CN107472516A - The total distance control apparatus of helicopter and helicopter and application - Google Patents
The total distance control apparatus of helicopter and helicopter and application Download PDFInfo
- Publication number
- CN107472516A CN107472516A CN201710630833.XA CN201710630833A CN107472516A CN 107472516 A CN107472516 A CN 107472516A CN 201710630833 A CN201710630833 A CN 201710630833A CN 107472516 A CN107472516 A CN 107472516A
- Authority
- CN
- China
- Prior art keywords
- helicopter
- control apparatus
- total distance
- distance control
- support tube
- 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
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
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
- B64C27/605—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of total distance control apparatus of helicopter, including being fixedly installed on support tube lower end and the base immediately below pitch, it is symmetrically disposed in the linear drives portion that support tube both sides and lower end are hinged with described base, the sliding block that in the support tube described in being arranged on and both ends are connected with described linear drives part can be slided up and down to, described sliding block is fixedly connected with pitch.The total distance control apparatus of helicopter of the present invention is arranged on immediately below pitch, by the device can realize to helicopter always away from control.Its suitability is strong, simple in construction firm, easy for installation, is easy to replicate and is adapted to, be rationally distributed, being suitable for shaking big installation environment on helicopter, can effectively improve unmanned aerial vehicle (UAV) control precision, ensures the operation of unmanned plane and safe to use.
Description
Technical field
The present invention relates to Helicopter Technology field, more particularly to a kind of total distance control apparatus of helicopter and helicopter.
Background technology
With the development of science and technology, application of the unmanned plane in fields such as agricultural plant protection, electric stringing, forest fire protections is more next
More popularize.Wherein, multi-rotor unmanned aerial vehicle has occupied larger proportion, but more rotors in unmanned plane field with the handling of its stabilization
Unmanned plane is usually electronic, and load-carrying small cruising time is short to be difficult to meet the needs of market development.Market is grown to heavy－duty continues a journey
The desirability of the multi-rotor unmanned aerial vehicle of time improves day by day.Heavy－duty length continuation of the journey multi-rotor unmanned aerial vehicle and small-sized more rotors
The dynamics of unmanned plane is identical, only motor need to be provided to power is replaced with engine and provide power.
A kind of common replacing means are to use an oil to move a rotor of the engine as more rotors, when so doing just not
Need the feathering characteristic of helicopter, it is only necessary to can control it always away from change.The motor of in the market provides power
The depopulated helicopter overwhelming majority can cyclic pitch, from resource for be a kind of waste, both wasted steering wheel cost structure
Cost more controls in need, it is impossible to the dynamic helicopter of adaptation oil very well.
The content of the invention
In view of the technical drawbacks of the prior art, it is an object of the present invention to provide a kind of helicopter always fills away from control
Put.
Inexpensive can simply it be controlled in view of the technical drawbacks of the prior art, it is an object of the present invention to provide a kind of
Helicopter.
Technical scheme is used by realize the purpose of the present invention：
A kind of total distance control apparatus of helicopter, including it is fixedly installed on support tube lower end and the bottom immediately below pitch
Seat, the linear drives portion that support tube both sides and lower end are hinged with described base is symmetrically disposed in, setting can be slided up and down to
In described support tube and both ends and the sliding block of described linear drives part drive connection, described sliding block are consolidated with pitch
Fixed connection.
Described linear drives portion is straight line steering wheel.
Described sliding block coordinates with the upward-downward translation in described support tube with described support ligament.
Also include linkage board, described linkage board center is be hinged with described sliding block and can deflect up and down, described linkage
The both ends of plate are hinged with described linear drives component upper ends.
Formed with groove therein is contained by described linkage board is embedding, described linkage board exists for described slider bottom or top
The deflection in predetermined angular is carried out in described groove.
The actuating length in described linear drives portion corresponds to propeller conversion range of angle of attack as 0 ° -9 °.
Described slider top is provided with three support bars, and described support bar lower end is fixedly connected with a slide block, upper end with
Pitch is hinged.
A kind of helicopter with the described total distance control apparatus of helicopter, described helicopter is multirotor helicopter,
Each or at least part rotor is correspondingly arranged the dynamic helicopter of oil and the total distance control apparatus of described helicopter.
A kind of application of described total distance control apparatus of helicopter after electric engine is changed to the dynamic engine of oil.
