CN206797726U - A kind of wing VUAV that verts using modular power - Google Patents
A kind of wing VUAV that verts using modular power Download PDFInfo
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- CN206797726U CN206797726U CN201720317367.5U CN201720317367U CN206797726U CN 206797726 U CN206797726 U CN 206797726U CN 201720317367 U CN201720317367 U CN 201720317367U CN 206797726 U CN206797726 U CN 206797726U
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- propeller power
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Abstract
It the utility model is related to unmanned plane field, there is provided a kind of wing VUAV that verts using modular power, including vert system, tailplane of main wing vert system, vertical tail；Main wing system of verting includes main wing and the first propeller power plant module, and tailplane system of verting includes tailplane and the second propeller power plant module；Main wing, tailplane use swept-back wing；First, second propeller power plant module is outer respectively to hang over main wing, on tailplane；Each corresponding one or more first propeller power plant modules of main wing；Each corresponding second propeller power plant module of tailplane；Second propeller power plant module is foldable.The beneficial effects of the utility model：Propeller power uses modularized design, main wing can 2 ~ 10 propeller power plant modules of carry, the unmanned plane of take-off weight seriation can be formed；VTOL, high aspect ratio fixed-wing layout, endurance are strong；Main wing and empennage design for swept-back wing, can avoid stall, have a smooth flight.
Description
Technical field
Unmanned air vehicle technique field is the utility model is related to, it is more particularly to a kind of vertically to be risen using the wing that verts of modular power
Unmanned plane drops.
Background technology
Traditional unmanned aerial vehicle design is all first given take-off weight, and design motivation system, transmission system, wing cloth accordingly
Office, particularly tilting rotor VUAV, when changing take-off weight, dynamical system must redesign.
Fig. 1 is that certain type verts the transmission mechanism of wing unmanned plane, by engine, clutch, deceleration belt, and preceding commutator, after
The composition such as commutator and four vertical commutators, mechanism are sufficiently complex.
Therefore, it is the inexorable trend of small-sized tilting rotor VUAV using modular dynamical system.
Utility model content
The purpose of this utility model is exactly overcome the deficiencies in the prior art, there is provided a kind of verting using modular power
Wing VUAV, propeller power use modularized design, main wing can 2 ~ 10 propeller power plant modules of carry, therefore
The unmanned plane product of take-off weight seriation can be formed.
The utility model uses the wing VUAV that verts of modular power, mainly solves problems with：
1st, the suitable fixed-wing totality aerodynamic arrangement of selection, it is adapted to modularized design.Power can be increased by modularization to fill
The extended mode put, increase the lift of aircraft, improve take-off weight；
2nd, the suitable wing of selection, it is adapted to the complicated air flow configuration of VTOL process.VUAV exists
Flat at a high speed to fly with vertical landing, the transfer process taken off, there is coupling in wing and prop-blast, and velocity interval changes
Greatly, it is necessary to which rational wing structure reduces air-flow separation, stall is avoided；
3rd, the suitable front and rear lift ratio of selection, realizes pose stabilization control.Realized and hovered by multiple modular powers.
To solve the above problems, the utility model uses following technical scheme：
A kind of wing VUAV that verts using modular power, including vert system, tailplane of main wing incline
Transfer from one department to another system, vertical tail；
Main wing system of verting includes main wing and the first propeller power plant module, and the tailplane system of verting includes
Tailplane and the second propeller power plant module；The main wing, tailplane are designed using swept-back wing；First propeller
Power plant module, the second propeller power plant module are outer respectively to hang over the main wing, on tailplane；
The main wing, tailplane are 2, each corresponding one or more first propeller power of the main wing
Module；Each corresponding second propeller power plant module of the tailplane；The second propeller power plant module is
Foldable design.
Further, the angle of sweep of the main wing is 10-45 °, and the angle of sweep of the tailplane is 45 °.
Further, the first propeller power plant module is 1-5.
Further, linked between the main wing, tailplane by internal synchronization mechanism, realization is synchronously verted.
Further, the first, second propeller power plant module is connected using independent motor gondola with wing,
The motor gondola is bolted on wing spar.
Further, the aspect ratio of wing is more than or equal to 10.
