CN105151295A - Vertical take-off and landing unmanned aerial vehicle - Google Patents
Vertical take-off and landing unmanned aerial vehicle Download PDFInfo
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- CN105151295A CN105151295A CN201510638647.1A CN201510638647A CN105151295A CN 105151295 A CN105151295 A CN 105151295A CN 201510638647 A CN201510638647 A CN 201510638647A CN 105151295 A CN105151295 A CN 105151295A
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- vuav
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Abstract
A vertical take-off and landing unmanned aerial vehicle comprises a fuselage, wings, propellers located at the head of the fuselage, three or more tail booms and three or more vertical tails. The tail booms are connected with the tail of the fuselage and can rotate around a rotating shaft perpendicular to the axis of the fuselage. Each vertical tail is connected with one tail boom. The tail booms are connected with the vertical tails and can rotate around the rotating shaft perpendicular to the axis of the fuselage. When the tail booms and the vertical tails rotate around the rotating shaft and are expanded outwards relative to the axis of the fuselage, the tail booms and the vertical tails can serve as an undercarriage for vertical take-off and landing. As the distance between supporting points becomes large, the upright stability of the vertical take-off and landing unmanned aerial vehicle is good. When the tail booms and the vertical tails rotate around the rotating shaft and are inwards folded relative to the axis of the fuselage, a similar complete vertical tail pneumatic layout is formed, and the stability of the vertical take-off and landing unmanned aerial vehicle is guaranteed.
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, wing and be positioned at the screw propeller of fuselage head, also comprise:
Shoe, the quantity of shoe is more than three or three, and shoe is connected with afterbody, and shoe can rotate around the S. A. perpendicular to fuselage axis;
Vertical fin, the quantity of vertical fin is more than three or three, and each vertical fin is connected with a shoe.
Further, the quantity of described shoe and described vertical fin is equal.
Further, the quantity of described shoe is four.
Further, the S. A. of each shoe is positioned at same plane.
Further, the S. A. of each shoe intersects formation equilateral polygon, and fuselage axis is through described equilateral polygon center.
Further, described shoe and afterbody hinged; Vertical fin is fixedly connected with shoe or is structure as a whole.
Further, shoe has first end and the second end, and first end is connected with afterbody, and the second end is connected with vertical fin.
Further, the width of shoe first end is greater than the width of the second end.
Further, be provided with aileron in described wing, described aileron is positioned at the slipstream of described screw propeller; Yaw rudder is provided with in described vertical fin.
Further, described fuselage interior is equipped with lithium cell, flight control system, electronic governor and motor.
Compared with prior art, technical scheme of the present invention has the following advantages:
Shoe is connected with vertical fin, and can rotate around the S. A. perpendicular to fuselage axis.
When shoe and vertical fin rotate around S. A., and after launching relative to fuselage axis alignment, can be used as alighting gear during vertical takeoff and landing outward, because strong point spacing becomes large, the upright good stability of VUAV.
When shoe and vertical fin rotate around S. A., and relative to packing up the complete vertical fin aerodynamic arrangement of rear formation class in fuselage axis alignment, ensure that VUAV stability.
Further, VUAV aileron, in propeller race district, can regulate the flight course of VUAV, realizes the flight attitudes such as upset.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of VUAV of the present invention;
Fig. 2 is schematic diagram when shoe and vertical fin are outwards opened in a kind of VUAV takeoff condition of the present invention process;
Fig. 3 is schematic diagram when shoe and vertical fin inwardly merge in a kind of VUAV takeoff condition of the present invention process;
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 flying 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.
The invention provides a kind of VUAV, with reference to figure 1, comprising:
Fuselage 1, lithium cell, flight control system, electronic governor and motor are equipped with in described fuselage 1 inside.Described lithium cell provides energy to make described motor drive the screw propeller 8 being positioned at fuselage head, produces the thrust being parallel to fuselage axis.The velocity of rotation of electronic governor regulation and control motor, flight control system is used for remote controller to the control of VUAV state of flight.
Wing 2, described wing 2 can produce relative motion with air when VUAV horizontal flight, and then produces lift to overcome the gravity of VUAV, keeps the horizontal flight of VUAV.
In a particular embodiment, be provided with aileron 5 in described wing 2, described aileron 5 is positioned at the slipstream of described screw propeller 8.Aileron 5 can regulate the flight course of VUAV, realizes the flight attitudes such as upset.VUAV aileron 5 is arranged in the slipstream of screw propeller 8, also effectively can control the flight attitude of VUAV when making VUAV speed lower.
Shoe 6, the quantity of shoe 6 is more than three or three, is four in the present embodiment.Shoe 6 is connected with afterbody, and shoe can rotate around the S. A. perpendicular to fuselage axis, and described S. A. is shoe S. A. 7.
In the present invention, the S. A. perpendicular to fuselage axis not only only refers to S. A. with fuselage axes intersect and vertical; And can be the S. A. met the following conditions: a plane and fuselage axis perpendicular can be found in the plane of this rotating shaft axis.
In the present embodiment, shoe S. A. 7 is positioned at same plane, and this plane orthogonal is in fuselage axis.The S. A. of each shoe intersects formation equilateral polygon, and fuselage axis is through described equilateral polygon center.Namely described shoe S. A. 7 with described equilateral polygon center for center of symmetry is centrosymmetric distribution.The flight attitude of this design mainly in order to make symmetrical shoe 6 effectively can control VUAV, and keep balance.
Vertical fin 3, the quantity of vertical fin 3 is more than three or three, and each vertical fin 3 is connected with a shoe 6.
In the present embodiment, vertical fin 3 is four.Vertical fin 3 is fixedly connected with shoe 6 or is structure as a whole.A vertical fin 3 is connected with a shoe 6.Yaw rudder 4 is provided with in described vertical fin 3.Yaw rudder 4 is for improving the stationarity of VUAV flight.
In a particular embodiment, shoe 6 has first end and the second end, and first end is connected with afterbody, and the second end is connected with vertical fin 3.The width of shoe 6 first end is greater than the width of the second end.
Introduce method of operation during landing and the horizontal flight of VUAV below:
When described VUAV takes off, with reference to figure 2, first shoe 6 and vertical fin 3 are opened relative to outside fuselage axis alignment, form four dispensing support points, be used as VUAV alighting gear, fuselage is vertically placed; By lithium cell drive motor under the control of flight control system, and carrying screws 8 rotates, and produces pulling force upwards, overcomes gravity and take off.
With reference to figure 3, after VUAV is liftoff, by servo driving, shoe 6 and vertical fin 3 merge relative in fuselage axis alignment, make VUAV change of flight attitude under the control of aileron 5, shoe 6 and vertical fin 3, steering horizontal flight gradually.
Shoe 6 and vertical fin 3 inwardly pack up rear formation four vertical fin aerodynamic arrangements, ensure that VUAV stability.Aileron 5, in screw propeller 8 slipstream, can regulate the flight course of VUAV, realizes the flight attitudes such as upset.
With reference to figure 4, setting up horizontal velocity by controlling electronic governor, making VUAV horizontal flight pattern.
When needs vertical landing, VUAV is under the control of aileron 5, shoe 6 and vertical fin 3, and fuselage head is pulled upwardly gradually, screw propeller 8 produce power upwards form pulling force gradually, and pulling force gradually with the dead in line of VUAV gravity; Then, reduce screw propeller 8 rotating speed and pulling force is reduced, when pulling force is less than VUAV gravity, under gravity, VUAV slowly declines; Meanwhile, VUAV shoe 6 and vertical fin 3 are opened relative to outside fuselage axis alignment under servo driving, form four dispensing support points, rely on four strong points upright after VUAV ground connection.Attitude after landing can continue with reference to figure 2.
When needs hover, VUAV is under the control of aileron 5, shoe 6 and vertical fin 3, and fuselage head is pulled upwardly gradually, screw propeller 8 produce power upwards form pulling force gradually, and pulling force gradually with the dead in line of VUAV gravity; Then, reduce screw propeller 8 rotating speed and pulling force is reduced, when pulling force is reduced to equal with VUAV gravity, landing unmanned plane can be made to be in floating state.
Otherwise, when needs make VUAV return level flight condition by floating state, VUAV can be controlled by aileron 5, shoe 6 and vertical fin 3, make fuselage head gradually toward drop-down, VUAV is made to be in horizontality, then, required horizontal flight speed is produced by screw propeller 8.
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, wing and be positioned at the screw propeller of fuselage head, it is characterized in that, also comprises:
Shoe, the quantity of shoe is more than three or three, and shoe is connected with afterbody, and shoe can rotate around the S. A. perpendicular to fuselage axis;
Vertical fin, the quantity of vertical fin is more than three or three, and each vertical fin is connected with a shoe.
2. VUAV as claimed in claim 1, it is characterized in that, the quantity of described shoe and described vertical fin is equal.
3. VUAV as claimed in claim 2, it is characterized in that, the quantity of described shoe is four.
4. the VUAV as described in claim 1,2 or 3, is characterized in that, the S. A. of each shoe is positioned at same plane.
5. VUAV as claimed in claim 4, is characterized in that, the S. A. of each shoe intersects formation equilateral polygon, and fuselage axis is through described equilateral polygon center.
6. VUAV as claimed in claim 1, is characterized in that, described shoe and afterbody hinged;
Vertical fin is fixedly connected with shoe or is structure as a whole.
7. VUAV as claimed in claim 1, it is characterized in that, shoe has first end and the second end, and first end is connected with afterbody, and the second end is connected with vertical fin.
8. VUAV as claimed in claim 7, it is characterized in that, the width of shoe first end is greater than the width of the second end.
9. VUAV as claimed in claim 1, it is characterized in that, be provided with aileron in described wing, described aileron is positioned at the slipstream of described screw propeller;
Yaw rudder is provided with in described vertical fin.
10. VUAV as claimed in claim 1, it is characterized in that, described fuselage interior is equipped with lithium cell, flight control system, electronic governor and motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510638647.1A CN105151295A (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 |
|---|---|---|---|
| CN201510638647.1A CN105151295A (en) | 2015-09-29 | 2015-09-29 | Vertical take-off and landing unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN105151295A true CN105151295A (en) | 2015-12-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201510638647.1A Pending CN105151295A (en) | 2015-09-29 | 2015-09-29 | Vertical take-off and landing unmanned aerial vehicle |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730676A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN105730677A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN106184773A (en) * | 2016-07-15 | 2016-12-07 | 北京航空航天大学 | A kind of tailstock formula duct unmanned aerial vehicle |
| CN106428548A (en) * | 2016-10-12 | 2017-02-22 | 曹萍 | Vertical take-off and landing unmanned aerial vehicle |
| CN112607012A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Vertical take-off and landing fixed wing unmanned aerial vehicle and take-off and landing method |
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| US5289994A (en) * | 1989-10-10 | 1994-03-01 | Juan Del Campo Aguilera | Equipment carrying remote controlled aircraft |
| CN101353084A (en) * | 2008-09-05 | 2009-01-28 | 龙川 | Light aerobat capable of landing or taking-off vertically |
| US20120248259A1 (en) * | 2011-03-24 | 2012-10-04 | Mark Allan Page | Long endurance vertical takeoff and landing aircraft |
| CN102897319A (en) * | 2012-08-10 | 2013-01-30 | 江闻杰 | Fuselage variant type vertical take off and landing aircraft |
| CN104470800A (en) * | 2012-02-13 | 2015-03-25 | 约翰内斯·赖特 | Wing adjusting mechanism |
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2015
- 2015-09-29 CN CN201510638647.1A patent/CN105151295A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2397632A (en) * | 1941-03-04 | 1946-04-02 | Gen Motors Corp | Airplane |
| US5289994A (en) * | 1989-10-10 | 1994-03-01 | Juan Del Campo Aguilera | Equipment carrying remote controlled aircraft |
| CN101353084A (en) * | 2008-09-05 | 2009-01-28 | 龙川 | Light aerobat capable of landing or taking-off vertically |
| US20120248259A1 (en) * | 2011-03-24 | 2012-10-04 | Mark Allan Page | Long endurance vertical takeoff and landing aircraft |
| CN104470800A (en) * | 2012-02-13 | 2015-03-25 | 约翰内斯·赖特 | Wing adjusting mechanism |
| CN102897319A (en) * | 2012-08-10 | 2013-01-30 | 江闻杰 | Fuselage variant type vertical take off and landing aircraft |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730676A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN105730677A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN106184773A (en) * | 2016-07-15 | 2016-12-07 | 北京航空航天大学 | A kind of tailstock formula duct unmanned aerial vehicle |
| CN106428548A (en) * | 2016-10-12 | 2017-02-22 | 曹萍 | Vertical take-off and landing unmanned aerial vehicle |
| CN106428548B (en) * | 2016-10-12 | 2019-09-27 | 曹萍 | A kind of vertical take-off and landing unmanned aerial vehicle |
| CN112607012A (en) * | 2020-12-24 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Vertical take-off and landing fixed wing unmanned aerial vehicle and take-off and landing method |
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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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20151216 |