CN106114815B - Graded-adjustable aircraft horn and aircraft - Google Patents
Graded-adjustable aircraft horn and aircraft Download PDFInfo
- Publication number
- CN106114815B CN106114815B CN201610601326.9A CN201610601326A CN106114815B CN 106114815 B CN106114815 B CN 106114815B CN 201610601326 A CN201610601326 A CN 201610601326A CN 106114815 B CN106114815 B CN 106114815B
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- Prior art keywords
- aircraft
- horn
- link
- aircraft horn
- adjustable
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- 230000005540 biological transmission Effects 0.000 claims abstract description 11
- 230000008602 contraction Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000003416 augmentation 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
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- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
- Details Of Aerials (AREA)
Abstract
The invention discloses an aircraft horn capable of being adjusted in a grading manner and an aircraft. The hierarchically adjustable aircraft horn of the invention comprises: the device comprises a central transmission mechanism, a plurality of first connecting rods, a plurality of second connecting rods and a plurality of movable arms; wherein the central transmission mechanism comprises a plurality of arms uniformly arranged around a center, each arm being pivotally connected to a respective first link and each first link being pivotally connected to a respective second link; each second link is mounted into a respective living arm.
Description
Technical Field
The invention relates to the field of aircraft design, in particular to an aircraft horn capable of being adjusted in a grading manner and an aircraft comprising the aircraft horn.
Background
Currently, in multi-axis aircrafts popular in the market, the supporting arms of the propellers are all of fixed structures, and only the flight parameters can be adjusted by means of the control unit, so that a means for controlling the flight adjustment by the appearance is absent.
Under the different demands on comprehensive performances such as operability, stability and sensitivity, an external mechanism which can be automatically adjusted according to the demands of clients at any time is designed for the flight requirement, so that the aircraft can better adapt to the working environment.
The control of the four-axis aircraft mainly uses lifting force generated by the four axes, and when the four axes are close to the center, the sensitivity of the whole machine control is higher. When the four shafts are far away from the center, the stability of the whole machine control is higher. Therefore, the flying performance can be adjusted by changing the shape structure by changing the distance between the four shafts and the center.
Currently, the regulation of aircrafts appearing on the market is carried out by adopting a flight controller, and the implementation means is single. Professional parametrics generally adjust the PID value (AVCS parameter) of the aircraft to adjust the stability of the maneuver, and adjust the parameters of the fly-control stability augmentation mode to adjust the relative stability of the fly. However, the flight control parameter adjustment belongs to the professional field range, is not suitable for new hand operation, and is very complicated to adjust. For general operators, it is difficult to self-adjust parameters of the aircraft, and various flight risks are liable to occur.
Accordingly, those skilled in the art have been working on developing a scalable aircraft horn that is easy to operate and simple to adjust, suitable for various personnel operations.
Disclosure of Invention
In view of the above-mentioned drawbacks of the prior art, an object of the present invention is to provide an aircraft horn which is easy to operate and simple to adjust, and is suitable for various personnel to operate, and an aircraft comprising the aircraft horn.
To achieve the above object, the present invention provides a hierarchically adjustable aircraft horn comprising: the device comprises a central transmission mechanism, a plurality of first connecting rods, a plurality of second connecting rods and a plurality of movable arms; wherein the central transmission mechanism comprises a plurality of arms uniformly arranged around a center, each arm being pivotally connected to a respective first link and each first link being pivotally connected to a respective second link; each second link is mounted into a respective living arm.
Preferably, each arm is pivotally connected to a respective first link by a screw.
Preferably, each first link is pivotally connected to a respective second link by a screw.
Preferably, each second link is mounted into the respective living arm by a screw.
Preferably, the hierarchically adjustable aircraft horn is used for a four-axis aircraft.
Preferably, the central transmission mechanism comprises four arms.
Preferably, the hierarchically adjustable aircraft horn further comprises an outer shell.
To achieve the above object, the present invention also provides an aircraft comprising the hierarchically adjustable aircraft horn.
In the invention, the element connecting structure of each support arm forms a contracted state and an expanded state by the pivotal connection between the support arm and the first connecting rod and the pivotal connection between the first connecting rod and the second connecting rod, and the contraction degree of the contracted state can be continuously adjusted. Moreover, the control and adjustment mode of the aircraft horn which can be adjusted in a grading way is simple and convenient to operate; the cost of the adjusting and controlling mechanism is low; and can realize that many rotors change simultaneously, stability is good.
The conception, specific structure, and technical effects of the present invention will be further described with reference to the accompanying drawings to fully understand the objects, features, and effects of the present invention.
Drawings
Fig. 1 is a schematic illustration of a contracted state of a hierarchically adjustable aircraft horn according to a preferred embodiment of the invention.
Fig. 2 is a schematic view of a hierarchically adjustable aircraft horn mounted in a housing in a contracted state according to a preferred embodiment of the invention.
Fig. 3 is a schematic view of the deployment state of a hierarchically adjustable aircraft horn according to a preferred embodiment of the invention.
