CN109533293A - A kind of pull rod guiding mechanism for helicopter flight manipulation - Google Patents
A kind of pull rod guiding mechanism for helicopter flight manipulation Download PDFInfo
- Publication number
- CN109533293A CN109533293A CN201811361199.5A CN201811361199A CN109533293A CN 109533293 A CN109533293 A CN 109533293A CN 201811361199 A CN201811361199 A CN 201811361199A CN 109533293 A CN109533293 A CN 109533293A
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- CN
- China
- Prior art keywords
- pull rod
- guide tube
- guiding mechanism
- helicopter flight
- support
- 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
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
- B64C13/30—Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
This application provides a kind of pull rod guiding mechanisms for helicopter flight manipulation, belong to helicopter control system structure-design technique field.The mechanism includes multiple pilot units (5) and support (6), the support (6) is fixed on the machine body, the multiple pilot unit (5) is fixed on side by side on the support (6), each pilot unit includes pull rod (51) and guide tube (52), wherein, guide tube (52) both ends pass through ball bushing (53) support pull rod (51) respectively.The application can be achieved at the same time multichannel movement transfer function, and can realize straight line or small-angle movement transmitting, save big quantity space.
Description
Technical field
The application belongs to helicopter control system structure-design technique field, and in particular to one kind is grasped for helicopter flight
Vertical pull rod guiding mechanism.
Background technique
Helicopter control system suffers from surrounding body structure and other systems components when arranging on helicopter
Limitation.Especially on big weight helicopter, linkage length is larger, and multichannel linear system arrangement is relatively difficult.
The general motion transfering device of flight control system is realized by pull rod rocker arm, as shown in figure 5, this form
Mainly comprising support 1, rocker arm 2 and pull rod 3,4 etc., support 1 is fixed in structure, and rocker arm 2 is mounted on support 1, pull rod
Both ends are connected on different rocker arms.Pull rod accepts the movement output that previous stage rocker arm is passed over, and drives latter
Grade rocker arm rotation.This motion-transmission manner needs biggish space, thus when multichannel linear system small space simultaneously
It often cannot achieve when arrangement.
Summary of the invention
At least one in order to solve the above-mentioned technical problem, this application provides a kind of pull rods for helicopter flight manipulation
Guiding mechanism, including multiple pilot units and support, the support are fixed on the machine body, and the multiple pilot unit is fixed side by side
On the support, each pilot unit includes pull rod and guide tube, wherein guide tube both ends pass through ball bushing respectively
Support the pull rod.
Preferably, the two end faces of the guide tube are provided with baffle, and the ball bushing is in the axial direction
The bearing race part of one end face contradicts on the baffle.
Preferably, the baffle is bolted on the guide tube.
It preferably, further include sliding block, the sliding block is fixed on the guide tube, and it is convex to pull rod direction to be extended with bar shaped
It rises, the pull rod is turned along the axial strip groove for having and being adapted to the strip bulge with limiting the pull rod relative to guide tube
It is dynamic.
Preferably, the pull rod both ends are provided with auricle structure.
Preferably, the auricle is rotatably connected on the pull rod.
Preferably, the pull rod both ends are provided with band arbor bearing structure.
Preferably, pump nozzle is provided on the guide tube, the pump nozzle is connected at the ball bushing.
Preferably, the guide tube end is provided with fixed plate, and the fixed plate is bolted on the support.
Key point of the invention: 1, it is equipped with guide tube component and fixes several groups bearing wherein, pull rod and bearing fit are realized
Move transfer function；2, pull rod is equipped with card slot, and guide tube component is equipped with sliding block and baffle, realizes guiding and limit function；3,
Pull rod both ends are equipped with fork ear or hold with arbor, realize input/output function；4, settable several groups pilot unit as needed, with
Realize the function of multichannel movement transmitting.
The present invention has the advantages that
1. realizing that multichannel moves transfer function simultaneously；
2. straight line or small-angle movement transmitting can be realized；
3. movement transferring is equipped with guiding and limit function；
4. saving space.
Detailed description of the invention
Fig. 1 is structural representation of the application for a preferred embodiment of the pull rod guiding mechanism of helicopter flight manipulation
Figure.
Fig. 2 is pilot unit knot of the application for a preferred embodiment of the pull rod guiding mechanism of helicopter flight manipulation
Structure schematic diagram.
Fig. 3 is that guide tube structure of the application for a preferred embodiment of the pull rod guiding mechanism of helicopter flight manipulation is shown
It is intended to.
Fig. 4 is that Tiebar structure of the application for a preferred embodiment of the pull rod guiding mechanism of helicopter flight manipulation shows
It is intended to.
Fig. 5 is pull rod rocker structure form schematic diagram in the prior art.
Wherein, 1- support, 2- rocker arm, 3- pull rod, 4- pull rod, 5- pilot unit, 6- support, 51- pull rod, 52- guide tube,
53- ball bushing, 54- baffle, 55- sliding block, 56- pump nozzle, 57- fixed plate.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction with the application embodiment
In attached drawing, the technical solution in the application embodiment is further described in more detail.In the accompanying drawings, identical from beginning to end
Or similar label indicates same or similar element or element with the same or similar functions.Described embodiment is
A part of embodiment of the application, rather than whole embodiments.Embodiment below with reference to attached drawing description is to show
Example property, it is intended to for explaining the application, and should not be understood as the limitation to the application.Based on the embodiment in the application,
Every other embodiment obtained by those of ordinary skill in the art without making creative efforts belongs to this
Apply for the range of protection.Presently filed embodiment is described in detail with reference to the accompanying drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
This application provides a kind of pull rod guiding mechanisms for helicopter flight manipulation, referring to Figure 1 and Figure 2, including it is more
A pilot unit 5 and support 6, the support 6 are fixed on the machine body, and the multiple pilot unit 5 is fixed on the support 6 side by side
On, each pilot unit includes pull rod 51 and guide tube 52, wherein 52 both ends of guide tube pass through ball bushing 53 respectively
Support the pull rod 51.
The application is directed to when multichannel linear system is when small space is simutaneously arranged, and is not available conventional whip formula guiding mechanism
And design, input/output function is realized by pull rod 51, by ball bushing 53 reduce pull rod 51 and fixed mechanism it
Between friction, linear motion bearing be pressed into guide tube (12) in, guarantee guide draw bar component movement it is smooth.Pilot unit is according to need
Settable several groups are wanted, arranged in parallel, when wherein one end institute's connecting rod generates movement to pull rod guiding device, pull rod is in straight line
It is moved along a straight line under the cooperation of motion bearings and sliding block, transmits motion to other end institute attachment device.
In the present embodiment, ball bushing 53 is fixed in guide tube 52, such as the end of guide tube 52 can be arranged
Step moves ball bearing 53 with straight limit, and guide tube 52 is provided with to the two parts that can rotate docking, to realize that straight line is transported
The installation of dynamic ball bearing 53, in some alternate embodiments, the both ends of the surface of the guide tube 52 are realized by setting baffle 54
Ball bushing 53 is axially moved limitation, in the embodiment, the ball bushing 53 in the axial direction one
The bearing race part of end face contradicts on the baffle 54.With reference to Fig. 3, baffle 53 has recess, the recess semicircular in shape, when this
When baffle 53 is adjacent on the end face of ball bushing 53, which is adjacent in ball bushing 53
Between through-hole round edge.
In some optional embodiments, with reference to Fig. 3, the baffle 54 is bolted on the guide tube 52.
It further include sliding block 55 in some optional embodiments, the sliding block 55 is fixed on the guide tube 52, and to drawing
Bar direction is extended with strip bulge, and the pull rod 51 is along the axial strip groove for having and being adapted to the strip bulge, with limitation
The pull rod 51 is rotated relative to guide tube 52.With reference to Fig. 4, pull rod 51 is provided with strip groove from outer circumferential central axial direction,
It is slided with cooperation along strip bulge.
It is understood that above-mentioned baffle 54 and sliding block 55 can be fixed on guide tube 52 by same bolt.
In some optional embodiments, 51 both ends of pull rod are provided with auricle structure, connect external machine for pull rod
Structure pitches ear by fastener and is fixed on drag link body.
In some optional embodiments, the auricle is rotatably connected on the pull rod 51.
In some optional embodiments, 51 both ends of pull rod are provided with band arbor bearing structure.
In some optional embodiments, pump nozzle 56 is provided on the guide tube 52, the pump nozzle 56 is connected to institute
It states at ball bushing 53, facilitates the addition of lubricating grease, realize the lubrication of bearing.
In some optional embodiments, 52 end of guide tube is provided with fixed plate 57, and the fixed plate 57 passes through spiral shell
Bolt is fixed on the support 6.
In the above-described embodiments, fixed plate 57 can be used as a part of guide tube 52, can also pass through the side such as clip
Formula is fixed on guide tube.Fixed plate 57 extends radially outwardly a fixed edge along guide tube, and above-mentioned baffle 54 and sliding block 55 can also lead to
Bolt is crossed fixed on the fixed edge.
Key point of the invention: 1, it is equipped with guide tube component and fixes several groups bearing wherein, pull rod and bearing fit are realized
Move transfer function；2, pull rod is equipped with card slot, and guide tube component is equipped with sliding block and baffle, realizes guiding and limit function；3,
Pull rod both ends are equipped with fork ear or hold with arbor, realize input/output function；4, settable several groups pilot unit as needed, with
Realize the function of multichannel movement transmitting.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (9)
1. a kind of pull rod guiding mechanism for helicopter flight manipulation, which is characterized in that including multiple pilot units (5) and branch
Seat (6), the support (6) are fixed on the machine body, and the multiple pilot unit (5) is fixed on side by side on the support (6), each
Pilot unit includes pull rod (51) and guide tube (52), wherein guide tube (52) both ends pass through ball bushing (53) respectively
Support the pull rod (51).
