US3319781A - Control wire dispenser for a guided missile - Google Patents
Control wire dispenser for a guided missile Download PDFInfo
- Publication number
- US3319781A US3319781A US508024A US50802465A US3319781A US 3319781 A US3319781 A US 3319781A US 508024 A US508024 A US 508024A US 50802465 A US50802465 A US 50802465A US 3319781 A US3319781 A US 3319781A
- Authority
- US
- United States
- Prior art keywords
- control wire
- former
- winding
- dispenser
- auxiliary winding
- 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
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65H—HANDLING THIN OR FILAMENTARY MATERIAL, e.g. SHEETS, WEBS, CABLES
- B65H49/00—Unwinding or paying-out filamentary material; Supporting, storing or transporting packages from which filamentary material is to be withdrawn or paid-out
- B65H49/02—Methods or apparatus in which packages do not rotate
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
- F41G7/30—Command link guidance systems
- F41G7/32—Command link guidance systems for wire-guided missiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
- F42B15/04—Arrangements thereon for guidance or control using wire, e.g. for guiding ground-to-ground rockets
Definitions
- SIMPSON ETAL 1 CONTROL WIRE DISPENSER FOR A GUIDED MISSILE 2 Sheets-Sheet 1 Filed Nov. 16, 1965 INVENTORS Jhmes C. SIMPSON.
- This invention relates to guided missiles of the type which are controlled in flight by signals transmitted from a control station, usually on the ground, to the missiles through control wires trailing behind the missiles.
- control wire dispenser for such a missle in which a generally-cylindrical hollow multi-layer main Winding of the control wire is wound on a cylindrical former for mounting in the missile body, the trailing end of the main winding being of tapering, for example frustoconical external form, and one or more auxiliary coils which do not conform to the general helical winding pattern of the main winding, and which comprise the lastwound few yards of control 'wire stored in the dispenser which will be withdrawn first from the dispenser when the missile is launched, are secured to the main winding, either coaxially therewith on or adjacent to the tapered rear end thereof, or as a separate pancake-like Winding whose coil or coils are secured by a rupturable connection on one side of the outer cylindrical surface of the main winding.
- These auxiliary coils become released relatively freely immediately after the missile has been launched and allow the missile to make an extremely abrupt change of course immediately after launching, for example through a complete right angle, without hindering the required change of course
- the present invention is concerned with providing an improved construction of control wire dispenser equipped with such auxiliary coils.
- a main winding of control wire of cylindrical external form having a rear end portion of non-tapering external form is wound on a cylindrical hollow former, and an auxiliary winding comprising one or more auxiliary coils which do not conform to the generally helical winding pattern of the main winding and which comprises the last-wound few yards of control wire stored in the dispenser which will be withdrawn first from the dispenser when the missile is launched, is wound on an annular support at the rear end of the former.
- the main winding and/or the auxiliary winding is preferably secured in position by a readily-rupturable connection, for example a layer of resin-bonded paper.
- the cylindrical former is provided at its rear end with an axially-projecting extension flange at its rear end which is of generally-tapered external form, the flange constituting the annular support for the auxiliary winding and being formed with a series "ice of axially-spaced external steps, ribs, serrations or other locating means by which the turns of the auxiliary winding are located.
- the auxiliary winding is supported on a separate annular support which is attached to the rear end of the cylindrical former of the main winding.
- the coils of the auxiliary winding may be secured by a rupturable connection to one flat face of an annular laminate whose other flat face is firmly attached to the rear end of the cylindrical former of the main winding.
- FIGURE 1 is a perspective view of one construction of control wire dispenser embodying the invention
- FIGURE 2 is a longitudinal section through the dispenser of FIGURE 1,
- FIGURE 3 is a side view of a guided missile incorporating the dispenser of FIGURES l and 2
- FIGURE 4 is a perspective view of a modified construction of control wire dispenser embodying the invention.
- FIGURE 5 is a longitudinal section through the dispenser of FIGURE 4, and
- FIGURE 6 is a side view of a guided missile incorporating the dispenser of FIGURES 4 and 5.
- a control wire dispenser 16 for a guided missile 11 of the type specified comprises a cast aluminium former 12 of generally hollow cylindrical form, provided with integral radial flanges 13 and 14 at its two ends defining a circumferential trough in which the main winding 15 of multi-core insulated control wire is located.
- the main winding 15 comprises a multi-layer helical winding having a generally cylindrical external surface. After the penultimate layer of the main winding has been wound, it is painted with a coat of synthetic resin varnish.
