CN105346725A - Vertical take-off and landing unmanned aerial vehicle - Google Patents
Vertical take-off and landing unmanned aerial vehicle Download PDFInfo
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- CN105346725A CN105346725A CN201510638973.2A CN201510638973A CN105346725A CN 105346725 A CN105346725 A CN 105346725A CN 201510638973 A CN201510638973 A CN 201510638973A CN 105346725 A CN105346725 A CN 105346725A
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Abstract
The invention provides a vertical take-off and landing unmanned aerial vehicle. The vertical take-off and landing unmanned aerial vehicle comprises a vehicle body, wings, ailerons, three or more vertical fins, motors and propellers. The ailerons are hinged to the wings. At least one vertical fin is arranged on the upper side of the vertical take-off and landing unmanned aerial vehicle, and at least one vertical fin is arranged on the lower side of the vertical take-off and landing unmanned aerial vehicle. The motors are connected with the vertical fins and comprise motor bearings. At least parts of the trailing edges of the vertical fins are located on the rear portions of the trailing edges of the wings, or the tails of the motors are located on the rear portions of the trailing edges of the wings. The propellers are connected with the motor bearings. When the vertical take-off and landing unmanned aerial vehicle is vertically placed, the vertical fins or the tails of the motors can serve as undercarriages. The vertical take-off and landing unmanned aerial vehicle vertically takes off or lands or hovers in upper air through rotation of the ailerons, and can also achieve a high-speed horizontal flight. Stability is improved through connection of the motors and the vertical fins.
Description
Technical field
The present invention relates to a kind of unmanned plane, be related specifically to a kind of VUAV.
Background technology
Because unmanned plane has the advantages such as small, cost is low, and along with the fast development of flight control technique, the communication technology and Eltec, the performance of unmanned plane constantly strengthens, type is on the increase, and its application demand in military domain and civil area is constantly increased.
Unmanned plane is divided into fixed-wing unmanned plane and rotary wings unmanned plane usually.
Wherein fixed-wing unmanned plane relies on engine propels, and engine drives to produce and is parallel to the horizontal thrust of fuselage axis, makes unmanned plane can high-speed flight aloft.But because engine can not produce the lift perpendicular to fuselage axis, so fixed-wing unmanned plane can only obtain lift by the relative motion between fixed-wing and air, to overcome the gravity of fixed-wing unmanned plane, there is positive correlation in the size of lift and the speed of relative movement between fixed-wing and air, speed of relative movement is larger, and the lift that fixed-wing unmanned plane obtains is also larger.In prior art, fixed-wing unmanned plane also exists two shortcomings: the first, needs longer runway that fixed-wing unmanned plane just can be made to obtain enough horizontal velocities, obtain enough lift take off to make fixed-wing unmanned plane when taking off; The second, fixed-wing unmanned plane needs to keep enough flying speeds could obtain enough lift to overcome the gravity of self after take off.
Rotary wings unmanned plane relies on engine to make rotary wings around own axes rotation, and rotary wings time rotational and air produce relative motion and obtain lift.Because the lift of rotary wings unmanned plane generation directly drives rotary wings from transferring to produce by engine, therefore rotary wings unmanned plane takes off without the need to having horizontal flight speed, namely no longer relies on runway, overcomes the shortcoming of fixed-wing unmanned plane dependence compared with long runway.Meanwhile, rotary wings unmanned plane also overcomes the shortcoming of the flying speed needing to keep enough after fixed-wing unmanned plane takes off, rotary wings unmanned plane can vertical lift, hovering, left and right flight forwards, backwards, there is the diversified advantage of flight attitude.But due to the mainly lift that rotary wings provides, the horizontal thrust being parallel to fuselage axis that rotary wings unmanned plane obtains is less, so horizontal flight speed is slower.
In sum, in prior art, unmanned plane or need to rely on long runway, and need after taking off to keep enough flying speed; Horizontal flight speed is slower.
Summary of the invention
The problem that the present invention solves is unmanned plane or need to rely on long runway in prior art, and needs after taking off to keep enough flying speed; Horizontal flight speed is slower.
For solving the problem, the invention provides a kind of VUAV, comprising: fuselage and wing, also comprise:
Aileron, aileron and wing hinged;
Vertical fin, the quantity of vertical fin is more than three or three, has at least a vertical fin to be arranged on the upside of VUAV, has at least a vertical fin to be arranged on the downside of VUAV;
Motor, motor is connected with vertical fin, and described motor comprises motor bearings; At least part of vertical fin trailing edge is positioned at trailing edge rear portion, or motor afterbody is positioned at trailing edge rear portion;
Screw propeller, screw propeller is connected with motor bearings.
