CN105129097A - Unmanned aerial vehicle capable of taking off and landing vertically - Google Patents
Unmanned aerial vehicle capable of taking off and landing vertically Download PDFInfo
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- CN105129097A CN105129097A CN201510571580.4A CN201510571580A CN105129097A CN 105129097 A CN105129097 A CN 105129097A CN 201510571580 A CN201510571580 A CN 201510571580A CN 105129097 A CN105129097 A CN 105129097A
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- unmanned plane
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Abstract
The invention discloses an unmanned aerial vehicle capable of taking off and landing vertically. The unmanned aerial vehicle comprise a power device, ailerons, undercarriages and an equipment compartment, wherein the power device is arranged at the top end of the unmanned aerial vehicle to be used for providing power for the unmanned aerial vehicle, the ailerons are arranged on the two sides of the unmanned aerial vehicle, extend to wing tips from wing roots of the unmanned aerial vehicle and are used for controlling pitching and rolling of the unmanned aerial vehicle, the undercarriages are connected with a wing of the unmanned aerial vehicle, arranged below the ailerons and used for keeping the body of the unmanned aerial vehicle perpendicular to the ground during taking off and landing, and the equipment compartment is arranged on the tail of the unmanned aerial vehicle and used for fixing aerial equipment with a cradle head.
Description
Technical field
The present invention relates to a kind of aviation aircraft technical field, particularly a kind of can the unmanned plane layout of vertical takeoff and landing.
Background technology
Can VUAV have take-off venue restriction little, can hover, flexible etc. the feature of flight attitude, be employed under circumstances in real world.Militarily, there are carrier-borne aircraft, scout etc. in adaptable place.There is stunt in the adaptable place of civil area, take photo by plane.Due to numerous advantage can be had by VUAV, current lot of domestic and international company all in the various layout of development can the layout of VUAV.
Can the aerodynamic characteristic of VUAV complicated, especially particularly evident when change of flight state, therefore need good pneumatic design layout and flight control system.Traditional the technology that adopts of VUAV can mainly contain vert motor or driving engine to reach the effect changing power direction, or in engine installation, increase duct to change power direction.But vert motor or the way of driving engine impairs power system, especially when being applied to pot motor or driving engine, can be attended by the life-span that powerful moment loading affects hardware itself in the process of verting.Increase duct can lose again power and increase the architecture quality of aircraft own and complexity, system reliability also can correspondingly decline.。
Therefore, wish a kind ofly the unmanned plane layout of vertical takeoff and landing can to overcome or at least alleviate the above-mentioned defect of prior art.
Summary of the invention
Technical matters to be solved by this invention is to overcome the defect existed in above-mentioned prior art, and provide a kind of can the unmanned plane layout of vertical takeoff and landing, described can VUAV be the all-wing aircraft aerodynamic arrangement of blended wing-body, possess preposition engine installation, what realize just controlling unmanned plane without the need to vert motor or driving engine flatly to fly, hovers and vertical takeoff and landing.
For solving the problems of the technologies described above, of the present inventionly a kind ofly can the unmanned plane layout of vertical takeoff and landing to comprise: engine installation, aileron, alighting gear and equipment compartment;
Engine installation, described engine installation is arranged on the top of described unmanned plane, for providing the power of described unmanned plane;
Aileron, described aileron is arranged on the both sides of described unmanned plane, and described aileron extends to the wing slightly from the wing root of described unmanned plane, for controlling aircraft pitching and rolling;
Alighting gear, described alighting gear is connected with the wing of described unmanned plane, and is arranged on the below of described aileron, keeps fuselage perpendicular to ground for described unmanned plane when rising and land;
Equipment compartment, described equipment compartment is arranged on the tail of described unmanned plane, for the equipment of taking photo by plane that fixing employing The Cloud Terrace is fixing.
Preferably, winglet is increased in the wing ending position of described unmanned plane to increase the stability of described unmanned plane.
