US2645999A - Nozzle closure-contact ring assembly for rockets - Google Patents

Nozzle closure-contact ring assembly for rockets Download PDF

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Publication number
US2645999A
US2645999A US761897A US76189747A US2645999A US 2645999 A US2645999 A US 2645999A US 761897 A US761897 A US 761897A US 76189747 A US76189747 A US 76189747A US 2645999 A US2645999 A US 2645999A
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Prior art keywords
contact ring
rockets
closure
ring assembly
nozzle
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Expired - Lifetime
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US761897A
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Ben T Bogard
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/06—Electric contact parts specially adapted for use with electric fuzes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • F02K9/978—Closures for nozzles; Nozzles comprising ejectable or discardable elements

Definitions

  • This invention relates to rockets, generally, and, in particular to a nozzle closure therefor incorporating an electrical contact ring.
  • the present invention obviates these difiiculties while combining in a unitary structure the contact ring and the nozzle closure.
  • Fig. 1 is a longitudinal section along the line l-l of Fig. 2;
  • Fig. 2 is a view along the line, 22 of Fig. l;
  • Fig. 3 is a perspective view of the metal spider including the contact ring.
  • the novel closure comprises a generally cupshaped metallic member I having a cylindrical wall 2 and a reentrant bottom preferably of openwork form and comprising spiders i having coplanar portions 5. A portion 5 is struck at the intersection of the spiders to provide an electric lead.
  • the unit is completed by placing the stamped metal ring or cup, which is preferably of the order of 0.0 2 inch in thickness, in a pressure mold and moldin plastic '5 around it in a manner to leave exposed the side portion 2 and to provide a trough [2 in a tapered form.
  • the plastic will cover the hole left by the struck portion 6 but will leave a portion of 6 exposed.
  • the plastic is preferably of high impact strength.
  • Ther- .moplastic or thermosetting plastic may be used,
  • the ungrounded side of the electrical circuit from the source of E. M. F. to the ignitor squib 9 is made through the exposed section 2 of the member I through a contactlD thence to the struck portion 5, to which one squib lead terminal is riveted or otherwise fixed before the assembly is cemented to the nozzle plate, through the lead 13, and from the squid and through return wire M to ground.
  • a projector tube is shown in phantom at E5.
  • the novel assembly combines the nozzle closure and contact ring, into one unit which is blown off at the time the rocket is fired.
  • the contact ring having been cleared of the rocket cannot add drag which so materially reduced the range of rockets which carry the contact ring with them.
  • An additional advantage is that'a plastic closure which gives a better and more permanent fit is made possible by the additional strengthening function of the contact ring.
  • the closure can withstand greater mistreatment in handling and storage and is not a likely to be dislodged due to contraction and expansion forces caused by temperature variations, a factor which has caused the greatest trouble in the use of purely plastic closures.
  • a nozzle closure for rockets comprising a plastic cup of generally cylindrical outer walls, an opened end and a closed bottom, a central inwardly elevated portion in said bottom having tapered walls, and tapered inner portions on said outer walls to provide an annular trough of downwardly diminishing width to snugly encompass the rim of a rocket nozzle, and a metal skeleton embedded in said cup having an outwardly exposed band portion peripherally of said outer walls, and having a struck portion centrally of said bottom exposed within the cup.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)

