US3782284A - Aircrew escape systems - Google Patents

Aircrew escape systems Download PDF

Info

Publication number
US3782284A
US3782284A US00227433A US3782284DA US3782284A US 3782284 A US3782284 A US 3782284A US 00227433 A US00227433 A US 00227433A US 3782284D A US3782284D A US 3782284DA US 3782284 A US3782284 A US 3782284A
Authority
US
United States
Prior art keywords
cord
sheath
flat
blast
lead
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.)
Expired - Lifetime
Application number
US00227433A
Inventor
R Gibb
G Galton
D Shepherd
D Smith
G Wickenden
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BAE Systems PLC
UK Secretary of State for Defence
Original Assignee
UK Secretary of State for Defence
Hawker Siddeley Aviation Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by UK Secretary of State for Defence, Hawker Siddeley Aviation Ltd filed Critical UK Secretary of State for Defence
Application granted granted Critical
Publication of US3782284A publication Critical patent/US3782284A/en
Assigned to BRITISH AEROSPACE PUBLIC LIMITED COMPANY reassignment BRITISH AEROSPACE PUBLIC LIMITED COMPANY CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). EFFECTIVE JAN. 2, 1981 Assignors: BRITISH AEROSPACE LIMITED
Assigned to BRITISH AEROSPACE reassignment BRITISH AEROSPACE ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: HAWKER SIDDELEY AVIATION LIMITED
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • B64C1/32—Severable or jettisonable parts of fuselage facilitating emergency escape

Definitions

  • ABSTRACT A detonating cord for causing fracture and break-up of an aircraft cockpit canopy for the purpose of emergency escape, consisting of an explosive core contained in a lead casing and surrounded by a plastic sheath, the cord being of substantially semicircular or D-shaped cross-section.
  • the semi-circular surface, but not the flat face, of the casing has several layers of lead tape applied to it within the plastic sheath which lead tape acts asblast-containing and reflecting material to direct the blast effect of the detonation preferentially through the flat-face.
  • an explosive cord device known as 'Miniature Detonating Cord or MDC, may be employed to cause fracture and break-up of the canopy transparency, or at least that area of it through which the aircrew member will pass.
  • the detonating cord is given a cross-sectional form having at least one flat, and there is embodied within the cord construction at least one layer of blast-containing and reflecting material which extends all around the explosive core of the cord except where the flat lies, so that the blast effect from detonation is directed preferentially through the region of the cord periphery constituted by said flat.
  • the cord is of semi-circular or D-section and the blast-containing and reflecting material is in the form of lead tape applied in layers to the curved portion of the outer surface of a lead casing containing the explosive core.
  • the flat provides a convenient base surface by means of which the cord can be adhered to the canopy transparency and gives a directional effect to the blast because the air to transparency path is eliminated.
  • the explosive filling 42 of the cord is contained within a formed lead casing 43 semi-circular in cross-section. This can be produce by flattening one side of the circular form resulting from a rolling operation. Attached only to the curved semicircular portion of the periphery of the lead casing are a number of lead tapes 44 adhesively secured one upon the other, and the whole assembly is contained within a heat-shrinkable plastic sheath 45 with adhesive 46 interposed between the sheath and the flat face of the lead case 43.
  • the build-up of the adhesive tape provides a backing such that, although there will still be a tendency to radial blast losses, the presence of the lead tape, or any other suitable backing material capable of providing the desired blast retention and reflection, will ensure an increased concentration of the blast effect in the direction of the flat face, which is the face applied contiguously to the canopy surface.
  • This form of MDC may be laid in a pattern on selected areas of canopy surface thus providing for a more predictable fracture. As it is not necessary to contain this present type of cord within a back-up extrusion such as is described in our aforementioned patent application, the vision loss through a canopy with a pattern-applied MDC will be minimal.
  • a detonating cord for producing fracture and break-up of an aircraft cockpit canopy for the purpose of emergency escape comprising an explosive core and a completely enclosing sheath surrounding said core, said core and sheath jointly possessing a cross-sectional fonn having at least one flat, and wherein there is embodied in the cord within the sheath at least one layer of metallic blast-containing and reflecting material which extends all around the explosive core of the cord except where the flat lies, whereby the blast effect from detonation is directed preferentially through the region of the cord periphery constituted by said flat.
  • cord according to claim 1 wherein the cord is of substantially semi-circular or D-cross-section.
  • a cord according to claim 1, wherein the blastcontaining and reflecting material is, at least in part, in the form of lead tape applied in layers.
  • a cord according to claim 1 having its flat face held in contiguity with a canopy surface, e.g. by adhe- SlVe.