Further, aileron and wing afterbody hinged, aileron can rotate around the S. A. perpendicular to fuselage axis; Be provided with steering wheel in wing, steering wheel can drive aileron to rotate.
Further, vertical fin trailing edge sweepback.
Further, the quantity of vertical fin is four, and wherein two vertical fins are arranged on the upside of VUAV, and two vertical fins are arranged on the downside of VUAV.
Further, two vertical fins be arranged on the upside of VUAV are symmetrical arranged along the fuselage plane of symmetry; Two vertical fins be arranged on the downside of VUAV are symmetrical arranged along the fuselage plane of symmetry.
Further, the vertical fin being arranged at fuselage plane of symmetry the same side is equal to the distance of the fuselage plane of symmetry.
Further, the quantity of motor is four, and each motor is connected with a vertical fin.
Further, described vertical fin is provided with electric machine support, described motor is placed in electric machine support.
Further, described motor bearings passes described electric machine support.
Further, described fuselage and wing are structure as a whole.
Compared with prior art, technical scheme of the present invention has the following advantages:
In technical scheme of the present invention, at least part of vertical fin trailing edge is positioned at trailing edge rear portion, or motor afterbody is positioned at trailing edge rear portion when VUAV is vertically placed, and vertical fin or motor afterbody can be used as alighting gear.
Aileron and wing hinged, the flight attitude of VUAV can be changed by rotating aileron, to make VUAV can realize vertical takeoff, landing or high-altitude hovering, VUAV high-speed horizontal flight can be realized.
Described motor is connected with vertical fin, decentralization when VUAV is vertically placed, and improves the stationarity of VUAV.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of VUAV of the present invention;
Structural representation when Fig. 2 is a kind of VUAV vertical takeoff and landing of the present invention;
Fig. 3 is that a kind of VUAV of the present invention is by the schematic diagram being transitioned into the horizontal flight stage takeoff phase;
Fig. 4 is the level flight condition schematic diagram of a kind of VUAV of the present invention.
Detailed description of the invention
Unmanned plane or need to rely on long runway in prior art, and need after taking off to keep enough horizontal flight speed; Horizontal flight speed is slower.
For enabling above-mentioned purpose of the present invention, feature and advantage more become apparent, and are described in detail specific embodiments of the invention below in conjunction with accompanying drawing.
Compared with fixed-wing unmanned plane, VUAV with zero velocity takeoff and anding, can possess hover capabilities, and can with the mode horizontal flight of fixed-wing flight.VUAV without dependence, and has the advantage that can hover to runway.
Compared with rotary wings unmanned plane, VUAV has much higher forward flight speed, and has larger voyage.
Just based on these advantages, VUAV is particularly useful for needs hovering or landing site is had to the occasion of particular/special requirement.
With reference to figure 1, the invention provides a kind of VUAV, comprising:
Fuselage 1 and wing.
Fuselage 1 and wing are integrated mechanism in the present embodiment, this air resistance be designed with when being beneficial to the flight of minimizing VUAV.
Lithium cell, flight control system are equipped with in the inside of described fuselage 1.Described lithium cell provides energy to make motor drive screw propeller 5, produces the power being parallel to fuselage axis.Flight control system is used for remote controller to the control of VUAV state of flight.
Described fuselage 1 is that Mirror Symmetry is arranged along the plane of symmetry, and the described plane of symmetry is called the fuselage plane of symmetry.
In the present embodiment, described fuselage 1 is provided with winglet 2, and winglet 2 is fixedly connected with fuselage 1.
Described fuselage 1 afterbody is hinged with aileron 6, is provided with steering wheel in described fuselage 1, and described steering wheel can drive aileron 6 to rotate around the S. A. perpendicular to fuselage axis.
The quantity of described aileron 6 is two, and two ailerons 6 are that Mirror Symmetry is arranged along the fuselage plane of symmetry.
Described VUAV also comprises vertical fin 3, and the quantity of described vertical fin 3 is at least three, and has at least a vertical fin to be arranged on the upside of VUAV, has at least a vertical fin to be arranged on the downside of VUAV.Be positioned at the side of top when wherein referring to VUAV horizontal flight on the upside of VUAV, when referring to VUAV horizontal flight on the downside of VUAV, be positioned at the side of below.
In the present embodiment, the quantity of vertical fin 3 is four, and wherein two vertical fins are arranged on the upside of VUAV, and two vertical fins are arranged on the downside of VUAV.
