CN103129737A - Inclined fixed wing unmanned plane - Google Patents
Inclined fixed wing unmanned plane Download PDFInfo
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- CN103129737A CN103129737A CN2013101008237A CN201310100823A CN103129737A CN 103129737 A CN103129737 A CN 103129737A CN 2013101008237 A CN2013101008237 A CN 2013101008237A CN 201310100823 A CN201310100823 A CN 201310100823A CN 103129737 A CN103129737 A CN 103129737A
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Abstract
The invention discloses an inclined fixed wing unmanned plane. The inclined fixed wing unmanned plane comprises a plane body and a wing inclined mechanism which can incline the wings, wherein the two sides of the plane body are provided with at least one pair of wings, and the tail of the plane body is also provided with a tail wing; and each wing is fixedly provided with a power device, each power device is connected with a screw propeller, the wings and the power devices are fixedly arranged together and can simultaneously move, and the rotation surfaces of the screw propellers are perpendicular to the horizontal planes of the wings all the time. The inclined fixed wing unmanned plane adopting the technical scheme can vertically take off and land and can realize high the cruising speed and power utilization efficiency and reasonable structure of a fixed wing plane; as the preferred technical scheme, the wings are both provided with subsidiary wings which are controlled by the wing inclined mechanism, and the power devices are all fixedly arranged on the middle parts of the wings; and the wings have enough rigidity and intensity, the wings are prevented from deforming because the power devices are fixedly arranged, and the localization of the wings is exact in revolution and fixation.
Description
Technical field
The invention belongs to the aviation aircraft design field, but especially relate to a kind of efficient, high-mobility, multipurpose, wheeled vehicle, not only vertical takeoff and landing, but also the verting of cruising speed that can reach fixed wing aircraft decide wing unmanned plane.
Background technology
Unmanned plane generally is divided into two types of fixed-wing and rotary wings, although conventional fixed-wing unmanned plane has advantages of that speed is fast, voyage is far away, taking off lands site requirements, can't carry out aerial fixed point suspension simultaneously; And but the rotor wing unmanned aerial vehicle vertical takeoff and landing does not require the take-off venue, and can aloft hover to execute the task.
How to overcome rotor craft and Fixed Wing AirVehicle separately shortcoming and keep both advantages, seek to fly fast and aircraft that can vertical takeoff and landing, be the problem that people think deeply always.Under this demand driving, the concept of tiltrotor and the fixed wing machine that verts has been carried out, and both existing identical point has again difference.Identical point is both all to combine the advantage of deciding wing aircraft and heligyro, can vertical takeoff and landing also can high-performance cruise fly; Difference is that tiltrotor is to come the change of flight state by the mode of tilting rotor, and the fixed wing machine that verts is the mode change of flight state of deciding the wing by verting.Tiltrotor and the fixed wing machine that verts have had both the advantage of heligyro and fixed wing aircraft by distinctive offline mode separately, filled up simultaneously the blank between helicopter and fixed wing aircraft flying speed envelope curve, all can play a significant role aspect military and civilian two.
Because but tilt wing aircraft has the vertical takeoff and landing performance of rotor wing unmanned aerial vehicle and high-speed, the large voyage performance of fixed wing aircraft concurrently, energy consumption is lower, load carrying ability is larger, show one's talent in numerous vertical take-off and landing aircraft (VTOL aircraft) schemes, early enter into the practical stage, the American-European state that waits has developed the serial tilt wing aircraft type as V-22 " osprey ", XV-3, XV-15, BA-609, EagleEye " hawkeye " etc.
Wherein, U.S. military secret V-22 " osprey " is the tiltrotor of at present real place in operation, it is also the Typical Representative in the tilting rotor type, the fuselage of V-22, wing and common fixed wing aircraft are substantially similar, the airscrew engine that different is is positioned at wing two ends can be rotated up and down, can realize the function that vertical takeoff and landing and fixed-wing cruise.But some technology of V-22 does not also reach a standard fully, and between its used life, accident frequently occurs.Its deficiency is mainly reflected in the following aspects: at first, during the V-22 vertical takeoff and landing, be positioned at the wing tip top of wing due to screw propeller (rotor), the downwash that proprotor produces, there is quite a few can beat upper surface at wing, stopped the air-flow that slip-stream moves downward, reduce effective lift, produced simultaneously random airflow influence the stability of aircraft, make and control difficulty and strengthen; Secondly, driving engine is positioned at the two ends of wing, in order to guarantee that driving engine is verting and accurate positioning fixedly the time, wing must have enough Rigidity and strengths to control distortion, therefore, its main wing wing tip must design generouslyer, and the area that keeps out the wind the when weight that has so namely increased wing has increased again landing has caused the result that increases complete machine weight, reduced lift.
