CN106114815A - Adjustable in steps aircraft horn and aircraft - Google Patents
Adjustable in steps aircraft horn and aircraft Download PDFInfo
- Publication number
- CN106114815A CN106114815A CN201610601326.9A CN201610601326A CN106114815A CN 106114815 A CN106114815 A CN 106114815A CN 201610601326 A CN201610601326 A CN 201610601326A CN 106114815 A CN106114815 A CN 106114815A
- Authority
- CN
- China
- Prior art keywords
- connecting rod
- adjustable
- aircraft
- steps
- horn
- 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.)
- Granted
Links
- 230000008602 contraction Effects 0.000 description 8
- 238000010586 diagram Methods 0.000 description 7
- 230000005540 biological transmission Effects 0.000 description 4
- 241000208340 Araliaceae Species 0.000 description 2
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 2
- 235000003140 Panax quinquefolius Nutrition 0.000 description 2
- 235000008434 ginseng Nutrition 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- 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
Abstract
The invention discloses a kind of adjustable in steps aircraft horn and aircraft.The adjustable in steps aircraft horn of the present invention includes: central control mechanism, multiple first connecting rod, multiple second connecting rod and multiple arm alive；Wherein said central control mechanism includes the multiple support arms being evenly arranged around center, and each support arm connects corresponding first connecting rod in the way of pivotable, and each first connecting rod connects corresponding second connecting rod in the way of pivotable；Each second connecting rod is installed and is lived in arm to corresponding.
Description
Technical field
The present invention relates to field of flight vehicle design, particularly relate to a kind of adjustable in steps aircraft horn and comprise this
The aircraft of aircraft horn.
Background technology
At present, the most popular Multi-axis aircraft, the support arm of propeller is fixed structure, and control can only be relied on single
Unit's regulation flight parameter, lacks profile and controls the means of flight regulation.
Under the different demands to the combination property such as handling, stability, susceptiveness, designing a flight requirement can be at any time
According to customer demand, from the external agency of Row sum-equal matrix so that aircraft can preferably adapt to working environment.
The lifting force controlling mainly to be produced by four axles of four-axle aircraft, when four axles are close to centre distance, complete machine control
The sensitivity of system is higher.When four axles are away from centre distance, the stability that complete machine controls is higher.Thus, by change four axles with
The far and near distance at center, it is possible to achieve the mode changing contour structures carries out the regulation of flying quality.
Currently, the regulation of the aircraft occurred on the market, all use flight controller regulation, it is achieved means more single
One.Specialty adjusts ginseng personnel typically to adjust the pid value (AVCS parameter) of aircraft in order to adjust manipulation stability, and regulation flies control and increases steady
The parameter of pattern regulates the relative stability of flight.But, fly control and adjust ginseng to belong to professional field scope, be not suitable for new hand behaviour
Make, adjust extremely complex.For general operator, it is difficult to from the parameter of Row sum-equal matrix aircraft, and various flying easily occurs
Sector-style danger.
Therefore, those skilled in the art to be devoted to exploitation a kind of easily operated and adjust and be simply suitable for all kinds of personnel
The adjustable in steps aircraft horn of operation.
Summary of the invention
Because the drawbacks described above of prior art, the technical problem to be solved be to provide a kind of easily operated and
Adjust and be simply suitable for the adjustable in steps aircraft horn of all kinds of human users and comprise flying of this aircraft horn
Row device.
For achieving the above object, the invention provides a kind of adjustable in steps aircraft horn, including: central transmission machine
Structure, multiple first connecting rod, multiple second connecting rod and multiple arm alive；Wherein said central control mechanism includes being evenly arranged around center
Multiple support arms, each support arm connects corresponding first connecting rod in the way of pivotable, and each first connecting rod is with can
Pivotally supported mode connects corresponding second connecting rod；Each second connecting rod is installed and is lived in arm to corresponding.
Preferably, each support arm connects corresponding first connecting rod by screw by the way of pivotable.
Preferably, each first connecting rod connects corresponding second connecting rod by screw by the way of pivotable.
Preferably, each second connecting rod is installed by screw and is lived in arm to corresponding.
Preferably, described adjustable in steps aircraft horn is used for four-axle aircraft.
Preferably, described central control mechanism includes four support arms.
Preferably, described adjustable in steps aircraft horn also includes shell.