Two vertical fins be arranged on the upside of VUAV are symmetrical arranged along the fuselage plane of symmetry, and two vertical fins be namely arranged on the upside of VUAV are equal to the distance of the fuselage plane of symmetry; Two vertical fins be arranged on the downside of VUAV are symmetrical arranged along the fuselage plane of symmetry, and two vertical fins be namely arranged on the downside of VUAV are equal to the distance of the fuselage plane of symmetry.
In the present embodiment, two vertical fins being positioned at fuselage plane of symmetry the same side are equal to the distance of the fuselage plane of symmetry.
In the present embodiment, vertical fin 3 is fixedly connected with fuselage 1 afterbody.
This being designed with is beneficial at use vertical fin as the stability improving VUAV during alighting gear.
In the present embodiment, at least part of vertical fin trailing edge is positioned at trailing edge rear portion, and that is vertical fin 3 has at least a part of position larger to the distance of fuselage head than any position of trailing edge to the distance of fuselage head.When can ensure that VUAV is vertically placed in the horizontal plane like this, vertical fin 3 can as alighting gear ground connection, any position of trailing edge is all unsettled.
In the present embodiment, the sweepback of vertical fin 3 trailing edge, namely vertical fin 3 trailing edge stretches backward.And the leading edge of vertical fin 3 also can be arranged to sweepback, fuselage 1 leading edge also can be arranged to sweepback.The Aerodynamic Characteristics of VUAV can be improved like this.
In the present embodiment, vertical fin 3 is provided with electric machine support 4, described electric machine support 4 is built with motor, and described motor comprises motor bearings, and described motor bearings passes electric machine support 4 and is connected with screw propeller 5.Described screw propeller 5 can rotate around own axes and produce power under the driving of motor.
Described motor is connected with vertical fin 3, decentralization when VUAV is vertically placed, and improves the stationarity of VUAV.
The quantity of described motor is 4, and each motor is connected with a vertical fin 3, and a vertical fin 3 connects a motor at most.
One end that described motor does not connect screw propeller 5 is called motor afterbody, and described motor afterbody is consistent with fuselage 1 caudal directions.
In other embodiments, can not have electric machine support 4, described vertical fin 3 is directly connected with motor.
In other embodiments, motor afterbody is positioned at trailing edge rear portion, and motor afterbody is positioned at the trailing edge rear portion of vertical fin 3.When can ensure that VUAV is vertically placed in the horizontal plane like this, motor afterbody can as alighting gear ground connection, any position of trailing edge is all unsettled, and vertical fin 3 trailing edge is also unsettled.
Introduce the method for operation of the VUAV in the present embodiment below:
With reference to figure 1 and Fig. 2, when taking off, first vertically placed by VUAV, fuselage axis is perpendicular to the ground, and four vertical fins 3 land as alighting gear; Under the control of flight control system, drive 4 electric machine rotations by lithium cell, and drive 4 screw propellers 5 around own axes rotation.And making 4 screw propellers 5 be divided into two groups according to diagonal line, the direction that described two groups of screw propellers 5 rotate is contrary, rotates to offset screw propeller 5 the anti-oar power produced.Screw propeller 5 produces the pulling force being parallel to fuselage axis around own axes rotation, make VUAV overcome gravity and take off.
With reference to figure 1 and Fig. 3, after VUAV rises to certain altitude, lithium cell drives steering wheel and drives aileron 6 to rotate around the S. A. perpendicular to fuselage axis under the control of flight control system, by regulating aileron 6, VUAV fuselage head is pulled down, and VUAV enters vertically flight to horizontal flight transition period.
In the present invention, the straight line perpendicular to fuselage axis not only only refers to straight line with fuselage axes intersect and vertical; And can be the straight line met the following conditions: a plane and fuselage axis perpendicular can be found in the plane of this straight line.
With reference to figure 1 and Fig. 4, along with VUAV fuselage head pulls down, the power that screw propeller 5 produces changes horizontal flight power gradually into, and VUAV enters the high-speed horizontal flight stage.
When VUAV needs landing, lithium cell drives steering wheel and drives aileron 6 to rotate around the S. A. perpendicular to fuselage axis under the control of flight control system, by regulating aileron 6, make VUAV fuselage head to pull-up, along with landing unmanned plane head is constantly pulled up, the horizontal flight power that screw propeller 5 provides changes pulling force upwards gradually into, the pulling force that final screw propeller 5 produces and VUAV self gravitation are on one wire, when the pulling force that screw propeller 5 produces is less than landing unmanned plane self gravitation, VUAV is vertical landing slowly.Can continue with reference to figure 2 during landing.