Compared with prior art, the beneficial effects of the invention are as follows：
The total distance control apparatus of helicopter of the present invention is arranged on immediately below pitch, can be realized by the device to going straight up to
Machine always away from control.Its suitability is strong, simple in construction firm, easy for installation, is easy to replicate and is adapted to, be rationally distributed, being suitable for
Big installation environment is shaken on helicopter, unmanned aerial vehicle (UAV) control precision can be effectively improved, ensures the operation of unmanned plane and safe to use.
Brief description of the drawings
Fig. 1 is the total distance control apparatus structural representation of helicopter of the present invention,
Fig. 2 is the schematic side view of the total distance control apparatus of helicopter of the present invention.
Embodiment
The present invention is described in further detail below in conjunction with the drawings and specific embodiments.It is it should be appreciated that described herein
Specific embodiment only to explain the present invention, be not intended to limit the present invention.
As illustrated, the total distance control apparatus of helicopter of the present invention includes the base 1 for being fixedly installed on the lower end of support tube 6,
Such as, base sheath is connected below the support tube of helicopter by riveting method and support tube, be symmetrically disposed in base both sides and
Two linear drives portions that lower end and described base are hinged, described two linear drives portion Synchronization Controls are to realize that push-and-pull is moved
Make, the sliding block that in the support tube described in being arranged on and both ends are connected with described linear drives part can be slided up and down to,
Described sliding block is fixedly connected with pitch.Wherein, support tube is usually a part for helicopter body, is enclosed on the outside of pitch
And along the axially extending setting of pitch, for protecting pitch and bending moment pull bar, need to be installed to if the not main stay tube
On helicopter.The actuating length in described linear drives portion corresponds to propeller conversion range of angle of attack as 0 ° -9 °.
It is more more reliable than one using two linear drives parts, more saved than two or more, symmetrical, layout
Rationally.From linear drives part, as straight line steering wheel is laid out than rocking arm steering wheel more compact, space is more saved, it is more easy to control.
Wherein, described linear drives portion is on the outside of described support tube, certainly, also can be by changing the shape of support tube
The straight line steering wheel is assemblied in support tube by shape.Straight line steering wheel is the existing matured product of in the market, can be moved with output linearity,
So that control is more accurate.Using straight line servos control helicopter always away from change, control is simple, and steadily, path increment is big.
The total distance control apparatus of helicopter of the present invention is arranged on immediately below pitch, can be realized by the device to going straight up to
Machine always away from control.Its suitability is strong, simple in construction firm, easy for installation, is easy to replicate and is adapted to, be rationally distributed, being suitable for
Big installation environment is shaken on helicopter, unmanned aerial vehicle (UAV) control precision can be effectively improved, ensures the operation of unmanned plane and safe to use.
Wherein, it is characterised in that described sliding block and described support ligament coordinate with described support tube
Lower translation, it is more smooth when may insure relative motion by smearing lubricating grease.Slided not because sliding block and main stay tube coordinate
Can topple, therefore pitch keep level and follow sliding block to slide up and down, so as to realize helicopter always away from increase and reduction.
As the presently preferred embodiments, described slider bottom center is hinged with strip linkage board, described linkage board both ends
Pass described support tube and be hinged with described linear drives component upper ends, it is preferable that described slider bottom is formed with general
Described linkage board is embedding to contain groove therein, and described linkage board carries out the deflection in predetermined angular in described groove, and two
Power is transferred to sliding block by individual straight line steering wheel by seesaw type linkage plate, and it is not exclusively synchronous effectively to eliminate both sides steering wheel stroke
The harmful effect brought.Meanwhile to mitigate the weight of linkage board, lightening hole, and both ends point are offered on described linkage board
It is not articulated and connected formed with U-shaped prong with realizing.
Wherein, described slider top is provided with three support bars, and described support bar lower end is fixedly connected with a slide block, on
End is point articulated with the fixation of pitch so that the posture of pitch is consistent with sliding block posture.Pass through what pitch was connected
The drawing of three connecting rods with pushing away the downwardly and upwardly motion for realizing pitch, so as to realize to helicopter always away from control.Wherein, three
Individual support bar be typically helicopter body it is intrinsic, three support bars can control helicopter displacement originally, realize helicopter
Landing, pitching, roll operation, after on sliding block, play individually control helicopter landing, simplify control.