For achieving the above object, present invention also offers a kind of flight including described adjustable in steps aircraft horn
Device.
In the present invention, it is connected by pivoting between support arm with first connecting rod and first connecting rod and second connecting rod
Between pivot so that the component connection structure of each support arm forms contraction state and deployed condition, and contraction state
Shrinkage degree continuously adjustable.And, adjust mode letter according to the control of the adjustable in steps aircraft horn of the present invention
Easily, it is simple to operation；And regulate the low cost of the mechanism of control；And it is capable of many rotors to change, good stability simultaneously.
Below with reference to accompanying drawing, the technique effect of design, concrete structure and the generation of the present invention is described further, with
It is fully understood from the purpose of the present invention, feature and effect.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the contraction state of the most adjustable in steps aircraft horn.
Fig. 2 be the most adjustable in steps aircraft horn contraction state under be arranged on shell
Schematic diagram in body.
Fig. 3 is the deployed condition schematic diagram of the most adjustable in steps aircraft horn.
Fig. 4 be the most adjustable in steps aircraft horn deployed condition under be arranged on shell
Schematic diagram in body.
It should be noted that accompanying drawing is used for illustrating the present invention, and the unrestricted present invention.Note, represent that the accompanying drawing of structure can
Can be not necessarily drawn to scale.Further, in accompanying drawing, same or like element indicates same or like label.
Detailed description of the invention
The present invention, by the cantilever mounted of the motor support of aircraft, changes over the structure of scalability.According in reality
Flight requirement, elongating or shortening by cantilever mounted, it is achieved the adjustment of flying quality.
Fig. 1 is the schematic diagram of the contraction state of the most adjustable in steps aircraft horn,
Fig. 2 be the most adjustable in steps aircraft horn contraction state under showing in the housing is installed
Being intended to, Fig. 3 is the deployed condition schematic diagram of the most adjustable in steps aircraft horn, and Fig. 4 is
Under the deployed condition of the most adjustable in steps aircraft horn, schematic diagram in the housing is installed.
As shown in Figures 1 to 4, the adjustable in steps aircraft horn of the preferred embodiment of the present invention includes: central transmission
Mechanism 10, multiple first connecting rod 21, multiple second connecting rod 22 and multiple arm alive 23；Wherein said central control mechanism 10 include around
Multiple support arms 11 that center is evenly arranged, each support arm 11 connects corresponding first connecting rod 21 in the way of pivotable, and
And each first connecting rod 21 connects corresponding second connecting rod 22 in the way of pivotable；Each second connecting rod 22 is installed to phase
In the arm alive 23 answered.
And specifically, it is preferable to ground, each support arm 11 connects corresponding first connecting rod by screw by the way of pivotable
21。
And specifically, it is preferable to ground, each first connecting rod 21 connects corresponding second by screw by the way of pivotable
Connecting rod 22.
And specifically, it is preferable to ground, each second connecting rod 22 is installed by screw and is lived in arm 23 to corresponding.
Preferably, described adjustable in steps aircraft horn is used for four-axle aircraft；Correspondingly, described central transmission machine
Structure 10 includes four support arms 11.
It is further preferred that as shown in Figure 2 and Figure 4, the adjustable in steps aircraft horn of the preferred embodiment of the present invention
Including shell 100.
The cantilever mounted of aircraft changes to two-part, and by center transmission mechanism, drivening rod performs linear reciprocation fortune
Dynamic, connecting rod is connected with arm of living, to promote the arm alive of aircraft to carry out stretching or shrinking simultaneously.Can control in state of flight
System.
In the present invention, it is connected by pivoting between support arm with first connecting rod and first connecting rod and second connecting rod
Between pivot so that the component connection structure of each support arm forms contraction state and deployed condition, and contraction state
Shrinkage degree continuously adjustable.And, adjust mode letter according to the control of the adjustable in steps aircraft horn of the present invention
Easily, it is simple to operation；And regulate the low cost of the mechanism of control；And it is capable of many rotors to change, good stability simultaneously.
In another preferred embodiment of the present invention, present invention also offers one and include described adjustable in steps flight
The aircraft of device horn.