The beneficial effects of the utility model are：
1st, VTOL can be realized, reduces the requirement to landing site；Use high aspect ratio routine fixed-wing simultaneously
Layout, can obtain longer cruising time；
2nd, main wing and empennage all design for swept-back wing, stall can be avoided in the wing inclination change stage, after switching to fixed-wing
Moved after aerodynamic center, make aircraft flight steady；
3rd, propeller power uses modularized design, main wing can 2 ~ 10 propeller power plant modules of carry, therefore can be formed
The unmanned plane product of take-off weight seriation.
Brief description of the drawings
Fig. 1 show prior art unmanned plane dynamic transfer system figure.
Fig. 2 show a kind of rising for wing VUAV that verts using modular power of the utility model embodiment
Fly original state schematic diagram.
Fig. 3 show the wing structure schematic diagram that verts.
Fig. 4 show the utility model embodiment state of flight schematic diagram（Each main wing uses 1 modular propeller
Unit）.
Fig. 5 show the utility model embodiment state of flight schematic diagram（Each main wing uses 2 modular propellers
Unit）.
Fig. 6 show the utility model embodiment state of flight schematic diagram（Each main wing uses 3 modular propellers
Unit）.
Fig. 7 show the utility model embodiment state of flight schematic diagram（Each main wing uses 4 modular propellers
Unit）.
Fig. 8 show the utility model embodiment state of flight schematic diagram（Each main wing uses 5 modular propellers
Unit）.
Fig. 9 show propeller folded state schematic diagram.
Wherein：1- fuselages, 2- main wings, 3- tailplanes, 4- vertical tails, the first propellers of 51- power plant module, 52-
Two propeller power plant modules, 6- main wings tiliting axis, 7- tailplane tiliting axis.
Embodiment
The utility model specific embodiment is described in detail below in conjunction with specific accompanying drawing.It should be noted that following implementations
Example described in technical characteristic or technical characteristic combination be not construed as it is isolated, they can be mutually combined from
And reach superior technique effect.In the accompanying drawing of following embodiments, the identical label that each accompanying drawing occurs represents identical spy
Sign or part, can be applied in different embodiments.
The total arrangement of the utility model embodiment puts wing, the normal arrangement overall plan of rearmounted empennage, machine using height
The wing, empennage are respectively arranged multiple modularization propeller power, it is possible to provide upward lift and thrust forward, blade is foldable
Design, hangs on main wing and empennage outside square formula, and modular configuration can be achieved.
As illustrated in figs. 2 through 8, a kind of wing VUAV that verts using modular power, including main wing vert and are
System, tailplane vert system, vertical tail 4；
Main wing system of verting includes the propeller power plant module 51 of main wing 2 and first, and the tailplane verts system
Including the propeller power plant module 52 of tailplane 3 and second；The main wing 2, tailplane 3 are designed using swept-back wing；It is described
First propeller power plant module 51, the second propeller power plant module 52 are outer respectively to hang over the main wing 2, on tailplane 3；
The main wing 2, tailplane 3 are 2, each corresponding one or more first propellers of the main wing 2
Power plant module 51；Each corresponding second propeller power plant module 52 of the tailplane 3；Second propeller moves
Power module 52 is foldable design.
Preferably, the angle of sweep of the main wing 2 is 10-45 °, and the angle of sweep of the tailplane 3 is 45 °.
For the first propeller power plant module 51 according to being actually needed and can select, scope is 1-5.
Linked between the main wing 2, tailplane 3 by internal synchronization mechanism, realization is synchronously verted, and common change is verted
Angle.
The first, second propeller power plant module 51,52 can be connected using various ways with wing, for example can be used only
Vertical motor gondola is connected with wing, and the motor gondola is bolted on wing spar.The connected mode is not
Limitation as the application.
Unmanned plane uses high aspect ratio, and the aspect ratio of wing reaches more than 10.
When Fig. 2 is using 3 first 51,1 the second propeller power plant modules 52 of propeller power plant module, the utility model
Embodiment unmanned plane takes off original state schematic diagram.
When Fig. 4-8 is respectively using 1-5 first 51,1 the second propeller power plant modules 52 of propeller power plant module, this
Utility model embodiment unmanned plane during flying view, under regular flight condition, the spiral shell of the second propeller power plant module 52
Rotation oar is in folded state.
Fig. 9 is that propeller is in folded state schematic diagram.
The beneficial effects of the utility model are：
1st, VTOL can be realized, reduces the requirement to landing site.Use high aspect ratio routine fixed-wing simultaneously
Layout, can obtain longer cruising time；
2nd, main wing and empennage all design for swept-back wing, stall can be avoided in the wing inclination change stage, after switching to fixed-wing
Moved after aerodynamic center, make aircraft flight steady；
3rd, propeller power uses modularized design, main wing can 2 ~ 10 propeller power plant modules of carry, therefore can be formed
The unmanned plane product of take-off weight seriation.
Although having been presented for several embodiments of the present utility model herein, those skilled in the art should manage
Solution, in the case where not departing from the utility model spirit, can be changed to the embodiments herein.Above-described embodiment simply shows
Example property, restriction that should not using the embodiments herein as the utility model interest field.
Claims (6)
1. a kind of wing VUAV that verts using modular power, it is characterised in that verted system, water including main wing
The horizontal tail wing verts system, vertical tail；
Main wing system of verting includes main wing and the first propeller power plant module, and tailplane system of verting includes level
Empennage and the second propeller power plant module；The main wing, tailplane use swept-back wing；The first propeller power mould
Block, the second propeller power plant module are outer respectively to hang over the main wing, on tailplane；
The main wing, tailplane are 2, each corresponding one or more first propeller power moulds of the main wing
Block；Each corresponding second propeller power plant module of the tailplane；The second propeller power plant module is can
Fold.
2. unmanned plane as claimed in claim 1, it is characterised in that the angle of sweep of the main wing is 10-45 °, the horizontal tail
The angle of sweep of the wing is 45 °.
3. unmanned plane as claimed in claim 1, it is characterised in that the first propeller power plant module is 1-5.
4. the unmanned plane as described in claim any one of 1-3, it is characterised in that by interior between the main wing, tailplane
Portion's lazy-tongs linkage, realization are synchronously verted.
5. the unmanned plane as described in claim any one of 1-3, it is characterised in that the first, second propeller power plant module
It is connected using independent motor gondola with wing, the motor gondola is bolted on wing spar.
6. the unmanned plane as described in claim any one of 1-3, it is characterised in that the aspect ratio of wing is more than or equal to 10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720317367.5U CN206797726U (en) | 2017-03-29 | 2017-03-29 | A kind of wing VUAV that verts using modular power |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720317367.5U CN206797726U (en) | 2017-03-29 | 2017-03-29 | A kind of wing VUAV that verts using modular power |
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| CN206797726U true CN206797726U (en) | 2017-12-26 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106986015A (en) * | 2017-03-29 | 2017-07-28 | 北京华信智航科技有限公司 | A kind of wing VUAV that verts of use modular power |
| CN110356547A (en) * | 2018-01-29 | 2019-10-22 | 田瑜 | The aerial unmanned plane of VTOL fixed-wing with replaceable cabin |
| DE102018116168A1 (en) | 2018-07-04 | 2020-01-09 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | aircraft |
| DE102018116154A1 (en) | 2018-07-04 | 2020-01-09 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | aircraft |
-
2017
- 2017-03-29 CN CN201720317367.5U patent/CN206797726U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106986015A (en) * | 2017-03-29 | 2017-07-28 | 北京华信智航科技有限公司 | A kind of wing VUAV that verts of use modular power |
| CN110356547A (en) * | 2018-01-29 | 2019-10-22 | 田瑜 | The aerial unmanned plane of VTOL fixed-wing with replaceable cabin |
| CN110356547B (en) * | 2018-01-29 | 2024-04-05 | 上海峰飞航空科技有限公司 | VTOL fixed wing aerial unmanned aerial vehicle with interchangeable cabins |
| DE102018116168A1 (en) | 2018-07-04 | 2020-01-09 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | aircraft |
| DE102018116154A1 (en) | 2018-07-04 | 2020-01-09 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | aircraft |
| DE102018116154B4 (en) | 2018-07-04 | 2022-09-01 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | aircraft |
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