Preferably, described engine installation adopts can the rotor driver of cyclic pitch, when described unmanned plane is in floating state, describedly the rotor driver of cyclic pitch can provide pitching and horizontal side force square for described unmanned plane, described can the rotor driver of cyclic pitch described unmanned plane can also be made to complete to fly from hovering peace between switching state.
Preferably, described rotor driver is high reduction ratio gear arrangement large oar footpath screw propeller.
Preferably, described aileron is differential type aileron, when described unmanned plane be in flat fly state time, described aileron controls described unmanned plane pitching, rolling; When described unmanned plane is in floating state, described aileron is for balancing the moment of torsion of described engine installation.
The invention provides a kind of can the unmanned plane layout of vertical takeoff and landing, described can VUAV be the all-wing aircraft aerodynamic arrangement of blended wing-body, possess preposition engine installation, what realize just controlling unmanned plane without the need to vert motor or driving engine flatly to fly, hovers and vertical takeoff and landing.
Accompanying drawing illustrates:
Fig. 1 is can the front view of unmanned plane layout of vertical takeoff and landing.
Fig. 2 is can the lateral plan of unmanned plane layout of vertical takeoff and landing
Detailed description of the invention:
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention
Can the unmanned plane layout of vertical takeoff and landing comprise according to a kind of of the present invention one broad embodiment: engine installation, aileron, alighting gear and equipment compartment;
Engine installation, described engine installation is arranged on the top of described unmanned plane, for providing the power of described unmanned plane;
Aileron, described aileron is arranged on the both sides of described unmanned plane, and described aileron extends to the wing slightly from the wing root of described unmanned plane, for controlling aircraft pitching and rolling;
Alighting gear, described alighting gear is connected with the wing of described unmanned plane, and is arranged on the below of described aileron, keeps fuselage perpendicular to ground for described unmanned plane when rising and land;
Equipment compartment, described equipment compartment is arranged on the tail of described unmanned plane, for the equipment of taking photo by plane that fixing employing The Cloud Terrace is fixing.
As shown in Figure 1, can the unmanned plane layout of vertical takeoff and landing comprise: engine installation 1, aileron 2, alighting gear 3, winglet 4 and equipment compartment 5.
Described engine installation 1 is arranged on the top of described unmanned plane, for providing the power of described unmanned plane; Described aileron 2 is arranged on the both sides of described unmanned plane, and described aileron 2 extends to the wing slightly from the wing root of described unmanned plane, for controlling aircraft pitching and rolling; Described alighting gear 3 is connected with the wing of described unmanned plane, and is arranged on the below of described aileron 2, keeps fuselage perpendicular to ground for described unmanned plane when rising and land; Described equipment compartment 5 is arranged on the tail of described unmanned plane, for the equipment of taking photo by plane that fixing employing The Cloud Terrace is fixing.
As shown in Figure 1, described unmanned plane adopts Flying-wing's form, omits vertical fin and horizontal tail, increases winglet 4 to increase system stability in wing ending position.
As shown in Figure 1, engine installation 1 is preposition can provide installation site for alighting gear 3, and the high velocity air that screw propeller produces in flight course also can increase the pneumatic effect of aileron 2.Because described unmanned plane adopts vertical type to take off mode, therefore the size of screw propeller can not be subject to described unmanned plane limitation in height, will the engine installation of employing high reduction ratio gear arrangement large oar footpath screw propeller, and the benefit done like this to provide higher thrust.
Described engine installation 1 adopts can the rotor driver of cyclic pitch, when described unmanned plane is in floating state, describedly the rotor driver of cyclic pitch can provide pitching and horizontal side force square for described unmanned plane, described can the rotor driver of cyclic pitch described unmanned plane can also be made to complete to fly from hovering peace between switching state.
Described aileron 2 is differential type aileron, when described unmanned plane be in flat fly state time, described aileron 2 controls described unmanned plane pitching, rolling; When described unmanned plane is in floating state, described aileron 2 is for balancing the moment of torsion of described engine installation, and described aileron 2 requires that pneumatic effect is higher, and therefore the area of rudder face is very large, and extending to the wing slightly from wing root, is also the unique pneumatic rudder face of full machine.
As shown in Figure 1, equipment compartment 5 is rearmounted, can be supplied to the equipment of taking photo by plane so almost without the camera angle at dead angle, and the equipment of taking photo by plane can adopt The Cloud Terrace collocation pick up camera, contributes to the advantage playing the equipment of taking photo by plane.
The invention has the advantages that:
1) novel unmanned plane distribution form is adopted can to realize vertical takeoff and landing and the horizontal flight of unmanned plane.
2) the all-wing aircraft aerodynamic configuration of blended wing-body is adopted can to produce lift-rising, drag reduction, rectification etc. effect.
3) the preposition engine installation of particular design is adopted can to provide thrust by the larger screw propeller of configuration sized.
4) adopt equipment compartment rearmounted, unscreened imaging environment can be provided for picture pick-up device, complete the task of taking photo by plane of greater angle.
5) differential aileron is adopted can to realize the effect of the balancing torque of aircraft when the gesture stability function of putting down when flying state and floating state.
6) adopt and the rotor of cyclic pitch can realize the gesture stability function of aircraft when floating state and hovering and the flat handoff functionality flown between state.
Above embodiments of the invention have been described in detail, but described content being only preferred embodiment of the present invention, can not being considered to for limiting practical range of the present invention.All equalizations done according to the present patent application scope change and improve, and all should still belong within patent covering scope of the present invention.
Claims (5)
1. can the unmanned plane layout of vertical takeoff and landing, it is characterized in that, comprising: engine installation, aileron, alighting gear and equipment compartment;
Engine installation, described engine installation is arranged on the top of described unmanned plane, for providing the power of described unmanned plane;
Aileron, described aileron is arranged on the both sides of described unmanned plane, and described aileron extends to the wing slightly from the wing root of described unmanned plane, for controlling aircraft pitching and rolling;
Alighting gear, described alighting gear is connected with the wing of described unmanned plane, and is arranged on the below of described aileron, keeps fuselage perpendicular to ground for described unmanned plane when rising and land;
Equipment compartment, described equipment compartment is arranged on the tail of described unmanned plane, for the equipment of taking photo by plane that fixing employing The Cloud Terrace is fixing.
2. according to described in claim 1 can the unmanned plane layout of vertical takeoff and landing, it is characterized in that: increase winglet in the wing ending position of described unmanned plane to increase the stability of described unmanned plane.
3. according to described in claim 1 can the unmanned plane layout of vertical takeoff and landing, it is characterized in that: described engine installation adopts can the rotor driver of cyclic pitch, when described unmanned plane is in floating state, describedly the rotor driver of cyclic pitch can provide pitching and horizontal side force square for described unmanned plane, described can the rotor driver of cyclic pitch described unmanned plane can also be made to complete to fly from hovering peace between switching state.
4. according to described in claim 3 can the unmanned plane layout of vertical takeoff and landing, it is characterized in that: described rotor driver is high reduction ratio gear arrangement large oar footpath screw propeller.
5. according to described in claim 1 can the unmanned plane layout of vertical takeoff and landing, it is characterized in that: described aileron is differential type aileron, when described unmanned plane be in flat fly state time, described aileron controls described unmanned plane pitching, rolling; When described unmanned plane is in floating state, described aileron is for balancing the moment of torsion of described engine installation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510571580.4A CN105129097A (en) | 2015-09-09 | 2015-09-09 | Unmanned aerial vehicle capable of taking off and landing vertically |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510571580.4A CN105129097A (en) | 2015-09-09 | 2015-09-09 | Unmanned aerial vehicle capable of taking off and landing vertically |
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| Publication Number | Publication Date |
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| CN105129097A true CN105129097A (en) | 2015-12-09 |
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| CN201510571580.4A Pending CN105129097A (en) | 2015-09-09 | 2015-09-09 | Unmanned aerial vehicle capable of taking off and landing vertically |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730676A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN105730677A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN106184741A (en) * | 2016-09-30 | 2016-12-07 | 中国科学院工程热物理研究所 | A kind of flying wing type ducted fan VUAV |
| CN107097949A (en) * | 2017-04-25 | 2017-08-29 | 河南三和航空工业有限公司 | A kind of VTOL fixed-wing unmanned plane |
| CN107618662A (en) * | 2017-09-27 | 2018-01-23 | 南方科技大学 | A kind of rearmounted VTOL Fixed Wing AirVehicle of propeller |
| CN108602551A (en) * | 2016-01-05 | 2018-09-28 | 空中客车英国运营有限责任公司 | Aircraft wing with the removable Wing tip device for Load alleviation |
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| EP1114772A1 (en) * | 1999-12-29 | 2001-07-11 | Gkn Westland Helicopters Limited | VTOL aircraft with variable wing sweep |
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| CN202414160U (en) * | 2011-11-15 | 2012-09-05 | 成都飞机设计研究所 | Vertical take-off and landing morphing aircraft |
| CN103287576A (en) * | 2013-05-24 | 2013-09-11 | 北京航空航天大学 | Tailless layout single tail seat type vertical take-off and landing aircraft |
| CN103287578A (en) * | 2012-03-01 | 2013-09-11 | 贵州帝三数字技术有限公司 | General miniature unmanned aerial vehicle |
| CN204184569U (en) * | 2014-10-10 | 2015-03-04 | 刘新广 | Autogyro |
| CN205366081U (en) * | 2015-09-09 | 2016-07-06 | 天峋创新（北京）科技有限公司 | But unmanned aerial vehicle structure of VTOL |
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| US5062587A (en) * | 1990-07-27 | 1991-11-05 | Wernicke Kenneth G | Landing gear for a tail sitting airplane |
| US5114096A (en) * | 1990-07-27 | 1992-05-19 | Wernicke Kenneth G | Tail sitter airplane |
| US5340057A (en) * | 1991-11-20 | 1994-08-23 | Freewing Aerial Robotics Corporation | Thrust vectoring free wing aircraft |
| CN1118591A (en) * | 1993-01-22 | 1996-03-13 | 自由翼飞机公司 | Stol/vtol free wing aircraft with articulated tail boom |
| RU2093422C1 (en) * | 1994-02-08 | 1997-10-20 | Венидикт Павлович Сафронов | Vertical takeoff and landing flying vehicle |
| EP1114772A1 (en) * | 1999-12-29 | 2001-07-11 | Gkn Westland Helicopters Limited | VTOL aircraft with variable wing sweep |
| US20050029399A1 (en) * | 2003-08-04 | 2005-02-10 | Lowe Jerry D. | Fyling craft camera and sensor mechanism lift platform using tubular linear guides |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108602551A (en) * | 2016-01-05 | 2018-09-28 | 空中客车英国运营有限责任公司 | Aircraft wing with the removable Wing tip device for Load alleviation |
| US11203410B2 (en) | 2016-01-05 | 2021-12-21 | Airbus Operations Limited | Aircraft wing with a moveable wing tip device for load alleviation |
| CN108602551B (en) * | 2016-01-05 | 2022-06-07 | 空中客车营运有限公司 | Aircraft wing with movable wing tip device for load mitigation |
| CN105730676A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN105730677A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN106184741A (en) * | 2016-09-30 | 2016-12-07 | 中国科学院工程热物理研究所 | A kind of flying wing type ducted fan VUAV |
| CN106184741B (en) * | 2016-09-30 | 2020-04-07 | 中国科学院工程热物理研究所 | Vertical take-off and landing unmanned aerial vehicle with flying wing type ducted fan |
| CN107097949A (en) * | 2017-04-25 | 2017-08-29 | 河南三和航空工业有限公司 | A kind of VTOL fixed-wing unmanned plane |
| CN107618662A (en) * | 2017-09-27 | 2018-01-23 | 南方科技大学 | A kind of rearmounted VTOL Fixed Wing AirVehicle of propeller |
| CN107618662B (en) * | 2017-09-27 | 2023-11-14 | 南方科技大学 | Vertical take-off and landing fixed wing aircraft with rear propeller |
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Application publication date: 20151209 |
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