in addition, in Chinese patent literature CN201712787U, disclose a kind of electric tilting rotor wing unmanned aerial vehicle, its technical scheme that adopts is that this electric tilting rotor wing unmanned aerial vehicle comprises that central authorities have the fuselage of rotor duct, the rotor wing rotation axle, the location carbon plate shelf, power motor, upper rotor, lower rotor, the steering wheel servomechanism, the steering wheel rocking bar, aspect is controlled rudder, rotor upset servomechanism, advance propeller,, central authorities have on the duct of fuselage of rotor duct and are connected with the rotor wing rotation axle, the intracardiac location carbon plate shelf that is provided with in the rotor wing rotation axle, location carbon plate shelf upper, the lower end is separately installed with power motor, and two power motors are connected respectively upper rotor and lower rotor by gear, and the rotating shaft coaxle of upper rotor and lower rotor is fixed on the center of location carbon plate shelf, the left side of location carbon plate shelf, the right side connects respectively two steering wheel servomechanisms, and the steering wheel servomechanism connects aspect by the steering wheel rocking bar and controls rudder, and the side that an aspect is controlled rudder is connected with rotor upset servomechanism, and the afterbody that central authorities have the rotor duct is provided with the propelling propeller.
In above-mentioned patent documentation CN201712787U, disclosed electric tilting rotor wing unmanned aerial vehicle adopts the power scheme of electronic " push away oar+co-axial rotor verts ", and its safety performance has unreliability, and the not good enough takeoff speed that causes of lift is slow.
Summary of the invention
The technical problem to be solved in the present invention is, but provide a kind of efficient, high-mobility, multipurpose, wheeled vehicle, not only vertical takeoff and landing, but also cruising speed, good, rational in infrastructure the verting of safety performance that can reach fixed wing aircraft decide wing unmanned plane.
For solving the problems of the technologies described above, the technical solution used in the present invention is, this can vert and decide wing unmanned plane and comprise fuselage, and described fuselage both sides are provided with at least one pair of wing, and the afterbody of described fuselage also is provided with empennage, also include the wing dropping mechanism that can make wing dropping, all be fixed with engine installation on every wing, be connected with a screw propeller on each engine installation, wing and engine installation are solidly installed, action simultaneously, the plane of revolution of described screw propeller is vertical all the time with the horizontal surface of described wing.
adopt verting of technique scheme structure to decide wing unmanned plane, power utilization efficient is high, hoisting force is large, this can vert and decide wing unmanned plane and have the wing that is positioned at the fuselage both sides, all be fixed with engine installation on every wing, be connected with a screw propeller on each engine installation, wing and engine installation are solidly installed, action simultaneously, adopt such structure setting, because wing and engine installation are solidly installed, action simultaneously, be connected with a screw propeller on each engine installation again, be actually and realized three's interlock, the beneficial effect of its generation is, utilize single wing dropping mechanism just can adjust quickly and easily wing, the position of engine installation and screw propeller, make it to switch fast between vertical takeoff and landing pattern and cruise mode and adjust, in addition, the plane of revolution of screw propeller is vertical all the time with the horizontal surface of described wing, like this, the downwash that proprotor produces has reduced to beat on wing to greatest extent, and the beneficial effect of its generation is, make wing reduce the amount that stops the air-flow that moves downward, but improved the hoisting force of tilting rotor wing unmanned aerial vehicle, avoided simultaneously the stability of chaotic airflow influence unmanned plane, controlled difficulty and greatly reduce.
As a further improvement on the present invention, described wing dropping mechanism is arranged on the junction of described fuselage and described wing, wing dropping mechanism is provided with to control the steering wheel of wing degree of dip, wing dropping mechanism is arranged on the junction of described fuselage and described wing, a steering wheel is controlled two wings (a pair of) about fuselage, make the degree of dip of the two-chip computer wing consistent, adopt such structural adjustment, make each block construction compact, reasonable, wing dropping mechanism is arranged on the junction of described fuselage and described wing, makes wing dropping corresponding fast.
