CN105173076A - VTOL (vertical take-off and landing) UAV (unmanned aerial vehicle) - Google Patents
VTOL (vertical take-off and landing) UAV (unmanned aerial vehicle) Download PDFInfo
- Publication number
- CN105173076A CN105173076A CN201510639108.XA CN201510639108A CN105173076A CN 105173076 A CN105173076 A CN 105173076A CN 201510639108 A CN201510639108 A CN 201510639108A CN 105173076 A CN105173076 A CN 105173076A
- Authority
- CN
- China
- Prior art keywords
- vuav
- wing
- motor
- fuselage
- 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.)
- Granted
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 6
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 5
- 229910052744 lithium Inorganic materials 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Landscapes
- Toys (AREA)
Abstract
A VTOL (vertical take-off and landing) UAV (unmanned aerial vehicle) comprises a vehicle body, wings, ailerons, three or more vertical fins, motors and propellers, wherein the ailerons are hinged with the wings; at least one vertical fin is arranged on the upper side of the VTOL UAV, at least one vertical fin is arranged on the lower side of the VTOL UAV, and at least part of the trailing edges of the vertical fins are located at the rear parts of the trailing edges of the wings; the motors are connected with the wings and comprise motor bearings; the propellers are connected with the motor bearings. At least part of the trailing edges of the vertical fins are located at the rear parts of the trailing edges of the wings, so that the trailing edges of the vertical fins serve as a landing gear to support the VTOL UAV when the VTOL UAV is placed vertically; the ailerons are hinged with the wings, and accordingly, the VTOL UAV can take off vertically, land vertically or hover at high altitude through rotation of the ailerons and can fly horizontally at a high speed.
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, have at least a vertical fin be arranged at vertical takeoff and landing without
Man-machine upside, has at least a vertical fin to be arranged on the downside of VUAV, after at least part of vertical fin
Edge is positioned at trailing edge rear portion;
Motor, motor is connected with wing, and described motor comprises motor bearings;
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 quantity of motor is four, and wherein two motors are connected with on the upside of wing, and two motors are connected with on the downside of wing.
Further, two motors be arranged on the upside of wing are symmetrical arranged along the fuselage plane of symmetry; Two motors be arranged on the downside of wing are symmetrical arranged along the fuselage plane of symmetry.
Further, be arranged at the motor on the upside of wing to the distance of the fuselage plane of symmetry to be greater than and to be arranged at the distance of the motor on the downside of wing to the fuselage plane of symmetry.
Further, also comprise: motor support arm, motor is connected with wing by motor support arm.
Further, also comprise: electric machine support, motor is placed in electric machine support, and electric machine support is connected with motor support arm.
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.
Further, described motor is connected with wing, and the quantity of motor is four, and wherein two motors are connected with on the upside of wing, and two motors are connected with on the downside of wing.This being designed with is beneficial to VUAV and keeps stable when vertically placing.
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 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.
In a particular embodiment, described wing 2 is provided with motor support arm 7, and motor support arm 7 is connected with electric machine support 5.As motor support arm 7 one end and wing 2 are connected or are structure as a whole, motor support arm 7 other end is connected with electric machine support 5 and is connected or is structure as a whole.
Described electric machine support 5 is built with motor, and motor comprises motor bearings, and motor bearings passes electric machine support 5 and is connected with screw propeller 6.Screw propeller 6 by motor drive can around own axes from then power is provided.
In other embodiments, also motor directly can be connected in wing, namely can there is no electric machine support 5 and motor support arm 7.
In the present embodiment, the quantity of described motor is four, and wherein two motors are connected with on the upside of wing 2, and two motors are connected with on the downside of wing 2.
Wherein refer on the upside of wing 2 VUAV be positioned at when horizontal flight above side, refer on the downside of wing 2 VUAV be positioned at when horizontal flight below side.
Two motors be arranged on the upside of wing 2 are symmetrical arranged along the fuselage plane of symmetry; Two motors be arranged on the downside of wing 2 are symmetrical arranged along the fuselage plane of symmetry.Can ensure that power that screw propeller 6 rotation produces is along fuselage plane of symmetry symmetry like this, VUAV can smooth flight; On the other hand, this design can ensure the stress balance of VUAV when vertically placing.
In the present embodiment, be arranged at the motor on the upside of wing 2 to the distance of the fuselage plane of symmetry to be greater than and to be arranged at the distance of the motor on the downside of wing 2 to the fuselage plane of symmetry.
Motor to the distance of the fuselage plane of symmetry can be on motor any position to the distance of the fuselage plane of symmetry, but each motor should select identical position to ensure that distance has comparability.
This being designed with is beneficial to the load-carrying of VUAV when horizontal flight on wing not only symmetry but also disperse, and can improve the stationarity of VUAV.
In other embodiments, be arranged at the motor on the upside of wing 2 to the distance of the fuselage plane of symmetry to be less than and to be arranged at the distance of the motor on the downside of wing 2 to the fuselage plane of symmetry.
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 8, and aileron 8 is hinged with wing 2 afterbody, and be provided with steering wheel in described wing 2, described steering wheel can drive aileron 8 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 8 is two, hinged with two wings 2 respectively, and two ailerons 8 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, drive 4 electric machine rotations by lithium cell, and drive 4 screw propellers 6 around own axes rotation.And making 4 screw propellers 6 be divided into two groups according to diagonal line, the direction that described two groups of screw propellers 6 rotate is contrary, rotates to offset screw propeller 6 the anti-oar power produced.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 8 to rotate around the S. A. perpendicular to fuselage axis under the control of flight control system, by regulating aileron 8, 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 power 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 8 to rotate around the S. A. perpendicular to fuselage axis under the control of flight control system, by regulating aileron 8, 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 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;
Motor, motor is connected with wing, and described motor comprises motor bearings;
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 1, it is characterized in that, the quantity of motor is four, and wherein two motors are connected with on the upside of wing, and two motors are connected with on the downside of wing.
7. VUAV as claimed in claim 6, it is characterized in that, two motors be arranged on the upside of wing are symmetrical arranged along the fuselage plane of symmetry;
Two motors be arranged on the downside of wing are symmetrical arranged along the fuselage plane of symmetry.
8. VUAV as claimed in claim 7, is characterized in that, is arranged at the motor on the upside of wing to the distance of the fuselage plane of symmetry and is greater than and is arranged at the distance of the motor on the downside of wing to the fuselage plane of symmetry.
9. VUAV as claimed in claim 8, is characterized in that, also comprise:
Motor support arm, motor is connected with wing by motor support arm.
10. VUAV as claimed in claim 9, is characterized in that, also comprise:
Electric machine support, motor is placed in electric machine support, and electric machine support is connected with motor support arm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510639108.XA CN105173076B (en) | 2015-09-29 | 2015-09-29 | A kind of vertical take-off and landing drone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510639108.XA CN105173076B (en) | 2015-09-29 | 2015-09-29 | A kind of vertical take-off and landing drone |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105173076A true CN105173076A (en) | 2015-12-23 |
| CN105173076B CN105173076B (en) | 2018-09-14 |
Family
ID=54895661
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510639108.XA Active CN105173076B (en) | 2015-09-29 | 2015-09-29 | A kind of vertical take-off and landing drone |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105173076B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428548A (en) * | 2016-10-12 | 2017-02-22 | 曹萍 | Vertical take-off and landing unmanned aerial vehicle |
| CN106494614A (en) * | 2016-10-28 | 2017-03-15 | 清华大学 | Aircraft |
| CN107499506A (en) * | 2017-07-07 | 2017-12-22 | 清华大学 | A kind of distributed propulsion tailstock formula VTOL Fixed Wing AirVehicle |
| WO2018070867A1 (en) * | 2016-10-12 | 2018-04-19 | Technische Universiteit Delft | Aerial vehicle with angularly displaced propulsion units |
| 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 |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| WO2008007147A1 (en) * | 2006-07-13 | 2008-01-17 | Hoverwing Limited | Aircraft |
| US20100032947A1 (en) * | 2008-03-06 | 2010-02-11 | Bevirt Joeben | Apparatus for generating power using jet stream wind power |
| CN102514712A (en) * | 2011-12-07 | 2012-06-27 | 上海大学 | Vertical take-off and landing aircraft |
| US20120286102A1 (en) * | 2009-08-24 | 2012-11-15 | Pranay Sinha | Remotely controlled vtol aircraft, control system for control of tailless aircraft, and system using same |
| CN102917765A (en) * | 2010-03-24 | 2013-02-06 | 马卡尼电力有限公司 | Planform configuration for stability of a powered kite and a system and method for use of same |
| CN202728574U (en) * | 2011-10-17 | 2013-02-13 | 田瑜 | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function |
-
2015
- 2015-09-29 CN CN201510639108.XA patent/CN105173076B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| WO2008007147A1 (en) * | 2006-07-13 | 2008-01-17 | Hoverwing Limited | Aircraft |
| US20100032947A1 (en) * | 2008-03-06 | 2010-02-11 | Bevirt Joeben | Apparatus for generating power using jet stream wind power |
| US20120286102A1 (en) * | 2009-08-24 | 2012-11-15 | Pranay Sinha | Remotely controlled vtol aircraft, control system for control of tailless aircraft, and system using same |
| CN102917765A (en) * | 2010-03-24 | 2013-02-06 | 马卡尼电力有限公司 | Planform configuration for stability of a powered kite and a system and method for use of same |
| CN202728574U (en) * | 2011-10-17 | 2013-02-13 | 田瑜 | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function |
| CN102514712A (en) * | 2011-12-07 | 2012-06-27 | 上海大学 | Vertical take-off and landing aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 万明: "《交通运输概论》", 28 February 2015, 人民交通出版社股份有限公司 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106428548A (en) * | 2016-10-12 | 2017-02-22 | 曹萍 | Vertical take-off and landing unmanned aerial vehicle |
| WO2018070867A1 (en) * | 2016-10-12 | 2018-04-19 | Technische Universiteit Delft | Aerial vehicle with angularly displaced propulsion units |
| NL2017611B1 (en) * | 2016-10-12 | 2018-04-20 | Univ Delft Tech | Aerial vehicle with angularly displaced propulsion units |
| CN106428548B (en) * | 2016-10-12 | 2019-09-27 | 曹萍 | A kind of vertical take-off and landing unmanned aerial vehicle |
| CN106494614A (en) * | 2016-10-28 | 2017-03-15 | 清华大学 | Aircraft |
| CN107499506A (en) * | 2017-07-07 | 2017-12-22 | 清华大学 | A kind of distributed propulsion tailstock formula VTOL Fixed Wing AirVehicle |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105173076B (en) | 2018-09-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201923320U (en) | Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle | |
| CN102133926B (en) | Tailstock type vertical take-off and landing unmanned aerial vehicle | |
| CN105346715A (en) | Vertical take-off and landing unmanned plane | |
| CN105083550A (en) | Fixed-wing aircraft realizing vertical take-off and landing | |
| CN106043696A (en) | Flying system for unmanned aerial vehicle | |
| CN105197237A (en) | Vertical takeoff and landing unmanned aerial vehicle | |
| CN106628162A (en) | Composite unmanned aerial vehicle | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN102514712A (en) | Vertical take-off and landing aircraft | |
| CN106218887A (en) | A kind of vertically taking off and landing flyer of distributed-power device layout | |
| CN205022862U (en) | Power device and fixed wing aircraft with mechanism of verting | |
| CN205022861U (en) | VTOL fixed wing aircraft | |
| CN105173076B (en) | A kind of vertical take-off and landing drone | |
| CN109319110A (en) | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure | |
| CN205418102U (en) | All -wing aircraft formula rotor craft that verts | |
| CN106927040A (en) | It is a kind of can VTOL the rotor tailless configuration aircraft of tailstock formula four | |
| CN206645007U (en) | Aircraft | |
| CN105109680A (en) | Vertical take-off and landing unmanned airplane | |
| CN206125421U (en) | VTOL unmanned vehicles | |
| CN110466297A (en) | A kind of hovercar and hovercar control method | |
| CN105151295A (en) | Vertical take-off and landing unmanned aerial vehicle | |
| CN105129097A (en) | Unmanned aerial vehicle capable of taking off and landing vertically | |
| CN113371190A (en) | Combined type high-speed helicopter based on conventional rotor wing configuration | |
| CN206187340U (en) | Aircraft | |
| CN106828919A (en) | It is a kind of can VTOL the coaxial Fan Jiang tailless configurations aircraft of tailstock formula |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| CB03 | Change of inventor or designer information |
Inventor after: Zhang Jie Inventor before: Zhang Jie Inventor before: Yu Chunguang Inventor before: Liu Zhuobin Inventor before: Zhou Yi Inventor before: Zhang Wang |
|
| COR | Change of bibliographic data | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20180409 Address after: 530007 Building No. 23, building No. 8, building No. 23, the Guangxi Zhuang Autonomous Region high tech Zone, the Guangxi Zhuang Autonomous Region, No. 208 Applicant after: Guangxi Saint Yao Aeronautical Science and Technology Co., Ltd. Address before: 200000 Free Trade Zone, Shanghai, Pudong New Area new Jinqiao Road, building 27, building 2, floor 13 Applicant before: SHANGHAI SHENGYAO INTELLIGENT TECHNOLOGY CO., LTD. |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: A vertical take off and landing UAV Effective date of registration: 20210422 Granted publication date: 20180914 Pledgee: Nanning United Innovation Venture Capital Co.,Ltd. Pledgor: Guangxi Sheng Yao science and technology of aviations Co.,Ltd. Registration number: Y2021450000010 |
|
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 530007 floor 102, block B, building 8, No. 23, Chuangxin Road, high tech Zone, Nanning, Guangxi Zhuang Autonomous Region Patentee after: Guangxi Shengyao Intelligent Technology Co.,Ltd. Address before: 530007 No. 208, building 8, 23 innovation road, hi tech Zone, Nanning, the Guangxi Zhuang Autonomous Region, B Patentee before: Guangxi Sheng Yao science and technology of aviations Co.,Ltd. |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20220606 Granted publication date: 20180914 Pledgee: Nanning United Innovation Venture Capital Co.,Ltd. Pledgor: Guangxi Sheng Yao science and technology of aviations Co.,Ltd. Registration number: Y2021450000010 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: A vertical takeoff and landing UAV Effective date of registration: 20220609 Granted publication date: 20180914 Pledgee: Guangxi Guihui Financing Guarantee Co.,Ltd. Pledgor: Guangxi Shengyao Intelligent Technology Co.,Ltd. Registration number: Y2022450000083 |