- the final layer of control wire is then wound and painted with varnish, after which an outer layer 16 of tissue paper is wound around the completed winding to cover it whilst the varnish is still wet, the paper being bonded to the winding by the varnish.
- the surface of the main winding 15 afforded by the external paper cover 16 is approximately level with the periphery of the radial flanges 13 and 14 at the two ends of the cast aluminium former 12.
- the cast former 12 carries an auxiliary rearwardly-protruding extension 18 of generally frustoconical external form, which is joined integrally to the radial flange 14 at the outer peripheral margin 14a of the latter.
- the frusto-conical outer surface of the extension 18, which extends generally at 45 to the axis of the former 12, is of serrated form, being provided with a series of small axially-spaced circumferential grooves or serrations as shown at 19.
- the control wire leading from the outer end of the main winding 15 is sleeved and this sleeved portion is formed into an auxiliary winding 20, comprising the first few yards of control wire to be pulled from the dispenser after the missile is launched, which is wound on the serrated frusto-conical outer surface 19 of the extension 13 and is secured in position by a readily rupturable connection, for example by a coating of epoxy resin varnish or other adhesive.
- the successive turns of the helical spiral auxiliary winding 20 lie in and are positioned by the serrations 19 of the extension 18.
- the length of wire constituting the auxiliary winding 20 will thus be determined by the mean diameter of the frusto-conical extension flange 18 on which it is wound, and by the axial pitch of the circumferential serrations 19.
- An outer covering of tissue paper may be bonded to the exterior of the auxiliary winding 20 by the resin varnish coating if required.
- This construction has the advantage that the dispenser spool 12 can be fully wound with both the main winding 15 and the auxiliary winding 20 in a single winding operation, and operates satisfactorily in practice up to a limited angle of change of course of the missile after launching, the limiting value of this angle being dependent upon the pull-off load involved and the angle of the conical flange.
- a cast or spun aluminium former 30 is used which is generally similar to the former 12 of the preceding embodiment and has radial flanges 31 and 32 at its rear and front ends respectively, but which does not have an integral frusto-conical serrated rear extension. Instead, the radial flange 31 at the rear end of the cast cylindrical former extends radially inwardly of the former wall at 33 as well as radially outwardly, affording a flat annular end face upon which can be mounted a separate supporting ring 35 carrying the auxiliary winding 36.
- This supporting ring 35 comprises a generally flat annular laminate to one face of which the auxiliary winding 36 is applied and held in position by stitching, and the opposite face of which is abutted against the end face of the flange 31, 33 of the cylindrical former 30 to which the annular laminate 35 is bolted.
- the auxiliary winding 36 in this case consists of a flattened multi-turn helical winding whose generally circular loops overlie and partially overlap one another, as shown .in FIGURE 4, the flattened winding 36 conforming in profile to the circular form of the face of the annular support 35 to which it is attached.
- the annular support 35 is formed with coaxial inner and outer rings of spaced holes 37 and 38, and the individual loops of the flattened helical auxiliary winding 36 are stitched to the annular support 35 by means of cotton thread which passes through the rings of holes 37 and 38 and secure the individual turns.
- a resin coating for example of epoxy resin
- a control wire dispenser for a guided missile which comprises a length of control wire, a hollow cylindrical former, a generally helical main winding of the control wire of cylindrical external form wound on the former, a supporting ring attached to one end of the former and having a generally flat end surface facing away from the former, a generally helical auxiliary winding of the control wire comprising loops flatly attached in a circle to said flat end surface of said supporting ring and individually secured thereto by rupturable stitching, the length of control wire having a trailing end leading away from one end of the auxiliary winding and each loop of the auxiliary winding partially overlapping the adjacent loop more remote from the said trailing end.
- a control wire dispenser as claimed in claim 1 in which each loop of said auxiliary winding is attached to the supporting ring by stitching at four places distributed around the loop.
- a control wire dispenser as claimed in claim 1 in which the cylindrical former includes at one end an integral radially-extending flange having an axially-facing annular end surface and in which said supporting ring is secured to said end surface of said integral flange.
- a control wire dispenser as claimed in claim 1 in which the supporting ring has coaxial circular outer and inner edges and in which the circle of loops constituting the auxiliary winding are located within limits defined by said outer and inner edges of the supporting ring.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Laying Of Electric Cables Or Lines Outside (AREA)
- Unwinding Of Filamentary Materials (AREA)
Description
Claims (1)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4685664 | 1964-11-17 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3319781A true US3319781A (en) | 1967-05-16 |
Family
ID=10442841
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US508024A Expired - Lifetime US3319781A (en) | 1964-11-17 | 1965-11-16 | Control wire dispenser for a guided missile |
Country Status (6)
Country | Link |
---|---|
US (1) | US3319781A (en) |
CH (1) | CH445307A (en) |
DE (1) | DE1272776B (en) |
FR (1) | FR1454257A (en) |
GB (1) | GB1058566A (en) |
NL (1) | NL140057B (en) |
Cited By (31)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3508644A (en) * | 1967-06-21 | 1970-04-28 | James Martin | Apparatus for stowing cables |
US3613619A (en) * | 1969-12-05 | 1971-10-19 | Us Navy | Payout coil impregnated with conductive adhesive |
US4165876A (en) * | 1976-12-01 | 1979-08-28 | Joseph Pasqualini | Container for a line for towing an aerial target and process for loading the line into the container |
US4573647A (en) * | 1984-05-30 | 1986-03-04 | The United States Of America As Represented By The Secretary Of The Army | Fiber deployment mechanism |
FR2574929A1 (en) * | 1984-12-14 | 1986-06-20 | Commissariat Energie Atomique | Device for dynamic measurement of parameters linked with small-size projectiles |
US4624185A (en) * | 1985-08-05 | 1986-11-25 | The United States Of America As Represented By The Secretary Of The Army | Missile ballast assembly |
US4907763A (en) * | 1987-03-31 | 1990-03-13 | The Boeing Company | Optical fiber guided tube-launched projectile system |
US4950049A (en) * | 1989-02-28 | 1990-08-21 | At&T Bell Laboratories | Stable package of elongated optical fiber strand material |
US4955688A (en) * | 1989-03-27 | 1990-09-11 | At&T Bell Laboratories | Optical fiber package and methods of making |
US4967980A (en) * | 1987-03-31 | 1990-11-06 | The Boeing Company | Optical fiber guided tube-launched projectile system |
EP0399067A1 (en) * | 1989-05-23 | 1990-11-28 | The Boeing Company | Zero crossover wound fiber optic bobbin and method for filling same |
US4974793A (en) * | 1989-12-15 | 1990-12-04 | The Boeing Company | Tapered chamber dispensing of optical fiber |
EP0404367A2 (en) * | 1989-06-23 | 1990-12-27 | Hughes Aircraft Company | Missile filament dispensing arrangement |
US5005930A (en) * | 1990-02-23 | 1991-04-09 | Hughes Aircraft Company | Multi-directional payout fiber optic canister |
FR2654204A1 (en) * | 1989-11-09 | 1991-05-10 | France Etat Armement | Guide wire dispenser device for a torpedo (missile) moving at high speed through a fluid |
US5040744A (en) * | 1989-06-23 | 1991-08-20 | Highes Aircraft Company | Missile filament dispensing arrangement |
US5052632A (en) * | 1988-05-02 | 1991-10-01 | The Boeing Company | Zero crossover wound fiber optic bobbin and method for filling same |
US5052636A (en) * | 1989-11-01 | 1991-10-01 | Hughes Aircraft Company | Damped filament dispenser |
US5104057A (en) * | 1989-11-01 | 1992-04-14 | Hughes Aircraft Company | Gas damped filament dispenser |
US5109470A (en) * | 1989-05-03 | 1992-04-28 | Gec-Marconi Limited | Data transmission line and storage body |
US5189253A (en) * | 1990-07-20 | 1993-02-23 | Hughes Aircraft Company | Filament dispenser |
US5205890A (en) * | 1989-02-28 | 1993-04-27 | At&T Bell Laboratories | Method for providing stable package of elongated optical fiber with bonded convolutions |
US5385319A (en) * | 1993-11-22 | 1995-01-31 | Hughes Missile Systems Company | Missile with inside payout optical fiber canister |
US5419512A (en) * | 1990-09-06 | 1995-05-30 | The United States Of America As Represented By The Secretary Of The Navy | Towed fiber optic data link payout system |
WO1996018865A1 (en) * | 1994-12-16 | 1996-06-20 | Sci Systems, Inc. | Fiber-optic cable dispenser and remotely controlled vehicle using same |
US6223659B1 (en) * | 1998-05-18 | 2001-05-01 | The United States Of America As Represented By The Secretary Of The Navy | Line storage device for preventing line entanglement |
FR2942577A1 (en) * | 2009-02-26 | 2010-08-27 | Andre Schaer | Device for bidirectional transmission of electric digital data between submarine observation drone and commanding and controlling station, has mechanism mounted with axis of drum, where speed of mechanism depends on speed of mobile |
US20110162247A1 (en) * | 2009-12-22 | 2011-07-07 | Diehl Bgt Defence Gmbh & Co. Kg | Grenade and grenade launching apparatus |
US20140131505A1 (en) * | 2012-11-12 | 2014-05-15 | Southwire Company | Wire and Cable Package |
USD802326S1 (en) * | 2011-09-14 | 2017-11-14 | San Jamar, Inc. | Insert for a web material dispenser |
USD904066S1 (en) | 2019-09-19 | 2020-12-08 | Georgia-Pacific LLC | Core plug |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3201019C2 (en) * | 1982-01-15 | 1983-12-01 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Cable reel for a weapon remotely controlled with the aid of a detachable cable |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US764606A (en) * | 1904-04-14 | 1904-07-12 | Draper Co | Filling-carrier for automatic feeler-looms. |
US3156185A (en) * | 1960-12-20 | 1964-11-10 | Hermann Joachim | Triggering device for a movable body |
US3163711A (en) * | 1958-08-20 | 1964-12-29 | Ludwig Bolkow | Cable-controlled flying objects and cables therefor |
US3266423A (en) * | 1961-06-19 | 1966-08-16 | Fairey Eng | Ground controlled rocket missiles |
-
1964
- 1964-11-17 GB GB42856/64A patent/GB1058566A/en not_active Expired
-
1965
- 1965-11-16 CH CH1577565A patent/CH445307A/en unknown
- 1965-11-16 NL NL656514894A patent/NL140057B/en unknown
- 1965-11-16 US US508024A patent/US3319781A/en not_active Expired - Lifetime
- 1965-11-17 FR FR38738A patent/FR1454257A/en not_active Expired
- 1965-11-17 DE DEB84551A patent/DE1272776B/en active Pending
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US764606A (en) * | 1904-04-14 | 1904-07-12 | Draper Co | Filling-carrier for automatic feeler-looms. |
US3163711A (en) * | 1958-08-20 | 1964-12-29 | Ludwig Bolkow | Cable-controlled flying objects and cables therefor |
US3156185A (en) * | 1960-12-20 | 1964-11-10 | Hermann Joachim | Triggering device for a movable body |
US3266423A (en) * | 1961-06-19 | 1966-08-16 | Fairey Eng | Ground controlled rocket missiles |
Cited By (41)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3508644A (en) * | 1967-06-21 | 1970-04-28 | James Martin | Apparatus for stowing cables |
US3613619A (en) * | 1969-12-05 | 1971-10-19 | Us Navy | Payout coil impregnated with conductive adhesive |
US4165876A (en) * | 1976-12-01 | 1979-08-28 | Joseph Pasqualini | Container for a line for towing an aerial target and process for loading the line into the container |
US4573647A (en) * | 1984-05-30 | 1986-03-04 | The United States Of America As Represented By The Secretary Of The Army | Fiber deployment mechanism |
FR2574929A1 (en) * | 1984-12-14 | 1986-06-20 | Commissariat Energie Atomique | Device for dynamic measurement of parameters linked with small-size projectiles |
US4624185A (en) * | 1985-08-05 | 1986-11-25 | The United States Of America As Represented By The Secretary Of The Army | Missile ballast assembly |
US4967980A (en) * | 1987-03-31 | 1990-11-06 | The Boeing Company | Optical fiber guided tube-launched projectile system |
US4907763A (en) * | 1987-03-31 | 1990-03-13 | The Boeing Company | Optical fiber guided tube-launched projectile system |
US5052632A (en) * | 1988-05-02 | 1991-10-01 | The Boeing Company | Zero crossover wound fiber optic bobbin and method for filling same |
US4950049A (en) * | 1989-02-28 | 1990-08-21 | At&T Bell Laboratories | Stable package of elongated optical fiber strand material |
US5205890A (en) * | 1989-02-28 | 1993-04-27 | At&T Bell Laboratories | Method for providing stable package of elongated optical fiber with bonded convolutions |
US5033389A (en) * | 1989-02-28 | 1991-07-23 | At&T Bell Laboratories | System for guiding a vehicle from a rest position to a target |
US4955688A (en) * | 1989-03-27 | 1990-09-11 | At&T Bell Laboratories | Optical fiber package and methods of making |
