CN105346714A - Vertical take-off and landing unmanned plane - Google Patents
Vertical take-off and landing unmanned plane Download PDFInfo
- Publication number
- CN105346714A CN105346714A CN201510638803.4A CN201510638803A CN105346714A CN 105346714 A CN105346714 A CN 105346714A CN 201510638803 A CN201510638803 A CN 201510638803A CN 105346714 A CN105346714 A CN 105346714A
- Authority
- CN
- China
- Prior art keywords
- motor
- fuselage
- vuav
- axis
- symmetry
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Toys (AREA)
Abstract
A vertical take-off and landing unmanned plane includes a fuselage, wings, a first motor, a first propeller, a second motor and a second propeller, the first motor comprises a first motor bearing, the angle between the first motor bearing axis and the fuselage axis is 0-degree, the first propeller is connected with the first motor bearing; the second motor includes a second motor bearing, the angle between the projection line of the second motor bearing axis on the fuselage symmetry plane and the fuselage axis is greater than 0-degree, and the second propeller is connected with the second motor bearing. The first motor of the vertical take-off and landing unmanned plane drives the first propeller to produce a force parallel to the fuselage axis, so that the vertical take-off and landing unmanned plane can horizontally fly at high speed. The second motor can drive the second propeller to produce a lifting force, so that the vertical take-off and landing unmanned plane can achieve zero horizontal flight taking off and landing or hovering in the air.
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:
First motor, the first motor comprises the first motor bearings, and the angle of the first motor bearings axis and fuselage axis is 0 °;
First screw propeller, the first screw propeller is connected with the first motor bearings;
Second motor, the second motor comprises the second motor bearings, and the angle of the projection straight line of the second motor bearings axis on the fuselage plane of symmetry and fuselage axis is greater than 0 °;
Second screw propeller, the second screw propeller is connected with the second motor bearings.
Further, the quantity of the first motor and the first screw propeller is one.
Further, the first motor bearings axis and fuselage dead in line.
Further, the first motor is connected with afterbody; Or the first motor is connected with fuselage head.
Further, the quantity of the second motor and the second screw propeller is four, and wherein two the second motors are arranged at the fuselage plane of symmetry first side, and another two the second motors are arranged at the fuselage plane of symmetry second side.
Further, two the second motors being positioned at the fuselage plane of symmetry first side and two the second motors being positioned at the fuselage plane of symmetry second side are symmetrical arranged along the fuselage plane of symmetry.
Further, described second motor is connected with fuselage or wing by electric machine support, and electric machine support comprises:
Cross bar, cross bar first end is connected with fuselage or wing;
Vertical pole, vertical pole first end is connected with the second motor, and vertical pole second end is connected with cross bar second end.
Further, cross bar first end is connected with wing, and cross bar axis being parallel is in fuselage axis, and cross bar axes normal is in vertical pole axis.
Further, the first end being positioned at two cross bars of fuselage plane of symmetry the same side is connected.
Further, two cross bars being positioned at fuselage plane of symmetry the same side 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, VUAV comprises the first motor and the second motor, because the angle of the first motor bearings axis and fuselage axis is 0 °, so the first motor can drive the first screw propeller to produce the power being parallel to fuselage axis around own axes rotation, VUAV high-speed horizontal flight can be made.Secondly, the angle of the projection straight line of the second motor bearings axis on the fuselage plane of symmetry and fuselage axis is greater than 0 °, such second motor can drive the second screw propeller to produce lift around own axes rotation, VUAV zero level can be made to fly and take off and land, or aloft hover.To overcome in prior art unmanned plane or need to rely on long runway, and needing after taking off to keep enough flying speeds; Horizontal flight speed is slower.
Accompanying drawing explanation
Fig. 1 is the structural representation 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 2.
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 to rotate around own axes.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 slot, described wing 2 is connected with fuselage 1 by embedding described slot, and this design makes described wing 2 detachable.
Described fuselage 1 afterbody is provided with vertical fin 3, and described vertical fin 3 is symmetrical arranged along the fuselage plane of symmetry.
In other embodiments, described VUAV also comprises: the common components such as elevating rudder, aileron and yaw rudder.