Fig. 4 is a schematic view of a hierarchically adjustable aircraft horn mounted in a housing in a deployed state according to a preferred embodiment of the invention.
It should be noted that the drawings are for illustrating the invention and are not to be construed as limiting the invention. Note that the drawings representing structures may not be drawn to scale. Also, in the drawings, the same or similar elements are denoted by the same or similar reference numerals.
Detailed Description
The invention changes the fixed cantilever supported by the motor of the aircraft into a telescopic structure. According to the flight requirement in reality, the adjustment of the flight performance is realized through the extension or shortening of the fixed cantilever.
Fig. 1 is a schematic view of a contracted state of a hierarchically adjustable aircraft horn according to a preferred embodiment of the invention, fig. 2 is a schematic view of a hierarchically adjustable aircraft horn according to a preferred embodiment of the invention mounted in a housing in a contracted state, fig. 3 is a schematic view of a deployed state of a hierarchically adjustable aircraft horn according to a preferred embodiment of the invention, and fig. 4 is a schematic view of a hierarchically adjustable aircraft horn according to a preferred embodiment of the invention mounted in a housing in a deployed state.
As shown in fig. 1 to 4, the hierarchically adjustable aircraft horn of the preferred embodiment of the present invention comprises: a central transmission mechanism 10, a plurality of first links 21, a plurality of second links 22, and a plurality of movable arms 23; wherein the central transmission mechanism 10 comprises a plurality of arms 11 uniformly arranged around a center, each arm 11 being pivotally connected to a respective first link 21, and each first link 21 being pivotally connected to a respective second link 22; each second link 22 is mounted into a respective living arm 23.
Specifically, each arm 11 is preferably pivotally connected to a corresponding first link 21 by a screw.
Specifically, each first link 21 is preferably pivotally connected to a corresponding second link 22 by a screw.
Specifically, each second link 22 is preferably mounted into a corresponding living arm 23 by a screw.
Preferably, the hierarchically adjustable aircraft horn is for a four-axis aircraft; correspondingly, the central transmission 10 comprises four arms 11.
Further preferably, as shown in fig. 2 and 4, the hierarchically adjustable aircraft horn of the preferred embodiment of the invention comprises a housing 100.
The fixed cantilever of the aircraft is changed into two sections, and the connecting rod is driven to execute linear reciprocating motion through the central transmission mechanism and is connected with the movable arm so as to push the movable arm of the aircraft to extend or retract simultaneously. Control may be performed in flight.
In the invention, the element connecting structure of each support arm forms a contracted state and an expanded state by the pivotal connection between the support arm and the first connecting rod and the pivotal connection between the first connecting rod and the second connecting rod, and the contraction degree of the contracted state can be continuously adjusted. Moreover, the control and adjustment mode of the aircraft horn which can be adjusted in a grading way is simple and convenient to operate; the cost of the adjusting and controlling mechanism is low; and can realize that many rotors change simultaneously, stability is good.
In a further preferred embodiment of the invention, the invention also provides an aircraft comprising the hierarchically adjustable aircraft horn.
While the foregoing description illustrates and describes the preferred embodiments of the present invention, as noted above, it is to be understood that the invention is not limited to the forms disclosed herein but is not to be construed as excluding other embodiments, and that various other combinations, modifications and environments are possible and may be made within the scope of the inventive concepts described herein, either by way of the foregoing teachings or by those of skill or knowledge of the relevant art. And that modifications and variations which do not depart from the spirit and scope of the invention are intended to be within the scope of the appended claims.
Claims (3)
1. A hierarchically adjustable aircraft horn, wherein the aircraft horn is for a four-axis aircraft, the aircraft horn comprising: the device comprises a central transmission mechanism, four first connecting rods, four second connecting rods and four movable arms; wherein the central transmission mechanism comprises four support arms which are uniformly arranged around the center, each support arm is connected with a corresponding first connecting rod in a pivotable manner through a screw, and each first connecting rod is connected with a corresponding second connecting rod in a pivotable manner through a screw; each second link is mounted into a respective living arm by a screw.
2. The hierarchically adjustable aircraft horn of claim 1, further comprising an outer shell.
3. An aircraft comprising a hierarchically adjustable aircraft horn according to any one of claims 1 to 2.
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 CN106114815A (en) | 2016-11-16 |
| CN106114815B true 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) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN107757913B (en) * | 2017-11-21 | 2020-01-07 | 歌尔科技有限公司 | Load control method and device based on unmanned aerial vehicle and unmanned aerial vehicle |
| 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 (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
| 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 |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102006019300B4 (en) * | 2006-04-26 | 2009-10-08 | Reinhardt, Gaby Traute | plane |
| US9573683B2 (en) * | 2014-04-28 | 2017-02-21 | Arch-Aerial, Llc | Collapsible multi-rotor UAV |
-
2016
- 2016-07-27 CN CN201610601326.9A patent/CN106114815B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106114815A (en) | 2016-11-16 |
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