Although the present invention discloses as above, the present invention is not defined in this.Any those skilled in the art, without departing from the spirit and scope of the present invention, all can make various changes or modifications, and therefore protection scope of the present invention should be as the criterion with claim limited range.
Claims (10)
1. a VUAV, comprising: fuselage and wing, is characterized in that, also comprises:
Aileron, aileron and wing hinged;
Vertical fin, the quantity of vertical fin is more than three or three, has at least a vertical fin to be arranged on the upside of VUAV, has at least a vertical fin to be arranged on the downside of VUAV;
Motor, motor is connected with vertical fin, and described motor comprises motor bearings; At least part of vertical fin trailing edge is positioned at trailing edge rear portion, or motor afterbody is positioned at trailing edge rear portion;
Screw propeller, screw propeller is connected with motor bearings.
2. VUAV as claimed in claim 1, is characterized in that, aileron and wing afterbody hinged, aileron can rotate around the S. A. perpendicular to fuselage axis;
Be provided with steering wheel in wing, steering wheel can drive aileron to rotate.
3. VUAV as claimed in claim 1, is characterized in that, the sweepback of vertical fin trailing edge.
4. VUAV as claimed in claim 1, it is characterized in that, the quantity of vertical fin is four, and wherein two vertical fins are arranged on the upside of VUAV, and two vertical fins are arranged on the downside of VUAV.
5. VUAV as claimed in claim 4, it is characterized in that, two vertical fins be arranged on the upside of VUAV are symmetrical arranged along the fuselage plane of symmetry;
Two vertical fins be arranged on the downside of VUAV are symmetrical arranged along the fuselage plane of symmetry.
6. VUAV as claimed in claim 5, it is characterized in that, the vertical fin being arranged at fuselage plane of symmetry the same side is equal to the distance of the fuselage plane of symmetry.
7. VUAV as claimed in claim 6, it is characterized in that, the quantity of motor is four, and each motor is connected with a vertical fin.
8. VUAV as claimed in claim 7, it is characterized in that, described vertical fin is provided with electric machine support, and described motor is placed in electric machine support.
9. VUAV as claimed in claim 8, it is characterized in that, described motor bearings passes described electric machine support.
10. VUAV as claimed in claim 1, it is characterized in that, described fuselage and wing are structure as a whole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510638973.2A CN105346725A (en) | 2015-09-29 | 2015-09-29 | Vertical take-off and landing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510638973.2A CN105346725A (en) | 2015-09-29 | 2015-09-29 | Vertical take-off and landing unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN105346725A true CN105346725A (en) | 2016-02-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510638973.2A Pending CN105346725A (en) | 2015-09-29 | 2015-09-29 | Vertical take-off and landing unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN105346725A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444632A (en) * | 2017-06-30 | 2017-12-08 | 马鞍山市赛迪智能科技有限公司 | It is a kind of can VTOL dalta 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 |
| CN109466745A (en) * | 2018-12-29 | 2019-03-15 | 河北天启通宇航空器材科技发展有限公司 | A kind of gyroplane tail structure |
| CN111846226A (en) * | 2020-07-28 | 2020-10-30 | 北京京东乾石科技有限公司 | Unmanned aerial vehicle and control method thereof |
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| US5516060A (en) * | 1993-03-29 | 1996-05-14 | Mcdonnell; William R. | Vertical take off and landing and horizontal flight aircraft |
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| CN101353084A (en) * | 2008-09-05 | 2009-01-28 | 龙川 | Light aerobat capable of landing or taking-off vertically |
| CN202728574U (en) * | 2011-10-17 | 2013-02-13 | 田瑜 | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function |
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Patent Citations (4)
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| US5516060A (en) * | 1993-03-29 | 1996-05-14 | Mcdonnell; William R. | Vertical take off and landing and horizontal flight aircraft |
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| CN101353084A (en) * | 2008-09-05 | 2009-01-28 | 龙川 | Light aerobat capable of landing or taking-off vertically |
| CN202728574U (en) * | 2011-10-17 | 2013-02-13 | 田瑜 | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function |
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| 方健等: "《单片机原理与应用技术》", 31 May 2013 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444632A (en) * | 2017-06-30 | 2017-12-08 | 马鞍山市赛迪智能科技有限公司 | It is a kind of can VTOL dalta 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 |
| CN109466745A (en) * | 2018-12-29 | 2019-03-15 | 河北天启通宇航空器材科技发展有限公司 | A kind of gyroplane tail structure |
| CN111846226A (en) * | 2020-07-28 | 2020-10-30 | 北京京东乾石科技有限公司 | Unmanned aerial vehicle and control method thereof |
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Application publication date: 20160224 |