CN205837182U - A kind of aircraft rotor structure and aircraft - Google Patents
A kind of aircraft rotor structure and aircraft Download PDFInfo
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- CN205837182U CN205837182U CN201620589720.0U CN201620589720U CN205837182U CN 205837182 U CN205837182 U CN 205837182U CN 201620589720 U CN201620589720 U CN 201620589720U CN 205837182 U CN205837182 U CN 205837182U
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- rotor
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- fuselage
- predetermined angle
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Abstract
This utility model provides a kind of aircraft rotor structure and aircraft, relates to unmanned vehicle technical field.Described aircraft rotor structure includes fuselage, described fuselage has head end and machine tail end, described head end is provided with the first rotor, described machine tail end is provided with the second rotor, described first rotor and described second rotor are symmetrical arranged about the middle cross section of described fuselage, described first rotor tilts to described machine tail end, and the rotational plane of described first rotor be the first predetermined angle in plane described in described fuselage, described second rotor tilts to described head end, and the rotational plane of described second rotor be the second predetermined angle in plane described in described fuselage, described first predetermined angle and described second predetermined angle are equal.Aircraft rotor structure described in the utility model can reduce energy consumption, extends cruising time.
Description
Technical field
This utility model relates to unmanned vehicle technical field, particularly relates to a kind of aircraft rotor structure and aircraft.
Background technology
Along with development and the raising of people's living standard of science and technology, market occurs in that increasing novel product, nothing
People's aircraft is exactly one of which, and people may utilize aircraft and take photo by plane, monitoring, or carrying small-sized article etc..Wherein, many
Rotor craft has had become as study hotspot at present.Existing rotor wing unmanned aerial vehicle generally makes multiple rotor simultaneously to fuselage
Geometric center tilts certain angle, and about the centrosymmetry of fuselage, this mode can reach to make unmanned plane hovering more stable
Purpose, but due to multiple rotors all to centroclinal, rotor wing rotation produce power can in the horizontal direction with on vertical direction
Produce component, and the component in these horizontal directions some can cancel out each other, now, aircraft is accomplished by strengthening rotor
Rotating speed is to maintain rotor in the power of vertical direction, it is ensured that it will not fall, thus causes so that energy consumption increases, and flying power drops
Low.
Utility model content
Embodiment of the present utility model provides a kind of aircraft rotor structure and aircraft, can reduce energy consumption, extends continuation of the journey
Time.
For reaching above-mentioned purpose, embodiment of the present utility model adopts the following technical scheme that
This utility model provides a kind of aircraft rotor structure, and including fuselage, described fuselage has head end and machine tail end,
Described head end is provided with the first rotor, described machine tail end be provided with the second rotor, described first rotor and described second rotor about
The middle cross section of described fuselage is symmetrical arranged, and described first rotor tilts to described machine tail end, and described first rotor turn
Dynamic plane be the first predetermined angle in plane described in described fuselage, described second rotor tilts to described head end, and described
It is the second predetermined angle in plane described in the rotational plane of the second rotor and described fuselage, described first predetermined angle and described the
Two predetermined angles are equal.
Preferably, described first predetermined angle and described second predetermined angle are 15 °.
Further, described head end is provided with multiple described first rotor, and described machine tail end is provided with multiple described second rotation
The wing, multiple described first rotors are symmetrical arranged about the middle cross section of described fuselage with multiple described second rotors.
Further, described first rotor and described second rotor all have two.
This utility model also provides for a kind of aircraft, including above-mentioned aircraft rotor structure.
Aircraft rotor structure described in the utility model and aircraft, when aircraft hovers, described fuselage institute
Being horizontal plane in plane, described first rotor and described second rotor all can produce dividing of the middle cross section to described fuselage
Power, and cancelling each other, thus ensure described aircraft will not deflection, reach the purpose making unmanned plane more stable.Work as unmanned plane
During advance, described fuselage turns forward the first predetermined angular so that the first rotor is the level of state, now, and described first rotor
Only produce lift vertically upward, make lift maximize.Described second rotor increases with the angle of horizontal plane, produces a level
Thrust forward and a lift vertically upward, owing to the most described first rotor does not the most produce horizontal thrust, therefore, institute
The horizontal thrust stating the second rotor generation will not be cancelled, and can realize maximizing, thus described unmanned plane can be promoted to advance.Make institute
State the principle of unmanned plane retrogressing ibid.Simultaneously as the unmanned plane most of the time enter the most before execution or setback, thus can
Effectively reduce energy consumption, extend cruising time.
Accompanying drawing explanation
In order to be illustrated more clearly that this utility model embodiment or technical scheme of the prior art, below will be to embodiment
Or the required accompanying drawing used is briefly described in description of the prior art, it should be apparent that, the accompanying drawing in describing below is only
It is embodiments more of the present utility model, for those of ordinary skill in the art, in the premise not paying creative work
Under, it is also possible to other accompanying drawing is obtained according to these accompanying drawings.
The schematic diagram of the aircraft rotor structure that Fig. 1 provides for this utility model.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of this utility model rather than whole
Embodiment.Based on the embodiment in this utility model, those of ordinary skill in the art are not under making creative work premise
The every other embodiment obtained, broadly falls into the scope of this utility model protection.
In description of the present utility model, it is to be understood that term " " center ", " on ", D score, "front", "rear",
The orientation of the instruction such as "left", "right", " vertically ", " level ", " top ", " end ", " interior ", " outward " or position relationship are for based on accompanying drawing institute
The orientation shown or position relationship, be for only for ease of description this utility model and simplify description rather than instruction or hint indication
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
Novel restriction.
With reference to a specific embodiment of the aircraft rotor structure that Fig. 1, Fig. 1 provide for this utility model, described flight
Device rotor structure includes that fuselage 1, described fuselage 1 have head end 11 and machine tail end 12, and described head end 11 is provided with the first rotor
2, it is horizontal about the middle part of described fuselage 1 that described machine tail end 12 is provided with the second rotor 3, described first rotor 2 and described second rotor 3
Cross section a is symmetrical arranged, and described first rotor 2 tilts to described machine tail end 12, and the rotational plane of described first rotor 2 is with described
Fuselage 1 place plane is the first predetermined included angle A, and described second rotor 3 tilts to described head end 11, and described second rotor 3
Rotational plane and described fuselage 1 described in be the second predetermined included angle B at interplanar, described first predetermined included angle A and described second
Predetermined included angle B is equal.
Aircraft rotor structure described in the utility model and aircraft, when aircraft hovers, described fuselage 1 institute
Being horizontal plane in plane, described first rotor 2 and described second rotor 3 all can produce the middle cross section a's to described fuselage 1
Component, and cancelling each other, thus ensure described aircraft will not deflection, reach the purpose making unmanned plane more stable.When unmanned
When machine advances, described fuselage 1 turns forward the first predetermined angular so that the first rotor 2 is the level of state, now, and described first
Rotor 2 produces lift vertically upward, makes lift maximize, and described second rotor 3 increases with the angle of horizontal plane, produces one
Individual horizontal forward thrust and a lift vertically upward, owing to described first rotor 2 does not the most produce horizontal thrust, because of
This, the horizontal thrust that described second rotor 3 produces will not be cancelled, it is achieved maximize, thus described unmanned plane can be promoted to advance.
Make the principle that described unmanned plane retreats ibid.Simultaneously as the unmanned plane most of the time enter the most before execution or setback, from
And energy consumption can be effectively reduced, extend cruising time.
Described first predetermined included angle A and described second predetermined included angle B are all unsuitable excessive or too small, the most all can be 15 °.
Described head end 11 is provided with multiple described first rotor 2, and described machine tail end 12 is provided with multiple described second rotor 3,
Multiple described first rotors 2 are symmetrical arranged about the middle cross section a of described fuselage 1 with multiple described second rotors 3, thus carry
High carrying capacity.
Described first rotor 2 and described second rotor 3 all have two, are improving while carrying capacity, make the structure will not
Excessively complicated, it is to avoid high cost.
This utility model embodiment also provides for a kind of aircraft, including above-mentioned aircraft rotor structure.Due in this enforcement
The aircraft rotor structure used in the aircraft of example and the aircraft of offer in each embodiment of above-mentioned aircraft rotor structure
Rotor structure is identical, and therefore the two can solve the problem that identical technical problem, and reaches identical Expected Results.
The above, detailed description of the invention the most of the present utility model, but protection domain of the present utility model does not limit to
In this, any those familiar with the art, in the technical scope that this utility model discloses, can readily occur in change
Or replace, all should contain within protection domain of the present utility model.Therefore, protection domain of the present utility model should be with described power
The protection domain that profit requires is as the criterion.
Claims (5)
1. an aircraft rotor structure, including fuselage, described fuselage has head end and machine tail end, and described head end is provided with
One rotor, it is horizontal about the middle part of described fuselage that described machine tail end is provided with the second rotor, described first rotor and described second rotor
Cross section is symmetrical arranged, it is characterised in that described first rotor tilts to described machine tail end, and the rotational plane of described first rotor
Being the first predetermined angle with described fuselage place plane, described second rotor tilts to described head end, and described second rotor
Rotational plane and described fuselage described in be the second predetermined angle at interplanar, described first predetermined angle and described second makes a reservation for
Angle is equal.
Aircraft rotor structure the most according to claim 1, it is characterised in that described first predetermined angle and described second
Predetermined angle is 15 °.
Aircraft rotor structure the most according to claim 1 and 2, it is characterised in that described head end is provided with multiple described
First rotor, described machine tail end is provided with multiple described second rotor, and multiple described first rotors close with multiple described second rotors
Middle cross section in described fuselage is symmetrical arranged.
Aircraft rotor structure the most according to claim 3, it is characterised in that described first rotor and described second rotor
All there are two.
5. an aircraft, including aircraft rotor structure described in any one of claim 1-4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620589720.0U CN205837182U (en) | 2016-06-15 | 2016-06-15 | A kind of aircraft rotor structure and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620589720.0U CN205837182U (en) | 2016-06-15 | 2016-06-15 | A kind of aircraft rotor structure and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205837182U true CN205837182U (en) | 2016-12-28 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620589720.0U Expired - Fee Related CN205837182U (en) | 2016-06-15 | 2016-06-15 | A kind of aircraft rotor structure and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205837182U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525643A (en) * | 2019-09-18 | 2019-12-03 | 深圳飞马机器人科技有限公司 | A kind of vertical take-off and landing drone and its manufacturing method |
| CN113232871A (en) * | 2021-04-14 | 2021-08-10 | 沃飞长空科技(成都)有限公司 | A vaulting pole and aircraft for installing rotor |
| WO2023201639A1 (en) * | 2022-04-21 | 2023-10-26 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
-
2016
- 2016-06-15 CN CN201620589720.0U patent/CN205837182U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110525643A (en) * | 2019-09-18 | 2019-12-03 | 深圳飞马机器人科技有限公司 | A kind of vertical take-off and landing drone and its manufacturing method |
| CN113232871A (en) * | 2021-04-14 | 2021-08-10 | 沃飞长空科技(成都)有限公司 | A vaulting pole and aircraft for installing rotor |
| WO2023201639A1 (en) * | 2022-04-21 | 2023-10-26 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161228 Termination date: 20190615 |