CN105346715A - Vertical take-off and landing unmanned plane - Google Patents
Vertical take-off and landing unmanned plane Download PDFInfo
- Publication number
- CN105346715A CN105346715A CN201510639205.9A CN201510639205A CN105346715A CN 105346715 A CN105346715 A CN 105346715A CN 201510639205 A CN201510639205 A CN 201510639205A CN 105346715 A CN105346715 A CN 105346715A
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- vuav
- vertical
- unmanned plane
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- fuselage
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Abstract
A vertical take-off and landing unmanned plane comprises a body, a motor, a propeller and wings, and further comprises ailerons and vertical fins; the ailerons are in hinged connection with the wings, the number of the vertical fins is three or more, at least one vertical fin is arranged on the upper side of the vertical take-off and landing unmanned plane, at least one vertical fin is arranged on the lower side of the vertical take-off and landing unmanned plane, and the tail edges of at least part of the vertical fins are located at the rear parts of the tail edges of the wings. The tail edges of at least part of the vertical fins are located at the rear parts of the tail edges of the wings, so that when the vertical take-off and landing unmanned plane is vertically placed, the tail edges of the vertical fins are used as an undercart for supporting the vertical take-off and landing unmanned plane. The ailerons are in hinged connection with the wings, so that the vertical take-off and landing unmanned plane flight attitude can be changed by turning the ailerons, vertical takeoff and landing or sky hovering of the vertical take-off and landing unmanned plane can be realized, and high speed horizontal flight of the vertical take-off and landing unmanned plane can be realized.
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, motor, screw propeller 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, and have at least a vertical fin to be arranged on the downside of VUAV, at least part of vertical fin trailing edge is positioned at trailing edge rear portion.
Further, aileron and wing afterbody hinged, aileron can rotate around the S. A. perpendicular to fuselage axis.
Further, 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, vertical fin is fixedly connected with wing.
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, two vertical fins being positioned at fuselage plane of symmetry the same side are equal to the distance of the fuselage plane of symmetry.
Further, described motor is embedded in wing nose.
Further, also comprise: winglet, described winglet is connected with wing.
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, and when VUAV is vertically placed, trailing edge is higher than at least part of vertical fin trailing edge, and vertical fin trailing edge plays VUAV as gear support.
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, can make to realize VUAV high-speed horizontal flight.
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, motor, screw propeller 6 and wing 2.
Lithium cell, flight control system are equipped with in the inside of described fuselage 1.Described lithium cell provides energy to make described motor drive screw propeller 6, produces the power being parallel to fuselage axis.Flight control system is used for remote controller to the control of VUAV state of flight.
Wing 2 and fuselage 1 smooth transition are to meet fluid mechanical design.Described wing 2 is arranged at fuselage 1 both sides, and is that Mirror Symmetry is arranged along the plane of symmetry, and the described plane of symmetry is called the fuselage plane of symmetry.
Described motor is embedded in wing 2 front end, and namely each wing nose respectively embeds a motor, and described motor is that Mirror Symmetry is arranged along the fuselage plane of symmetry.
In the present embodiment, described motor embeds wing 2 front end by electric machine support 5, electronic governor is also housed to regulate the rotating speed of motor in electric machine support 5.
Described motor has motor bearings, and described motor bearings is connected with screw propeller 6, and under the driving of motor, screw propeller 6 can around own axes from transferring generation power.
In other embodiments, also can only have a motor, described motor is connected with fuselage, and described motor bearings axis and fuselage axis are point-blank.
In the present embodiment, described wing 2 is provided with winglet 3, and winglet 3 is fixedly connected with wing 2.
Described wing 2 is hinged with aileron 7, and aileron 7 is hinged with wing 2 afterbody, and in a particular embodiment, aileron 7 is in the slip-stream region of corresponding screw propeller 6, to improve the control of aileron 7 pairs of aircraft flight attitude.Be provided with steering wheel in described wing 2, described steering wheel can drive aileron 7 to rotate around the S. A. perpendicular to fuselage axis.
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.
The quantity of described aileron 7 is two, hinged with two wings 2 respectively, and two ailerons 7 are that Mirror Symmetry is arranged along the fuselage plane of symmetry.
The VUAV of the present embodiment also comprises vertical fin 4, and the quantity of described vertical fin 4 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 4 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 4 is fixedly connected with wing 2.
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 wing 2 trailing edge rear portion, and that is vertical fin 4 has at least a part of position larger to the distance of fuselage head than any position of wing 2 trailing edge to the distance of fuselage head.When can ensure that VUAV is vertically placed in the horizontal plane like this, vertical fin 4 can as alighting gear ground connection, any position of wing 2 trailing edge is all unsettled.
In the present embodiment, the sweepback of vertical fin 4 trailing edge, namely vertical fin 4 trailing edge stretches backward.And the leading edge of vertical fin 4 also can be arranged to sweepback, wing 2 also can be swept wing.The Aerodynamic Characteristics of VUAV can be improved like this.
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 4 land as alighting gear; Under the control of flight control system, 2 electric machine rotations of wing 2 leading edge are driven by lithium cell, and drive 2 screw propellers 6 around own axes rotation, and make the sense of rotation of 2 screw propellers 6 on the contrary to make anti-oar moment cancel out each other, screw propeller 6 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 7 to rotate around the S. A. perpendicular to fuselage axis under the control of flight control system, by regulating aileron 7, VUAV fuselage head is pulled down, and VUAV enters vertically flight to horizontal flight transition period.
With reference to figure 1 and Fig. 4, along with VUAV fuselage head pulls down, the pulling force that screw propeller 6 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 7 to rotate around the S. A. perpendicular to fuselage axis under the control of flight control system, by regulating aileron 7, make VUAV fuselage head to pull-up, along with landing unmanned plane head is constantly pulled up, the horizontal flight power that screw propeller 6 provides changes pulling force upwards gradually into, the pulling force that final screw propeller 6 produces and VUAV self gravitation are on one wire, when the pulling force that screw propeller 6 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, motor, screw propeller 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, and have at least a vertical fin to be arranged on the downside of VUAV, at least part of vertical fin trailing edge is positioned at trailing edge rear portion.
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.
3. VUAV as claimed in claim 2, it is characterized in that, be provided with steering wheel in wing, steering wheel can drive aileron to rotate.
4. VUAV as claimed in claim 1, is characterized in that, the sweepback of vertical fin trailing edge.
5. 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.
6. VUAV as claimed in claim 5, it is characterized in that, vertical fin is fixedly connected with wing.
7. VUAV as claimed in claim 6, 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.
8. VUAV as claimed in claim 7, it is characterized in that, two vertical fins being positioned at fuselage plane of symmetry the same side are equal to the distance of the fuselage plane of symmetry.
9. VUAV as claimed in claim 1, it is characterized in that, described motor is embedded in wing nose.
10. VUAV as claimed in claim 1, is characterized in that, also comprise:
Winglet, described winglet is connected with wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510639205.9A CN105346715A (en) | 2015-09-29 | 2015-09-29 | Vertical take-off and landing unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510639205.9A CN105346715A (en) | 2015-09-29 | 2015-09-29 | Vertical take-off and landing unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105346715A true CN105346715A (en) | 2016-02-24 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510639205.9A Pending CN105346715A (en) | 2015-09-29 | 2015-09-29 | Vertical take-off and landing unmanned plane |
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| CN (1) | CN105346715A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105818981A (en) * | 2016-04-06 | 2016-08-03 | 江富余 | Helicopter with rotor, fixed wing and propellers |
| CN105905295A (en) * | 2016-06-14 | 2016-08-31 | 临沂高新区翔鸿电子科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| CN106114817A (en) * | 2016-08-17 | 2016-11-16 | 优利科技有限公司 | A kind of aircraft and flight system |
| CN107176286A (en) * | 2017-05-16 | 2017-09-19 | 华南理工大学 | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems |
| CN107618662A (en) * | 2017-09-27 | 2018-01-23 | 南方科技大学 | A kind of rearmounted VTOL Fixed Wing AirVehicle of propeller |
| CN107985589A (en) * | 2017-10-18 | 2018-05-04 | 沈阳航空航天大学 | Vertical take-off and landing drone with vectored thrust duct engine |
| CN108263594A (en) * | 2018-01-31 | 2018-07-10 | 曹蔚萌 | A kind of bladeless fan power vertical take-off and landing drone |
| CN108706093A (en) * | 2018-04-28 | 2018-10-26 | 云南同硕环保科技有限公司 | A kind of wing is equipped with the plate wing machine of large-scale winglet |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105818981A (en) * | 2016-04-06 | 2016-08-03 | 江富余 | Helicopter with rotor, fixed wing and propellers |
| CN105905295A (en) * | 2016-06-14 | 2016-08-31 | 临沂高新区翔鸿电子科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| CN106114817A (en) * | 2016-08-17 | 2016-11-16 | 优利科技有限公司 | A kind of aircraft and flight system |
| CN107176286A (en) * | 2017-05-16 | 2017-09-19 | 华南理工大学 | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems |
| CN107176286B (en) * | 2017-05-16 | 2023-08-22 | 华南理工大学 | Double-duct fan power system-based foldable fixed wing vertical take-off and landing unmanned aerial vehicle |
| 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 |
| CN107985589B (en) * | 2017-10-18 | 2022-02-01 | 沈阳航空航天大学 | Take VTOL unmanned aerial vehicle of vector thrust duct engine |
| CN107985589A (en) * | 2017-10-18 | 2018-05-04 | 沈阳航空航天大学 | Vertical take-off and landing drone with vectored thrust duct engine |
| CN108263594B (en) * | 2018-01-31 | 2019-05-10 | 曹蔚萌 | A kind of bladeless fan power vertical take-off and landing drone |
| CN108263594A (en) * | 2018-01-31 | 2018-07-10 | 曹蔚萌 | A kind of bladeless fan power vertical take-off and landing drone |
| CN108706093A (en) * | 2018-04-28 | 2018-10-26 | 云南同硕环保科技有限公司 | A kind of wing is equipped with the plate wing machine of large-scale winglet |
| CN108706093B (en) * | 2018-04-28 | 2023-09-12 | 昆明鞘翼科技有限公司 | Plate wing machine |
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Application publication date: 20160224 |
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