Described VUAV is also provided with the first motor, in the present embodiment, first motor is one, first motor comprises the first motor bearings, the angle of the first motor bearings axis and fuselage axis is 0 °, namely described first motor bearings axis is with fuselage axis line parallel or overlap, and the direction that this design can ensure the power that the first motor drives screw propeller rotation to produce also with fuselage axis line parallel or overlap, and then makes VUAV keep balance when flying.
In the present embodiment, the first motor bearings axis and fuselage dead in line, and the first motor is connected with afterbody, connection mode can be that the first motor is embedded afterbody, and the first motor bearings is positioned at afterbody outside, and is connected with screw propeller.
Described first motor bearings is connected with the first screw propeller 4, and described first motor drives the first screw propeller 4 rotation to produce thrust.During the first electric motor starting, described VUAV can high-speed horizontal flight, overcomes the shortcoming that in prior art, rotary wings unmanned plane forward flight speed is low.
In other embodiments, the first motor is connected with fuselage head, and described first motor drives the first screw propeller 4 rotation to produce pulling force, and during the first electric motor starting, pulling force also can make described VUAV high-speed horizontal flight.
Described VUAV also comprises the second motor, second motor comprises the second motor bearings, the angle of the projection straight line of the second motor bearings axis on the fuselage plane of symmetry and fuselage axis is greater than 0 °, and namely the second motor bearings axis is not with fuselage axis line parallel or overlap.Second motor drives screw propeller rotation to produce lift component.
When the second motor bearings axis is in the fuselage plane of symmetry, the projection straight line of the second motor bearings axis on the fuselage plane of symmetry is exactly the second motor bearings axis itself.
Second motor bearings is connected with the second screw propeller 5.
In the present embodiment, the quantity of the second motor and the second screw propeller 5 is four, and wherein two the second motors are arranged at the fuselage plane of symmetry first side, and another two the second motors are arranged at the fuselage plane of symmetry second side.
Two the second motors being positioned at the fuselage plane of symmetry first side and two the second motors being positioned at the fuselage plane of symmetry second side are symmetrical arranged along the fuselage plane of symmetry.
In other embodiments, the quantity of the second motor and the second screw propeller 5 is one, described second motor is connected with fuselage, second motor bearings axis is positioned at the fuselage plane of symmetry, second motor bearings axis is by VUAV center of gravity, and described second motor bearings axis and fuselage axes normal.
In other embodiments, the quantity of the second motor and the second screw propeller 5 can be also other numbers, as long as when can ensure the second electric motor starting, the second screw propeller can produce lift component, and except lift and be parallel to fuselage axis direction power except, the power on other directions is zero.
Described second motor bearings is connected with the second screw propeller 5, and during the second electric motor starting, the second motor bearings rotation drives the second screw propeller 5 also around own axes rotation, thus produces lift component.
In the present embodiment, described second motor is connected with fuselage or wing by electric machine support, and electric machine support comprises:
Cross bar 7, cross bar 7 first end is connected with fuselage 1 or wing 2;
Vertical pole 6, vertical pole 6 first end is connected with the first motor, and vertical pole 6 second end is connected with cross bar 7 second end.
In the present embodiment, cross bar 7 first end is connected with wing 2, and cross bar 7 axis being parallel is in fuselage axis, and cross bar 7 axes normal is in vertical pole 6 axis.This design, the power that the second screw propeller 5 time rotational produces is lift, and the power on other directions is zero entirely.
In other embodiments, cross bar 7 first end is connected with fuselage 1, and cross bar 7 axes normal is in the fuselage plane of symmetry, and cross bar 7 axes normal is in vertical pole 6 axis.This design, the power that the second screw propeller 5 time rotational produces is lift, and the power on other directions is zero entirely.
In the present embodiment, the first end being positioned at two cross bars 7 of fuselage plane of symmetry the same side is connected, or two cross bars 7 being positioned at fuselage plane of symmetry the same side are structure as a whole.
In the present embodiment, the cross bar 7 of same electric machine support and vertical pole 6 are integrated mechanism.
In the present embodiment, the second motor is connected with vertical pole 6 by the first end embedding vertical pole 6, and the second motor bearings passes the first end of vertical pole 6, and is connected with the second screw propeller 5.
