CN106564614A - Aileron state locking method of aerobus A320 series type and aileron actuator cylinder lock - Google Patents
Aileron state locking method of aerobus A320 series type and aileron actuator cylinder lock Download PDFInfo
- Publication number
- CN106564614A CN106564614A CN201610936183.7A CN201610936183A CN106564614A CN 106564614 A CN106564614 A CN 106564614A CN 201610936183 A CN201610936183 A CN 201610936183A CN 106564614 A CN106564614 A CN 106564614A
- Authority
- CN
- China
- Prior art keywords
- aileron
- polished rod
- pressurized strut
- locked
- clamping block
- 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.)
- Withdrawn
Links
Landscapes
- Actuator (AREA)
Abstract
The invention relates to the technical field of aileron state locking of an aerobus A320 series type, in particular to an aileron state locking method of an aerobus A320 series type and an aileron actuator cylinder lock. The locking method comprises the following steps that under the conditions that an aileron is not powered on and hydraulic pressure is not applied, the aileron is turned upwards, a polished rod of an aileron actuator cylinder extends to the limit position, then the aileron actuator cylinder lock is mounted on the extending polished rod of the aileron actuator cylinder to prevent the polished rod from retracting, and the polished rod is locked at the limit position. According to the locking method, the aileron state can be simply and effectively locked under the conditions that during C check and the like, the aileron is not powered on and hydraulic pressure is not applied.
Description
Technical field
The present invention relates to Air Passenger A320 series model ailerons state locking technical field.
Background technology
As shown in figure 1, aileron 1 refers to the movable aerofoil of a fritter on the outside of the wingtip trailing edge of wing 2.For aircraft
It is motor-driven that rolling moment produced by the differential deflection of main operation rudder face, pilot guidance or so aileron 1 can make aircraft do roll.
Air Passenger A320 series aircrafts carry out C inspections when safeguarding, aileron is not powered on, does not apply hydraulic pressure, and now, aileron goes to naturally
Downward state.Require according to the production schedule, need to check aileron accordingly and part replacement.But aileron be in
Under state, maintenance channel can be taken, bring inconvenience to the work of maintainer.
Solve the above problems, typically there is following three scheme in prior art：
1) when maintainer works, the aileron that holds in the palm makes its upset upwards, to concede maintenance channel.
2) first aileron turned, concedes maintenance channel, carpet is then filled between wing and aileron, prevent aileron
It is flipped back to again come.
3) aileron is turned, concedes maintenance channel, the end of aileron and aileron pressurized strut is then withstood on using short circuit bar
Between head.
Above the first scheme, increases the difficulty of construction of maintainer, and consumes very much the muscle power of maintainer.Second
Plant and the third scheme, security is low.
The content of the invention
First goal of the invention of the present invention is to provide one kind and is not powered on, does not apply under hydraulic pressure conditions, the most in ailerons such as C inspections
The method of simple and effective locking aileron state.
Second goal of the invention of the present invention is to provide the aileron pressurized strut lock in a kind of enforcement said method.
First goal of the invention of the present invention is achieved through the following technical solutions：A kind of Air Passenger A320 series models aileron state
Locking means, comprise the steps：
It is not powered on, do not apply under hydraulic pressure conditions in aileron, aileron is overturn upwards, the polished rod for making aileron pressurized strut is elongated to
Extreme position, then by installing aileron pressurized strut lock on the polished rod that aileron pressurized strut extends, prevents polished rod retraction, will be described
Polished rod is locked in the extreme position.
Second goal of the invention of the present invention is achieved through the following technical solutions：A kind of aileron start in enforcement said method
Cylinder lock, aileron pressurized strut lock is the U-shaped clamping block for being installed on the polished rod of aileron pressurized strut elongation, the U-shaped
Least one set is provided with the relative two side of clamping block to perforation, the aileron pressurized strut lock also includes being worn for inserting described pair
Kong Zhong, so that by the spacing lock pin in the U-shaped clamping block of the polished rod, the aileron pressurized strut lock is arranged on the institute stretched out
When stating on polished rod, the polished rod retraction is prevented, the polished rod is locked in into the maximum extreme position of extension elongation.
Aileron is arranged on wing by aileron pressurized strut, and aileron spins upside down, and the polished rod of aileron pressurized strut is also stretched therewith
Long retraction, and when aileron upset is upwards, the polished rod of aileron pressurized strut is elongated to extreme position, and the present invention passes through aileron start
The polished rod of aileron pressurized strut is locked in extreme position by cylinder lock, prevents aileron state change.
The U-shaped clamping block rear end is provided with horizontal flanging.
The U-shaped clamping block two ends are installed by neonychium.