Described above is only the preferred embodiment of the present invention, it is noted that for the common skill of the art
For art personnel, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications
Also it should be regarded as protection scope of the present invention.
Claims (9)
1. a kind of total distance control apparatus of helicopter, it is characterised in that including being fixedly installed on support tube lower end and being located at pitch
The base of underface, the linear drives portion that support tube both sides and lower end are hinged with described base is symmetrically disposed in, can be upper and lower
It is slidably arranged in the sliding block that in described support tube and both ends are connected with described linear drives part, described sliding block
It is fixedly connected with pitch.
2. the total distance control apparatus of helicopter as claimed in claim 1, it is characterised in that described linear drives portion is straight line rudder
Machine.
3. the total distance control apparatus of helicopter as claimed in claim 1, it is characterised in that described sliding block and described support tube
Gap coordinates with the upward-downward translation in described support tube.
4. the total distance control apparatus of helicopter as claimed in claim 1, it is characterised in that also including linkage board, described linkage
Plate center is be hinged with described sliding block and can deflect up and down, the both ends of described linkage board and described linear drives component upper ends
It is be hinged.
5. the total distance control apparatus of helicopter as claimed in claim 4, it is characterised in that described slider bottom or top is formed
Have and contain groove therein by described linkage board is embedding, described linkage board carries out inclined in predetermined angular in described groove
Turn.
6. the total distance control apparatus of helicopter as claimed in claim 1, it is characterised in that the action row in described linear drives portion
Journey corresponds to propeller conversion range of angle of attack as 0 ° -9 °.
7. the total distance control apparatus of helicopter as claimed in claim 1, it is characterised in that described slider top is provided with three
Support bar, described support bar lower end are fixedly connected with a slide block, and upper end is hinged with pitch.
8. a kind of helicopter, it is characterised in that described helicopter is multirotor helicopter, each or at least part rotor pair
The dynamic engine of oil and the total distance control apparatus of helicopter as described in claim any one of 1-7 should be set.
9. a kind of total distance control apparatus of helicopter as described in claim any one of 1-7 is changed to the dynamic engine of oil in electric engine
Application afterwards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710630833.XA CN107472516B (en) | 2017-07-28 | 2017-07-28 | Helicopter collective pitch control device, helicopter and application |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710630833.XA CN107472516B (en) | 2017-07-28 | 2017-07-28 | Helicopter collective pitch control device, helicopter and application |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107472516A true CN107472516A (en) | 2017-12-15 |
| CN107472516B CN107472516B (en) | 2023-09-05 |
Family
ID=60596844
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710630833.XA Active CN107472516B (en) | 2017-07-28 | 2017-07-28 | Helicopter collective pitch control device, helicopter and application |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107472516B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533318A (en) * | 2018-09-28 | 2019-03-29 | 北京因时机器人科技有限公司 | Pitch driving mechanism and model helicopter |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB652817A (en) * | 1948-09-14 | 1951-05-02 | Pennine Aircraft Ltd | Improvements in means for controlling the pitch of rotor blades of helicopters |
| RU2155702C1 (en) * | 1999-04-15 | 2000-09-10 | Кумертауское авиационное производственное предприятие | System of two coaxial main rotors of flying vehicle |
| CN201253488Y (en) * | 2008-08-21 | 2009-06-10 | 罗之洪 | Airplane model direction control system |
| CN101612481A (en) * | 2008-11-26 | 2009-12-30 | 罗之洪 | Slide type airplane model steering engine |
| CN202994453U (en) * | 2012-12-25 | 2013-06-12 | 中国直升机设计研究所 | An operation matching mechanism of a rotor testing platform |
| CN103318407A (en) * | 2013-06-05 | 2013-09-25 | 王开林 | Standalone control system of coaxial double-rotor unmanned helicopter control system |