US5064490A (en) * | 1989-03-27 | 1991-11-12 | At&T Bell Laboratories | Methods of providing an optical fiber package |
US5035169A (en) * | 1989-03-27 | 1991-07-30 | At&T Bell Laboratories | Guided vehicle system |
US5109470A (en) * | 1989-05-03 | 1992-04-28 | Gec-Marconi Limited | Data transmission line and storage body |
EP0399067A1 (en) * | 1989-05-23 | 1990-11-28 | The Boeing Company | Zero crossover wound fiber optic bobbin and method for filling same |
US5014930A (en) * | 1989-06-23 | 1991-05-14 | Hughes Aircraft Company | Missile filament dispensing arrangement |
US5040744A (en) * | 1989-06-23 | 1991-08-20 | Highes Aircraft Company | Missile filament dispensing arrangement |
EP0404367A2 (en) * | 1989-06-23 | 1990-12-27 | Hughes Aircraft Company | Missile filament dispensing arrangement |
EP0404367A3 (en) * | 1989-06-23 | 1991-10-30 | Hughes Aircraft Company | Missile filament dispensing arrangement |
US5052636A (en) * | 1989-11-01 | 1991-10-01 | Hughes Aircraft Company | Damped filament dispenser |
US5104057A (en) * | 1989-11-01 | 1992-04-14 | Hughes Aircraft Company | Gas damped filament dispenser |
FR2654204A1 (en) * | 1989-11-09 | 1991-05-10 | France Etat Armement | Guide wire dispenser device for a torpedo (missile) moving at high speed through a fluid |
US4974793A (en) * | 1989-12-15 | 1990-12-04 | The Boeing Company | Tapered chamber dispensing of optical fiber |
US5005930A (en) * | 1990-02-23 | 1991-04-09 | Hughes Aircraft Company | Multi-directional payout fiber optic canister |
US5189253A (en) * | 1990-07-20 | 1993-02-23 | Hughes Aircraft Company | Filament dispenser |
US5419512A (en) * | 1990-09-06 | 1995-05-30 | The United States Of America As Represented By The Secretary Of The Navy | Towed fiber optic data link payout system |
US5385319A (en) * | 1993-11-22 | 1995-01-31 | Hughes Missile Systems Company | Missile with inside payout optical fiber canister |
EP0660071A1 (en) * | 1993-11-22 | 1995-06-28 | Hughes Aircraft Company | Missile with inside payout optical fiber canister |
WO1996018865A1 (en) * | 1994-12-16 | 1996-06-20 | Sci Systems, Inc. | Fiber-optic cable dispenser and remotely controlled vehicle using same |
US5678785A (en) * | 1994-12-16 | 1997-10-21 | Sci Industries, Inc. | Fiber-optic cable dispenser and remotely controlled vehicle using same |
US6223659B1 (en) * | 1998-05-18 | 2001-05-01 | The United States Of America As Represented By The Secretary Of The Navy | Line storage device for preventing line entanglement |
FR2942577A1 (en) * | 2009-02-26 | 2010-08-27 | Andre Schaer | Device for bidirectional transmission of electric digital data between submarine observation drone and commanding and controlling station, has mechanism mounted with axis of drum, where speed of mechanism depends on speed of mobile |
US20110162247A1 (en) * | 2009-12-22 | 2011-07-07 | Diehl Bgt Defence Gmbh & Co. Kg | Grenade and grenade launching apparatus |
US9488422B2 (en) * | 2009-12-22 | 2016-11-08 | Diehl Bgt Defence Gmbh & Co. Kg | Grenade and grenade launching apparatus |
USD802326S1 (en) * | 2011-09-14 | 2017-11-14 | San Jamar, Inc. | Insert for a web material dispenser |
US20140131505A1 (en) * | 2012-11-12 | 2014-05-15 | Southwire Company | Wire and Cable Package |
US11117737B2 (en) * | 2012-11-12 | 2021-09-14 | Southwire Company, Llc | Wire and cable package |
US11858719B2 (en) | 2012-11-12 | 2024-01-02 | Southwire Company, Llc | Wire and cable package |
USD904066S1 (en) | 2019-09-19 | 2020-12-08 | Georgia-Pacific LLC | Core plug |
Also Published As
Publication number | Publication date |
---|---|
CH445307A (en) | 1967-10-15 |
NL140057B (en) | 1973-10-15 |
FR1454257A (en) | 1966-07-22 |
NL6514894A (en) | 1966-05-18 |
GB1058566A (en) | 1967-02-15 |
DE1272776B (en) | 1968-07-11 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: BRITISH AEROSPACE PUBLIC LIMITED COMPANY Free format text: CHANGE OF NAME;ASSIGNOR:BRITISH AEROSPACE LIMITED;REEL/FRAME:004080/0820 Effective date: 19820106 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 |
|
AS | Assignment |
Owner name: BAC AND BRITISH AEROSPACE, BROOKLANDS RD., WEYBRID Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:BRITISH AIRCRAFT CORPORATION LIMITED,;REEL/FRAME:003957/0227 Effective date: 19811218 |