CN101481017B - Safeguard structure of passenger plane service for exploding and cutting hinge flap during emergency opening - Google Patents
Safeguard structure of passenger plane service for exploding and cutting hinge flap during emergency opening Download PDFInfo
- Publication number
- CN101481017B CN101481017B CN2009100250627A CN200910025062A CN101481017B CN 101481017 B CN101481017 B CN 101481017B CN 2009100250627 A CN2009100250627 A CN 2009100250627A CN 200910025062 A CN200910025062 A CN 200910025062A CN 101481017 B CN101481017 B CN 101481017B
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- protective layer
- passenger plane
- exploding
- fail
- emergency opening
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Abstract
The invention discloses a protecting structure of an exploding and cutting hinge plate when a passenger airplane service module door is opened in emergency in the air. The protecting structure comprises a protecting layer, cutter installing grooves and a shoulder hole, wherein the cutter installing grooves are symmetrically arranged on both side surfaces of the hinge plate, the protecting layer is covered on the cutter installing grooves, and the shoulder hole which is used for arranging an energy magnifying device in an explosion system is arranged on the protecting layer. The contact type installing method of the invention is beneficial for limiting explosion time effect in a minimum range, and the protecting structure has a small shape, is suitable for the characteristic of the small space in the module and ensures convenient and reliable installation and reliable cutting effect.
Description
Technical field
The fail-safe structure of blast cutting hinge flap when the present invention relates to the aerial emergency opening of a kind of passenger plane service cabin door.
Background technology
According to the 15 article of (four) regulation of CCAR-21R2 " civil aviation product and parts qualified authorization regulation " " except that aerodone or manned balloon; the applicant has all taked enough measures in the time of should proving each flight test, so that the group membership that takes a flight test can emergency escape and use parachute; ".For guaranteeing aircraft group membership's the safety of taking a flight test in the process of taking a flight test, need also assembling " ARJ21-700 aircraft aerial main cabin emergency pressure relief and service door open system " in the aircraft of taking a flight test of development.
This system adopts the precision blasting technology, the emergency pressure relief in the realization high-speed flight passenger plane cabin and the quick unlatching of service cabin door.Need to adopt line style blast cutting technique forming the pressure release hole on the nacelle rear covering, cutting off hinge and snap close on the service cabin door, remove of the constraint of fuselage doorframe, so that the quick unlatching of service cabin door to service cabin door.Because the space is narrow and small relatively in the passenger plane cabin, the group of taking a flight test personnel are apart from the closest range of blast cut point only about 2m, therefore, must effectively protect the shock wave of jet cutter generation, noise, metal flying etc.
Summary of the invention
Goal of the invention: service cabin door flap architectural feature when the objective of the invention is at the aerial emergency opening of passenger plane service cabin door, corresponding safe, reliable, efficient contact integrated protection structure is provided, and this structure also is applicable to the safety precaution of implementing the cutting of line style amplitude transformer under other like environment.
Technical scheme: in order to realize the foregoing invention purpose, the technical solution used in the present invention is:
According to service cabin door flap architectural feature and split requirement, and consider reliable, the comfort feature that installs and fixes, designed a kind of integrated protection structure, this fail-safe structure is formed by protecting and installing and fixing two-part structure, generally should be integral type, also can be split type, but must mortise.
The fail-safe structure of blast cutting hinge flap during the aerial emergency opening of a kind of passenger plane service cabin door, this fail-safe structure comprises protective layer, cutter mounting groove and stepped hole; Symmetry is provided with two cutter mounting grooves on two sides of flap; Described protective layer covers on this cutter mounting groove; On described protective layer, be provided with the stepped hole of the energy amplifying device that is used for being provided with initiation system.
Described protective layer has two, connects with connecting hinge at the one end, connects with stress bolt at the other end.
In described cutter mounting groove, be provided with jet cutter.
The basal surface of described protective layer and jet cutter all fits tightly with the flap of service cabin door.
This fail-safe structure is made up of two cuboids that have the cutter mounting groove, two protective layers are symmetricly set on two sides of service cabin door flap, the connection hinge of two protective layers has guaranteed the symmetry of jet cutter mounting groove, and the basal surface of protective layer and jet cutter all fits tightly with the flap of service cabin door; Stress bolt is broken in jet cutter blast back, and whole device by gravity comes off automatically, has guaranteed follow-up hatch door is promoted not produce any obstacle.
Above-mentioned protective layer is made by the composite material that adhering with epoxy resin forms by being primary raw material with carbon cloth, natural rubber, Kafra fiber cloth.
Beneficial effect: the fail-safe structure of blast cutting hinge flap during the aerial emergency opening of passenger plane service cabin door of the present invention, contact mounting means help the inferior effect limits of blast in minimum zone; The body of fail-safe structure is little, has adapted to the narrow and small characteristics in space in the cabin; Guaranteed that convenience, the failure-free installed also guaranteed the failure-free cutting effect simultaneously.Little, the good looking appearance of the body of fail-safe structure.
Description of drawings
Fig. 1 is a fail-safe structure scheme drawing of the present invention.
Fig. 2 is the cutaway view of fail-safe structure of the present invention.
Fig. 3 is the vertical view cutaway drawing of fail-safe structure of the present invention.
The specific embodiment
Below in conjunction with accompanying drawing the present invention is done further explanation.
The flap cross dimensions of ARJ21-700 passenger plane service cabin door is 70 * 15.9mm, by import aviation made from aluminium profile.
As Fig. 1, Fig. 2 and shown in Figure 3, the fail-safe structure of blast cutting hinge flap during for the aerial emergency opening of passenger plane service cabin door of the present invention.The guard section of this fail-safe structure is made up of two cuboids that have the cutter mounting groove, wherein: 1 is protective layer, 2 is the cutter mounting groove, 3 for being cut member, be flap, 5 for connecting the hinge of two protection bodies, and 6 is stress bolt, 4 is stepped hole, is used for being provided with the energy amplifying device of initiation system.
Two protective layers 1 are symmetricly set on two sides of service cabin door flap 3, and the connection hinge 5 of two protective layers has guaranteed the symmetry of jet cutter mounting groove 2, and the basal surface of protective layer 1 and jet cutter all fits tightly with the flap 3 of service cabin door; Stress bolt 6 is broken in jet cutter blast back, and whole device by gravity comes off automatically, has guaranteed follow-up hatch door is promoted not produce any obstacle
Every protection height of this protective layer 1 is 170mm, and protective layer 1 thickness is 24mm, wide 40mm; The radius of cutter mounting groove 2 is 7mm, and stress bolt 6 diameters are 4mm.Protective layer 1 is made by the composite material that adhering with epoxy resin forms by being primary raw material with carbon cloth, natural rubber, Kafra fiber cloth.
Through test, this protective device has adapted to the constructional feature of service cabin door hinge, can effectively block the blast impulse wave propagation and reduce noise.
Claims (1)
1. the fail-safe structure of blast cutting hinge flap during the aerial emergency opening of a passenger plane service cabin door, this fail-safe structure comprises protective layer (1), cutter mounting groove (2) and stepped hole (4); Symmetry is provided with two cutter mounting grooves (2) on two sides of flap; Described protective layer (1) covers on this cutter mounting groove (2); Be provided with the stepped hole (4) of the energy amplifying device that is used for being provided with initiation system on described protective layer (1), it is characterized in that: described protective layer (1) has two, connects with connecting hinge (5) at the one end, connects with stress bolt (6) at the other end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100250627A CN101481017B (en) | 2009-02-16 | 2009-02-16 | Safeguard structure of passenger plane service for exploding and cutting hinge flap during emergency opening |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100250627A CN101481017B (en) | 2009-02-16 | 2009-02-16 | Safeguard structure of passenger plane service for exploding and cutting hinge flap during emergency opening |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101481017A CN101481017A (en) | 2009-07-15 |
| CN101481017B true CN101481017B (en) | 2010-06-02 |
Family
ID=40878348
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009100250627A Expired - Fee Related CN101481017B (en) | 2009-02-16 | 2009-02-16 | Safeguard structure of passenger plane service for exploding and cutting hinge flap during emergency opening |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101481017B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102211659B (en) * | 2011-05-04 | 2013-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Explosive cutting rope protection method for airframe truss or frame structure |
| CN109573077B (en) * | 2019-02-01 | 2023-09-01 | 中国工程物理研究院流体物理研究所 | Aircraft antiknock structure and design method thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4407468A (en) * | 1981-04-30 | 1983-10-04 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Explosively activated egress area |
| US4649825A (en) * | 1984-06-25 | 1987-03-17 | The United States Of America As Represented By The Secretary Of The Navy | Explosive separation system for composite materials |
| US5170004A (en) * | 1991-08-05 | 1992-12-08 | Teledyne Industries, Inc. | Hydraulic severance shaped explosive |
| CN1238256A (en) * | 1998-04-09 | 1999-12-15 | 瑟泰姆阿姆斯特丹公司 | Collapsible panel and method for controlled callapsing thereof |
-
2009
- 2009-02-16 CN CN2009100250627A patent/CN101481017B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4407468A (en) * | 1981-04-30 | 1983-10-04 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Explosively activated egress area |
| US4649825A (en) * | 1984-06-25 | 1987-03-17 | The United States Of America As Represented By The Secretary Of The Navy | Explosive separation system for composite materials |
| US5170004A (en) * | 1991-08-05 | 1992-12-08 | Teledyne Industries, Inc. | Hydraulic severance shaped explosive |
| CN1238256A (en) * | 1998-04-09 | 1999-12-15 | 瑟泰姆阿姆斯特丹公司 | Collapsible panel and method for controlled callapsing thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101481017A (en) | 2009-07-15 |
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| PB01 | Publication | ||
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| C14 | Grant of patent or utility model | ||
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100602 Termination date: 20180216 |