| CN205087145U (en) * | 2015-11-04 | 2016-03-16 | 中航维拓（北京）科技有限责任公司 | Half differential course control's of upper rotor unmanned helicopter control system of close coupled type |
| CN207450237U (en) * | 2017-07-28 | 2018-06-05 | 一飞智控(天津)科技有限公司 | The total distance control apparatus of helicopter and helicopter |
-
2017
- 2017-07-28 CN CN201710630833.XA patent/CN107472516B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB652817A (en) * | 1948-09-14 | 1951-05-02 | Pennine Aircraft Ltd | Improvements in means for controlling the pitch of rotor blades of helicopters |
| RU2155702C1 (en) * | 1999-04-15 | 2000-09-10 | Кумертауское авиационное производственное предприятие | System of two coaxial main rotors of flying vehicle |
| CN201253488Y (en) * | 2008-08-21 | 2009-06-10 | 罗之洪 | Airplane model direction control system |
| CN101612481A (en) * | 2008-11-26 | 2009-12-30 | 罗之洪 | Slide type airplane model steering engine |
| CN202994453U (en) * | 2012-12-25 | 2013-06-12 | 中国直升机设计研究所 | An operation matching mechanism of a rotor testing platform |
| CN103318407A (en) * | 2013-06-05 | 2013-09-25 | 王开林 | Standalone control system of coaxial double-rotor unmanned helicopter control system |
| CN205087145U (en) * | 2015-11-04 | 2016-03-16 | 中航维拓（北京）科技有限责任公司 | Half differential course control's of upper rotor unmanned helicopter control system of close coupled type |
| CN207450237U (en) * | 2017-07-28 | 2018-06-05 | 一飞智控(天津)科技有限公司 | The total distance control apparatus of helicopter and helicopter |
Non-Patent Citations (1)
| Title |
|---|
| 袁夏明;朱纪洪;陈志刚;鲁兴举;: "一种共轴式直升机操纵机构的运动学建模与分析" * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109533318A (en) * | 2018-09-28 | 2019-03-29 | 北京因时机器人科技有限公司 | Pitch driving mechanism and model helicopter |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107472516B (en) | 2023-09-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105636865B (en) | Flight control assemblies for aircraft | |
| US20190039721A1 (en) | Lopsided payload carriage gimbal for air and water-borne vehicles | |
| CA2837160A1 (en) | Flying electric generators with undisturbed air rotors | |
| EP1905687A2 (en) | Kite, method of generating power using such a kite, method of providing driving force to a vehicle using such a kite, vehicle provided with such a kite, power generation assembly comprising such a kite | |
| DE102007054126A1 (en) | Unmanned gyroplane for advertising or other display purposes, e.g. sports events or demonstrations, has rigid connecting body formed in elongated manner, where two lift generating rotor devices are provided and spaced at connecting body | |
| CN104859854A (en) | Heavy-load low-structure-complexity double-coaxial-twin-rotor unmanned aerial vehicle | |
| DE102012202698A1 (en) | Vertical take-off and landing aircraft for transporting people or loads, has signal processing unit performing position control such that aircraft is horizontally located in space without pilot's control inputs or remote control | |
| CN108750104B (en) | Flapping wing aircraft with self-adaptive and actively twisted wings | |
| CN108674651B (en) | Flapping wing device and flapping wing machine | |
| CN107472516A (en) | The total distance control apparatus of helicopter and helicopter and application | |
| CN102779438B (en) | Flight simulated mechanical execution system simulating full-motion of airplane | |
| DE112018006754T5 (en) | FLIGHT DEVICE AND FLIGHT PROCEDURES FOR IT | |
| CN207450237U (en) | The total distance control apparatus of helicopter and helicopter | |
| US7770839B2 (en) | Flight machinery | |
| CN202481312U (en) | Unidirectional flapping mechanism capable of realizing two-dimensional motion | |
| DE602004012128T2 (en) | Wind turbine with vertical axis of rotation with a control system for kites | |
| CN111977010A (en) | Unmanned aerial vehicle take-off and landing platform and building | |
| KR101129249B1 (en) | A vertical takeoff and landing aircraft | |
| CN111874250B (en) | Outdoor operation equipment of unmanned aerial vehicle | |
| CN107234623B (en) | A kind of quadripartion high-voltage dc transmission electric wire magnetic drive crusing robot | |
| US9673554B2 (en) | Aircraft rotor fitted with a connector device for connecting electrical power between a hub and blades of the rotor | |
| CN105438466B (en) | A kind of manpower driving fixed wing aircraft | |
| CN201524421U (en) | Model airplane | |
| CN109822894B (en) | Multifunctional 3D Printer | |
| CN202327574U (en) | Lifting support of signal collection instrument |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |