CN209535458U - A kind of unmanned plane based on multi-composite type dynamical system - Google Patents
A kind of unmanned plane based on multi-composite type dynamical system Download PDFInfo
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- CN209535458U CN209535458U CN201920123155.2U CN201920123155U CN209535458U CN 209535458 U CN209535458 U CN 209535458U CN 201920123155 U CN201920123155 U CN 201920123155U CN 209535458 U CN209535458 U CN 209535458U
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- nacelle
- dynamical system
- composite type
- unmanned plane
- propeller
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Abstract
The utility model discloses a kind of unmanned planes based on multi-composite type dynamical system, it includes fuselage, wing, empennage and wheel, there are two wing is set, it is respectively perpendicular on the both sides of fuselage, empennage is connected to the rear end of fuselage, wheel is connected to the lower end of fuselage, the front side of each wing connects multiple nacelles, the rear side of each wing connects a long cabin of power, front propeller is all connected on front side of each nacelle, the upper end in each long cabin of power is all connected with propeller, and lower end is all connected with lower propeller, and each nacelle is all connected with corresponding steering engine.The advantages of the utility model: when VTOL mode, nacelle vertically downward, provides lift needed for aircraft under the control of corresponding steering engine；When sliding race landing mode, nacelle is adjusted to horizontal facing forward, takes off after so that aircraft is reached certain speed by pulling force；When short take-off and landing mode, nacelle is adjusted to 45 ° obliquely, both provides forward pulling force or provides upward pulling force, realizes short take-off and landing.
Description
Technical field
The utility model relates to a kind of unmanned planes based on multi-composite type dynamical system, belong to air vehicle technique field.
Background technique
Unmanned plane on the market is mostly the combined moving Force system that VTOL adds tilting rotor, is had a disadvantage in that only
It can be carried out VTOL, subsequent reconvert mode is cruised, and single landing mode can not fully meet cruel outfield
Flying condition.
Utility model content
The technical problems to be solved in the utility model is to provide a kind of unmanned plane based on multi-composite type dynamical system,
The dynamical system can meet various takeoff conditions, such as VTOL, sliding race landing, short distance VTOL etc., in addition distribution
The redundancy design of formula power reinforces the security performance guarantee of aircraft.
The utility model is realized by following proposal: a kind of unmanned plane based on multi-composite type dynamical system comprising machine
Body, wing, empennage and wheel there are two the wing is set, are respectively perpendicular the right and left in the fuselage, the empennage connection
In the rear end of the fuselage, the wheel is connected to the lower end of the fuselage, and the front side of each wing connects multiple power
Nacelle, the rear side of each wing connect a long cabin of power, are all connected with front propeller on front side of each nacelle,
The upper end in each long cabin of the power is all connected with propeller, and lower end is all connected with lower propeller, and each nacelle connects
Connect corresponding steering engine.
The steering engine adjusts the direction of the nacelle.
The steering engine adjust the nacelle vertically downward or it is horizontal forward or 45 ° obliquely.
Corresponding motor is equipped in each nacelle and each long cabin of the power.
The upper propeller and the lower propeller it is oppositely oriented.
The front propeller is foldable propeller.
The rotation direction of the front propeller and wingtip vortex it is oppositely oriented.
The utility model has the following beneficial effects:
1, a kind of unmanned plane based on multi-composite type dynamical system of the utility model does not need runway, can be detached from place limit
System, can complex mountainous landing again.
2, lift resistance ratio can be improved in a kind of unmanned plane based on multi-composite type dynamical system of the utility model, extends endurance,
Flight energy consumption is reduced, while multiple groups distributed-power can satisfy Different Altitude flight and require；
3, a kind of unmanned plane based on multi-composite type dynamical system of the utility model provides starting power of hanging down, and is doing height above sea level
Area provides level cruise power；
4, for a kind of unmanned plane based on multi-composite type dynamical system of the utility model in VTOL mode, institute is dynamic
Nacelle vertically downward, provides lift needed for aircraft, is switching to cruise mode in the sky under the control of corresponding steering engine；It is run sliding
In landing mode, all nacelles are adjusted to horizontal facing forward, take off after so that aircraft is reached certain speed by pulling force；Short
Away from landing mode, all nacelles are adjusted to 45 ° obliquely, both provide forward pulling force or provide upward pulling force,
Realize short take-off and landing；
5, a kind of front propeller of the unmanned plane based on multi-composite type dynamical system of the utility model uses foldable
Propeller reduces the air drag under cruise mode；
6, a kind of unmanned plane based on multi-composite type dynamical system of the utility model is equipped with multiple nacelles and power is long
Cabin destroys the wingtip vortex that wing tip generates using the air-flow that the middle propeller of distributed-power generates, reduces induced drag, save consumption
Oil increases endurance, improves flying speed and then increases voyage.
7, a kind of unmanned plane redundancy design based on multi-composite type dynamical system of the utility model can be the safety of aircraft
It is a ensure is provided more.
Detailed description of the invention
Fig. 1 is a kind of overlooking structure diagram of the unmanned plane based on multi-composite type dynamical system of the utility model.
Fig. 2 is a kind of present invention looks up structural representation of the unmanned plane based on multi-composite type dynamical system of the utility model.
Fig. 3 is a kind of positive structure diagram of the unmanned plane based on multi-composite type dynamical system of the utility model.
In figure: 1 is fuselage, and 2 be wing, and 3 be empennage, and 4 be wheel, and 5 be nacelle, and 6 be the long cabin of power, and 7 be preceding spiral shell
Paddle is revolved, 8 be upper propeller, and 9 be lower propeller, and 10 be steering engine.
Specific embodiment
Below with reference to Fig. 1-3, the present invention will be further described, but scope of protection of the utility model is not limited in described
Hold.
Wherein identical components are presented with like reference characters.It should be noted that word used in the following description
Language "front", "rear", "left", "right", "up" and "down" refer to that the direction in attached drawing, word "inner" and "outside" refer respectively to court
To or far from geometric center of specific component direction, and attached drawing is all made of very simplified form and uses non-accurate ratio
Rate, only to convenient, lucidly aid illustration the utility model embodiment purpose.
For clarity, not describing whole features of practical embodiments, in the following description, it is not described in detail well known function
And structure, because they can make the utility model chaotic due to unnecessary details, it will be understood that in any practical embodiments
Exploitation in, it is necessary to make a large amount of implementation details to realize the specific objective of developer, such as according to related system or related quotient
The limitation of industry changes into another embodiment by one embodiment, additionally, it should think this development may be it is complicated and
It is time-consuming, but to those skilled in the art it is only routine work.
A kind of unmanned plane based on multi-composite type dynamical system comprising fuselage 1, wing 2, empennage 3 and wheel 4, wing 2
If there are two, it is respectively perpendicular the right and left in fuselage 1, empennage 3 is connected to the rear end of fuselage 1, and wheel 4 is connected to fuselage 1
Lower end, the front side of each wing 2 connect multiple nacelles 5, and the rear side of each wing 2 connects the long cabin 6, Mei Gedong of a power
The front side of power nacelle 5 is all connected with front propeller 7, and the upper end in each long cabin 6 of power is all connected with propeller 8, and lower end is all connected with down
Propeller 9, each nacelle 5 are all connected with corresponding steering engine 10.
The direction of 10 motivation of adjustment nacelle 5 of steering engine, the direction how steering engine 10 adjusts motivation of adjustment nacelle 5 is existing known
Technology, details are not described herein for internal structure, working principle and the course of work.
10 motivation of adjustment nacelle 5 of steering engine vertically downward or it is horizontal forward or 45 ° obliquely.
Corresponding motor is equipped in each nacelle 5 and the long cabin 6 of each power.
Upper propeller 8 and lower propeller 9 it is oppositely oriented.
Front propeller 7 is foldable propeller.
The rotation direction of front propeller 7 and wingtip vortex it is oppositely oriented.
When flight, in VTOL mode, all nacelles 5 are under the control of corresponding steering engine 10, vertically downward；?
Sliding to run in landing mode, all nacelles 5 are adjusted to horizontal facing forward；In short take-off and landing mode, all nacelles 5 are
It is adjusted to 45 ° obliquely.
Although having done more detailed elaboration to the technical solution of the utility model and having enumerated, it should be understood that for
For those skilled in the art, modifications to the embodiments described above may be made or uses equivalent alternative solution, this skill to this field
Be for art personnel it is clear that on the basis of without departing from the spirit of the present invention these modifications or improvements, belong to
In the range of the requires of the utility model protection.
Claims (7)
1. a kind of unmanned plane based on multi-composite type dynamical system comprising fuselage (1), wing (2), empennage (3) and wheel
(4), there are two the wing (2) sets, it is respectively perpendicular the right and left in the fuselage (1), the empennage (3) is connected to described
The rear end of fuselage (1), the wheel (4) are connected to the lower end of the fuselage (1), it is characterised in that: each wing (2)
Front side connects multiple nacelles (5), and the rear side of each wing (2) connects a long cabin of power (6), each power
It being all connected on front side of nacelle (5) front propeller (7), the upper end of each long cabin of power (6) is all connected with propeller (8), under
End is all connected with lower propeller (9), and each nacelle (5) is all connected with corresponding steering engine (10).
2. a kind of unmanned plane based on multi-composite type dynamical system according to claim 1, it is characterised in that: the steering engine
(10) direction of the nacelle (5) is adjusted.
3. a kind of unmanned plane based on multi-composite type dynamical system according to claim 2, it is characterised in that: the steering engine
(10) adjust the nacelle (5) vertically downward or it is horizontal forward or 45 ° obliquely.
4. a kind of unmanned plane based on multi-composite type dynamical system according to claim 1, it is characterised in that: each described
Corresponding motor is equipped in nacelle (5) and each long cabin of the power (6).
5. a kind of unmanned plane based on multi-composite type dynamical system according to claim 1, it is characterised in that: the upper spiral shell
Revolve the oppositely oriented of paddle (8) and the lower propeller (9).
6. a kind of unmanned plane based on multi-composite type dynamical system according to claim 1, it is characterised in that: the preceding spiral shell
Revolving paddle (7) is foldable propeller.
7. a kind of unmanned plane based on multi-composite type dynamical system according to claim 1, it is characterised in that: the preceding spiral shell
Revolve paddle (7) rotation direction and wingtip vortex it is oppositely oriented.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920123155.2U CN209535458U (en) | 2019-01-24 | 2019-01-24 | A kind of unmanned plane based on multi-composite type dynamical system |
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| CN201920123155.2U CN209535458U (en) | 2019-01-24 | 2019-01-24 | A kind of unmanned plane based on multi-composite type dynamical system |
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| CN209535458U true CN209535458U (en) | 2019-10-25 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573013A (en) * | 2019-01-24 | 2019-04-05 | 猎鸢科技(厦门)有限公司 | A kind of unmanned plane and its flying method based on multi-composite type dynamical system |
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2019
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109573013A (en) * | 2019-01-24 | 2019-04-05 | 猎鸢科技(厦门)有限公司 | A kind of unmanned plane and its flying method based on multi-composite type dynamical system |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220223 Address after: 361000 No. 66, Biyun Middle Road, Hongtang Town, Tong'an District, Xiamen City, Fujian Province (No. 5 plant) Patentee after: XIAMEN HAN'S EAGLE AVIATION TECHNOLOGY CO.,LTD. Address before: 361000 room 116, building B, talent entrepreneurship Park, No. 2002, Tongji Road, Tong'an District, Xiamen City, Fujian Province Patentee before: Kunlun Wing Technology (Xiamen) Co.,Ltd. |