Compared to prior art, the present invention has the advantages that：
1) the inventive method on the polished rod that aileron pressurized strut extends by installing aileron pressurized strut lock by aileron pressurized strut
Polished rod is locked in extreme position, aileron state is locked with most simple and effective way, compared to the scheme 1 in background technology), this
Inventive method will not increase the difficulty of construction of maintainer, and can reduce the physical demands of maintainer, compared to scheme 2),
3), locking of the inventive method to aileron state, more reliable and more stable, safe；
2) effectively aileron pressurized strut polished rod can be locked in into the device of extreme position, aileron pressurized strut of the present invention as a kind of
Lockset has simple structure, and low cost is easy to use, the characteristics of stable to the locking of rudder, reliable.
Description of the drawings
The front view that Fig. 1 locks for the aileron pressurized strut of the specific embodiment of the invention；
The left view that Fig. 2 locks for the aileron pressurized strut of the specific embodiment of the invention；
Fig. 3 is the use state of the aileron pressurized strut lock of the specific embodiment of the invention with reference to figure.
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
As shown in figure 3, the present invention on the polished rod 31 that aileron pressurized strut 3 extends by installing special locking device ---
Aileron pressurized strut lock 4, is locked in the maximum extreme position of extension elongation, so as to lock aileron shape by the polished rod 31 of aileron pressurized strut 3
State, it is to avoid it is downwardly turned over.
As shown in Figure 1, 2, it is for being installed on aileron pressurized strut to the concrete structure of the aileron pressurized strut lock 4 of the present embodiment
An aluminum U-shaped clamping block on the polished rod 31 of 3 elongations, U-shaped clamping block rear end is provided with horizontal flanging, and U-shaped clamping block is relative
Two side length direction middle part is provided with one group to perforation 41, and aileron pressurized strut lock 4 also includes lock pin 42.
As shown in figure 3, aileron pressurized strut lock 4 is directly installed on the polished rod 31 of the elongation of aileron pressurized strut 3, using very square
Just, aileron pressurized strut is locked 4 rear ends and is offseted with the outer tube 32 of aileron pressurized strut 3, and the horizontal flanging of U-shaped clamping block rear end can increase
Aileron pressurized strut 3 and the contact area of outer tube 32, aileron pressurized strut is locked the 4 front ends termination 311 larger with the external diameter of polished rod 31 and is offseted,
Prevent polished rod 31 from bouncing back, polished rod 31 is locked in into the maximum extreme position of extension elongation.During lock pin 42 is inserted to perforation 41, by light
Bar 31 is spacing in U-shaped clamping block.
The one end of above-mentioned lock pin 42 can be fixed on U-shaped clamping block by steel wire rope, make aileron pressurized strut lock 4 be integrally formed formula
Structure.
U-shaped clamping block two ends can install neonychium, to reduce contact wear.
Claims (4)
1. a kind of Air Passenger A320 series models aileron state locking means, it is characterised in that comprise the steps：
It is not powered on, do not apply under hydraulic pressure conditions in aileron, aileron is overturn upwards, the polished rod for making aileron pressurized strut is elongated to the limit
Position, then by installing aileron pressurized strut lock on the polished rod that aileron pressurized strut extends, prevents polished rod retraction, by the polished rod
It is locked in the extreme position.
2. a kind of aileron pressurized strut implemented in claim 1 methods described is locked, it is characterised in that the aileron pressurized strut is locked and is
For the U-shaped clamping block being installed on the polished rod of aileron pressurized strut elongation, the U-shaped clamping block is provided with relative two side
Least one set to perforation, lock in also including for inserting described pair of perforation, so that the polished rod is spacing by the aileron pressurized strut
Lock pin in the U-shaped clamping block, when the aileron pressurized strut lock is arranged on the polished rod for stretching out, prevents the polished rod
Retraction, by the polished rod the maximum extreme position of extension elongation is locked in.
3. aileron pressurized strut according to claim 2 is locked, it is characterised in that the U-shaped clamping block rear end is provided with outside level
Flange.
4. aileron pressurized strut according to claim 3 is locked, it is characterised in that the U-shaped clamping block two ends.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610936183.7A CN106564614A (en) | 2016-11-01 | 2016-11-01 | Aileron state locking method of aerobus A320 series type and aileron actuator cylinder lock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610936183.7A CN106564614A (en) | 2016-11-01 | 2016-11-01 | Aileron state locking method of aerobus A320 series type and aileron actuator cylinder lock |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106564614A true CN106564614A (en) | 2017-04-19 |
Family
ID=58534511
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610936183.7A Withdrawn CN106564614A (en) | 2016-11-01 | 2016-11-01 | Aileron state locking method of aerobus A320 series type and aileron actuator cylinder lock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106564614A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108216683A (en) * | 2017-12-08 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of unlocking method for rotation class actuator failure protecting device |
| CN109649680A (en) * | 2018-12-05 | 2019-04-19 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of civil aircraft spoiler actuator ground maintenance safety convenience instrument |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6520067B1 (en) * | 2001-12-12 | 2003-02-18 | Michael H. Hunt | Hydraulic piston locking device |
| JP2004132495A (en) * | 2002-10-11 | 2004-04-30 | Furukawa Co Ltd | Stopper for cylinder of construction vehicle |
| JP2006168851A (en) * | 2004-12-13 | 2006-06-29 | Hitachi Constr Mach Co Ltd | Working machine |
| CN104776085A (en) * | 2015-04-02 | 2015-07-15 | 中船重工中南装备有限责任公司 | Buffered powerful machine self-locking hydraulic cylinder |
-
2016
- 2016-11-01 CN CN201610936183.7A patent/CN106564614A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6520067B1 (en) * | 2001-12-12 | 2003-02-18 | Michael H. Hunt | Hydraulic piston locking device |
| JP2004132495A (en) * | 2002-10-11 | 2004-04-30 | Furukawa Co Ltd | Stopper for cylinder of construction vehicle |
| JP2006168851A (en) * | 2004-12-13 | 2006-06-29 | Hitachi Constr Mach Co Ltd | Working machine |
| CN104776085A (en) * | 2015-04-02 | 2015-07-15 | 中船重工中南装备有限责任公司 | Buffered powerful machine self-locking hydraulic cylinder |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108216683A (en) * | 2017-12-08 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of unlocking method for rotation class actuator failure protecting device |
| CN108216683B (en) * | 2017-12-08 | 2021-05-07 | 中国航空工业集团公司成都飞机设计研究所 | Unlocking method for fault protection device of rotary actuator |
| CN109649680A (en) * | 2018-12-05 | 2019-04-19 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of civil aircraft spoiler actuator ground maintenance safety convenience instrument |
| CN109649680B (en) * | 2018-12-05 | 2022-04-19 | 中国航空工业集团公司西安飞行自动控制研究所 | Civil aircraft spoiler actuator ground maintenance safety guarantee device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109515683A (en) | A kind of Variable Geometry Wing of variable chord length and camber | |
| Lee et al. | Experimental investigation of simulated large-droplet ice shapes on airfoil aerodynamics | |
| WO2016116102A1 (en) | Multi-functional flap used as a back-flow flap | |
| DE602004002786T2 (en) | Wing with inflatable, fiber-reinforced device for altering the wing element | |
| CN106564614A (en) | Aileron state locking method of aerobus A320 series type and aileron actuator cylinder lock | |
| DE102009049049A1 (en) | Flow body especially for aircraft | |
| DE102010041111A1 (en) | Rotor blade with integrated passive surface flap | |
| CN104943850A (en) | Main wing retractable type fixed wing airplane | |
| CN208665533U (en) | A kind of small drone is risen and fallen frame locking means | |
| CN206394908U (en) | The pressurized strut of Air Passenger A320 series model ailerons is locked | |
| CN204507249U (en) | What be applied to undercarriage fault emergency rescue device embraces latch mechanism | |
| DE102015113347A1 (en) | Multifunctional flaps for improving energy efficiency and safety | |
| EP3191364B1 (en) | Aircraft having hydraulic support struts between fuselage and wings | |
| CN107444660A (en) | A kind of opening mechanism and deployment method of aircraft drag umbrella hatch door | |
| DE102013226935A1 (en) | Flow body, wing, aircraft and method for balancing aerodynamic loads | |
| CN106486918A (en) | A kind of portable down conductor reset erecting device and method | |
| DE102012108289A1 (en) | A rotor blade assembly and method of modifying the load characteristic of the rotor blade in a wind turbine | |
| CN109365719A (en) | Riveting guide-localization holder-on | |
| CN204895839U (en) | Light aerocraft all -moving wing | |
| DE102010014633A1 (en) | Wing assembly for airplane e.g. cargo aircraft, has wing adaptor section whose V-angle increases in specific degree from outer rib of wing base section to outer rib of wing adaptor section, where angle is produced along local span direction | |
| CN104590549A (en) | Device capable of preventing aircraft out of control from colliding mountains and flying toward oceans in air | |
| CN207791190U (en) | Tripod is fixed on a kind of adjustable ground for space shuttle | |
| CN109703758A (en) | Two-way all-wing aircraft flight vehicle aerodynamic shape and design method | |
| CN105509992A (en) | External store model system excitation method for flutter wind tunnel test | |
| DE102004019496B4 (en) | Wing for aircraft with engines |
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 | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20170419 |