CN107097944A - Aircraft - Google Patents
Aircraft Download PDFInfo
- Publication number
- CN107097944A CN107097944A CN201710357282.4A CN201710357282A CN107097944A CN 107097944 A CN107097944 A CN 107097944A CN 201710357282 A CN201710357282 A CN 201710357282A CN 107097944 A CN107097944 A CN 107097944A
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- China
- Prior art keywords
- framework
- axle
- propeller
- main body
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The application provides a kind of aircraft, including：Main body；It is respectively arranged at the first propeller and the second propeller of direction of rotation conversely on the main body tow sides；Around the first framework of the main body, first framework is pivotally connected by first axle and the main body, to enable the main body to be overturn in a first direction relative to first framework；Around the second framework of first framework, second framework is pivotally connected by the second axle and first framework, to enable first framework to be overturn in a second direction relative to second framework；The first direction is different from the second direction.The aircraft that the application is provided has the twin screw rotated towards opposite direction being arranged in main body, and the moment of torsion that propeller is produced is overcome with this.And it is possible to the upset by main body relative to the first framework, and the first framework, relative to the upset of the second framework, control aircraft flies towards any direction.
Description
Technical field
The present embodiments relate to technical field of aerospace, more particularly to a kind of aircraft.
Background technology
With the development of science and technology, multi-rotor aerocraft applied in industry-by-industry field more and more extensively, therefore by
Numerous citizen and the favor of enterprise.
The rotor of Multi-axis aircraft is all that multiaxis is horizontally mounted in the market, can only in order to realize the translation of aircraft
The speed discrepancy by adjusting multiple rotors is reached, makes body to be flown with bottom surface in the posture of angle, so as to get level
The power in direction, realize aircraft forward, backward, to the left, to the right or around postures such as axis body rotations.But in the process of flight
In, if posture crosses the three-axis gyroscope overload (outranging) that conference is easily caused in flight control system.
In addition, existing multi-rotor aerocraft layout is chaotic, because it includes multiple sensors, circuit module, control
Module etc., therefore easily produce mutual electromagnetic interference between component, and then it is easily caused that aircraft is out of control, crash.
Accordingly, it would be desirable to provide again it is a kind of can either keep various complicated flight attitudes, can try one's best flight appearance again
State control module, drive module, actuated element etc. try one's best balanced arrangement to offset the aircraft of electromagnetic interference.
The content of the invention
In view of defect present in prior art, the present invention provides a kind of aircraft, including：
First framework；
It is arranged in first framework, and the first axle that two ends are pivotally connected with first framework respectively；
It is arranged at upper the first propeller and the second propeller of the first axle, first propeller and the second spiral
Oar can synchronously be overturn relative to first framework in a first direction under the drive of the first axle, and can mutually be supported
Racemization torque；
Around the second framework of first framework, second framework is pivoted by the second axle and first framework to be connected
Connect, to enable first framework to be overturn in a second direction relative to second framework；
The first direction is different from the second direction.
In certain embodiments of the present invention, described aircraft includes：
Main body；
First framework is pivotally connected by the first axle and the main body, with enable the main body relative to
First framework is overturn in a first direction；
The direction of rotation of first propeller and the second propeller is on the contrary, and be respectively arranged at the main body tow sides
On.
The aircraft that the present invention is provided has the twin screw rotated towards opposite direction being arranged in main body, with this gram
Take the moment of torsion of propeller generation.And it is possible to the upset by main body relative to the first framework, and the first framework is relative to
The upset of two frameworks, realizes any direction of propeller, and then control aircraft to be flown towards any direction.
In certain embodiments of the present invention, the first axle and second axle are arranged mutual vertically.
In certain embodiments of the present invention, described aircraft includes：
Be arranged on first framework for the first steering wheel for driving the first axle to rotate forward or backwards；
Be arranged on second framework for the second steering wheel for driving second axle to rotate forward or backwards.
The aircraft that the present invention is provided is the change by the vector propeller positioned at main center during flight,
Make aircraft occurred level location deflection.This gesture stability axle is arranged in the position of centre of gravity of the axle of fuselage three, and two vectors
Steering wheel can be installed according to arbitrary orientation, keep aircraft to be deflected in X and Y-axis by adjustment vector steering wheel.In other words, this hair
Bright power unit is set in the main body at center, and direction controlling unit is separately positioned on the first framework and the second framework
On, there is a certain distance between three, will not disturb each other.Therefore, the present invention is for existing aircraft
Structure is simpler, and flight efficiency is high, and fault-tolerant ability is high, and the existing aircraft of mixed dynamic control ratio is few, and safety coefficient is high.
In certain embodiments of the present invention, first framework has the madial wall towards the body side and position
Lateral wall in opposite side；First steering wheel is arranged on the lateral wall of first framework；One of second framework
The side away from first framework is divided to protrude to form the receiving portion for accommodating first steering wheel.
In certain embodiments of the present invention, first framework and second framework are annular.
In order that obtaining the aircraft of the invention provided has more succinct profile and compact result, especially first
One is devised between framework and the second framework is used to accommodate the receiving space of steering wheel, make it that no matter the first framework is relative to the
How two frameworks overturn, and steering wheel is all without as obstacle.
In certain embodiments of the present invention, the aircraft, can also include：
It is arranged on second framework and towards the base that extends of vertical direction of plane residing for second framework
Support.
In certain embodiments of the present invention, the base support has multiple and is evenly distributed in second frame
On frame, the end of multiple base supports is interconnected so as to form bearing end.
The base support of aircraft is used for all external equipment of carry, is also taken as the undercarriage of aircraft, while
It is the main load part of the aircraft.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the accompanying drawing used required in technology description to be briefly described, it should be apparent that, drawings in the following description are this hairs
Some bright embodiments, for those of ordinary skill in the art, on the premise of not paying creative work, can be with root
Other accompanying drawings are obtained according to these accompanying drawings.
The stereogram for the aircraft that Fig. 1 provides for an embodiment of the present invention；
Fig. 2 is the left view of the aircraft shown by Fig. 1；
Fig. 3 is the top view of the aircraft shown by Fig. 1；
Fig. 4 is the stereogram for the aircraft that the embodiment of the present invention two is provided；
Fig. 5 is the stereogram for the aircraft that the embodiment of the present invention three is provided.
Embodiment
To make the purpose, technical scheme and advantage of the embodiment of the present invention clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
A part of embodiment of the present invention, rather than whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
It should be noted that in the case where not conflicting, the embodiment in the present invention and the feature in embodiment can phases
Mutually combination.Describe the present invention in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
Embodiment 1
Shown in reference picture 1~3, the present invention provides a kind of aircraft, mainly includes main body 1, the first propeller 2, the second spiral shell
Revolve oar 3, the first framework 4 and the second framework 5.
Specifically, the first propeller 2 and the second propeller 3 are respectively arranged at the positive and negative both sides of main body 1, and their rotation
Turn in opposite direction, to overcome the moment of torsion produced by rotation.First framework 4 arranges that it passes through first axle 6 and main body 1 around main body 1
It is pivotally connected, so that obtaining main body 1 can in a first direction overturn relative to the first framework 4.Second framework 5 surrounds the first framework
4 arrangements (the second framework is located at the more lateral of main body relative to the first framework), the second framework 5 passes through the second axle 7 and the first framework 4
It is pivotally connected, to enable the first framework 4 to be overturn in a second direction relative to the second framework 5.Second direction is different from the
One direction.
The present invention some preferred embodiment in, first axle and 6 second axles 7 are arranged mutual vertically.Therefore,
One propeller 2 and the second propeller 3 can provide lift for the aircraft and realize horizontal deflection towards any direction.
In certain embodiments of the present invention, the aircraft also includes the first steering wheel 8 and the second steering wheel 9.First steering wheel 8
It is arranged on the first framework 4, it is used to drive first axle 6 to rotate forward or backwards, can be relative to the first frame so as to obtain main body 1
Frame 4 is overturn in a first direction.Second steering wheel 9 is arranged on the second framework 5, and it is used to drive the second axle 7 to revolve forward or backwards
Turn, to enable the first framework 4 to be overturn in a second direction relative to the second framework 5.
In order that obtaining, the Flight Vehicle Structure of the invention provided is compacter, and the first framework 4 has towards in the side of main body 1
Side wall and the lateral wall positioned at opposite side, the first steering wheel 8 are fixedly arranged on above-mentioned lateral wall.A part for second framework 5
Protruded away from the side of the first framework 4 to form the receiving portion 41 for accommodating the first steering wheel.Therefore, in the second framework 5
When being overturn relative to the first framework 1, above-mentioned receiving portion 41 can provide space for the first steering wheel 8.Set in the manner described above
Put, it is not necessary to form very big gap between the first framework 4 and the second framework 5, relative upset can also be completed.
First framework 4 and the second framework 5 can be designed as annular.In order to avoid the second axle 7 disturbs the phase of the first framework 4
Overturn for the second framework 5, the second axle 7 is designed as two sections and is arranged in the symmetric position of the first framework 4 by the present embodiment, respectively
It is pivotally connected the second framework 5.
In certain embodiments of the present invention, the aircraft also includes being arranged on the second framework 5 and towards second
The base support 10 that the vertical direction of plane residing for framework 5 is extended.Base support 10 has multiple and is evenly distributed in the
On two frameworks 5, the ends of multiple base supports 10 is connected with each other, moulded to form one, for all external of carry
Equipment.
Embodiment 2
As shown in figure 4, another aircraft that provides of the present invention, mainly include the first propeller 2, the second propeller 3, the
One framework 4, the second framework 5, the axle 7 of first axle 6 and second.
The present embodiment is different from the part of embodiment 1 and is that the aircraft does not include main body 1, the first propeller 2 and the second spiral shell
Rotation oar 3 is set directly in first axle 6, and the two is arranged in the same direction.
Specifically, first axle 6 is arranged in the first framework 4, and its two ends and two ends pivot with the first framework 4 connect respectively
Connect.First propeller 2 and the second propeller 3 are arranged in first axle 6, therefore, and the first propeller 2 and the second propeller 3 can
When first axle rotates, relative to the synchronous upset in a first direction of the first framework 5.First propeller 2 and the court of the second propeller 3
It is located at symmetrical position to same direction, and in first axle 6, the direction of rotation of the two conversely enables to rotation of cancelling out each other
Torque.
Second framework 5 surrounds the first framework 4, and the second framework 5 is pivotally connected by the second axle 7 and the first framework 4, to cause
First framework 4 can in a second direction be overturn relative to the second framework 5；The first direction is different from the second direction.
Embodiment 3
As shown in figure 5, another aircraft that provides of the present invention, mainly include the first propeller 2, the second propeller 3, the
One framework 4, the second framework 5, the axle 7 of first axle 6 and second.
The present embodiment is different from the part of embodiment 1 and is that the aircraft does not include main body 1, the first propeller 2 and the second spiral shell
Rotation oar 3 is set directly in first axle 6, the two reversed arrangement.
Specifically, first axle 6 is arranged in the first framework 4, and its two ends and two ends pivot with the first framework 4 connect respectively
Connect.First propeller 2 and the second propeller 3 are arranged in first axle 6, therefore, and the first propeller 2 and the second propeller 3 can
When first axle rotates, relative to the synchronous upset in a first direction of the first framework 5.First propeller 2 and the court of the second propeller 3
Round about, and in first axle 6 it is located at symmetrical position, the direction of rotation of the two conversely enables to rotation of cancelling out each other
Torque.
Second framework 5 surrounds the first framework 4, and the second framework 5 is pivotally connected by the second axle 7 and the first framework 4, to cause
First framework 4 can in a second direction be overturn relative to the second framework 5；The first direction is different from the second direction.
Finally it should be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although
The present invention is described in detail with reference to the foregoing embodiments, it will be understood by those within the art that：It still may be used
To be modified to the technical scheme described in foregoing embodiments, or equivalent substitution is carried out to which part technical characteristic；
And these modification or replace, do not make appropriate technical solution essence depart from various embodiments of the present invention technical scheme spirit and
Scope.
Claims (8)
1. aircraft, it is characterised in that including：
First framework；
It is arranged in first framework, and the first axle that two ends are pivotally connected with first framework respectively；
It is arranged at upper the first propeller and the second propeller of the first axle, first propeller and the second propeller energy
It is enough synchronously to be overturn in a first direction relative to first framework under the drive of the first axle, and the rotation that can cancel out each other
Torque；
Around the second framework of first framework, second framework is pivotally connected by the second axle and first framework,
To enable first framework to be overturn in a second direction relative to second framework；
The first direction is different from the second direction.
2. aircraft according to claim 1, it is characterised in that including：
Main body；
First framework is pivotally connected by the first axle and the main body, to enable the main body relative to described
First framework is overturn in a first direction；
The direction of rotation of first propeller and the second propeller is on the contrary, and be respectively arranged on the main body tow sides.
3. aircraft according to claim 1, it is characterised in that：
The first axle and second axle are arranged mutual vertically.
4. aircraft according to claim 1 or 2, it is characterised in that including：
Be arranged on first framework for the first steering wheel for driving the first axle to rotate forward or backwards；
Be arranged on second framework for the second steering wheel for driving second axle to rotate forward or backwards.
5. aircraft according to claim 4, it is characterised in that：
First framework has the madial wall and the lateral wall positioned at opposite side towards the body side；
First steering wheel is arranged on the lateral wall of first framework；
A part for second framework is protruded away from the side of first framework to be used to accommodate described first to be formed
The receiving portion of steering wheel.
6. aircraft according to claim 5, it is characterised in that：
First framework and second framework are annular.
7. aircraft according to claim 1, it is characterised in that including：
It is arranged on second framework and towards the base support that extends of vertical direction of plane residing for second framework.
8. aircraft according to claim 7, it is characterised in that：
The base support has multiple and is evenly distributed on second framework, the end phase of multiple base supports
Connect to form bearing end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710357282.4A CN107097944A (en) | 2017-05-19 | 2017-05-19 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710357282.4A CN107097944A (en) | 2017-05-19 | 2017-05-19 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107097944A true CN107097944A (en) | 2017-08-29 |
Family
ID=59669852
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710357282.4A Pending CN107097944A (en) | 2017-05-19 | 2017-05-19 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107097944A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229359A (en) * | 2018-09-25 | 2019-01-18 | 王君钰 | A kind of coaxial dual-rotor helicopter and its flight control method |
| CN111422343A (en) * | 2020-03-31 | 2020-07-17 | 山东大学 | Special unmanned aerial vehicle of half aviation transition electromagnetic detection receiving system |
| CN111645855A (en) * | 2020-05-28 | 2020-09-11 | 西南交通大学 | Diaxon module and use unmanned aerial vehicle of this subassembly |
| CN113022860A (en) * | 2021-05-24 | 2021-06-25 | 四川迅联达智能科技有限公司 | Electric control multifunctional differential course control system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2486448A (en) * | 2010-12-15 | 2012-06-20 | Alexander Glass | Tilting mechanism for aircraft propulsion system |
| CN105235897A (en) * | 2015-10-16 | 2016-01-13 | 华南理工大学 | Parallel-shaft quad-rotor aircraft with rotatable aircraft arm shafts |
| CN105835640A (en) * | 2016-03-28 | 2016-08-10 | 上海交通大学 | Three degree-of-freedom attitude control device, system and method |
| CN106428543A (en) * | 2016-11-11 | 2017-02-22 | 杨超峰 | Rotor control mechanism and dual-rotor unmanned plane |
| CN207045714U (en) * | 2017-05-19 | 2018-02-27 | 锐合防务技术（北京）有限公司 | Aircraft |
-
2017
- 2017-05-19 CN CN201710357282.4A patent/CN107097944A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2486448A (en) * | 2010-12-15 | 2012-06-20 | Alexander Glass | Tilting mechanism for aircraft propulsion system |
| CN105235897A (en) * | 2015-10-16 | 2016-01-13 | 华南理工大学 | Parallel-shaft quad-rotor aircraft with rotatable aircraft arm shafts |
| CN105835640A (en) * | 2016-03-28 | 2016-08-10 | 上海交通大学 | Three degree-of-freedom attitude control device, system and method |
| CN106428543A (en) * | 2016-11-11 | 2017-02-22 | 杨超峰 | Rotor control mechanism and dual-rotor unmanned plane |
| CN207045714U (en) * | 2017-05-19 | 2018-02-27 | 锐合防务技术（北京）有限公司 | Aircraft |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229359A (en) * | 2018-09-25 | 2019-01-18 | 王君钰 | A kind of coaxial dual-rotor helicopter and its flight control method |
| CN111422343A (en) * | 2020-03-31 | 2020-07-17 | 山东大学 | Special unmanned aerial vehicle of half aviation transition electromagnetic detection receiving system |
| CN111422343B (en) * | 2020-03-31 | 2021-08-27 | 山东大学 | Special unmanned aerial vehicle of half aviation transition electromagnetic detection receiving system |
| CN111645855A (en) * | 2020-05-28 | 2020-09-11 | 西南交通大学 | Diaxon module and use unmanned aerial vehicle of this subassembly |
| CN111645855B (en) * | 2020-05-28 | 2023-03-07 | 西南交通大学 | Diaxon module and use unmanned aerial vehicle of this subassembly |
| CN113022860A (en) * | 2021-05-24 | 2021-06-25 | 四川迅联达智能科技有限公司 | Electric control multifunctional differential course control system |
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Legal Events
| Date | Code | Title | Description |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20190731 Address after: 518054 Virtual University Park C505, No. 2 Sandao, Yuexing Street, Nanshan District, Shenzhen City, Guangdong Province Applicant after: Shenzhen Ruihe Aircraft Intelligent Equipment Co., Ltd. Address before: 100191 Beijing, Zhichun Road, College of International Building, No. 912,, 1 Applicant before: Sharp Defense Technology (Beijing) Co., Ltd. |
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170829 |