Abstract

A detonating cord is provided, for causing fracture and break-up of an aircraft cockpit canopy for the purpose of emergency escape, consisting of an explosive core contained in a lead casing and surrounded by a plastic sheath, the cord being of substantially semi-circular or D-shaped cross-section. The semicircular surface, but not the flat face, of the casing has several layers of lead tape applied to it within the plastic sheath which lead tape acts as blast-containing and reflecting material to direct the blast effect of the detonation preferentially through the flat-face.

Description

United States Patent [191 Gibb et al.
[ Jan. 1,1974
[ AIRCREW ESCAPE SYSTEMS [75] Inventors: Robert David Gibb, Hessle; Donald Rowand Smith, Kirk Ella; Geoffrey Charles Wickenden, Hull; Graham Norman Galton, Kingston-upon-Thames; Dennis Robert Shepherd, Bromley, all of England [73] Assignees: Hawker Siddeley Aviation Limited,
' Surrey; Secretary of State for Defence of Great Britain, London, both of England [22] Filed: Feb. 18, 1972 [21] Appl. N0.: 227,433
[30] Foreign Application Priority Data Feb. 19, 1971 Great Britain 5,021/71 [52] US. Cl 102/27 R [51] Int. Cl. C06c 5/04 [58] Field of Search 102/24 HC, 27
[56] References Cited UNITED STATES PATENTS 3,241,489 3/1966 Andrew et al 102/24 HC Pike 102/27 R Rush et al. l02/24 HC FOREIGN PATENTS OR APPLICATIONS 655,92] 8/1951 Great Britain 102/24 HC Primary ExaminerVerlin R. Pendegrass Attorney-Howard L. Rose et a1.
[ ABSTRACT A detonating cord is provided, for causing fracture and break-up of an aircraft cockpit canopy for the purpose of emergency escape, consisting of an explosive core contained in a lead casing and surrounded by a plastic sheath, the cord being of substantially semicircular or D-shaped cross-section. The semi-circular surface, but not the flat face, of the casing has several layers of lead tape applied to it within the plastic sheath which lead tape acts asblast-containing and reflecting material to direct the blast effect of the detonation preferentially through the flat-face.
7 Claims, 1 Drawing Figure AIRCREW ESCAPE SYSTEMS This invention relates to the emergency escape of aircrew from an aircraft.
In US. Patent Application Ser. No. 217,896 filed Jan. 14th, 1972 by Frederick John Potts and Geoffrey Charles Wickenden, it is explained how, in order to enable an aircrew member to escape through the cockpit canopy of an aircraft, for instance upon operation of an ejector seat, an explosive cord device, known as 'Miniature Detonating Cord or MDC, may be employed to cause fracture and break-up of the canopy transparency, or at least that area of it through which the aircrew member will pass. It is also explained that there are difficulties in ensuring that such cord exerts its blast energy, upon detonation, in a direction to give good cutting of the canopy material and dispersal of the broken fragments out of the path of the escaping crew member, without blow-back of material or undesirable blast pressures being directed toward the crew member. And the influence of the cross-sectional shape of the MDC upon this is briefly discussed. It is an object of this invention to provide a novel form of detonating cord which is an improvement in these respects.
According to the present invention, the detonating cord is given a cross-sectional form having at least one flat, and there is embodied within the cord construction at least one layer of blast-containing and reflecting material which extends all around the explosive core of the cord except where the flat lies, so that the blast effect from detonation is directed preferentially through the region of the cord periphery constituted by said flat.
Preferably, the cord is of semi-circular or D-section and the blast-containing and reflecting material is in the form of lead tape applied in layers to the curved portion of the outer surface of a lead casing containing the explosive core. The flat provides a convenient base surface by means of which the cord can be adhered to the canopy transparency and gives a directional effect to the blast because the air to transparency path is eliminated.
One arrangement in accordance with the invention will now be described by way of example, with reference to the accompanying drawing, which shows a miniature detonating cord in cross section.
Referring to the drawing, the explosive filling 42 of the cord is contained within a formed lead casing 43 semi-circular in cross-section. This can be produce by flattening one side of the circular form resulting from a rolling operation. Attached only to the curved semicircular portion of the periphery of the lead casing are a number of lead tapes 44 adhesively secured one upon the other, and the whole assembly is contained within a heat-shrinkable plastic sheath 45 with adhesive 46 interposed between the sheath and the flat face of the lead case 43.
It will be understoodthat although this build-up of the cord is described in relation to semi-circular cord a similar technique can equally be applied to rectangular, triangular or other flatted sections, with lead tapes covering the periphery of the inner lead casing except for one flat.
The build-up of the adhesive tape provides a backing such that, although there will still be a tendency to radial blast losses, the presence of the lead tape, or any other suitable backing material capable of providing the desired blast retention and reflection, will ensure an increased concentration of the blast effect in the direction of the flat face, which is the face applied contiguously to the canopy surface.
Although such cord can still advantageously be held in place on the canopy by retaining plates as in the aforesaid US. Patent Application Ser. No. 217,896, the development of suitable bonding techniques will permit the direct attachment of the cord to selected areas of canopy surface, the flat base providing an adequate adhesive area.
This form of MDC may be laid in a pattern on selected areas of canopy surface thus providing for a more predictable fracture. As it is not necessary to contain this present type of cord within a back-up extrusion such as is described in our aforementioned patent application, the vision loss through a canopy with a pattern-applied MDC will be minimal.
What we claim is: j
l. A detonating cord for producing fracture and break-up of an aircraft cockpit canopy for the purpose of emergency escape, comprising an explosive core and a completely enclosing sheath surrounding said core, said core and sheath jointly possessing a cross-sectional fonn having at least one flat, and wherein there is embodied in the cord within the sheath at least one layer of metallic blast-containing and reflecting material which extends all around the explosive core of the cord except where the flat lies, whereby the blast effect from detonation is directed preferentially through the region of the cord periphery constituted by said flat.
2. A cord according to claim 1, wherein the cord is of substantially semi-circular or D-cross-section.
3. A cord according to claim 1, wherein the blastcontaining and reflecting material is, at least in part, in the form of lead tape applied in layers.
4. A cord according to claim 3, wherein the layers of lead tape are applied to a lead casing containing the explosive core.
5. A cord according to claim 1 wherein said sheath is an external plastic sheath.
6. A cord according to claim 4, wherein adhesive is provided between the sheath and the lead casing in the region of the flat face.
7. A cord according to claim 1, having its flat face held in contiguity with a canopy surface, e.g. by adhe- SlVe.

Claims (7)

1. A detonating cord for producing fracture and break-up of an aircraft cockpit canopy for the purpose of emergency escape, comprising an explosive core and a completely enclosing sheath surrounding said core, said core and sheath jointly possessing a cross-sectional form having at least one flat, and wherein there is embodied in the cord within the sheath at least one layer of metallic blast-containing and reflecting material which extends all around the explosive core of the cord except where the flat lies, whereby the blast effect from detonation is directed preferentially through the region of the cord periphery constituted by said flat.
2. A cord according to claim 1, wherein the cord is of substantially semi-circular or D-cross-section.
3. A cord according to claim 1, wherein the blast-containing and reflecting material is, at least in part, in the form of lead tape applied in layers.
4. A cord according to claim 3, wherein the layers of lead tape are applied to a lead casing containing the explosive core.
5. A cord according to claim 1 wherein said sheath is an external plastic sheath.
6. A cord according to claim 4, wherein adhesive is provided between the sheath and the lead casing in the region of the flat face.
7. A cord according to claim 1, having its flat face held in contiguity with a canopy surface, e.g. by adhesive.
US00227433A 1971-02-19 1972-02-18 Aircrew escape systems Expired - Lifetime US3782284A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB502171A GB1383512A (en) 1971-02-19 1971-02-19 Detonating cord for aircraft canpoy emergency break-up systems

Publications (1)

Publication Number Publication Date
US3782284A true US3782284A (en) 1974-01-01

Family

ID=9788247

Family Applications (1)

Application Number Title Priority Date Filing Date
US00227433A Expired - Lifetime US3782284A (en) 1971-02-19 1972-02-18 Aircrew escape systems

Country Status (4)

Country Link
US (1) US3782284A (en)
DE (1) DE2207941C3 (en)
FR (1) FR2125588B1 (en)
GB (1) GB1383512A (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4239003A (en) * 1978-08-14 1980-12-16 The United States Of America As Represented By The Secretary Of The Navy Method for transmitting detonation at a sharp angle
US4301707A (en) * 1979-10-29 1981-11-24 Mcdonnell Douglas Corporation Embedded explosive severance of non-metallic materials
US4333381A (en) * 1979-01-04 1982-06-08 Societe Nationale Industrielle Aerospatiale Plate-glass fitted with an explosion-cutting device
US4753170A (en) * 1983-06-23 1988-06-28 Jet Research Center Polygonal detonating cord and method of charge initiation
US5217244A (en) * 1989-07-14 1993-06-08 Tip Engineering Group Arrangement for forming an air bag deployment opening
US20040055495A1 (en) * 2002-04-23 2004-03-25 Hannagan Harold W. Tin alloy sheathed explosive device
US20080017426A1 (en) * 2006-03-23 2008-01-24 Walters Raul J Modular vehicle system and method
US10739112B1 (en) * 2013-08-15 2020-08-11 The United States Of America As Represented By The Secretary Of The Navy Impulse dampening system for emergency egress
US10947169B2 (en) * 2018-06-29 2021-03-16 River Front Services, Inc. Deployable explosive charge structure
US11174982B2 (en) 2016-11-08 2021-11-16 River Front Services, Inc. Deployable prop
US11319260B2 (en) 2019-11-05 2022-05-03 Goodrich Corporation Detonating cord stress concentrators
US11454482B2 (en) 2017-08-24 2022-09-27 River Front Services, Inc. Explosive detonating system and components
US11543224B2 (en) 2017-08-24 2023-01-03 River Front Services, Inc. Explosive detonating system and components

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2634171B1 (en) * 1988-07-13 1990-09-28 Aerospatiale PYROTECHNIC SYSTEM FOR PROVIDING A EMERGENCY EXIT IN A WALL OF AN AIRCRAFT AND AIRCRAFT EQUIPPED WITH SAID SYSTEM
EP0950576B1 (en) 1998-04-09 2003-03-12 Certime Amsterdam B.V. Collapsible panel and method for controlled collapsing thereof

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB655921A (en) * 1948-10-30 1951-08-08 Edgar William John Phillips Improvements in or relating to explosive line charges for fire-fighting and like purposes
US3241489A (en) * 1963-05-06 1966-03-22 Ensign Bickford Co Composite explosive signal transmission cord and method of making same
US3336868A (en) * 1965-04-02 1967-08-22 Trw Inc Separation device
US3374737A (en) * 1967-02-15 1968-03-26 Earl A. Pike Detonating tape

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3248072A (en) * 1964-04-01 1966-04-26 Mcdonnell Aircraft Corp Underwater explosive effects attenuator
GB1268947A (en) * 1968-06-27 1972-03-29 Explosive Tech Improvements in or relating to the explosive forming of openings in wall-like structures

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB655921A (en) * 1948-10-30 1951-08-08 Edgar William John Phillips Improvements in or relating to explosive line charges for fire-fighting and like purposes
US3241489A (en) * 1963-05-06 1966-03-22 Ensign Bickford Co Composite explosive signal transmission cord and method of making same
US3336868A (en) * 1965-04-02 1967-08-22 Trw Inc Separation device
US3374737A (en) * 1967-02-15 1968-03-26 Earl A. Pike Detonating tape

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4239003A (en) * 1978-08-14 1980-12-16 The United States Of America As Represented By The Secretary Of The Navy Method for transmitting detonation at a sharp angle
US4333381A (en) * 1979-01-04 1982-06-08 Societe Nationale Industrielle Aerospatiale Plate-glass fitted with an explosion-cutting device
US4301707A (en) * 1979-10-29 1981-11-24 Mcdonnell Douglas Corporation Embedded explosive severance of non-metallic materials
US4753170A (en) * 1983-06-23 1988-06-28 Jet Research Center Polygonal detonating cord and method of charge initiation
US5217244A (en) * 1989-07-14 1993-06-08 Tip Engineering Group Arrangement for forming an air bag deployment opening
US20040055495A1 (en) * 2002-04-23 2004-03-25 Hannagan Harold W. Tin alloy sheathed explosive device
US20080017426A1 (en) * 2006-03-23 2008-01-24 Walters Raul J Modular vehicle system and method
WO2008060318A2 (en) * 2006-03-23 2008-05-22 Walters & Clune, Llc Modular vehicle system and method
WO2008060318A3 (en) * 2006-03-23 2008-11-13 Walters & Clune Llc Modular vehicle system and method
US10739112B1 (en) * 2013-08-15 2020-08-11 The United States Of America As Represented By The Secretary Of The Navy Impulse dampening system for emergency egress
US11174982B2 (en) 2016-11-08 2021-11-16 River Front Services, Inc. Deployable prop
US11454482B2 (en) 2017-08-24 2022-09-27 River Front Services, Inc. Explosive detonating system and components
US11543224B2 (en) 2017-08-24 2023-01-03 River Front Services, Inc. Explosive detonating system and components
US10947169B2 (en) * 2018-06-29 2021-03-16 River Front Services, Inc. Deployable explosive charge structure
US11319260B2 (en) 2019-11-05 2022-05-03 Goodrich Corporation Detonating cord stress concentrators

Also Published As

Publication number Publication date
FR2125588B1 (en) 1976-10-29
FR2125588A1 (en) 1972-09-29
DE2207941C3 (en) 1974-11-14
GB1383512A (en) 1974-02-12
DE2207941B2 (en) 1974-04-11
DE2207941A1 (en) 1972-09-07

Similar Documents

Publication Publication Date Title
US3782284A (en) Aircrew escape systems
US4301707A (en) Embedded explosive severance of non-metallic materials
US5368904A (en) Bullet resistant glass
GB1383511A (en) Aircraft canopy emergency
GB1320969A (en) Missile with fragmenting cover
US3841954A (en) Compressed rigid laminated material including stitching reinforcement
GB1274343A (en) Improvements in or relating to acoustic linings
ES8301753A1 (en) Gaseous diffusion resistant article.
US3970006A (en) Protective cover for a missile nose cone
GB1274568A (en) Composite shafts with integral end flanges and methods of making same
US2774306A (en) Means for initiating explosion
US4407468A (en) Explosively activated egress area
GB1383513A (en) Aircrew escape systems
GB995228A (en) Bladed structure, for example, for a gas turbine engine compressor
GB1084503A (en) Improvements in fire-resistant panels and fireproof containers made therefrom
US6247410B1 (en) High-output insensitive munition detonating cord
IT1145736B (en) AIRCRAFT WITH ROCKET PROPULSION AND RELATED GOVERNMENT SYSTEM
US6487971B1 (en) Light initiated detonator
US3279405A (en) Torpedo nose cap retaining device
US2802396A (en) Frangible jackets for missiles and the like
IT8047554A0 (en) IMPROVEMENT IN THE ATTACHMENT ARRANGEMENTS OF BOMBS, ROCKETS AND THE LIKE ON LOAD-BEARING STRUCTURES OF AIRPLANES
US2943571A (en) Explosive device
US3010398A (en) Composite nose cone structure
US3688988A (en) Disposable rocket motor nozzle
US4512538A (en) Device for maintaining a detonating cord against a transparent aircraft canopy member

Legal Events

Date Code Title Description
AS Assignment

Owner name: BRITISH AEROSPACE PUBLIC LIMITED COMPANY, DISTRICT

Free format text: CHANGE OF NAME;ASSIGNOR:BRITISH AEROSPACE LIMITED;REEL/FRAME:004080/0820

Effective date: 19820106

Owner name: BRITISH AEROSPACE PUBLIC LIMITED COMPANY

Free format text: CHANGE OF NAME;ASSIGNOR:BRITISH AEROSPACE LIMITED;REEL/FRAME:004080/0820

Effective date: 19820106

AS Assignment

Owner name: BRITISH AEROSPACE, BROOKLANDS RD., WEYBRIDGE SURRE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST. AS OF APR. 17,1978;ASSIGNOR:HAWKER SIDDELEY AVIATION LIMITED;REEL/FRAME:003953/0751

Effective date: 19811218

Owner name: BRITISH AEROSPACE, ENGLAND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:HAWKER SIDDELEY AVIATION LIMITED;REEL/FRAME:003953/0751

Effective date: 19811218