CN102991667A - Spring swing arm assembly and application method thereof - Google Patents
Spring swing arm assembly and application method thereof Download PDFInfo
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- CN102991667A CN102991667A CN2011102725609A CN201110272560A CN102991667A CN 102991667 A CN102991667 A CN 102991667A CN 2011102725609 A CN2011102725609 A CN 2011102725609A CN 201110272560 A CN201110272560 A CN 201110272560A CN 102991667 A CN102991667 A CN 102991667A
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- rocking arm
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Abstract
The invention relates to a spring swing arm assembly comprising a supporting seat, a swing arm, and a spring. The swing arm is hinged with the supporting seat through a pin. Two ends of the reset spring are respectively fixed on spring fixing points of the supporting seat and the swing arm, such that a variable triangle is formed. The spring swing arm assembly can be used for opening an aircraft flap. The supporting seat is fixed on a plane body, and the flap is fixedly connected to the other end of the swing arm. A reset spring maximum extension length state is adopted as a swing arm power assistance point. The swing arm drives the flap to orbit between a positive limit state and a negative limit state on two sides of the power assistance point around the hinge point, such that the opening and closing the flap are realized.
Description
Technical field
The present invention relates to aeroplane structure design, (door, lid etc.) open method and (door, lid etc.) fields such as insurance measure when closing.
Background technology
The use of aircraft system equipment, especially driving engine, frequency of maintenance are all higher, system equipment, driving engine and annex thereof are safeguarded and are changed because being convenient to when the design of fuselage and engine nacelle, designed a large amount of maintenances and lid is installed.These lids can become according to the examination and maintenance Frequency Design of system equipment and driving engine corresponding site quick-release type.
At present, in the maintenance process of system equipment, driving engine and annex thereof, at first want the opening cover lock, again lid is opened to the angle that needs unlatching, then with strut lid is supported, make lid keep the state that is unlocked, begin at last handling labor.Therefore require to safeguard that lid must conveniently open and locking, require simultaneously to safeguard that lid is supported fixing after opening, and these requirements must be satisfied the characteristics of aircraft utilization, are exactly reliable and security insurance.The rocker arm assembly of present unlatching only plays hinge, and the position of strut also affected normally carrying out of handling labor, and control step is more, and handling labor is made troubles.
Summary of the invention
For the unlatching that solves the aircraft maintenance lid and remain on fixing holding state so that the carrying out of handling labor, the application's purpose is to disclose a kind of rocker arm assembly and using method thereof.
A kind of spring rocker arm assembly, contain bearing, rocking arm and spring, it is characterized in that described bearing has the stationary plane of a protrusion, described rocking arm is a rigid connecting rod; the termination of rocking arm is hinged by the stationary plane of bearing pin and bearing, also is provided with the first spring attachment point on the stationary plane of bearing, is provided with the second spring attachment point at the body of rod of rocking arm; described spring is a stretchable retracing spring, and its two ends are separately fixed on the first spring attachment point and the second spring attachment point.Hinge-point and the first spring attachment point, the second spring attachment point by rocking arm and bearing stationary plane have formed variable leg-of-mutton three summits.
A kind of using method of spring rocker arm assembly, use spring rocker arm assembly as claimed in claim 1 to open airplane hatch cover, bearing is fixed on the airframe, lid is fixedly connected on the other end of rocking arm, power-assisted point take the maximum development length state of retracing spring as rocking arm; rocking arm is around hinge-point moving between the just spacing state of power-assisted point both sides and negative spacing state; rocking arm is in power-assisted when putting the just spacing state of a side; connect lid and be in closed condition; when rocking arm is in the negative spacing state of power-assisted point opposite side, the connection lid is in opening.
In order to limit the moving scope of rocking arm, be respectively equipped with the rocking arm position-limited lever vertical with stationary plane at the stationary plane of bearing, comprise upper limit bar and lower limit bar.
The invention has the advantages that the spring rocker arm assembly utilizes the variable triangular structure of retracing spring composition novel reliable, the tension force of retracing spring has increased the damping insurance that lid is opened and supported, reduced the control step the when ground crew safeguards aircraft, improve aircraft maintenance efficient, alleviate rocker arm assembly and the open method of structural weight.
Below in conjunction with the embodiment accompanying drawing this application is described in further detail.
Description of drawings
Fig. 1 is the structural representation of rocker arm assembly
Fig. 2 is the deformation principle scheme drawing of rocker arm assembly
Fig. 3 is the state of kinematic motion scheme drawing of rocker arm assembly
Number description: 1. bearing; 2. rocking arm; 3. spring; 4. the first spring attachment point axle; 5. upper arresting pin; 6. lower limit pin; 7. the second spring attachment point axle; 8. bearing pin; 9. lid
The specific embodiment
Referring to accompanying drawing, in the enforcement, referring to Fig. 2, bearing 1, rocking arm 2 select LY12-BCZYU sheet material machinery to be processed into; Spring 3 is selected HB3-1-1 * 6 * 15II; The bearing pin 8 of the first spring attachment point axle 4 upper arresting pins 5 and lower limit pin 6, the second spring attachment point axle 7 and hinge-point is selected the 30CrMnSiA bar.
In the state of kinematic motion signal of Fig. 3 rocker arm assembly, see more clearly application advantage of the present invention, during concrete the application, power-assisted point take the maximum development length state of retracing spring as rocking arm or be called the dead point; rocking arm is around hinge-point moving between the just spacing state of power-assisted point both sides and negative spacing state; rocking arm is in power-assisted when putting the just spacing state of a side; rocking arm 2 contact with upper arresting pin 5; the connection lid is in closed condition; when rocking arm is in the negative spacing state of power-assisted point opposite side; rocking arm 2 contacts with lower limit pin 6, and the connection lid is in opening.
Rocking arm 2 is in just spacing state; rocking arm 2 contacts with upper arresting pin 5; lid 9 is closed fully; the motion process of opening lid is that under the effect of external force, rocking arm 2 is around bearing pin 8 clickwises; spring 3 clockwise rotates around its centre of gration first spring attachment point under the drive of rocking arm 2; length of spring 3 is elongated gradually, and when the length of spring 3 fades to when the longest, three-link mechanism is in power-assisted point position; Rocking arm 2 continues around bearing pin 8 clickwises, three-link mechanism will be by the power-assisted point, spring 3 length shorten gradually, this moment is only under the boosting of spring force; rocking arm 2 will continue automatically to clockwise rotate, until lower limit pin 6 contacts with rocking arm 2, restriction rocking arm 2 is rotated further; rocking arm 2 is in the lower limit state, realizes fully unlatching and the lifting of lid.
The closing process of lid just in time is the inverse process of the opening process of lid, and the retracing spring counterpart was built castering action when lid that different is was opened fully, no longer by parts such as struts; And lid when closing fully spring lid is applied predetermincd tension, can reduce the vibration of lid in the aircraft flight process, reduce the probability that crackle produces, and closing of lid played safety effect, even in the situation that the lid lock lost efficacy, lid can not be unlocked yet.
In implementation process, the rigging position of rocker arm assembly can appropriately adjust as the case may be.As: the opening angle of lid can be regulated by the position of upper arresting pin 5 and lower limit pin 6, or limit pin hole is made slotted hole, replaces locating dowel pin with bolt, pad and nut; The length of spring can be regulated by the position of the hinge-point of spring attachment point and rocking arm and fixed body; Therefore formed another feature of rocker arm assembly: flexibly with general.
Claims (5)
1. spring rocker arm assembly, contain bearing; rocking arm and spring; it is characterized in that described bearing has the fixed body of a protrusion; described rocking arm is a rigid connecting rod; the termination of rocking arm is hinged by the fixed body of bearing pin and bearing; also be provided with the first spring attachment point on the fixed body of bearing; the body of rod at rocking arm is provided with the second spring attachment point; described spring is a stretchable retracing spring; its two ends are separately fixed on the first spring attachment point and the second spring attachment point, by hinge-point and the first spring attachment point of rocking arm and bearing fixed body; the second spring attachment point has formed variable leg-of-mutton three summits.
2. spring rocker arm assembly as claimed in claim 1 is characterized in that being respectively equipped with the rocking arm position-limited lever vertical with stationary plane at the stationary plane of described bearing.
3. spring rocker arm assembly as claimed in claim 1 or 2 is characterized in that described rocking arm is half frame type pipe link of a rigidity, but in the other end captive joint lid of rocking arm.