Introduce the method for operation of the VUAV in the present embodiment below:
When taking off, the first motor does not start, the second electric motor starting, makes the second screw propeller 5 around own axes rotation, for VUAV provides lift; When the lift that the second screw propeller 5 produces is greater than the gravity of VUAV, the starting of VUAV takes off.
After VUAV takes off, the first motor keeps cutting out, and flies before VUAV can be made to keep hovering or low speed.By the various combination of the second motor, the pitching of differentiating control VUAV, rolling and driftage can also be adopted.
First motor does not start, reduce gradually the second screw propeller around 5 rotating speed, lift reduces gradually, when lift is less than the gravity of VUAV, VUAV start landing.
After VUAV rises and flies to certain altitude, second screw propeller keeps rotating speed constant around 5, make VUAV held stationary, start the first motor, the first screw propeller 4 rotation is made to produce thrust, the horizontal flight speed of VUAV starts to accelerate, and VUAV enters the transition stage of takeoff condition to level flight condition.When VUAV reach certain horizontal flight speed after, the second motor quits work, and VUAV enters level flight condition.
When VUAV needs hovering, the first motor quits work, and the thrust that the first screw propeller 4 produces is kept to zero; Second electric motor starting, drives the second screw propeller 5 rotation to produce lift, and make VUAV keep present level flight, when horizontal flight speed reduces to zero, VUAV is in floating state.
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:
First motor, the first motor comprises the first motor bearings, and the angle of the first motor bearings axis and fuselage axis is 0 °;
First screw propeller, the first screw propeller is connected with the first motor bearings;
Second motor, the second motor comprises the second motor bearings, and the angle of the projection straight line of the second motor bearings axis on the fuselage plane of symmetry and fuselage axis is greater than 0 °;
Second screw propeller, the second screw propeller is connected with the second motor bearings.
2. VUAV as claimed in claim 1, it is characterized in that, the quantity of the first motor and the first screw propeller is one.
3. VUAV as claimed in claim 1, is characterized in that, the first motor bearings axis and fuselage dead in line.
4. VUAV as claimed in claim 1, it is characterized in that, the first motor is connected with afterbody; Or,
First motor is connected with fuselage head.
5. VUAV as claimed in claim 1, it is characterized in that, the quantity of the second motor and the second screw propeller is four, and wherein two the second motors are arranged at the fuselage plane of symmetry first side, and another two the second motors are arranged at the fuselage plane of symmetry second side.
6. VUAV as claimed in claim 5, is characterized in that, two the second motors being positioned at the fuselage plane of symmetry first side and two the second motors being positioned at the fuselage plane of symmetry second side are symmetrical arranged along the fuselage plane of symmetry.
7. the VUAV as described in claim 5 or 6, is characterized in that, described second motor is connected with fuselage or wing by electric machine support, and electric machine support comprises:
Cross bar, cross bar first end is connected with fuselage or wing;
Vertical pole, vertical pole first end is connected with the second motor, and vertical pole second end is connected with cross bar second end.
8. VUAV as claimed in claim 7, it is characterized in that, cross bar first end is connected with wing, and cross bar axis being parallel is in fuselage axis, and cross bar axes normal is in vertical pole axis.
9. VUAV as claimed in claim 7, it is characterized in that, the first end being positioned at two cross bars of fuselage plane of symmetry the same side is connected.