2. the pull rod guiding mechanism for helicopter flight manipulation as described in claim 1, which is characterized in that the guide tube
(52) two end faces are provided with baffle (54), the bearing of the end face of the ball bushing (53) in the axial direction
Circle part contradicts on the baffle (54).
3. the pull rod guiding mechanism for helicopter flight manipulation as claimed in claim 2, which is characterized in that the baffle
(54) it is bolted on the guide tube (52).
4. the pull rod guiding mechanism for helicopter flight manipulation as described in claim 1, which is characterized in that further include sliding block
(55), the sliding block (55) is fixed on the guide tube (52), and is extended with strip bulge, the pull rod (51) to pull rod direction
Along the axial strip groove for having and being adapted to the strip bulge, rotated with limiting the pull rod (51) relative to guide tube (52).
5. the pull rod guiding mechanism for helicopter flight manipulation as described in claim 1, which is characterized in that the pull rod
(51) both ends are provided with auricle structure.
6. the pull rod guiding mechanism for helicopter flight manipulation as claimed in claim 5, which is characterized in that the auricle turns
It is dynamic to be connected on the pull rod (51).
7. the pull rod guiding mechanism for helicopter flight manipulation as described in claim 1, which is characterized in that the pull rod
(51) both ends are provided with band arbor bearing structure.
8. the pull rod guiding mechanism for helicopter flight manipulation as described in claim 1, which is characterized in that the guide tube
(52) it is provided on pump nozzle (56), the pump nozzle (56) is connected at the ball bushing (53).
9. the pull rod guiding mechanism for helicopter flight manipulation as described in claim 1, which is characterized in that the guide tube
(52) end is provided with fixed plate (57), and the fixed plate (57) is bolted on the support (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811361199.5A CN109533293A (en) | 2018-11-15 | 2018-11-15 | A kind of pull rod guiding mechanism for helicopter flight manipulation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811361199.5A CN109533293A (en) | 2018-11-15 | 2018-11-15 | A kind of pull rod guiding mechanism for helicopter flight manipulation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109533293A true CN109533293A (en) | 2019-03-29 |
Family
ID=65847508
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811361199.5A Pending CN109533293A (en) | 2018-11-15 | 2018-11-15 | A kind of pull rod guiding mechanism for helicopter flight manipulation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109533293A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110733629A (en) * | 2019-10-12 | 2020-01-31 | 中航通飞研究院有限公司 | flight control system guide piece device |
| CN111516860A (en) * | 2020-04-30 | 2020-08-11 | 中国直升机设计研究所 | Helicopter flight control system transmission mechanism with waterproof sealing function |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140021303A1 (en) * | 2012-07-17 | 2014-01-23 | Mason Electric Co. | Complex-dynamic air and ground vehicle control inceptor |
| CN106477040A (en) * | 2016-11-30 | 2017-03-08 | 中国直升机设计研究所 | Rotor driver is manipulated in a kind of axle |
| CN106697280A (en) * | 2017-01-24 | 2017-05-24 | 重庆通用航空产业集团有限公司 | Automatic helicopter inclinator |
| CN108928477A (en) * | 2018-06-27 | 2018-12-04 | 中国直升机设计研究所 | A kind of device for maneuvering motion transmitting |
-
2018
- 2018-11-15 CN CN201811361199.5A patent/CN109533293A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140021303A1 (en) * | 2012-07-17 | 2014-01-23 | Mason Electric Co. | Complex-dynamic air and ground vehicle control inceptor |
| CN106477040A (en) * | 2016-11-30 | 2017-03-08 | 中国直升机设计研究所 | Rotor driver is manipulated in a kind of axle |
| CN106697280A (en) * | 2017-01-24 | 2017-05-24 | 重庆通用航空产业集团有限公司 | Automatic helicopter inclinator |
| CN108928477A (en) * | 2018-06-27 | 2018-12-04 | 中国直升机设计研究所 | A kind of device for maneuvering motion transmitting |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110733629A (en) * | 2019-10-12 | 2020-01-31 | 中航通飞研究院有限公司 | flight control system guide piece device |
| CN111516860A (en) * | 2020-04-30 | 2020-08-11 | 中国直升机设计研究所 | Helicopter flight control system transmission mechanism with waterproof sealing function |
| CN111516860B (en) * | 2020-04-30 | 2023-06-27 | 中国直升机设计研究所 | Helicopter flight control system transmission mechanism with waterproof sealing function |
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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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190329 |