Described above illustrate and describes the preferred embodiments of the present invention, as previously mentioned, it should be understood that the present invention not office
Be limited to form disclosed herein, be not to be taken as the eliminating to other embodiments, and can be used for other combinations various, amendment and
Environment, and can be changed by above-mentioned teaching or the technology of association area or knowledge in invention contemplated scope described herein
Dynamic.And the change that those skilled in the art are carried out and change are without departing from the spirit and scope of the present invention, the most all should be appended by the present invention
In scope of the claims.
Claims (8)
1. an adjustable in steps aircraft horn, it is characterised in that including: central control mechanism, multiple first connecting rod, many
Individual second connecting rod and multiple arm alive；Wherein said central control mechanism includes the multiple support arms being evenly arranged around center, Mei Gezhi
Arm connects corresponding first connecting rod in the way of pivotable, and each first connecting rod connects in the way of pivotable
Corresponding second connecting rod；Each second connecting rod is installed and is lived in arm to corresponding.
Adjustable in steps aircraft horn the most as claimed in claim 1, it is characterised in that each support arm by screw with can
Pivotally supported mode connects corresponding first connecting rod.
Adjustable in steps aircraft horn the most as claimed in claim 1 or 2, it is characterised in that each first connecting rod passes through
Screw connects corresponding second connecting rod in the way of pivotable.
Adjustable in steps aircraft horn the most as claimed in claim 1 or 2, it is characterised in that each second connecting rod passes through
Screw is installed and is lived in arm to corresponding.
Adjustable in steps aircraft horn the most as claimed in claim 1 or 2, it is characterised in that described adjustable in steps
Aircraft horn is used for four-axle aircraft.
Adjustable in steps aircraft horn the most as claimed in claim 1 or 2, it is characterised in that described central control mechanism
Including four support arms.
Adjustable in steps aircraft horn the most as claimed in claim 1 or 2, it is characterised in that also include shell.
8. the aircraft of the adjustable in steps aircraft horn included as according to any one of claim 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610601326.9A CN106114815B (en) | 2016-07-27 | 2016-07-27 | Graded-adjustable aircraft horn and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610601326.9A CN106114815B (en) | 2016-07-27 | 2016-07-27 | Graded-adjustable aircraft horn and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106114815A true CN106114815A (en) | 2016-11-16 |
| CN106114815B CN106114815B (en) | 2024-02-27 |
Family
ID=57289760
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610601326.9A Active CN106114815B (en) | 2016-07-27 | 2016-07-27 | Graded-adjustable aircraft horn and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106114815B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106697271A (en) * | 2016-12-12 | 2017-05-24 | 成都育芽科技有限公司 | Adjustable multi-rotor-wing unmanned aerial vehicle |
| CN106828868A (en) * | 2017-02-08 | 2017-06-13 | 深圳市贝优通新能源技术开发有限公司 | A kind of changeable intelligent unmanned machine of flexible structure |
| CN107757913A (en) * | 2017-11-21 | 2018-03-06 | 歌尔科技有限公司 | Load-carrying control method, equipment and unmanned plane based on unmanned plane |
| US11518489B2 (en) * | 2019-03-26 | 2022-12-06 | Arizona Board Of Regents On Behalf Of Arizona State University | Systems and methods for an origami-inspired foldable quad-rotor |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090084890A1 (en) * | 2006-04-26 | 2009-04-02 | Gert Joachim Reinhardt | Aircraft |
| CN204056292U (en) * | 2014-06-19 | 2014-12-31 | 程京伟 | Closed type multi-rotor aerocraft |
| CN104260878A (en) * | 2014-10-16 | 2015-01-07 | 北京理工大学 | Four-rotor aircraft rack with capacity of automatic folding and spreading |
| CN104401484A (en) * | 2014-10-16 | 2015-03-11 | 北京理工大学 | Six-rotor aircraft rack capable of being folded and expanded automatically |
| CN105035317A (en) * | 2015-09-01 | 2015-11-11 | 湖南云顶智能科技有限公司 | Propeller folding and unfolding device for unmanned aerial vehicle |
| CN105035305A (en) * | 2015-09-01 | 2015-11-11 | 湖南云顶智能科技有限公司 | Propeller folding device for unmanned aerial vehicle |
| WO2015169279A1 (en) * | 2014-05-06 | 2015-11-12 | Fachhochschule Westküste Hochschule für Wirtschaft & Technik | Multifunctional boom with at least one drive, in particular for use in a multicopter system |
| US20150321755A1 (en) * | 2014-04-28 | 2015-11-12 | Arch Aerial, Llc | Collapsible multi-rotor uav |
| CN204802080U (en) * | 2015-05-29 | 2015-11-25 | 刘琳 | Intelligent Mobile Terminal and intelligent flight system with flight function |
| CN105460211A (en) * | 2015-12-30 | 2016-04-06 | 联想(北京)有限公司 | Flight device |
| CN205221097U (en) * | 2015-10-27 | 2016-05-11 | 镇江顺宇飞行器有限公司 | Can realize flexible six aircraft of folding |
| CN205293088U (en) * | 2015-11-05 | 2016-06-08 | 深圳零度智能飞行器有限公司 | Rotation type beta structure and foldable flying device |
| CN205854474U (en) * | 2016-07-27 | 2017-01-04 | 上海未来伙伴机器人有限公司 | Adjustable in steps aircraft horn and aircraft |
-
2016
- 2016-07-27 CN CN201610601326.9A patent/CN106114815B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090084890A1 (en) * | 2006-04-26 | 2009-04-02 | Gert Joachim Reinhardt | Aircraft |
| US20150321755A1 (en) * | 2014-04-28 | 2015-11-12 | Arch Aerial, Llc | Collapsible multi-rotor uav |
| WO2015169279A1 (en) * | 2014-05-06 | 2015-11-12 | Fachhochschule Westküste Hochschule für Wirtschaft & Technik | Multifunctional boom with at least one drive, in particular for use in a multicopter system |
| CN204056292U (en) * | 2014-06-19 | 2014-12-31 | 程京伟 | Closed type multi-rotor aerocraft |
| CN104401484A (en) * | 2014-10-16 | 2015-03-11 | 北京理工大学 | Six-rotor aircraft rack capable of being folded and expanded automatically |
| CN104260878A (en) * | 2014-10-16 | 2015-01-07 | 北京理工大学 | Four-rotor aircraft rack with capacity of automatic folding and spreading |
| CN204802080U (en) * | 2015-05-29 | 2015-11-25 | 刘琳 | Intelligent Mobile Terminal and intelligent flight system with flight function |
| CN105035305A (en) * | 2015-09-01 | 2015-11-11 | 湖南云顶智能科技有限公司 | Propeller folding device for unmanned aerial vehicle |
| CN105035317A (en) * | 2015-09-01 | 2015-11-11 | 湖南云顶智能科技有限公司 | Propeller folding and unfolding device for unmanned aerial vehicle |
| CN205221097U (en) * | 2015-10-27 | 2016-05-11 | 镇江顺宇飞行器有限公司 | Can realize flexible six aircraft of folding |
| CN205293088U (en) * | 2015-11-05 | 2016-06-08 | 深圳零度智能飞行器有限公司 | Rotation type beta structure and foldable flying device |
| CN105460211A (en) * | 2015-12-30 | 2016-04-06 | 联想(北京)有限公司 | Flight device |
| CN205854474U (en) * | 2016-07-27 | 2017-01-04 | 上海未来伙伴机器人有限公司 | Adjustable in steps aircraft horn and aircraft |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106697271A (en) * | 2016-12-12 | 2017-05-24 | 成都育芽科技有限公司 | Adjustable multi-rotor-wing unmanned aerial vehicle |
| CN106697271B (en) * | 2016-12-12 | 2019-05-14 | 贵州大鸟创新科技有限公司 | A kind of adjustable multi-rotor unmanned aerial vehicle |
| CN106828868A (en) * | 2017-02-08 | 2017-06-13 | 深圳市贝优通新能源技术开发有限公司 | A kind of changeable intelligent unmanned machine of flexible structure |
| CN106828868B (en) * | 2017-02-08 | 2019-05-14 | 广东省路桥建设发展有限公司 | A kind of changeable intelligent unmanned machine of flexible structure |
| CN107757913A (en) * | 2017-11-21 | 2018-03-06 | 歌尔科技有限公司 | Load-carrying control method, equipment and unmanned plane based on unmanned plane |
| US11518489B2 (en) * | 2019-03-26 | 2022-12-06 | Arizona Board Of Regents On Behalf Of Arizona State University | Systems and methods for an origami-inspired foldable quad-rotor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106114815B (en) | 2024-02-27 |
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