10. VUAV as claimed in claim 7, it is characterized in that, two cross bars being positioned at fuselage plane of symmetry the same side are structure as a whole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510638803.4A CN105346714A (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 |
|---|---|---|---|
| CN201510638803.4A CN105346714A (en) | 2015-09-29 | 2015-09-29 | Vertical take-off and landing unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105346714A true CN105346714A (en) | 2016-02-24 |
Family
ID=55322830
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510638803.4A Pending CN105346714A (en) | 2015-09-29 | 2015-09-29 | Vertical take-off and landing unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105346714A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275416A (en) * | 2016-09-12 | 2017-01-04 | 上海圣尧智能科技有限公司 | The composite aircraft that fixed-wing forms with many rotors |
| CN106275417A (en) * | 2016-09-12 | 2017-01-04 | 上海圣尧智能科技有限公司 | A kind of Fixed Wing AirVehicle with many rotors |
| CN106585951A (en) * | 2016-12-09 | 2017-04-26 | 上海圣尧智能科技有限公司 | Folding structure and aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010024593A2 (en) * | 2008-08-29 | 2010-03-04 | Lim Chaeho | Vtol aircraft using variable rotor |
| CN103043212A (en) * | 2011-10-17 | 2013-04-17 | 田瑜 | Combined aircraft composed of fixed wing and electric multi-rotor wing |
| KR20140125222A (en) * | 2013-04-18 | 2014-10-28 | 건국대학교 산학협력단 | Unmanned air vehicles for performing vertical take-off and landing, and method of maneuverability flight of unmanned air vehicles |
| CN204452934U (en) * | 2015-02-05 | 2015-07-08 | 仉军 | The double mode aircraft of rotor, fixed-wing |
-
2015
- 2015-09-29 CN CN201510638803.4A patent/CN105346714A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010024593A2 (en) * | 2008-08-29 | 2010-03-04 | Lim Chaeho | Vtol aircraft using variable rotor |
| CN103043212A (en) * | 2011-10-17 | 2013-04-17 | 田瑜 | Combined aircraft composed of fixed wing and electric multi-rotor wing |
| KR20140125222A (en) * | 2013-04-18 | 2014-10-28 | 건국대학교 산학협력단 | Unmanned air vehicles for performing vertical take-off and landing, and method of maneuverability flight of unmanned air vehicles |
| CN204452934U (en) * | 2015-02-05 | 2015-07-08 | 仉军 | The double mode aircraft of rotor, fixed-wing |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275416A (en) * | 2016-09-12 | 2017-01-04 | 上海圣尧智能科技有限公司 | The composite aircraft that fixed-wing forms with many rotors |
| CN106275417A (en) * | 2016-09-12 | 2017-01-04 | 上海圣尧智能科技有限公司 | A kind of Fixed Wing AirVehicle with many rotors |
| CN106585951A (en) * | 2016-12-09 | 2017-04-26 | 上海圣尧智能科技有限公司 | Folding structure and aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10279904B2 (en) | Fixed structure type vertical take-off and landing aircraft based on dual flying control systems and control method therefor | |
| RU2700084C2 (en) | Multi-rotor with rotary wing | |
| CN105109680A (en) | Vertical take-off and landing unmanned airplane | |
| AU2017272341A1 (en) | Vertical take-off and landing (VTOL) winged air vehicle with complementary angled rotors | |
| CN204822069U (en) | Four rotor unmanned aerial vehicle configurations of duct | |
| CN104276284B (en) | A kind of series type fan rotor aircraft layout | |
| CN206645007U (en) | Aircraft | |
| CN105197237A (en) | Vertical takeoff and landing unmanned aerial vehicle | |
| CN105346715A (en) | Vertical take-off and landing unmanned plane | |
| CN106043696A (en) | Flying system for unmanned aerial vehicle | |
| CN206704537U (en) | A kind of fixed-wing unmanned plane | |
| CN204688409U (en) | The unmanned vehicle that a kind of many rotors and fixed-wing combine | |
| CN105346718A (en) | Vertical take-off and landing unmanned plane | |
| CN105173076B (en) | A kind of vertical take-off and landing drone | |
| CN105151295A (en) | Vertical take-off and landing unmanned aerial vehicle | |
| CN206187340U (en) | Aircraft | |
| CN105346714A (en) | Vertical take-off and landing unmanned plane | |
| CN103754360A (en) | Similar flying saucer type rotaplane | |
| CN106275416A (en) | The composite aircraft that fixed-wing forms with many rotors | |
| CN105346725A (en) | Vertical take-off and landing unmanned aerial vehicle | |
| US10864987B2 (en) | Counter rotating torque drive for rotary wing vehicle propulsion | |
| CN110254711A (en) | Two horizontal four vertical blades can turn six wheeled dynamic wing unmanned planes | |
| KR20140089096A (en) | System for controlling angle of attack of unmanned air vehicle based on multi-rotor system | |
| CN206107566U (en) | Aircraft | |
| CN105346716A (en) | Unmanned aerial vehicle power system and vertical take-off and landing unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160224 |
|
| RJ01 | Rejection of invention patent application after publication |