flow produced by driven by motor propeller and promote aircraft flight.This kind of aircraft landing needs a longer runway, needs when taking off to bring up to and just can take off at a high speed, bigger by the influence of topography.
The correlation technique content of the application has no report.
Summary of the invention
The purpose of the application is in that to propose a kind of simple in construction, can at the VTOL formula Fixed Wing AirVehicle of any landform VTOL.
The purpose of the application is achieved in that VTOL formula Fixed Wing AirVehicle includes center housing, described center housing includes upside cavity suction unit and the underside cavity jet portion of connection, cavity suction unit upper end offers air entry, in cavity suction unit or cavity jet portion, the getter device supplied gas in oriented jet portion is set, offering and some puff prots of jet portion inner space in cavity jet portion excircle place equi-spaced apart, ring spray gas portion is outside equipped with the outer thin annular wing of interior thickness.
The application sprays high velocity air by symmetrically arranged puff prot to annular wing so that annular wing upper and lower surface bad student's pressure reduction, so that aircraft obtains lift upwards.In takeoff and landing process, by progressively changing the rotating speed of high-speed induction motor, it is ensured that takeoff and landing stablized by aircraft.In flight course, by regulate aileron can change of flight device ambient air density, the flow direction, and then adjust flight attitude, it is achieved turn to, hover, front fly.In sum, the application simple in construction, it may be achieved in the purpose of any landform VTOL.The application cost puts into low, is conducive to being widely used in agricultural spray, and environment such as seeks and visits at the field.
Accompanying drawing illustrates: the concrete structure of the application is provided by following drawings and Examples:
Fig. 1 is the structural representation of VTOL formula Fixed Wing AirVehicle；
Fig. 2 is the plan structure schematic diagram of VTOL formula Fixed Wing AirVehicle.
Legend: 1, center of gravity regulates spin-block, 2, connecting rod, 3, blade, 4, suction unit, 4-1, air entry, 5, center housing, 6, high-speed induction motor, 7, undercarriage, 8, electric appliance box, 9, jet portion, 9-1, puff prot, 10, annular wing, 10-1, wing inner edge, 10-2, wing outer rim, 10-3, arc convex, 11, aileron.
Detailed description of the invention: the application, not by the restriction of following embodiment, can determine specific embodiment according to the technical scheme of the application and practical situation.
Embodiment: as shown in Figure 1, 2, VTOL formula Fixed Wing AirVehicle includes center housing 5, described center housing 5 includes upside cavity suction unit 4 and the underside cavity jet portion 9 of connection, cavity suction unit 4 upper end offers air entry 4-1, in cavity suction unit 4 or cavity jet portion 9, the getter device supplied gas in oriented jet portion 9 is set, offering the some puff prot 9-1 with jet portion 9 inner space in cavity jet portion 9 excircle place equi-spaced apart, ring spray gas portion 9 is outside equipped with the outer thin annular wing 10 of interior thickness.
The blade 3 that described getter device is rotated by high-speed induction motor 6 forms, and described blade 3 is positioned close to air entry 4-1 place.
Described center housing 5 external symmetry distribution has to connect some connecting rods 2 of annular wing 10.Described connecting rod 2 is screw mandrel, is connected with center of gravity thereon and regulates spin-block 1.The spin-block 1 position in connecting rod 2 is regulated by adjusting center of gravity, the position of centre of gravity that namely adjustable the application is overall, thus the first successive step the application stability when flight.
Annular wing 10 upper surface has an arc convex 10-3 near 10-1 place, wing inner edge, and the wing inner edge 10-1 end face of described annular wing 10 is arcwall face.Puff prot 9-1 place is just provided with the aileron 11 that can swing up and down by the wing outer rim 10-2 of annular wing 10, by adjusting swinging up and down of aileron 11, change the air-flow speed by annular wing 10 lower surface with aileron 11 lower surface, thus change annular wing 10 low pressure, and then the flight attitude that adjustable the application is when flight.
It is equiped with undercarriage 7 in center housing 5 lower surface, electric appliance box 8 it is provided with between undercarriage 7 and center housing 5, it is provided with in electric appliance box 8 to control high-speed induction motor 6 rotating speed, in order to control the control circuit that aileron 11 swings, the non-the present application point of this circuit, it can adopt control circuit of the prior art, and physical circuit is not described in detail at this.
Be provided with in electric appliance box 8 side to install take photo by plane, the instrument container of the instrument such as sampling.
When taking off, by getter device, air stream is sucked in jet portion 9, and outwards sprayed by puff prot 9-1, air stream is to the 10-1 place, wing inner edge of annular wing 10, being divided into upper and lower two strands of air-flows, annularly the upper and lower surface of wing 10 is flow through respectively, again converges outside diffluence at wing outer rim 10-2.Owing to annular wing 10 upper surface has arc convex 10-3, flow tube is relatively thin, illustrates that flow velocity is accelerated, and pressure reduces.And annular wing 10 lower surface, airflow obstruction gear effect, flow tube is thicker, flows decrease, and pressure increases, and then the upper and lower surface of annular wing 10 occurs in that pressure differential, and the pressure differential being perpendicular to relative wind direction forms lift, aircraft takeoff.
Air-flow is outwards guided by equally distributed some puff prot 9-1, aircraft can be made steadily to take off, if the current rate of a certain puff prot 9-1 is inadequate, then adjustable aileron 11, annular wing 10 is made to be positioned at the upper and lower surface pressure differential equilibrium at each puff prot 9-1 place so that aircraft steadily takes off.
Obviously, the described above of the application is only for clearly demonstrating the application example, and is not the restriction to presently filed embodiment.Apparent change that every technical scheme belonging to the application is amplified out or variation are still in the row of the protection domain of the application.
Claims (7)
1. a VTOL formula Fixed Wing AirVehicle, it is characterized in that: include center housing, described center housing includes upside cavity suction unit and the underside cavity jet portion of connection, cavity suction unit upper end offers air entry, in cavity suction unit or cavity jet portion, the getter device supplied gas in oriented jet portion is set, offering and some puff prots of jet portion inner space in cavity jet portion excircle place equi-spaced apart, ring spray gas portion is outside equipped with the outer thin annular wing of interior thickness.
2. VTOL formula Fixed Wing AirVehicle as claimed in claim 1, it is characterised in that: the blade that described getter device is rotated by high-speed induction motor forms, and described blade is positioned close to air entry place.
3. VTOL formula Fixed Wing AirVehicle as claimed in claim 1, it is characterised in that: described center housing external symmetry distribution has to connect some connecting rods of annular wing, and described connecting rod is screw mandrel, is connected with center of gravity thereon and regulates spin-block.
4. VTOL formula Fixed Wing AirVehicle as claimed in claim 1, it is characterised in that: annular wing includes wing outer rim and wing inner edge, has an arc convex at annular wing upper surface near wing inner edge place.
5. VTOL formula Fixed Wing AirVehicle as claimed in claim 4, it is characterised in that: the wing inner peripheral end surfaces of described annular wing is arcwall face.
6. VTOL formula Fixed Wing AirVehicle as claimed in claim 4, it is characterised in that: puff prot place is just provided with the aileron that can swing up and down by the wing outer rim of annular wing.
7. VTOL formula Fixed Wing AirVehicle as claimed in claim 1, it is characterised in that: it is equiped with undercarriage in center housing lower surface, between undercarriage and center housing, is provided with electric appliance box, electric appliance box side is provided with instrument container.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620145156.3U CN205366075U (en) | 2016-02-26 | 2016-02-26 | VTOL formula fixed wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620145156.3U CN205366075U (en) | 2016-02-26 | 2016-02-26 | VTOL formula fixed wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205366075U true CN205366075U (en) | 2016-07-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620145156.3U Active CN205366075U (en) | 2016-02-26 | 2016-02-26 | VTOL formula fixed wing aircraft |
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| Country | Link |
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| CN (1) | CN205366075U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106364667A (en) * | 2016-09-28 | 2017-02-01 | 韩建刚 | Aircraft |
| CN107813955A (en) * | 2017-10-18 | 2018-03-20 | 广州市智专信息科技有限公司 | A kind of unmanned plane and corresponding unmanned plane formation display methods |
-
2016
- 2016-02-26 CN CN201620145156.3U patent/CN205366075U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106364667A (en) * | 2016-09-28 | 2017-02-01 | 韩建刚 | Aircraft |
| WO2018059244A1 (en) * | 2016-09-28 | 2018-04-05 | 韩建刚 | Aircraft |
| CN107813955A (en) * | 2017-10-18 | 2018-03-20 | 广州市智专信息科技有限公司 | A kind of unmanned plane and corresponding unmanned plane formation display methods |
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|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |