CN109592014A - A kind of general-purpose aircraft rudder pivot structure and method of operating - Google Patents
A kind of general-purpose aircraft rudder pivot structure and method of operating Download PDFInfo
- Publication number
- CN109592014A CN109592014A CN201811306792.XA CN201811306792A CN109592014A CN 109592014 A CN109592014 A CN 109592014A CN 201811306792 A CN201811306792 A CN 201811306792A CN 109592014 A CN109592014 A CN 109592014A
- Authority
- CN
- China
- Prior art keywords
- rudder
- lower contact
- top connection
- pin shaft
- rotary pin
- 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)
- Pivots And Pivotal Connections (AREA)
Abstract
A kind of general-purpose aircraft rudder pivot structure and deflection method, top connection and lower contact are equipped on rudder beam, a rotary pin shaft is fixed in top connection, lower contact is the column structure of one with rudder Liangping row, a rotation bolt is equipped in the bottom center of lower contact, above-mentioned rotary pin shaft and rotation bolt is coaxial relation, its axial line is overlapped with rudder pivot center, 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, the rotation bolt of lower contact is connected by the vertical tail of lower rotary shaft support and aircraft, an operating rock arm is equipped on the column structure of lower contact, the outer end of the operating rock arm is connect with control operating rod.
Description
Technical field
The application belongs to airplane design technical field, specifically general-purpose aircraft rudder pivot structure and method of operating.
Background technique
Rudder of aircraft, it is desirable that can be along determining axis deflection.Shaft is generally by two branch of rudder face spanwise arrangement
The line of support point determines.Two supporting points of rudder spanwise arrangement in the prior art are connected and fixed by bolt and nut
's.It when installation direction rudder, needs that the bolt and nut on each supporting point is successively installed, entire rudder could be loaded onto；When
It when disassembly direction rudder, needs successively to dismantle the bolt and nut on each supporting point, entire rudder could be removed.Work as supporting point
It when more, generally requires to install or remove more bolt and nuts, causes dismounting heavy workload, disassembly and assembly time is long, dismounting effect
Rate is not high.
Summary of the invention
The application's is designed to provide a kind of general-purpose aircraft rudder pivot structure and deflection method.
A kind of general-purpose aircraft rudder pivot structure, which is characterized in that top connection and lower contact are equipped on rudder beam,
A rotary pin shaft is fixed in top connection, lower contact is the column structure of one with rudder Liangping row, at the bottom of lower contact
End center is equipped with a rotation bolt, and above-mentioned rotary pin shaft and rotation bolt are coaxial relation, axial line and rudder
Pivot center be overlapped, with rudder Liangping row, the rotary pin shaft of top connection is plugged on upper shaft support, the upper shaft support with
The vertical tail of aircraft connects, and the rotation bolt of lower contact is connected by the vertical tail of lower rotary shaft support and aircraft, connects under
The column structure of head is equipped with an operating rock arm, and the outer end of the operating rock arm is connect with control operating rod.
A kind of deflection method of general-purpose aircraft rudder is equipped with top connection and lower contact, in top connection on rudder beam
It is fixed with a rotary pin shaft, which forms the upper fulcrum of rudder, and lower contact is one and rudder Liangping row
Column structure is equipped with a rotation bolt in the bottom center of lower contact, which forms the lower fulcrum of rudder, above-mentioned
Rotary pin shaft and rotation bolt be coaxial relation, axial line is overlapped with rudder pivot center, the rotating dog of top connection
Axis is plugged on upper shaft support, the vertical tail connection of the upper shaft support and aircraft, under the rotation bolt of lower contact passes through
The connection of the vertical tail of shaft seating and aircraft, is equipped with an operating rock arm, the operating rock arm on the column structure of lower contact
Outer end connect with control operating rod, by control operating rod reciprocating sliding operating rock arm make the rotation bolt of lower contact bottom center with
Lower rotary shaft support is fulcrum rotation, and lower contact is moved the above shaft seating of top connection rotary pin shaft by rudder sill bolt and turned for fulcrum
It is dynamic, and then realize the deflection control of rudder.
The beneficial effects of the present invention are: 1) rudder top connection connection rotary pin shaft formed rudder upper fulcrum,
Rudder lower contact connection rotation bolt formed rudder lower fulcrum, upper fulcrum, lower fulcrum line constitute shaft, it is described on
It is fixedly connected between fulcrum, lower fulcrum and housing construction, is connected between shaft lower fulcrum and rudder ontology by manipulation connector,
The manipulation connector is equipped with rocker arm, and control stick is connected on rudder rocker arm, and reciprocating sliding rocker arm makes direction to control stick back and forth
Rudder makees dead axle yaw motion around the shaft that upper lower fulcrum line is constituted.Structure type is simple and efficient.2) rudder is opened up to passing through
The positioning of lower rotary shaft support, and upper shaft is using pivot pin, lower rotary shaft is bolt.This design is so that joint form is simple, just
It is docked to rudder with stabilization and convenient disassembly.
Detailed description of the invention
Fig. 1 is a kind of general-purpose aircraft rudder pivot structure
Fig. 2 is that fulcrum structure is illustrated on rudder
Fig. 3 is rudder lower fulcrum structural representation
Explanation: 1 top connection, 2 lower contacts, 3, control operating rod, 4 beams, 5 rotary pin shafts, 6 upper shafts, 7 rotation spiral shells is numbered in figure
Bolt, 8 lower rotary shaft supports, 9 operating rock arms
Specific embodiment
Referring to attached drawing, a kind of general-purpose aircraft rudder pivot structure is equipped with top connection 1 and lower contact on rudder beam 4
2, a rotary pin shaft 5 is fixed in top connection 1, and lower contact 2 is a column structure parallel with rudder beam 4, is connect under
First 2 bottom center is equipped with a rotation bolt 6, and above-mentioned rotary pin shaft 5 and rotation bolt 6 are coaxial relation, and axial direction connects
Line is overlapped with rudder pivot center, is plugged on upper shaft support 7 with the rotary pin shaft 4 of rudder Liangping row, top connection 1,
The upper shaft support 7 is connect with the vertical tail of aircraft, rotation bolt 6 the hanging down by lower rotary shaft support 8 and aircraft of lower contact 2
Straight tail connection, is equipped with an operating rock arm 9, the outer end of the operating rock arm 9 and control operating rod on the column structure of lower contact 2
3 connections.
A kind of deflection method of general-purpose aircraft rudder is equipped with top connection 1 and lower contact 2, top connection on rudder beam 4
A rotary pin shaft 5 is fixed on 1, which forms the upper fulcrum of rudder, and lower contact 2 is one and rudder beam 4
Parallel column structure is equipped with a rotation bolt 6 in the bottom center of lower contact 2, which forms under rudder
Fulcrum, above-mentioned rotary pin shaft 5 and rotation bolt 6 are coaxial relation, and axial line is overlapped with rudder pivot center, are above connect
First 1 rotary pin shaft 5 is plugged on upper shaft support 7, which connect with the vertical tail of aircraft, lower contact 2
Rotation bolt 6 is connect by lower rotary shaft support 8 with the vertical tail of aircraft, and a behaviour is equipped on the column structure of lower contact 2
The outer end of pitching arm 9, the operating rock arm 9 is connect with control operating rod 3, by 3 reciprocating sliding operating rock arm 9 of control operating rod, under making
6 or less the shaft seating 8 of rotation bolt of 2 bottom center of connector is fulcrum rotation, and lower contact 2 is driven by rudder beam 4 and connect
Head 5 or more shaft seating 7 of rotary pin shaft is fulcrum rotation, and then realizes the deflection control of rudder.
Claims (2)
1. a kind of general-purpose aircraft rudder pivot structure, which is characterized in that top connection and lower contact are equipped on rudder beam, on
A rotary pin shaft is fixed on connector, lower contact is the column structure of one with rudder Liangping row, in the bottom end of lower contact
Center is equipped with a rotation bolt, and above-mentioned rotary pin shaft and rotation bolt are coaxial relation, and axial line and rudder turn
Shaft line be overlapped, with rudder Liangping row, the rotary pin shaft of top connection is plugged on upper shaft support, the upper shaft support and fly
The vertical tail of machine connects, and the rotation bolt of lower contact is connected by the vertical tail of lower rotary shaft support and aircraft, in lower contact
Column structure be equipped with an operating rock arm, the outer end of the operating rock arm is connect with control operating rod.
2. a kind of deflection method of general-purpose aircraft rudder, which is characterized in that top connection and lower contact are equipped on rudder beam,
A rotary pin shaft is fixed in top connection, lower contact is the column structure of one with rudder Liangping row, at the bottom of lower contact
End center is equipped with a rotation bolt, and above-mentioned rotary pin shaft and rotation bolt are coaxial relation, axial line and rudder
Pivot center is overlapped, and the rotary pin shaft of top connection is plugged on upper shaft support, the vertical tail of the upper shaft support and aircraft
The rotation bolt of connection, lower contact is connected by the vertical tail of lower rotary shaft support and aircraft, on the column structure of lower contact
Equipped with an operating rock arm, the outer end of the operating rock arm is connect with control operating rod, passes through control operating rod reciprocating sliding operating rock arm
Make the following shaft seating fulcrum rotation of the rotation bolt of lower contact bottom center, lower contact moves top connection by rudder sill bolt
The above shaft seating of rotary pin shaft is fulcrum rotation, and then realizes the deflection control of rudder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811306792.XA CN109592014A (en) | 2018-11-02 | 2018-11-02 | A kind of general-purpose aircraft rudder pivot structure and method of operating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811306792.XA CN109592014A (en) | 2018-11-02 | 2018-11-02 | A kind of general-purpose aircraft rudder pivot structure and method of operating |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109592014A true CN109592014A (en) | 2019-04-09 |
Family
ID=65957448
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811306792.XA Pending CN109592014A (en) | 2018-11-02 | 2018-11-02 | A kind of general-purpose aircraft rudder pivot structure and method of operating |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109592014A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090256025A1 (en) * | 2008-04-12 | 2009-10-15 | Airbus Espana S.L. | Stabilizing and directional-control surface of aircraft |
| 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 |
| CN103318404A (en) * | 2013-05-30 | 2013-09-25 | 江西洪都航空工业集团有限责任公司 | Guided missile aileron control mechanism |
| CN103569346A (en) * | 2013-11-13 | 2014-02-12 | 中国航空工业集团公司西安飞机设计研究所 | Vertical fin structure of ship-borne transportation airplanes |
| CN108622371A (en) * | 2018-06-12 | 2018-10-09 | 精功（绍兴）复合材料有限公司 | Unmanned aerial vehicle composite material rudder and preparation method |
-
2018
- 2018-11-02 CN CN201811306792.XA patent/CN109592014A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090256025A1 (en) * | 2008-04-12 | 2009-10-15 | Airbus Espana S.L. | Stabilizing and directional-control surface of aircraft |
| 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 |
| CN103318404A (en) * | 2013-05-30 | 2013-09-25 | 江西洪都航空工业集团有限责任公司 | Guided missile aileron control mechanism |
| CN103569346A (en) * | 2013-11-13 | 2014-02-12 | 中国航空工业集团公司西安飞机设计研究所 | Vertical fin structure of ship-borne transportation airplanes |
| CN108622371A (en) * | 2018-06-12 | 2018-10-09 | 精功（绍兴）复合材料有限公司 | Unmanned aerial vehicle composite material rudder and preparation method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207807748U (en) | A kind of comprehensive spray painting intelligent robot of spraying for building | |
| CN103318404B (en) | A kind of guided missile aileron control mechanism | |
| CN203473238U (en) | Missile aileron control mechanism | |
| CN104290901B (en) | Double-rocker transmission mechanism applicable to movable control surface of aerial vehicle | |
| CN206968964U (en) | A kind of unmanned airplane empennage rudder face directly drives control device | |
| CN204070280U (en) | A kind of spherical rotating type transmission line of electricity bird-resistant | |
| CN205872376U (en) | Rocking arm formula chock | |
| CN105501434B (en) | Helicopter tail rotor bending moment operating mechanism | |
| CN109592014A (en) | A kind of general-purpose aircraft rudder pivot structure and method of operating | |
| CN207417129U (en) | A kind of unmanned plane rudder face driving structure | |
| CN204755199U (en) | Hydraulic pressure becomes oar bearing assembly | |
| CN105539821A (en) | Deformable folding structure of multi-rotor type aircraft | |
| CN109606631B (en) | Wing folding mechanism capable of being folded in large angle through linear driving and double rotation | |
| CN106516105A (en) | Aircraft propeller surface regulating mechanism | |
| CN207703441U (en) | A kind of big angle of attack pitching dynamic derivative testing adaptive excitation device | |
| CN205737690U (en) | A kind of syllogic drag link turns to linkage rod system | |
| CN206171816U (en) | Tail -rotor structure of unmanned helicopter | |
| CN206265303U (en) | A kind of aircraft oar face governor motion | |
| CN204433036U (en) | Without bulge aircraft aileron structure | |
| CN108032992A (en) | Agricultural unmanned plane blade pitch control mechanism | |
| CN202414155U (en) | Double-seesaw boss mechanism for helicopter | |
| CN109229420B (en) | Variable-pitch actuating structure of helicopter tail rotor test bed | |
| CN203765439U (en) | Double-row spherical surface superfinishing swing angle automatic adjusting mechanism | |
| CN219506240U (en) | Rotor head structure of double-rotor unmanned aerial vehicle | |
| CN207945217U (en) | A kind of joint arrangement |
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 |
Application publication date: 20190409 |
|
| WD01 | Invention patent application deemed withdrawn after publication |