CN204871605U - Gyroplane can vert - Google Patents
Gyroplane can vert Download PDFInfo
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- CN204871605U CN204871605U CN201520588813.7U CN201520588813U CN204871605U CN 204871605 U CN204871605 U CN 204871605U CN 201520588813 U CN201520588813 U CN 201520588813U CN 204871605 U CN204871605 U CN 204871605U
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- wing
- vert
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Abstract
The utility model discloses a gyroplane can vert, this gyroplane include the rotor that four groups can vert, two wings that can deflect, and the vertical fin, the engine, vert mechanism and pitch -changing mechanism and flight control, vertical fin, wing install respectively on the fuselage and controlled by control system, and four group's rotors are connected with the engine respectively, mechanism and pitch -changing mechanism vert, every group the rotor that can vert includes a plurality of paddles, propeller hub, displacement pull rod and the nacelle that verts, each paddle respectively through propeller hub and displacement pull rod and the nacelle that verts is connected, it is equipped with the mechanism of verting in the nacelle to vert, it connects on the wing girder through the hinge that verts to vert the mechanism, and the wing has one set of independent deflection mechanism can realize the upper and lower deflection of wing in addition. The utility model discloses combined gyroplane and fixed -wing aircraft's advantage, but not only VTOL but also can realize the level flight of long voyage, fast speed flight envelope has been increased, has overcome the shortcoming separately of two kinds of traditional aircraft.
Description
Technical field
The utility model belongs to unmanned plane and control technology field thereof, and being specifically related to one can tiltrotor.
Background technology
On market, existing unmanned plane is mainly divided into two large classes: fixed-wing unmanned plane and rotor wing unmanned aerial vehicle.The former voyage is far away, horizontal flight speed is fast, but needs landing runway.The latter does not need landing runway, but because its thrust realizes by the horizontal direction component of rotor lift, therefore horizontal direction speed does not have fixed wing aircraft fast, and because the generation of its lift produces through fixed-wing by the generation of engine drive main rotor instead of air-flow, therefore the consumption of current of gas consumption rate or same flying distance is more than fixed wing aircraft.
Utility model content
Utility model object: the purpose of this utility model is to solve deficiency of the prior art, provide a kind of not only can vertical takeoff and landing but also the horizontal flight of long voyage, fast speed can be realized, what increase flight envelope can tiltrotor.
Technical scheme: one described in the utility model can tiltrotor, comprise four groups of rotors that can vert, two deflectable wings, vertical fin, driving engine, inclining rotary mechanism and pitch-changing mechanism and flight control system, described vertical fin, wing to be arranged on respectively on fuselage and to control by flight control system, and described four groups of rotors that can vert are connected to driving engine, inclining rotary mechanism and pitch-changing mechanism; The rotor that often can vert described in group comprises some blades, propeller hub, pitch-change-link and the nacelle that verts, each blade is connected with the described nacelle that verts with pitch-change-link respectively by propeller hub, described propeller hub comprises pendulum shake hinge, flapping hinge and pitch hinge, wing inclining rotary mechanism is provided with in the described nacelle that verts, described wing inclining rotary mechanism is hinged and connected to by verting on wing crossbeam, described wing is also provided with deflection machanism, realizes the deflection up and down of wing.
Further, the wherein two groups of rotors in described four groups of rotors that can vert are connected with wing.
Further, the wherein one group of rotor in described four groups of rotors that can vert is connected with vertical fin.
Further, the rear rotor height in described four groups of rotors that can vert is greater than the height of front rotor.
Beneficial effect: effect of the present utility model is the advantage combining cyclogyro and fixed wing aircraft, not only can vertical takeoff and landing but also can realize the horizontal flight of long voyage, fast speed, increased flight envelope, overcame the respective shortcoming of two kinds of conventional aircraft.Compared to the V-22 osprey formula tiltrotor of the U.S., there is not the occlusive effects to rotor down-wash flow in all-moving wing of the present utility model; Owing to still having former and later two rotors to provide lift in the process of verting, thus vertical takeoff and landing pattern and the front speed range flying to change between pattern also wider; In addition provide the diameter of same lift four rotors less than the diameter of two rotors, make this aircraft also by two, left and right rotor is realized landing as screw propeller with sliding attitude of running.Four groups of rotors of the present utility model can share the power of two driving engines in addition, and like this when after a wherein power failure, whole frame aircraft still effectively can run and be unlikely air crash, and the power be just assigned on each rotor can reduce to some extent.
Current the utility model is intended being used for unmanned plane field, after practice test is feasible, also can be used for manned craft.If for AIRLINE & AIRPORT, this aircraft can not realize landing by geographical conditions restriction, can realize navigating by water more at a distance than helicopter simultaneously.If for military field, this aircraft can reach the destination fast as propeller aeroplane, can be detained for a long time to scout or to hit again as helicopter in overhead, destination.
Accompanying drawing explanation
Fig. 1 is the integral structure schematic diagram of the utility model cyclogyro;
Fig. 2 is one group of rotor structure schematic diagram that can vert of the present utility model;
View when Fig. 3 is the high-speed flight of the utility model cyclogyro;
View when Fig. 4 is the utility model cyclogyro high-speed flight driftage.
Detailed description of the invention
One as depicted in figs. 1 and 2 can tiltrotor, comprise four groups of rotors that can vert, the deflectable wing 5,6 of 4, two, front rotor 1, rear rotor 3, the left-handed wing 2 and the dextrorotation wing respectively, vertical fin 7, driving engine, inclining rotary mechanism and pitch-changing mechanism and flight control system, described vertical fin 7, wing 5,6 are connected with described rotor respectively, and described rotor is connected to driving engine, inclining rotary mechanism and pitch-changing mechanism; As shown in Figure 2, the rotor that often can vert described in group comprises three blades 11,12,13, propeller hub 16(comprises pitch hinge 14, lead lag hinge 17, flapping hinge 18), pitch-change-link 19 and the nacelle 20 that verts, each blade is connected with the described nacelle 20 that verts with pitch-change-link 19 respectively by propeller hub 16, be provided with wing inclining rotary mechanism 21 in the described nacelle 20 that verts, described wing inclining rotary mechanism 21 is connected with wing by hinge 22 of verting, and described wing is made up of wing crossbeam 23 and wing shell 24.
As the further optimization of technique scheme, the wherein two groups of rotors in described four groups of rotors that can vert are connected with wing.Wherein one group of rotor in described four groups of rotors that can vert is connected with vertical fin.The quantity of described blade is 2,3 or more sheets.Described blade adopts resilient paddles or rigid blades.Flexible sheets 15 is also provided with between described blade and described propeller hub.For front rotor 1 trailing vortex during minimizing high-speed horizontal flight is to the aerodynamic interference of rear rotor 3, rear rotor 3 is filled higher, reserved position also to the installation of vertical fin simultaneously.
The control process of cyclogyro of the present utility model comprises vertical takeoff and landing, low-speed operations, high-speed flight and the several pattern of driftage turning:
When needing vertical takeoff and landing, the way becoming total distance is adopted to increase or reduce lift by four groups of pitch-changing mechanisms.When needing low-speed operations, the way of feathering is adopted to provide thrust by lift component in the horizontal direction by four groups of pitch-changing mechanisms.When needing high-speed flight, as shown in Figure 3, will wherein two rotors (2,4) tilt forward to perpendicular to heading to provide larger thrust, the change of this thrust can adopt the way becoming total distance to realize by two groups of pitch-changing mechanisms, left and right two wing (5,6) is deflected to horizontal direction to compensate the loss of lift caused after two rotors tilt forward simultaneously.Along with the increase of flying speed, by two groups of pitch-changing mechanisms by two of aircraft top rotor (1,3) furnishing full feathering states, under the effect of relative wind at a high speed, these two rotors still rotate and provide certain lift, do not need driving engine to carry out power input to these two rotors.
During low-speed operations, this aircraft relies on the total of left and right two rotors to realize rolling apart from change, relies on the feathering of four rotors to realize driftage.During high-speed flight, the turning action of this aircraft relies on the deflection of wing and vertical fin to realize.As shown in Figure 4, come back deflection, starboard wing 6 of the port wing 5 that is horizontal is bowed deflection, and the lift just achieving left and right wing is asymmetric, and aircraft is roll to the right; Vertical fin is deflected left simultaneously, just achieve aircraft and go off course to the right; Roll to the right and to the right driftage combine and namely achieve right-hand corner.
Effect of the present utility model is the advantage combining cyclogyro and fixed wing aircraft, not only can vertical takeoff and landing but also can realize the horizontal flight of long voyage, fast speed, increases flight envelope, overcomes the respective shortcoming of two kinds of conventional aircraft.Compared to the V-22 osprey formula tiltrotor of the U.S., there is not the occlusive effects to rotor down-wash flow in all-moving wing of the present utility model; Owing to still having former and later two rotors to provide lift in the process of verting, thus vertical takeoff and landing pattern and the front speed range flying to change between pattern also wider; In addition provide the diameter of same lift four rotors less than the diameter of two rotors, make this aircraft also by two, left and right rotor is realized landing as screw propeller with sliding attitude of running.Four groups of rotors of the present utility model can share the power of two driving engines in addition, and like this when after a wherein power failure, whole frame aircraft still effectively can run and be unlikely air crash, and the power be just assigned on each rotor can reduce to some extent.
Current the utility model is intended being used for unmanned plane field, after practice test is feasible, also can be used for manned craft.If for AIRLINE & AIRPORT, this aircraft can not realize landing by geographical conditions restriction, can realize navigating by water more at a distance than helicopter simultaneously.If for military field, this aircraft can reach the destination fast as propeller aeroplane, can be detained for a long time to scout or to hit again as helicopter in overhead, destination.
The above, it is only preferred embodiment of the present utility model, not any pro forma restriction is done to the utility model, although the utility model discloses as above with preferred embodiment, but and be not used to limit the utility model, any those skilled in the art, do not departing within the scope of technical solutions of the utility model, make a little change when the technology contents of above-mentioned announcement can be utilized or be modified to the Equivalent embodiments of equivalent variations, in every case be the content not departing from technical solutions of the utility model, according to any simple modification that technical spirit of the present utility model is done above embodiment, equivalent variations and modification, all still belong in the scope of technical solutions of the utility model.
Claims (5)
1. one kind can tiltrotor, it is characterized in that: comprise four groups of rotors that can vert, two deflectable wings, vertical fin, driving engine, inclining rotary mechanism and pitch-changing mechanism and flight control system, described vertical fin, wing to be arranged on respectively on fuselage and to control by flight control system, and described four groups of rotors that can vert are connected to driving engine, inclining rotary mechanism and pitch-changing mechanism; The rotor that often can vert described in group comprises some blades, propeller hub, pitch-change-link and the nacelle that verts, each blade is connected with the described nacelle that verts with pitch-change-link respectively by propeller hub, described propeller hub comprises pendulum shake hinge, flapping hinge and pitch hinge, wing inclining rotary mechanism is provided with in the described nacelle that verts, described wing inclining rotary mechanism is hinged and connected to by verting on wing crossbeam, described wing is also provided with deflection machanism, realizes the deflection up and down of wing.
2. one according to claim 1 can tiltrotor, it is characterized in that: the wherein two groups of rotors in described four groups of rotors that can vert are connected with wing.
3. one according to claim 1 can tiltrotor, it is characterized in that: the wherein one group of rotor in described four groups of rotors that can vert is connected with vertical fin.
4. the one according to claim 1 or 2 or 3 can tiltrotor, it is characterized in that: the rear rotor height in described four groups of rotors that can vert is greater than the height of front rotor.
5. one according to claim 1 can tiltrotor, it is characterized in that: be also provided with flexible sheets between described pitch hinge and described universal hinge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520588813.7U CN204871605U (en) | 2015-08-03 | 2015-08-03 | Gyroplane can vert |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520588813.7U CN204871605U (en) | 2015-08-03 | 2015-08-03 | Gyroplane can vert |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204871605U true CN204871605U (en) | 2015-12-16 |
Family
ID=54816010
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520588813.7U Expired - Fee Related CN204871605U (en) | 2015-08-03 | 2015-08-03 | Gyroplane can vert |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204871605U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105083551A (en) * | 2015-08-03 | 2015-11-25 | 江苏工程职业技术学院 | Tilt rotary-wing aircraft and control method thereof |
| CN113232851A (en) * | 2021-06-28 | 2021-08-10 | 宁波阿瑞斯自动化技术有限公司 | Multi-shaft coaxial double-propeller multi-rotor unmanned aerial vehicle |
-
2015
- 2015-08-03 CN CN201520588813.7U patent/CN204871605U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105083551A (en) * | 2015-08-03 | 2015-11-25 | 江苏工程职业技术学院 | Tilt rotary-wing aircraft and control method thereof |
| CN113232851A (en) * | 2021-06-28 | 2021-08-10 | 宁波阿瑞斯自动化技术有限公司 | Multi-shaft coaxial double-propeller multi-rotor unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151216 Termination date: 20160803 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |