CN206155789U - But fixed wing uavs of VTOL - Google Patents
But fixed wing uavs of VTOL Download PDFInfo
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- CN206155789U CN206155789U CN201621217002.7U CN201621217002U CN206155789U CN 206155789 U CN206155789 U CN 206155789U CN 201621217002 U CN201621217002 U CN 201621217002U CN 206155789 U CN206155789 U CN 206155789U
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- unmanned plane
- power output
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Abstract
The utility model discloses a but fixed wing uavs of VTOL, include fuselage, wing, fin, afterbody power output structure and install the perpendicular power output structure under the wing, the afterbody power output structure install the tail end of fuselage, the wing is installed the fuselage both sides, the fin is installed the top of fuselage tail end. The utility model relates to a but fixed wing uavs of VTOL, perpendicular power output structure's installation with make unmanned aerial vehicle can the VTOL, can hover and to accomplish some special tasks again, the fuselage adopts portable lock joint with wing coupling part, and all circuits adopt contact type connection, effectively shortens the unmanned aerial vehicle installation and removes between the time receiving portable and transportation.
Description
Technical field
The utility model belongs to aircraft field, more particularly to it is a kind of can VTOL fixed-wing unmanned plane.
Background technology
Unmanned plane is a kind of flight instruments in developing rapidly, its have maneuverability, reaction quick, unmanned flight,
Operation requires low advantage.Can be widely applied to the fields such as agricultural, exploration, photography, border patrol.
Unmanned plane is distinguished from type of aircraft can be divided into fixed-wing and rotor wing unmanned aerial vehicle, and gyroplane has single rotor again
Be exactly helicopter and many rotors point.
Fixed-wing unmanned plane is the Mainstream Platform of military and most civilian unmanned planes, and maximum feature is that voyage is long, face of cruising
Product is big, and cruising speed is fast, and flying height is high, and flight efficiency is high.Have the disadvantage the special open ground of needs for landing of taking off, it is impossible to
Realize hovering.
The small volume of rotor wing unmanned aerial vehicle, lightweight, easy accessibility, are adapted to multi-platform, many spaces and use, and can vertically rise
Drop, hovering, mobility strong has the disadvantage that flight efficiency is low, and cruising time is short.
Analyze existing UAS, fixed-wing unmanned plane is in meet cruising time long, high-performance cruise, high efficiency flight
In the case of, with victory inconvenient to carry, need special place or device to be launched and reclaimed, in severe and limit cycle
The shortcomings of use in border is restricted.And running into needs where emphasis investigation, it is impossible to realize hovering so as to enter line number
According to detailed collection, for these above-mentioned problems, we have proposed a kind of modified that be able to can be hovered again with VTOL
Fixed-wing unmanned plane structure and corresponding flight control system.
Utility model content
The purpose of this utility model be that provide to solve the above problems it is a kind of can VTOL fixed-wing without
It is man-machine.
The utility model is achieved through the following technical solutions above-mentioned purpose：
It is a kind of can VTOL fixed-wing unmanned plane, including fuselage, wing, empennage, afterbody power output structure and peace
Dress Vertical Dynamic export structure under the wings of an airplane, the afterbody power output structure is arranged on the tail end of the fuselage, the machine
The wing is arranged on the fuselage both sides, and the empennage is arranged on the top of the fuselage tail end.
Specifically, the Vertical Dynamic export structure include two engines, two rotor blades and Quick Release hanging sticks, two
The engine is arranged on inside the two ends of the Quick Release hanging stick, and the power output shaft of an engine is corresponded to and an institute
State rotor blade to be connected.
Further, the Quick Release hanging stick passes through pin and the wing positioned in alignment, and by screw and the wing
It is fixedly connected.
Specifically, the wing includes the first wing and the second wing, is provided with connecting hole on the fuselage, described first
Snapping connecting rod is installed, the end of the snapping connecting rod is that squash type inserts head, is provided with second wing slotting in wing
Enter connecting rod, the end of the insertion connecting rod is concave gland, and the snapping connecting rod and the insertion connecting rod are inserted into institute
State in connecting hole, and the snapping in the connecting hole.
Further, the fuselage is connected with the electronic circuit of first wing and second wing passes through respectively
It is arranged on the electronic contact structure on the fuselage, first wing and second wing to complete.
Further, pin is provided with first wing and second wing and the joint face of the fuselage,
Fixing hole is provided with the joint face of the fuselage, first wing and second wing are by pin and the fuselage pair
Neat location and installation.
Further, it is mounted on a Vertical Dynamic export structure under first wing and second wing.
Specifically, afterbody power output structure includes engine and afterbody blade, the power output shaft of the engine with
The afterbody blade is connected.
Specifically, the unmanned plane also includes radome fairing, and the radome fairing is arranged on the afterbody power output structure.
Specifically, it is provided with carbon fiber honeycomb interlayer inside the fuselage, the wing and the empennage.Meeting knot
On the basis of structure strength and stiffness, accomplish maximum loss of weight, effectively raise flight efficiency.
The beneficial effects of the utility model are：
The utility model it is a kind of can VTOL fixed-wing unmanned plane, the installation of Vertical Dynamic export structure and using making
Unmanned plane can be hovered and can complete some special tasks again with VTOL；Fuselage and wing connection point
Using portable snapping, all circuits are connected using contact, are effectively shortened unmanned plane and are installed and remove between the time receiving, are easy to carry and are transported
It is defeated.
Description of the drawings
Fig. 1 be the utility model it is a kind of can VTOL fixed-wing unmanned plane structural representation；
Fig. 2 be the utility model it is a kind of can VTOL fixed-wing unmanned plane configuration schematic diagram；
Fig. 3 be the utility model it is a kind of can VTOL fixed-wing unmanned plane middle fuselage it is detailed with the attachment structure of wing
Figure；
Fig. 4 is that the utility model is a kind of can Vertical Dynamic export structure schematic diagram in the fixed-wing unmanned plane of VTOL；
Fig. 5 be the utility model it is a kind of can the attachment structure of fixed-wing unmanned plane middle fuselage and wing of VTOL illustrate
Figure.
In figure：1- fuselages, 2- wings, 3- empennages, 4- radome fairings, 5- afterbody blades, 6- rotor blades, 7- Quick Release hanging sticks,
8- inserts connecting rod, 9- snapping connecting rods, 10- connecting holes, 11- insertion heads, 12- glands.
Specific embodiment
Below in conjunction with the accompanying drawings the utility model is described in further detail：
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4 and Fig. 5, the utility model it is a kind of can VTOL fixed-wing unmanned plane, bag
Fuselage 1, wing 2, empennage 3, afterbody power output structure and the Vertical Dynamic export structure under wing 2 are included, afterbody is moved
Power export structure is arranged on the tail end of fuselage 1, and wing 2 is arranged on the both sides of fuselage 1, and empennage 3 is arranged on the top of the tail end of fuselage 1.
Vertical Dynamic export structure includes two engines, two rotor blades 6 and Quick Release hanging sticks 7, two engine peaces
It is mounted in inside the two ends of Quick Release hanging stick 7, the power output shaft correspondence of an engine is connected with a rotor blade 6.Hurry up
Hanging stick 7 is torn open by pin and the positioned in alignment of wing 2, and is fixedly connected with wing 2 by screw.
Wing 2 includes the first wing and the second wing, and connecting hole 10 is provided with fuselage 1, and button is provided with the first wing
Connective pole 9, the end of snapping connecting rod 9 is squash type insertion 11, and insertion connecting rod 8 is provided with the second wing 2, inserts connecting rod 8
End be concave gland 12, snapping connecting rod 9 and insertion connecting rod 8 be inserted in connecting hole 10, and in connecting hole 10
Snapping.Fuselage 1 be connected with the electronic circuit of the first wing and the second wing respectively by be arranged on fuselage 1, the first wing and
Electronic contact structure on second wing is completing.Pin is provided with the joint face of the first wing and the second wing and fuselage 1,
Fixing hole is provided with the joint face of fuselage 1, the first wing and the second wing are installed by pin with the positioned in alignment of fuselage 1.The
A Vertical Dynamic export structure is mounted under one wing and the second wing.
Afterbody power output structure includes engine and afterbody blade 5, and power output shaft and the afterbody blade 5 of engine are passed
Dynamic connection.
Unmanned plane also includes radome fairing 4, and radome fairing 4 is arranged on afterbody power output structure.
Carbon fiber honeycomb interlayer is provided with inside fuselage 1, wing 2 and empennage 3.It is strong in the structure for meeting whole unmanned plane
On the basis of degree and rigidity, accomplish maximum lightweight, effectively reduce the weight of aircraft itself, in lift-drag ratio not
In the case of change, the payload of aircraft has been correspondingly improved.
Unmanned plane in the utility model, taking off, land, and hovering process lift and before fly power by vertically moving
Power export structure is provided, and afterbody power output structure is not involved in work, and unmanned plane is by adjusting sending out for Vertical Dynamic export structure
Motivation rotating speed realizes the change of lift, so as to control attitude and the position of unmanned plane changing the rotating speed of rotor blade 6.Four
The two neighboring rotation direction in flight course of rotor blade 6 is contrary, therefore when unmanned plane balances flight, gyro effect
Should be cancelled with air force moment of torsion effect.When unmanned plane reaches certain height, need to enter cruise shape by floating state
When state, provided by afterbody power output structure and equal the thrust and lift for flying, four rotor blades 6 are in and quit work the stage.
Aircraft enters efficient cruising phase, during so as to effectively raising cruising radius and boat.
Effective combination that the utility model passes through outstanding wing state of flight and fixed-wing state of flight, can be by different flight
Pattern carries out in real time effectively conversion so that the mobility and flight efficiency of unmanned plane is effectively improved.
The decomposing state of the critical piece of unmanned plane is as shown in Fig. 2 including wing 2, fuselage 1, afterbody paddle, two Quick Release
Hanging stick 7 and four outstanding wing paddles, and each part places respectively packing, once need unmanned plane to take off, you can install at any time.
As shown in Figure 3 and Figure 5, the Quick Release connection between wing 2 and fuselage 1 is by snapping connection realization, by squash type
Insertion 11 is inserted in concave gland 12, the bullet of the stuck squash type of concave gland 12 insertion 11 of elastic conjunction
Property port, so as to carry out final fixation.
In the present embodiment, squash type insertion 11 is integrally formed with insertion connecting rod 8, and concave gland 12 connects with snapping
Bar 9 is integrally formed, and inserts the part of connecting rod 8 and snapping connecting rod 9 inside fuselage 1 and is fixed with glue.
Pin is provided with the joint face of the first wing and the second wing and fuselage 1, is provided with the joint face of fuselage 1 solid
Determine hole, the first wing and the second wing are installed by pin with the positioned in alignment of fuselage 1.By shop bolt be capable of achieving wing 2 with
Fuselage 1 is quickly positioned.
In the present embodiment, Quick Release hanging stick 7 is to carry out fast accurate by pin to align with the connection of wing 2, eventually through
The screw of one M8 is fixedly connected.
When carrying, by the individually placed overall fortune for being easy to whole unmanned plane structure of afterbody blade 5 and rotor blade 6
Defeated, this Quick Release, fast-assembling mode can avoid afterbody blade 5 and rotor blade 6 in transportation from being collided with by unnecessary,
So as to affect the aeroperformance of afterbody blade 5 and rotor blade 6, or the takeoff data for affecting aircraft.
Preferred embodiment of the present utility model is these are only, it is all in this practicality not to limit the utility model
Any modification, equivalent and improvement made within new spirit and principle etc., should be included in guarantor of the present utility model
In the range of shield.
Claims (10)
1. it is a kind of can VTOL fixed-wing unmanned plane, including fuselage, wing, empennage and afterbody power output structure are described
Afterbody power output structure is arranged on the tail end of the fuselage, and the wing is arranged on the fuselage both sides, and the empennage is installed
At the top of the fuselage tail end, it is characterised in that：Also include Vertical Dynamic export structure under the wings of an airplane is installed.
2. it is according to claim 1 it is a kind of can VTOL fixed-wing unmanned plane, it is characterised in that：The Vertical Dynamic
Export structure includes two engines, two rotor blades and Quick Release hanging sticks, and two engines are outstanding installed in the Quick Release
Inside the two ends of bar, the power output shaft correspondence of an engine is connected with a rotor blade.
3. it is according to claim 2 it is a kind of can VTOL fixed-wing unmanned plane, it is characterised in that：The Quick Release hanging stick
By pin and the wing positioned in alignment, and it is fixedly connected with the wing by screw.
4. it is according to claim 1 it is a kind of can VTOL fixed-wing unmanned plane, it is characterised in that：The wing includes
First wing and the second wing, are provided with connecting hole on the fuselage, snapping connecting rod, the button are provided with first wing
The end of connective pole is that squash type inserts head, and insertion connecting rod is provided with second wing, and the end of the insertion connecting rod is
Concave gland, the snapping connecting rod and the insertion connecting rod are inserted in the connecting hole, and in the connecting hole
Snapping.
5. it is according to claim 4 it is a kind of can VTOL fixed-wing unmanned plane, it is characterised in that：The fuselage difference
Be connected with the electronic circuit of first wing and second wing by be arranged on the fuselage, first wing and
Electronic contact structure on second wing is completing.
6. it is according to claim 4 it is a kind of can VTOL fixed-wing unmanned plane, it is characterised in that：First wing
Pin is provided with joint face of second wing with the fuselage, on the joint face of the fuselage fixing hole is provided with,
First wing and second wing are installed by pin with the fuselage positioned in alignment.
7. it is according to claim 4 it is a kind of can VTOL fixed-wing unmanned plane, it is characterised in that：First wing
With a Vertical Dynamic export structure is mounted under second wing.
8. it is according to claim 1 it is a kind of can VTOL fixed-wing unmanned plane, it is characterised in that：Afterbody power output
Structure includes engine and afterbody blade, and the power output shaft of the engine is connected with the afterbody blade.
9. it is according to claim 1 it is a kind of can VTOL fixed-wing unmanned plane, it is characterised in that：The unmanned plane is also
Including radome fairing, the radome fairing is arranged on the afterbody power output structure.
10. it is according to claim 1 it is a kind of can VTOL fixed-wing unmanned plane, it is characterised in that：The fuselage, institute
State and be provided with carbon fiber honeycomb interlayer inside wing and the empennage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621217002.7U CN206155789U (en) | 2016-11-11 | 2016-11-11 | But fixed wing uavs of VTOL |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621217002.7U CN206155789U (en) | 2016-11-11 | 2016-11-11 | But fixed wing uavs of VTOL |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206155789U true CN206155789U (en) | 2017-05-10 |
Family
ID=58658730
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621217002.7U Active CN206155789U (en) | 2016-11-11 | 2016-11-11 | But fixed wing uavs of VTOL |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206155789U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109720537A (en) * | 2018-10-26 | 2019-05-07 | 深圳市科卫泰实业发展有限公司 | A kind of combined type vertical take-off and landing drone easy to disassemble with vanning |
| CN110466750A (en) * | 2019-08-19 | 2019-11-19 | 西北工业大学 | A kind of Portable vertical landing scouting monitoring unmanned plane |
| CN113665785A (en) * | 2021-08-11 | 2021-11-19 | 西安羚控电子科技有限公司 | Hang up fixed wing unmanned aerial vehicle |
-
2016
- 2016-11-11 CN CN201621217002.7U patent/CN206155789U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109720537A (en) * | 2018-10-26 | 2019-05-07 | 深圳市科卫泰实业发展有限公司 | A kind of combined type vertical take-off and landing drone easy to disassemble with vanning |
| CN110466750A (en) * | 2019-08-19 | 2019-11-19 | 西北工业大学 | A kind of Portable vertical landing scouting monitoring unmanned plane |
| CN113665785A (en) * | 2021-08-11 | 2021-11-19 | 西安羚控电子科技有限公司 | Hang up fixed wing unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20211029 Address after: 430000 No. 100, Weihu Road, Shamao street, Hannan District, Wuhan City, Hubei Province Patentee after: Hubei Jili Taili Flying Car Co.,Ltd. Patentee after: ZHEJIANG GEELY HOLDING GROUP Co.,Ltd. Address before: 610000 room 1103, floor 11, building 1, No. 1800, middle section of Yizhou Avenue, high tech Zone, Chengdu, Sichuan Patentee before: SICHUAN AOSSCI TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230706 Address after: 610000 China (Sichuan) pilot Free Trade Zone, Chengdu Patentee after: SICHUAN AOSSCI TECHNOLOGY Co.,Ltd. Address before: 430000 No. 100, Weihu Road, Shamao street, Hannan District, Wuhan City, Hubei Province Patentee before: Hubei Jili Taili Flying Car Co.,Ltd. Patentee before: ZHEJIANG GEELY HOLDING GROUP Co.,Ltd. |
|
| TR01 | Transfer of patent right |