CN109592013A - A kind of restraint method of general-purpose aircraft rudder rudder face - Google Patents
A kind of restraint method of general-purpose aircraft rudder rudder face Download PDFInfo
- Publication number
- CN109592013A CN109592013A CN201811305842.2A CN201811305842A CN109592013A CN 109592013 A CN109592013 A CN 109592013A CN 201811305842 A CN201811305842 A CN 201811305842A CN 109592013 A CN109592013 A CN 109592013A
- Authority
- CN
- China
- Prior art keywords
- rudder
- confined planes
- limited block
- top connection
- shaft 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
A kind of restraint method of general-purpose aircraft rudder rudder face, top connection and lower contact are equipped on rudder beam, a rotary pin shaft is fixed in top connection, above-mentioned rotary pin shaft is overlapped with the pivot center of rudder, the rotary pin shaft of top connection is plugged on upper shaft support, the connection of the vertical tail of the upper shaft support and aircraft, confined planes are equipped on upper shaft support, the angle of the confined planes is corresponding with the limit deflection angle of rudder, below top connection, the suitable position of rudder beam is equipped with a limited block, limited block is rotated synchronously with rudder, when when the surface pivots of limited block to the limit face contact with upper shaft support, the rudder face angle of rudder is extreme angles.
Description
Technical field
The application belongs to airplane design technical field, the restraint method of specifically a kind of general-purpose aircraft rudder rudder face
Background technique
Rudder of aircraft rudder face restraint device (Rudder surface stopper device of rudder) is usually
Restraint screw is installed on the input mechanism of rudder rudder face shaft, according to the rotational angle of rudder face, in input mechanism interposition
Restraint bracket is installed, the left side restraint screw contact when rudder rudder face turns left, on input mechanism in the structural frames set
On the left of restraint bracket；When rudder rudder face turns right, on the right side of the right side restraint screw contact restraint bracket on input mechanism.
The restraint device of this form, needs to be arranged on input mechanism the mounting base of restraint screw, and sets on body corresponding position
Restraint bracket is set, causes input mechanism and restraint support configurations all relative complex, pts wt weight, and restraint mode is limited
Dynamic screw withstands restraint bracket, is typical single-contact, cause biggish impact injury to structure using meeting for a long time.
Summary of the invention
It is an object of the invention to disclose a kind of Small General Aircraft rudder rudder face restraint device, by restraint mode by list
Point contact is changed to plane-plane contact, improves mechanical characteristic, reduces structural damage, improves reliability.
A kind of restraint method of general-purpose aircraft rudder rudder face, which is characterized in that on rudder beam be equipped with top connection and
Lower contact is fixed with a rotary pin shaft in top connection, and above-mentioned rotary pin shaft is overlapped with the pivot center of rudder, top connection
Rotary pin shaft be plugged on upper shaft support, the vertical tail of the upper shaft support and aircraft connection, on upper shaft support
Equipped with confined planes, the angle of the confined planes and the limit deflection angle of rudder are corresponding, below top connection, the conjunction of rudder beam
Right position has installed a limited block, and limited block is rotated synchronously with rudder, when limited block surface pivots to upper shaft support
Limit face contact when, the rudder face angle of rudder is extreme angles.
Confined planes, left side confined planes and right side confined planes there are two being set on the shaft seating, left side confined planes and right side
Confined planes are symmetrical, and set up separately on the ontology of shaft seating center two sides, the extreme position that the limited block turns left
It is bonded with left side confined planes, the extreme position that limited block turns right is bonded with right side confined planes.
The beneficial effects of the present application are as follows: 1) restraint mode by single-contact is changed to shaft seating confined planes and limited block
Face contact, reduce structural damage, improve reliability.2) cleverly left and right confined planes are designed in shaft seating ontology
Two sides, limited block are rotated with rudder around upper shaft support, and upper shaft support two sides confined planes will effectively be realized inclined to rudder
The limit of gyration, achieves the object of the present invention.3) limit contact area is big, and contact stress is small, and structure is simple and efficient, dismounting dimension
Shield convenience.
Attached drawing is described in further detail the application with reference to embodiments.
Detailed description of the invention
Fig. 1 is the restraint position signal of general-purpose aircraft rudder rudder face.
Fig. 2 is position limiting structure signal.
Fig. 3 is the motion profile signal of limited block.
In figure number explanation: 1 top connection, 2 lower contacts, 3 rudder beams, 4 upper shaft supports, 5 limited blocks, 6 rotary pin shafts,
7 confined planes, 8 right avertence turn extreme position, 9 left avertences turn extreme position
Specific embodiment
Referring to attached drawing, the restraint method of the general-purpose aircraft rudder rudder face of the application is equipped with top connection on rudder beam 3
1 and lower contact 2, a rotary pin shaft 6, the pivot center weight of above-mentioned rotary pin shaft 6 and rudder are fixed in top connection 1
It closes, the rotary pin shaft 6 of top connection 2 is plugged on the connecting hole of upper shaft support 4, the vertical end of the upper shaft support 4 and aircraft
The wing connects (not shown), and confined planes 7 are equipped on the ontology of upper shaft support 4, which is a tapered plane, limit
The angle of plane 7 is corresponding with the limit deflection angle of rudder, and below top connection, the suitable position of rudder beam 3 is equipped with one
A limited block 5, limited block 5 are rotated synchronously with rudder, when the surface pivots of limited block 5 are to the confined planes 7 with upper shaft support
When contact, the rudder face angle of rudder is extreme angles.
Since rudder swings, set on above-mentioned upper shaft support 4 there are two confined planes 7, left side limits
Plane and right side confined planes, left side confined planes and right side confined planes are symmetrical, and set up the sheet in shaft seating center two sides separately
On body, the limited block 5 turns left with rudder when turning extreme position 9 to left avertence, and limited block 5 is bonded with left side confined planes,
The limited block 5 turns right with rudder when turning extreme position 8 to right avertence, and limited block 5 is bonded with right side confined planes, realizes pair
The restraint function of rudder rudder face.
Claims (2)
1. a kind of restraint method of general-purpose aircraft rudder rudder face is equipped with top connection and lower contact, top connection on rudder beam
On be fixed with a rotary pin shaft, which is characterized in that above-mentioned rotary pin shaft is overlapped with the pivot center of rudder, top connection
Rotary pin shaft is plugged on upper shaft support, and the vertical tail connection of the upper shaft support and aircraft is set on upper shaft support
Have confined planes, the angle of the confined planes and the limit deflection angle of rudder are corresponding, below top connection, rudder beam it is suitable
Position is equipped with a limited block, and limited block rotates synchronously with rudder, when limited block surface pivots to upper shaft support
When limiting face contact, the rudder face angle of rudder is extreme angles.
2. the restraint method of general-purpose aircraft rudder rudder face as described in claim 1, which is characterized in that on the shaft seating
If there are two confined planes, left side confined planes and right side confined planes, left side confined planes and right side confined planes are symmetrical, and set up separately
On the ontology of shaft seating center two sides, the extreme position that the limited block turns left is bonded with left side confined planes, limited block
The extreme position to turn right is bonded with right side confined planes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811305842.2A CN109592013A (en) | 2018-11-02 | 2018-11-02 | A kind of restraint method of general-purpose aircraft rudder rudder face |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811305842.2A CN109592013A (en) | 2018-11-02 | 2018-11-02 | A kind of restraint method of general-purpose aircraft rudder rudder face |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109592013A true CN109592013A (en) | 2019-04-09 |
Family
ID=65957768
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811305842.2A Pending CN109592013A (en) | 2018-11-02 | 2018-11-02 | A kind of restraint method of general-purpose aircraft rudder rudder face |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109592013A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110598294A (en) * | 2019-09-03 | 2019-12-20 | 中国航空工业集团公司西安飞机设计研究所 | Method and device for determining flight trajectory stability of airplane with conventional layout |
| CN114194379A (en) * | 2021-11-22 | 2022-03-18 | 北京机电工程研究所 | Combined rudder method for improving control capability of X-shaped pneumatic layout |
| CN114440728A (en) * | 2020-11-02 | 2022-05-06 | 丰翼科技(深圳)有限公司 | Control surface calibrating device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB734446A (en) * | 1953-03-20 | 1955-08-03 | Armstrong Whitworth Co Eng | Operating the flaps of aircraft wings |
| US20110061579A1 (en) * | 2009-02-03 | 2011-03-17 | Van Gelder Klaas Boudewijn | Dynamic fin comprising coupled fin sections |
| CN102815394A (en) * | 2012-08-13 | 2012-12-12 | 湖南山河科技股份有限公司 | Light aircraft rudder spring centering positioning mechanism |
| CN105836106A (en) * | 2016-05-23 | 2016-08-10 | 南京航空航天大学 | Morphing wing trailing edge driven based on shape memory alloy and deflection method thereof |
| CN206374966U (en) * | 2016-12-30 | 2017-08-04 | 万丰航空工业有限公司 | A kind of rudder middle position locking device of light aerocraft |
-
2018
- 2018-11-02 CN CN201811305842.2A patent/CN109592013A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB734446A (en) * | 1953-03-20 | 1955-08-03 | Armstrong Whitworth Co Eng | Operating the flaps of aircraft wings |
| US20110061579A1 (en) * | 2009-02-03 | 2011-03-17 | Van Gelder Klaas Boudewijn | Dynamic fin comprising coupled fin sections |
| CN102815394A (en) * | 2012-08-13 | 2012-12-12 | 湖南山河科技股份有限公司 | Light aircraft rudder spring centering positioning mechanism |
| CN105836106A (en) * | 2016-05-23 | 2016-08-10 | 南京航空航天大学 | Morphing wing trailing edge driven based on shape memory alloy and deflection method thereof |
| CN206374966U (en) * | 2016-12-30 | 2017-08-04 | 万丰航空工业有限公司 | A kind of rudder middle position locking device of light aerocraft |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110598294A (en) * | 2019-09-03 | 2019-12-20 | 中国航空工业集团公司西安飞机设计研究所 | Method and device for determining flight trajectory stability of airplane with conventional layout |
| CN110598294B (en) * | 2019-09-03 | 2023-05-19 | 中国航空工业集团公司西安飞机设计研究所 | Method and device for determining flight trajectory stability of airplane with conventional layout |
| CN114440728A (en) * | 2020-11-02 | 2022-05-06 | 丰翼科技(深圳)有限公司 | Control surface calibrating device |
| CN114194379A (en) * | 2021-11-22 | 2022-03-18 | 北京机电工程研究所 | Combined rudder method for improving control capability of X-shaped pneumatic layout |
| CN114194379B (en) * | 2021-11-22 | 2023-10-13 | 北京机电工程研究所 | Combined rudder method for improving control capacity of X-type pneumatic layout |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109592013A (en) | A kind of restraint method of general-purpose aircraft rudder rudder face | |
| CN101963499B (en) | Tool and method for measuring deflection angle of airplane control surface | |
| CN103308023B (en) | A kind of angle displacement measuring device and measuring method | |
| CN207777893U (en) | A kind of equipment vibration isolation buffering device | |
| CN204433041U (en) | Vehicle rudder drive mechanism | |
| CN107844158B (en) | Rocker device | |
| CN102425591A (en) | Quick release lock with spring device | |
| US8967550B2 (en) | Aerofoil comprising a high lift flap | |
| CN104229145A (en) | Lead screw push rod type aircraft head deflection driving device | |
| CN106275407B (en) | A kind of wing of foldable unmanned plane | |
| CN107499499B (en) | Airplane actuating system with mechanical centering function | |
| CN203585192U (en) | In-position buffering mechanism | |
| CN203996908U (en) | The electric motor mounting structure of unmanned plane and unmanned plane | |
| CN104344954B (en) | The fatigue machine of the self-lubricating knuckle bearing in flexible hub rotor | |
| CN107284697B (en) | A kind of landing buffer mechanism approaching signal device | |
| CN102944207A (en) | Springback type angle displacement measurement device and measurement method thereof | |
| CN108609158A (en) | A kind of passive servo-actuated seal structure | |
| CN210374810U (en) | Small-size rudder face folding mechanism subassembly | |
| CN103466077A (en) | Roller trigger device | |
| CN109017378B (en) | Automatic navigation vehicle charging support | |
| CN112648481A (en) | Zero adjustment device and method for angular displacement sensor | |
| CN107228749B (en) | A kind of wind tunnel model small size axial direction varied angle mechanism | |
| CN110385661A (en) | Assembly tooling | |
| US20150097080A1 (en) | Rocking bogie mechanism | |
| KR100938268B1 (en) | Apparatus to Suppress Vibration of Aircraft Control Surface due to Freeplay and Backlash |
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 | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190409 |