EP0484958A2 - Couche de protection pour des ailettes de projectiles - Google Patents

Couche de protection pour des ailettes de projectiles Download PDF

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Publication number
EP0484958A2
EP0484958A2 EP91119054A EP91119054A EP0484958A2 EP 0484958 A2 EP0484958 A2 EP 0484958A2 EP 91119054 A EP91119054 A EP 91119054A EP 91119054 A EP91119054 A EP 91119054A EP 0484958 A2 EP0484958 A2 EP 0484958A2
Authority
EP
European Patent Office
Prior art keywords
projectile
coating
fins
ablative
fibers
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.)
Withdrawn
Application number
EP91119054A
Other languages
German (de)
English (en)
Other versions
EP0484958A3 (en
Inventor
F. Joseph Walker
Mark P. Jones
Loren J. Walensky
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.)
Northrop Grumman Innovation Systems LLC
Original Assignee
Alliant Techsystems Inc
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 Alliant Techsystems Inc filed Critical Alliant Techsystems Inc
Publication of EP0484958A2 publication Critical patent/EP0484958A2/fr
Publication of EP0484958A3 publication Critical patent/EP0484958A3/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/04—Stabilising arrangements using fixed fins
    • F42B10/06—Tail fins
    • 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
    • F42B15/34—Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements

Definitions

  • the present invention is directed generally to a coating for protecting stabilizing fins from thermal degradation and abrasion in high velocity artillery projectiles and, more particularly, to achieving such protection by the addition of an ablative coating applied as an overlayer for the protection of such fins.
  • Very high velocity artillery projectiles are often provided with a rear fin assembly in which a separate assembly having a plurality of stabilizing fins is attached to the rear of the projectile to help control stability and attitude so that the projectile will maintain proper aerodynamics in flight and guide the ordnance to the target along a predetermined trajectory after it is fired.
  • a multiple segment sabot assembly is also typically provided surrounding a portion of the munition forward or the stabilizing fins to engage the barrel or bore of the artillery piece or cannon to protect the fins from unwanted contact with the barrel or bore and to properly guide the shell along the barrel during firing.
  • the sabot Just after the fired shell emerges from the barrel of the cannon, the sabot separates into its segments and falls away from the projectile leaving the stabilizing fins in full contact with the air.
  • Such a discarding sabot system is shown in Campoli, et al. U.S. Patent 4 187 783. To the extent knowledge regarding the sabot system is required to better understand the present invention, such information is deemed to be incorporated by reference herein.
  • the peak velocity of such projectiles is usually supersonic and may approach an air speed of Mach V.
  • the stabilizing fins are subjected to a great deal of friction which, in turn, produces a great deal of heat and abrasion.
  • the fin assemblies are preferably fabricated from aluminum inasmuch as it has the required weight and relative strength to properly balance the munition.
  • Anodized aluminum functions fairly well under the high heat and abrasion conditions as long as the layer of anodize on the surface of the aluminum survives.
  • it is stripped off readily upon firing so that the bare aluminum is exposed to the severe conditions of launch and high speed flight. Under these conditions, the aluminum fins quickly suffer severe control surface damage and, therefore, have heretofore proven unsatisfactory for this application. Attempts to provide a thicker oxide coating on the aluminum fins have not proved successful.
  • the present invention provides an ablative coating for the fins of cannon-fired, high velocity munition projectiles of the class having stabilizing fins subject to thermal degradation and abrasion loss upon firing.
  • Such munitions generally have a substantially ogive shaped nose, relatively elongated intermediate body and a plurality of stabilizing fins attached to the rear portion of the body.
  • the fins are preferably made of aluminum or aluminum alloy and the ablative coating consists of a siloxane polymer which becomes a protective ablative ceramic char when heated in the air and which protects the aluminum fins to prevent thermal degradation and abrasion of the control surfaces of the fins during shell firing and ablates during projectile flight.
  • the ablative coating may contain an amount of stabilizing fibers, such as carbon or glass fibers, and is in the nature of a pliable, rubberized polysiloxane coating after application. This helps protect the fin assembly during production and assembly of the shell.
  • the ablative coating is in the form of a pasta including the carbon and/or silicon carbide and/or glass fibers which is subsequently applied from an hydrocarbon solution of the paste as by spraying.
  • a paste sold under the designation No. 93-104 by Dow Corning Corporation of Midland, Michigan.
  • Another material which does not contain the stabilizing fibers is available from General Electric Corporation, Schenectady, New York, under the name TBS 758.
  • the ablative coating is normally applied as by spraying from an hydrocarbon solution to a thickness in the range of from about 0.005" to about 0.050". However, much thicker layers of up to 1.0 inches can be used for some applications where more initial protection is required.
  • the coating containing the carbon or glass fibers imparts a wrinkled texture to the external surface of the fins. This texture has not been found to adversely affect the performance of the projectile when fired.
  • Figure 1 depicts, partially in section, a typical cannon-fired high velocity munition round showing generally at 10. It includes a large caliber cartridge case 11 which may be alloy or stainless steel and having a primer 12 utilized to fire an internal charge of smokeless propellant which, in turn, launches the projectile 13 along and out of the barrel in a well known manner.
  • the projectile 13 has a generally ogive shaped nose 14, a central body portion 15 and a rear or tail portion 16.
  • a stabilizing fin assembly shown generally at 17 is attached as by threads (not shown) to the end of the tail section 16 at 18.
  • the stabilizing fin assembly includes a plurality of aerodynamic guidance stabilizing fins 19 arranged symmetrically about a central member 20.
  • the illustrative embodiment includes six such fins, four of which are visible in the view depicted. As better seen in Figures 2, 3A and 3B, the fins are provided with a textured coating as best soon at 21 in Figure 3B.
  • the coating 21 is applied to the anodized surface of the aluminum fin assembly prior to its being attached to the munition projectile which is subsequently assembled to the cartridge case 11.
  • the ablative coating is usually in the form of a paste including the carbon and/or silicon carbide and/or glass fibers which is subsequently applied to the control surfaces from an hydrocarbon solution of the paste as by spraying.
  • the coating can also be painted on, or the fin assembly can be dipped in the mixture, if desired, or the material may be molded in place on the fin.
  • One such material is a paste sold under the designation No. 93-104 by Dow Corning Corporation of Midland, Michigan.
  • Another material which does not contain the stabilizing fibers is available from General Electric Corporation, Schenectady, New York, under the name TBS 758. It is further contemplated that many other compounds of the silicone (siloxane) organosilicon oxide polymer of the structure (I) in which the polymerized material takes on a plastic or rubber-like property will provide the required protection by forming a protective silica (Si0 2 ) coating when the powder is ignited.
  • the ablative coating is normally applied as to a thickness in the range of from about 0.005" to about 0.050". A much heavier coating of up to about 1.0 inches in thickness can be used, if desired, however.
  • the coating containing the carbon or glass fibers, imparts a wrinkled texture to the external surface of the fins.
  • the silicon based organic polymer forms a silicon dioxide based ceramic char which is strengthened by the presence of the various fibers.
  • the char insulates the anodize from the firing environment and, after launch, ablates and flakes off leaving the anodized control surfaces to provide the desired ballistic characteristics during the flight of the projectile.
  • the coating imparts the protection to the metal surface when required during the firing of the shell and thereafter allows the full flight control of the projectile by restoring the metal control surfaces.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Laminated Bodies (AREA)
  • Paints Or Removers (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP19910119054 1990-11-09 1991-11-08 Protective coating for projectile fins Withdrawn EP0484958A3 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US61112190A 1990-11-09 1990-11-09
US611121 1990-11-09

Publications (2)

Publication Number Publication Date
EP0484958A2 true EP0484958A2 (fr) 1992-05-13
EP0484958A3 EP0484958A3 (en) 1992-10-28

Family

ID=24447712

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19910119054 Withdrawn EP0484958A3 (en) 1990-11-09 1991-11-08 Protective coating for projectile fins

Country Status (2)

Country Link
EP (1) EP0484958A3 (fr)
KR (1) KR920010250A (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5474256A (en) * 1994-09-08 1995-12-12 The United States Of American As Represented By The Secretary Of The Army Combustible fin protection device
EP3088929A1 (fr) * 2015-04-27 2016-11-02 CCS Technology Inc. Câble à fibre optique

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR102214730B1 (ko) * 2019-10-25 2021-02-09 김용수 공진단의 약리 효능을 증진시키기 위한 사향의 수용화 방법

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3296153A (en) * 1963-03-22 1967-01-03 North American Aviation Inc Insulation material prepared from a halogenated epoxy, siloxane and a polyamine-amide curing agent
US3380941A (en) * 1964-07-27 1968-04-30 North American Rockwell Ablative thermal insulation composition of a silicone, epoxy resin, cork and curing agent
US3723481A (en) * 1965-07-09 1973-03-27 Gen Electric Ablative coating compositions
US3755223A (en) * 1969-12-05 1973-08-28 Dyna Therm Corp An epoxy ablative coating containing a silicone resin, a fibrous reinforcing material, and a non-alkali metal phosphate and borate salt mixture
DE2629283A1 (de) * 1976-06-30 1978-01-12 Messerschmitt Boelkow Blohm Ablativ wirkende isolationszusammensetzung insbesondere fuer die auskleidung von brennkammern und fuer wiedereintrittskoerper
US4098194A (en) * 1977-06-01 1978-07-04 The United States Of America As Represented By The Secretary Of The Army Hypervelocity projectile with aluminum components of high resistance to thermodynamic ablation
GB1604865A (en) * 1977-12-29 1981-12-16 Secr Defence Projectile tail fin units
EP0249525A1 (fr) * 1986-06-05 1987-12-16 ETAT-FRANCAIS représenté par le DELEGUE GENERAL POUR L'ARMEMENT (DPAG) Empennage pour projectile à énergie cinétique de type flèche

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3296153A (en) * 1963-03-22 1967-01-03 North American Aviation Inc Insulation material prepared from a halogenated epoxy, siloxane and a polyamine-amide curing agent
US3380941A (en) * 1964-07-27 1968-04-30 North American Rockwell Ablative thermal insulation composition of a silicone, epoxy resin, cork and curing agent
US3723481A (en) * 1965-07-09 1973-03-27 Gen Electric Ablative coating compositions
US3755223A (en) * 1969-12-05 1973-08-28 Dyna Therm Corp An epoxy ablative coating containing a silicone resin, a fibrous reinforcing material, and a non-alkali metal phosphate and borate salt mixture
DE2629283A1 (de) * 1976-06-30 1978-01-12 Messerschmitt Boelkow Blohm Ablativ wirkende isolationszusammensetzung insbesondere fuer die auskleidung von brennkammern und fuer wiedereintrittskoerper
US4098194A (en) * 1977-06-01 1978-07-04 The United States Of America As Represented By The Secretary Of The Army Hypervelocity projectile with aluminum components of high resistance to thermodynamic ablation
GB1604865A (en) * 1977-12-29 1981-12-16 Secr Defence Projectile tail fin units
EP0249525A1 (fr) * 1986-06-05 1987-12-16 ETAT-FRANCAIS représenté par le DELEGUE GENERAL POUR L'ARMEMENT (DPAG) Empennage pour projectile à énergie cinétique de type flèche

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5474256A (en) * 1994-09-08 1995-12-12 The United States Of American As Represented By The Secretary Of The Army Combustible fin protection device
EP3088929A1 (fr) * 2015-04-27 2016-11-02 CCS Technology Inc. Câble à fibre optique
US10436994B2 (en) 2015-04-27 2019-10-08 Corning Optical Communications LLC Optical fiber cable

Also Published As

Publication number Publication date
EP0484958A3 (en) 1992-10-28
KR920010250A (ko) 1992-06-26

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