As a further improvement on the present invention, described fuselage both sides are provided with two pairs of wings, owing on each wing, engine installation being installed, like this, in 4 engine installations, when unmanned plane is under cruise mode, if an engine installation cisco unity malfunction is arranged, close another engine installation relative with it, unmanned plane still can continue flight, the safety that has improved unmanned plane.
As a further improvement on the present invention, on described wing, the aileron that is subjected to the wing dropping mechanism controls is installed all.
The aileron that is subjected to the wing dropping mechanism controls all is installed on wing, be on every a slice wing, aileron to be installed all, the beneficial effect of its generation is, mechanism can control aileron inclination certain angle by wing dropping, thereby control the attitude angle of unmanned plane, such structure makes wing vert and accurate positioning fixedly the time.
Be positioned at the wing of fuselage both sides, no matter be a pair of or two pairs, or some how right, a pair of wing, totally two, to make the as a whole fuselage that crosses, the useful technique effect of its generation is, the both sides wing can integral body be adjusted inclination, and wing is mobilizable being arranged on fuselage, and the wing dropping structure is arranged on inside fuselage, the every pair of wing correspondence is provided with a wing dropping mechanism, there are 3 steering wheels in this wing dropping mechanism, and 1 is to control the two-chip computer wing to tilt, and also has 2 to be to control aileron to tilt.
As a further improvement on the present invention, described engine installation all is packed in the middle part of described wing, makes wing have enough Rigidity and strengths, avoids wing distortion to occur because being fixed with engine installation, in addition,
As a further improvement on the present invention, described engine installation is provided with motor.
As a further improvement on the present invention, described empennage comprises two tailplanes and a vertical tail.
Adopt verting of technical solution of the present invention to decide wing unmanned plane, its remarkable advantage is:
(1) can vert and decide wing unmanned plane and adopt the thrust vectoring form, rotor can provide lift, and the power that flies before level can be provided again, and power utilization efficient is high;
(2) also design aileron on wing, made unmanned plane pass through aileron under various offline mode, controlled the attitude angle of unmanned plane;
When (3) changing horizontal flight over to, thrust tilts forward, because the aerofoil air rate is lower, pneumatic efficiency is higher, therefore bear part or all of lift by wing, so under same case, the unmanned plane that adopts wing to obtain lift has higher flight efficiency than pure helicopter, and obtains thus farther voyage;
(4) owing to adopting four rotor mechanisms, if any a motor et out of order, unmanned function continues flight in the process of cruising.
in addition, the contriver is through the creative work discovery, and wing can also adopt double-girder type structure, arrange two and strengthen ribs in the middle part of wing, the engine installation motor is installed on to be strengthened on rib, the further position of fixed electrical machinery and wing, guaranteed simultaneously wing not can due to motor increase the weight of rupture, wing can be high mounted wing, and when avoiding aircraft wing to land, wing tip has the danger of contacting to earth, and shoulder-wing configuration can be hung in fuselage below wing, can protect wing to a certain extent, prevents from contacting to earth, wing can be straight wing, its low speed aeroperformance is good, induced drag is little, 1ift-drag ratio is large, the aspect of straight wing generally has rectangle and trapezoidal two kinds, the first stall of RECTANGULAR WINGS wing root, has inherent stall safety performance, and the load of whole wing distributes also comparatively desirable, and tapered airfoil has soft tip stall characteristic, when taper ratio select suitable the time, the sub-elliptical wing, the load of whole wing distributes also comparatively moderate, consider from the angle of making and assembling, the more trapezoidal straight wing of rectangular wing, it is unified that it makes needed rib shape, making and assembly precision require lower, be convenient to make, technological requirement easily guarantees.
Description of drawings
Further describe below in conjunction with accompanying drawing and embodiments of the present invention:
Fig. 1 is the airframe structure schematic diagram that prior art electric tilting rotor wing unmanned aerial vehicle central authorities have the rotor duct;
Fig. 2 is the structural representation of prior art electric tilting rotor wing unmanned aerial vehicle;
Fig. 3 is that of the present invention verting decided wing unmanned plane overall structure schematic diagram;
Aileron airflow influence schematic diagram during Fig. 4 helicopter mode flight of the present invention;
The structural representation of Fig. 5 rotor pattern of the present invention;
The structural representation of Fig. 6 cruise mode of the present invention;
Wherein: 1-fuselage, 2-wing, 3-aileron, 4-engine installation, 5-screw propeller, 6-wing dropping mechanism, 7-tailplane, 8-vertical tail, 9-empennage.
The specific embodiment
For deepening the understanding to technical solution of the present invention, first disclosed electric tilting rotor wing unmanned aerial vehicle in the Chinese patent literature CN201712787U that mentions in existing background technology is described in detail.
Hereinafter alleged " left side ", " right side ", " on ", D score is consistent with the direction of accompanying drawing itself, but structure of the present invention do not played the restriction effect.
as Fig. 1, shown in 2, existing electric tilting rotor wing unmanned aerial vehicle is to realize like this, central authorities have on the duct of fuselage 101 of rotor duct and are connected with rotor wing rotation axle 102, the intracardiac location carbon plate shelf 103 that is provided with in rotor wing rotation axle 102, locate the upper of carbon plate shelf 103, the lower end is separately installed with power motor 104, two power motors 104 are connected respectively upper rotor 105 and lower rotor 106 by gear, the rotating shaft coaxle of upper rotor 105 and lower rotor 106 is fixed on the center of location carbon plate shelf 103, the left side of location carbon plate shelf 103, the right side connects respectively two steering wheel servomechanisms 107, steering wheel servomechanism 107 connects aspect by steering wheel rocking bar 108 and controls rudder 109, the side that one aspect is controlled rudder 109 is connected with rotor upset servomechanism 110, fuselage 101 afterbodys that central authorities have the rotor duct are provided with propelling propeller 111.
Adopt the electric tilting rotor wing unmanned aerial vehicle of technique scheme, its shortcoming just as described in the background section: safety performance has unreliability, and the not good enough takeoff speed that causes of lift is slow.
in the present embodiment, as shown in Figure 3, this can vert and decide wing unmanned plane and comprise fuselage 1, fuselage 1 both sides are provided with two pairs to wing 2, i.e. four wings 2, the afterbody of fuselage 1 also is provided with empennage 9, also include the wing dropping mechanism 6 that can make that wing 2 tilts, all be fixed with engine installation 4 on every wing 2, be connected with a screw propeller 5 on each engine installation 4, wing 2 is solidly installed with engine installation 4, action simultaneously, the plane of revolution of described screw propeller 5 is vertical all the time with the horizontal surface of described wing 2, wing dropping mechanism 6 is arranged on the junction of described fuselage 1 and wing 2, wing dropping mechanism 6 is provided with to control the steering wheel of wing 2 degree of dip, the aileron 3 that controlled by wing dropping mechanism 6 all is installed on described wing 2, described engine installation 4 all is packed in the middle part of described wing 2, engine installation 4 is provided with motor, empennage 9 comprises two tailplanes 7 and a vertical tail 8, wing 2 is high mounted wings, wing 2 middle parts arrange two and strengthen rib, motor is installed on to be strengthened on rib.
Motor and wing 2 are fixed together, control the inclination of wing by the steering wheel of wing dropping mechanism 6, when taking off, enable the vertical takeoff and landing pattern, motor and wing 2 all are in plumbness, take off complete after, switch to cruise mode, motor and wing 2 reach 90 degree (90 of indication degree are that rotation reaches 90 degree, make the motor parallel with horizontal surface with wing 2) here and enter cruise mode and fly, and carry out rapidly aerial mission.
As shown in Figure 4, the middle part of wing 2 is provided with screw propeller 5 and aileron 3, and when unmanned plane was in vertical takeoff and landing and cruise mode, the relative angle of controlling aileron 3 and wing 2 was controlled the yaw angle of aircraft; During the variation offline mode, control the attitude angle of unmanned plane by the inclination angle of adjusting aileron 3, to guarantee the flight stability of unmanned plane; Also to utilize aileron 3 to control three attitude angle of unmanned plane in cruise mode.
As shown in Figure 5, when taking off, motor and wing 2 are in plumbness, and the plane of revolution of screw propeller 5 is parallel to horizontal surface, provide lift by screw propeller 5, when lift increases to a certain degree, the vertical pull-up of unmanned plane quilt, under this offline mode, two rotational freedom (pitching, rolling) be that the rotating speed of controlling four motors is controlled, this moment, empennage 9 was inoperative.
In conjunction with Fig. 6, when unmanned plane was in cruise mode, wing 2 forwards tilted with respect to fuselage 1 beginning, until reach 90 degree, at this moment lift is begun to provide by wing 2, and unmanned plane begins to carry out high-performance cruise flight.During cruising flight, wing 2 is locked with fuselage 1 relative position, and wing dropping mechanism 6 quits work, and UAV Attitude is controlled by aileron 3, and mode is identical with general fixed-wing unmanned plane.
During landing, wing 2 and fuselage 1 release, wing dropping mechanism 6 starts working, the relative fuselage 1 of wing 2 verts backward, the pulling force of screw propeller 5 is changed into vertically upward, and the lift of unmanned plane is substituted by the lift of screw propeller 5, and unmanned plane reduces speed now, progressively variation is helicopter mode, final vertical landing.
The above is described in detail embodiments of the present invention by reference to the accompanying drawings, but the invention is not restricted to above-mentioned embodiment, for example the storing passage can be in the ken that affiliated technical field those of ordinary skill possesses, and can also make a variety of changes under the prerequisite that does not break away from aim of the present invention.
Claims (10)
1. one kind can vert and decides wing unmanned plane, comprise fuselage (1), described fuselage (1) both sides are provided with at least one pair of wing (2), the afterbody of described fuselage (1) also is provided with empennage (9), it is characterized in that, also include the wing dropping mechanism (6) that wing (2) is tilted, all be fixed with engine installation (4) on every wing (2), be connected with a screw propeller (5) on each engine installation (4), wing (2) is solidly installed with engine installation (4), action simultaneously, the plane of revolution of described screw propeller (5) is vertical all the time with the horizontal surface of described wing (2).
2. according to claim 1 verting decided wing unmanned plane, it is characterized in that, described wing dropping mechanism (6) is arranged on the junction of described fuselage (1) and described wing (2), and wing dropping mechanism (6) is provided with to control the steering wheel of wing (2) degree of dip.
3. according to claim 1 and 2 verting decided wing unmanned plane, it is characterized in that, described fuselage both sides are provided with two pairs of wings (2).
4. according to claim 3 verting decided wing unmanned plane, it is characterized in that, the aileron (3) that controlled by wing dropping mechanism (6) all is installed on described wing (2).
5. according to claim 4 verting decided wing unmanned plane, it is characterized in that, described engine installation (4) all is packed in the middle part of described wing (2).
6. according to claim 5 verting decided wing unmanned plane, it is characterized in that, described engine installation (4) is provided with motor.
7. according to claim 6 verting decided wing unmanned plane, it is characterized in that, described empennage (9) comprises two tailplanes (7) and a vertical tail (8).
8. according to claim 1, described the verting of 2,4 ~ 8 any one decide wing unmanned plane, it is characterized in that, described wing (2) is high mounted wing.
9. according to claim 1, described the verting of 2,4 ~ 8 any one decide wing unmanned plane, it is characterized in that, described wing (2) is straight wing.
10. according to claim 9 verting decided wing unmanned plane, it is characterized in that, the aspect of described straight wing is rectangle or trapezoidal.
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| CN2013101008237A CN103129737A (en) | 2013-03-27 | 2013-03-27 | Inclined fixed wing unmanned plane |
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| CN103434642A (en) * | 2013-08-20 | 2013-12-11 | 朱幕松 | Linked double-wing and double-rotor-wing vertical lifting aircraft |
| CN104044734A (en) * | 2014-06-20 | 2014-09-17 | 中国科学院合肥物质科学研究院 | Multi-rotor unmanned airplane with inclined wings and rotors and control system and method |
| CN104058093A (en) * | 2014-06-20 | 2014-09-24 | 吴智勇 | Novel tiltable rotor wing vertical take-off and landing plane |
| CN104401480A (en) * | 2014-11-06 | 2015-03-11 | 南京航空航天大学 | Ducted tilt aircraft |
| CN104925254A (en) * | 2015-06-24 | 2015-09-23 | 吴畏 | Vertical take-off and landing aircraft |
| CN105197237A (en) * | 2015-09-29 | 2015-12-30 | 上海圣尧智能科技有限公司 | Vertical takeoff and landing unmanned aerial vehicle |
| CN105564642A (en) * | 2016-03-03 | 2016-05-11 | 辽宁猎鹰航空科技有限公司 | Tilt-rotor UAV (Unmanned Aerial Vehicle) |
| CN105667783A (en) * | 2016-02-29 | 2016-06-15 | 南京信息工程大学 | Tiliting fixed-wing water unmanned plane with power structure |
| CN106628168A (en) * | 2016-11-30 | 2017-05-10 | 北京天宇新超航空科技有限公司 | Novel tilt rotor aircraft |
| CN106628162A (en) * | 2016-12-21 | 2017-05-10 | 曹萍 | Composite unmanned aerial vehicle |
| JP2017159751A (en) * | 2016-03-08 | 2017-09-14 | 国立大学法人京都大学 | Tilt wing configuration unmanned aircraft |
| CN107336833A (en) * | 2017-07-05 | 2017-11-10 | 天津曙光天成科技有限公司 | A kind of compound unmanned plane and control method |
| CN107600403A (en) * | 2017-08-21 | 2018-01-19 | 西北工业大学 | A kind of trapezoidal layout tandem tilting wing aircraft and its inclining rotary mechanism |
| CN107719659A (en) * | 2017-08-28 | 2018-02-23 | 南京达索航空科技有限公司 | A kind of VTOL fixed-wing formula aircraft |
| CN111051196A (en) * | 2017-06-30 | 2020-04-21 | 空中客车A^3有限责任公司 | Vertical take-off and landing aircraft adopting passive wing inclination |
| CN111605708A (en) * | 2019-02-25 | 2020-09-01 | 飞巧科技有限公司 | Deflection wing aircraft |
| US10839336B2 (en) | 2013-12-26 | 2020-11-17 | Flir Detection, Inc. | Unmanned delivery |
| US11673650B2 (en) | 2013-12-26 | 2023-06-13 | Teledyne Flir Detection, Inc. | Adaptive thrust vector unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103434642A (en) * | 2013-08-20 | 2013-12-11 | 朱幕松 | Linked double-wing and double-rotor-wing vertical lifting aircraft |
| US10839336B2 (en) | 2013-12-26 | 2020-11-17 | Flir Detection, Inc. | Unmanned delivery |
| US11673650B2 (en) | 2013-12-26 | 2023-06-13 | Teledyne Flir Detection, Inc. | Adaptive thrust vector unmanned aerial vehicle |
| CN104044734B (en) * | 2014-06-20 | 2016-03-02 | 中国科学院合肥物质科学研究院 | There is many rotor wing unmanned aerial vehicles control system and the method for tiltable wing and rotor |
| CN104044734A (en) * | 2014-06-20 | 2014-09-17 | 中国科学院合肥物质科学研究院 | Multi-rotor unmanned airplane with inclined wings and rotors and control system and method |
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| CN104401480A (en) * | 2014-11-06 | 2015-03-11 | 南京航空航天大学 | Ducted tilt aircraft |
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| CN105564642A (en) * | 2016-03-03 | 2016-05-11 | 辽宁猎鹰航空科技有限公司 | Tilt-rotor UAV (Unmanned Aerial Vehicle) |
| JP2017159751A (en) * | 2016-03-08 | 2017-09-14 | 国立大学法人京都大学 | Tilt wing configuration unmanned aircraft |
| CN106628168A (en) * | 2016-11-30 | 2017-05-10 | 北京天宇新超航空科技有限公司 | Novel tilt rotor aircraft |
| CN106628162A (en) * | 2016-12-21 | 2017-05-10 | 曹萍 | Composite unmanned aerial vehicle |
| CN111051196A (en) * | 2017-06-30 | 2020-04-21 | 空中客车A^3有限责任公司 | Vertical take-off and landing aircraft adopting passive wing inclination |
| CN107336833A (en) * | 2017-07-05 | 2017-11-10 | 天津曙光天成科技有限公司 | A kind of compound unmanned plane and control method |
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Application publication date: 20130605 |