4. spring rocker arm assembly as claimed in claim 3, it is characterized in that described the first spring attachment point has one perpendicular to the first minor axis of bearing stationary plane, the second spring attachment point also has one perpendicular to the second minor axis of rocking arm body, described retracing spring is the spring of two parastates, is separately fixed between the first minor axis and the second minor axis.
5. the using method of a spring rocker arm assembly, it is characterized in that using spring rocker arm assembly as claimed in claim 1 to open airplane hatch cover, bearing is fixed on the airframe, lid is fixedly connected on the other end of rocking arm, power-assisted point take the maximum development length state of retracing spring as rocking arm; rocking arm is around hinge-point moving between the just spacing state of power-assisted point both sides and negative spacing state; rocking arm is in power-assisted when putting the just spacing state of a side; connect lid and be in closed condition; when rocking arm is in the negative spacing state of power-assisted point opposite side, the connection lid is in opening.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011102725609A CN102991667A (en) | 2011-09-14 | 2011-09-14 | Spring swing arm assembly and application method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011102725609A CN102991667A (en) | 2011-09-14 | 2011-09-14 | Spring swing arm assembly and application method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102991667A true CN102991667A (en) | 2013-03-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011102725609A Pending CN102991667A (en) | 2011-09-14 | 2011-09-14 | Spring swing arm assembly and application method thereof |
Country Status (1)
| Country | Link |
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| CN (1) | CN102991667A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184702A (en) * | 2016-09-23 | 2016-12-07 | 江西洪都航空工业集团有限责任公司 | Waterproof quick-release combination lid |
| CN106697254A (en) * | 2017-01-05 | 2017-05-24 | 江苏美龙振华科技有限公司 | Ditching stopping mechanism for airplane cabin door ventilator hole cover |
| CN107054620A (en) * | 2017-03-30 | 2017-08-18 | 江苏美龙振华科技有限公司 | A kind of hatch door lifts power assisting device |
| CN110723272A (en) * | 2019-11-12 | 2020-01-24 | 中航电测仪器股份有限公司 | Power-assisted buffering reel device for boarding door |
| CN112373671A (en) * | 2020-12-12 | 2021-02-19 | 江西洪都航空工业集团有限责任公司 | Semi-active cabin door upper lock |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2085842U (en) * | 1990-06-05 | 1991-10-02 | 章林 | Spring door closer |
| CN2224893Y (en) * | 1995-03-31 | 1996-04-17 | 王玉洲 | Door shutter |
| CN202249390U (en) * | 2011-09-14 | 2012-05-30 | 西安飞机工业（集团）有限责任公司 | Spring rocker assembly |
-
2011
- 2011-09-14 CN CN2011102725609A patent/CN102991667A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2085842U (en) * | 1990-06-05 | 1991-10-02 | 章林 | Spring door closer |
| CN2224893Y (en) * | 1995-03-31 | 1996-04-17 | 王玉洲 | Door shutter |
| CN202249390U (en) * | 2011-09-14 | 2012-05-30 | 西安飞机工业（集团）有限责任公司 | Spring rocker assembly |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184702A (en) * | 2016-09-23 | 2016-12-07 | 江西洪都航空工业集团有限责任公司 | Waterproof quick-release combination lid |
| CN106697254A (en) * | 2017-01-05 | 2017-05-24 | 江苏美龙振华科技有限公司 | Ditching stopping mechanism for airplane cabin door ventilator hole cover |
| CN106697254B (en) * | 2017-01-05 | 2023-08-11 | 江苏美龙振华科技有限公司 | Water forced landing blocking mechanism of airplane cabin door ventilating cover |
| CN107054620A (en) * | 2017-03-30 | 2017-08-18 | 江苏美龙振华科技有限公司 | A kind of hatch door lifts power assisting device |
| CN107054620B (en) * | 2017-03-30 | 2023-09-01 | 江苏美龙振华科技有限公司 | Cabin door lifting power assisting device |
| CN110723272A (en) * | 2019-11-12 | 2020-01-24 | 中航电测仪器股份有限公司 | Power-assisted buffering reel device for boarding door |
| CN112373671A (en) * | 2020-12-12 | 2021-02-19 | 江西洪都航空工业集团有限责任公司 | Semi-active cabin door upper lock |
| CN112373671B (en) * | 2020-12-12 | 2022-07-22 | 江西洪都航空工业集团有限责任公司 | Semi-active cabin door up lock |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130327 |