CN106218856A - A kind of airplane hatch cover opener - Google Patents
A kind of airplane hatch cover opener Download PDFInfo
- Publication number
- CN106218856A CN106218856A CN201610843678.5A CN201610843678A CN106218856A CN 106218856 A CN106218856 A CN 106218856A CN 201610843678 A CN201610843678 A CN 201610843678A CN 106218856 A CN106218856 A CN 106218856A
- Authority
- CN
- China
- Prior art keywords
- push rod
- regulating sleeve
- gusset plate
- spring
- hatch cover
- 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.)
- Granted
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Closures For Containers (AREA)
Abstract
The invention discloses a kind of airplane hatch cover opener, it includes spacing gusset plate and the pre-tightening mechanism that push rod is connected with fuselage frame, it is characterized in that, the middle and upper part of described push rod is provided with boss, the upper end of push rod passes spacing gusset plate, and by spacing gusset plate upper limit, described pre-tightening mechanism includes spring and regulating sleeve, regulating sleeve is connected with fuselage base plate, and spring housing is located between the boss of push rod and regulating sleeve.Present configuration is simple, failure rate is low, facilitate implementation, using spring and push rod is the main body of opener, and regulated the unlatching moment of push rod by regulating sleeve, with the restrained condition of airplane hatch cover self as control condition, it is not necessary to extra complex control system just can realize work.
Description
Technical field
The invention belongs to field of airplane structure, relate to a kind of airplane hatch cover opener.
Background technology
Lid is widely used in aircraft circles, for the use of aircraft, safeguard in need to check, repair, adjust, fill out
The equipment that fills, decompose or change, adnexa, housing construction is respectively provided with lid.Usually requiring that when aircraft is shut down, no matter undercarriage is in
Which kind of compressive state, all of lid all should be able to be normally-open.Need a kind of reliable and stable lid opener auxiliary lid
Open.Lid opener uses increasingly popular on current aircraft, especially the invisbile plane of a new generation, and its execution adds in the air
It is required for reliable lid opener when oil or combat mission, but is applied to the usual structure of lid opener of advanced opportunity of combat
Form is complicated, and control system complexity is higher, and working service is relatively costly, it is impossible to be suitably applied in some special duty
On dopey or SUAV.For middle dopey or SUAV, some special task lids need flying
Opening in row, even some lid requires to throw, and such as drag parachute lid, Landing Buffer equipment lid, sheds smoke signal lid
Deng.This type of lid needs a set of simple in construction, failure rate is low, the lid opener that facilitates implementation.
Summary of the invention
It is an object of the invention to optimize the deficiency of existing production technology, adapt to reality need, it is provided that a kind of airplane hatch cover
Opener.
In order to realize the purpose of the present invention, the technical solution used in the present invention is:
A kind of airplane hatch cover opener, it includes spacing gusset plate and pre-tightening mechanism, the described push rod that push rod is connected with fuselage frame
Middle and upper part be provided with boss, the upper end of push rod passes spacing gusset plate, and by spacing gusset plate upper limit, described pre-tightening mechanism includes
Spring and regulating sleeve, regulating sleeve is connected with fuselage base plate, and spring housing is located between the boss of push rod and regulating sleeve.
Further, described regulating sleeve has two sets, and two set regulating sleeves are setting up and down, and often set regulating sleeve is by two semicircles
Sleeve forms, and two and half round busses are jointly to push rod regulation locking, and assem-bly facing of said two half round buss is equipped with screw
Hole, two and half round busses are connected by screw and self-locking nut.
Further, described push rod being arranged with buffer rubber gasket, buffer rubber gasket is located at the boss of spacing gusset plate and push rod
Between.
Further, described push rod being also arranged with two packing rings, two packing rings are respectively arranged on the two ends of spring.
The beneficial effects of the present invention is:
1. present configuration is simple, failure rate is low, facilitate implementation, and using spring and push rod is the main body of opener, and passes through
Regulating sleeve regulates the unlatching moment of push rod, with the restrained condition of airplane hatch cover self as control condition, it is not necessary to extra answers
Miscellaneous control system just can realize work,
2. use packing ring and rubber blanket that mechanism is protected, improve the service life of mechanism.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the side view of the present invention；
Fig. 3 is the structural representation of push rod of the present invention；
Fig. 4 is the structural representation of regulating sleeve；
In figure；Lid 1, fuselage frame 2, push rod 3, spacing gusset plate 4, buffer rubber gasket 5, packing ring 6, spring 7, regulating sleeve 8, even
Fitting 9, self-locking nut 10.
Detailed description of the invention
The present invention is further described with embodiment below in conjunction with the accompanying drawings:
Embodiment: see Fig. 1 Fig. 2.
A kind of airplane hatch cover opener, it includes spacing gusset plate 4 and the pre-tightening mechanism that push rod 3 is connected with fuselage frame 2,
Lid 1 is present invention object to be opened, and fuselage frame 2 is the installation site of the present invention, and push rod 3 and spring 7 are the present invention's
Groundwork component, push rod 3 reliablely and stablely opens lid under the effect of spring 7, and the middle and upper part of push rod 3 is provided with boss, top
The upper end of bar 3 passes spacing gusset plate 4, and by spacing gusset plate 4 upper limit, spacing gusset plate 4 is then by connector 9 and fuselage frame 2
Connect,
Pre-tightening mechanism includes spring 7 and regulating sleeve 8, and regulating sleeve 8 is connected with fuselage base plate, and spring 7 is set in the convex of push rod 3
Between platform and regulating sleeve 8.
Spacing gusset plate 4 and regulating sleeve 8 are for regulating the spring active force to push rod, i.e. regulation push rod provides to lid
Open moment.Spacing gusset plate 4 is used for regulating incipient opening force square, selects spacing angle in the range of spring 7 its length allows
The setting height(from bottom) of sheet 4, determines the initial compression amount of spring, after mechanism installs, also can choose to install tune according to job demand
Joint sleeve, it is achieved the lid after mechanism is installed opens torque adjusting, to this end, regulating sleeve 8 has two sets, two set regulating sleeves 8
Setting up and down, often set regulating sleeve 8 is made up of two and half round busses, and two and half round busses are jointly to push rod 3 regulation locking, described
Assem-bly facing of two and half round busses is equipped with screw hole, and two and half round busses are connected by screw and self-locking nut 10.(such as figure
3).
Being arranged with buffer rubber gasket 5 and two packing rings 6 on described push rod 3, buffer rubber gasket 5 is located at spacing gusset plate 4 and top
Between the boss of bar 3, one of them packing ring 6 is located between the boss of push rod 3 and spring 7, and another packing ring 6 is located at regulating sleeve
Between 8 and spring 7, buffer rubber gasket 5 and two packing rings 6 are for improving reliability and the service life of mechanism.Airplane hatch cover
Constraint release time spring 7 constraint also moment release, now push rod 3 will produce shock loading on spacing gusset plate 4, this kind load
The service life of mechanism will be brought very adverse influence by lotus, and buffer rubber gasket 5 is used for buffering this shock loading, can be effective
Improve the service life of mechanism.Two packing rings 6 are installed on spring 7 two ends, for increasing the contact area of both ends of the spring, can have
Effect improves push rod 3 convex platform (such as Fig. 2) and the service life of regulating sleeve 8.
Push rod 3 is pressed into fuselage interior by the constraint of lid self under non-opening by lid of the present invention, now spring 7
Being in compressive state, when lid needs to open, release the constraint of lid, lid is ejected under the effect of spring 7 by push rod 3, as
This can ensure that lid is normally-open.Mechanism is not only simple in structure, failure rate is low, facilitate implementation.Additionally, the present invention is also equipped with mouth
Lid opens that moment is adjustable, security reliability high has longer service life, installation form can the characteristics of three aspects such as selection flexibly.
Claims (4)
1. an airplane hatch cover opener, it includes spacing gusset plate (4) and the pretightening machine that push rod (3) is connected with fuselage frame (2)
Structure, it is characterised in that the middle and upper part of described push rod (3) is provided with boss, the upper end of push rod (3) passes spacing gusset plate (4), and passes through
Spacing gusset plate (4) upper limit, described pre-tightening mechanism includes spring (7) and regulating sleeve (8), regulating sleeve (8) and fuselage base plate
Connecting, spring (7) is set between the boss of push rod (3) and regulating sleeve (8).
A kind of airplane hatch cover opener the most according to claim 1, it is characterised in that described regulating sleeve (8) has two
Set, two sets regulating sleeve (8) are setting up and down, often overlap regulating sleeve (8) and are made up of two and half round busses, and two and half round busses are common
To push rod (3) regulation locking, assem-bly facing of said two half round buss is equipped with screw hole, and two and half round busses pass through screw
And self-locking nut (10) connects.
A kind of airplane hatch cover opener the most according to claim 1 and 2, it is characterised in that described push rod (3) is upper sheathed
Buffer rubber gasket (5), buffer rubber gasket (5) is had to be located between the boss of spacing gusset plate (4) and push rod (3).
A kind of airplane hatch cover opener the most according to claim 1 and 2, it is characterised in that described push rod also overlaps on (3)
Being provided with two packing rings (6), two packing rings (6) are respectively arranged on the two ends of spring (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610843678.5A CN106218856B (en) | 2016-09-23 | 2016-09-23 | A kind of airplane hatch cover opener |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610843678.5A CN106218856B (en) | 2016-09-23 | 2016-09-23 | A kind of airplane hatch cover opener |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106218856A true CN106218856A (en) | 2016-12-14 |
| CN106218856B CN106218856B (en) | 2018-05-04 |
Family
ID=58076736
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610843678.5A Active CN106218856B (en) | 2016-09-23 | 2016-09-23 | A kind of airplane hatch cover opener |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106218856B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444660A (en) * | 2017-07-04 | 2017-12-08 | 西安飞机工业（集团）有限责任公司 | A kind of opening mechanism and deployment method of aircraft drag umbrella hatch door |
| CN107618652A (en) * | 2017-09-11 | 2018-01-23 | 珠海天晴航空航天科技有限公司 | A kind of unmanned plane lid quick-release structure and jacking system |
| CN113525665A (en) * | 2021-08-08 | 2021-10-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Self-opening aircraft flap structure |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2094308C1 (en) * | 1995-05-24 | 1997-10-27 | Ракетно-космическая корпорация "Энергия" им.С.П.Королева | Hatch cover of thermostatic control system |
| CN201427610Y (en) * | 2009-05-27 | 2010-03-24 | 比亚迪股份有限公司 | Engine compartment cover supporting rod mechanism |
| US20130284855A1 (en) * | 2011-10-18 | 2013-10-31 | Airbus Operations Gmbh | Guiding mechanism for opening and closing a cargo door of an aircraft, aircraft with such a guiding mechanism and method for opening and closing a cargo door of an aircraft |
| CN204937466U (en) * | 2015-08-19 | 2016-01-06 | 中航航空服务保障(天津)有限公司 | The reliable strut of high strength |
| CN105329436A (en) * | 2015-11-17 | 2016-02-17 | 江西洪都航空工业集团有限责任公司 | Covering cap brace device |
| CN206125398U (en) * | 2016-09-23 | 2017-04-26 | 江西洪都航空工业集团有限责任公司 | Aircraft flap opening mechanism |
-
2016
- 2016-09-23 CN CN201610843678.5A patent/CN106218856B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2094308C1 (en) * | 1995-05-24 | 1997-10-27 | Ракетно-космическая корпорация "Энергия" им.С.П.Королева | Hatch cover of thermostatic control system |
| CN201427610Y (en) * | 2009-05-27 | 2010-03-24 | 比亚迪股份有限公司 | Engine compartment cover supporting rod mechanism |
| US20130284855A1 (en) * | 2011-10-18 | 2013-10-31 | Airbus Operations Gmbh | Guiding mechanism for opening and closing a cargo door of an aircraft, aircraft with such a guiding mechanism and method for opening and closing a cargo door of an aircraft |
| CN204937466U (en) * | 2015-08-19 | 2016-01-06 | 中航航空服务保障(天津)有限公司 | The reliable strut of high strength |
| CN105329436A (en) * | 2015-11-17 | 2016-02-17 | 江西洪都航空工业集团有限责任公司 | Covering cap brace device |
| CN206125398U (en) * | 2016-09-23 | 2017-04-26 | 江西洪都航空工业集团有限责任公司 | Aircraft flap opening mechanism |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444660A (en) * | 2017-07-04 | 2017-12-08 | 西安飞机工业（集团）有限责任公司 | A kind of opening mechanism and deployment method of aircraft drag umbrella hatch door |
| CN107618652A (en) * | 2017-09-11 | 2018-01-23 | 珠海天晴航空航天科技有限公司 | A kind of unmanned plane lid quick-release structure and jacking system |
| CN107618652B (en) * | 2017-09-11 | 2024-04-02 | 珠海天晴航空航天科技有限公司 | Unmanned aerial vehicle flap quick-release structure and jacking device |
| CN113525665A (en) * | 2021-08-08 | 2021-10-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Self-opening aircraft flap structure |
| CN113525665B (en) * | 2021-08-08 | 2024-06-11 | 中国航空工业集团公司沈阳飞机设计研究所 | Self-opening aircraft flap structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106218856B (en) | 2018-05-04 |
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