Description

y 1953 B. T. BOGARD 2',
NOZZLE CLOSURE-CONTACT RING ASSEMBLY FOR ROCKETS Filed July 18, 194? Patented July 21, 1953 NQZZLE CLOSURE-CONTACT RING ASSEMBLY FOR ROCKETS 1 Claim.
(Granted under Title 35, U. S. Code (1952),
, l The invention described in the following specification and claim may be manufactured and used by or for the Government for governmental purposes without the payment to me of any royalty thereon. I
This invention relates to rockets, generally, and, in particular to a nozzle closure therefor incorporating an electrical contact ring.
In the past development of rockets the problems of a contact ring assembly and of a satis-. factory nozzle closure have been matters of some concern. The greatest difficulty encountered with the contact ring assembly was the decrease in range of the rocket occasioned thereby, amounting to as much as one-fifth of the maximum obtainable range. Nozzle closures have been unsatisfactory due to the characteristics of the materials used and the ease with which the closure could be dislodged from the rocket'nozzle during ordinary handling, shipping and storage.
The present invention obviates these difiiculties while combining in a unitary structure the contact ring and the nozzle closure.
It is therefore an object of the invention to provide a nozzle closure for a rocket which is secure and reliable and to improve the performance thereof with respect to its contact ring.
To these and other ends, reference is had to the accompanying specification and t the drawings in which:
Fig. 1 is a longitudinal section along the line l-l of Fig. 2;
Fig. 2 is a view along the line, 22 of Fig. l; and
Fig. 3 is a perspective view of the metal spider including the contact ring.
The novel closure comprises a generally cupshaped metallic member I having a cylindrical wall 2 and a reentrant bottom preferably of openwork form and comprising spiders i having coplanar portions 5. A portion 5 is struck at the intersection of the spiders to provide an electric lead.
The unit is completed by placing the stamped metal ring or cup, which is preferably of the order of 0.0 2 inch in thickness, in a pressure mold and moldin plastic '5 around it in a manner to leave exposed the side portion 2 and to provide a trough [2 in a tapered form. The plastic will cover the hole left by the struck portion 6 but will leave a portion of 6 exposed. The plastic is preferably of high impact strength. Ther- .moplastic or thermosetting plastic may be used,
the former being easier to mold and otherwise satisfactory even though its expansion coefiicient is extremely great in comparison to the steel of the rocket. The framework around which sec. 266) the plastic is molded tends to hold the plastic tightly against the surface of the nozzle plate 8 on which it bears. The closure is cemented to the nozzle plate over the entire bearing areas.
The ungrounded side of the electrical circuit from the source of E. M. F. to the ignitor squib 9 is made through the exposed section 2 of the member I through a contactlD thence to the struck portion 5, to which one squib lead terminal is riveted or otherwise fixed before the assembly is cemented to the nozzle plate, through the lead 13, and from the squid and through return wire M to ground. A projector tube is shown in phantom at E5.
It is thus seen that the novel assembly combines the nozzle closure and contact ring, into one unit which is blown off at the time the rocket is fired. The contact ring having been cleared of the rocket cannot add drag which so materially reduced the range of rockets which carry the contact ring with them. An additional advantage is that'a plastic closure which gives a better and more permanent fit is made possible by the additional strengthening function of the contact ring. The closure can withstand greater mistreatment in handling and storage and is not a likely to be dislodged due to contraction and expansion forces caused by temperature variations, a factor which has caused the greatest trouble in the use of purely plastic closures.
Having thu described my invention, what I desire to claim as new and secure by Letters Patent is:
A nozzle closure for rockets comprising a plastic cup of generally cylindrical outer walls, an opened end and a closed bottom, a central inwardly elevated portion in said bottom having tapered walls, and tapered inner portions on said outer walls to provide an annular trough of downwardly diminishing width to snugly encompass the rim of a rocket nozzle, and a metal skeleton embedded in said cup having an outwardly exposed band portion peripherally of said outer walls, and having a struck portion centrally of said bottom exposed within the cup.
BEN T. BOGARD.
References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 2,299,466 Coffman Oct. 20, 1942 2,335,763 Imber Nov. 30, 1943 FOREIGN EATENTS Number Country Date 14,000 Great Britain 1896 540,559 Great Britain Oct. 22, 1941
US761897A 1947-07-18 1947-07-18 Nozzle closure-contact ring assembly for rockets Expired - Lifetime US2645999A (en)

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US761897A US2645999A (en) 1947-07-18 1947-07-18 Nozzle closure-contact ring assembly for rockets

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Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1000718B (en) * 1953-12-01 1957-01-10 Nils Olov Malmstroem Practice bullet for recoilless firearms
US2801587A (en) * 1953-02-06 1957-08-06 Albert S Gould Folding fins for rockets and missiles
US2836105A (en) * 1953-09-01 1958-05-27 Jr Robert A Doak Contact type latch and firing mechanism for rocket launcher
US2912903A (en) * 1957-11-25 1959-11-17 James W Crothers Insulator ring
US2935843A (en) * 1954-07-01 1960-05-10 Gen Electric Combustion motor starting and signal means
US2952972A (en) * 1957-09-09 1960-09-20 Norman A Kimmel Rocket motor and method of operating same
US2960824A (en) * 1955-08-01 1960-11-22 Rohr Aircraft Corp Rocket starter for gas turbine
US3088373A (en) * 1958-12-31 1963-05-07 Roger A Robert Apparatus for storing and firing rocket bombs from aircraft
US3091052A (en) * 1959-04-10 1963-05-28 John W Ryan Multiple-stage projectile
US3139794A (en) * 1962-01-08 1964-07-07 Texaco Experiment Inc Launcher and rocket
US3190033A (en) * 1961-02-13 1965-06-22 Wilburn W Wood Thermally actuated power aerial device
US3194119A (en) * 1962-07-17 1965-07-13 Louise Rosemonde Paulette Jacq Closing devices for rocket bomb nozzle
US3228334A (en) * 1964-02-12 1966-01-11 George K Oss Bondless "high performance" rocket nozzle closure
US3229635A (en) * 1964-02-12 1966-01-18 George K Oss Rocket nozzle diaphragm seal
US3358933A (en) * 1962-09-14 1967-12-19 Aerojet General Co Rocket nozzle with automatically adjustable auxiliary nozzle portion
DE977712C (en) * 1957-03-03 1968-08-08 Franz Rudolf Dipl-Ing Thomanek A missile-powered missile equipped with a lined shaped charge
US3699893A (en) * 1971-03-30 1972-10-24 Us Navy Ignition band and cover assembly
US4009661A (en) * 1957-10-24 1977-03-01 Imrie Dodd Missile warheads
US4232843A (en) * 1977-05-25 1980-11-11 Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of National Defence Molded nozzle for rocket motor
RU2513862C1 (en) * 2013-01-30 2014-04-20 Открытое акционерное общество Научно-производственное объединение "Искра" Rocket engine nozzle plug
RU2775891C1 (en) * 2022-01-10 2022-07-11 Акционерное общество "Корпорация "Московский институт теплотехники" (АО "Корпорация "МИТ") Solid-fuel rocket engine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB189614000A (en) * 1896-06-24 1897-05-29 Alfred Vincent Newton Improvements in War Rockets.
GB540559A (en) * 1940-11-08 1941-10-22 Victor George Bull Improvements in or relating to electric primers and detonators for ammunition cartridges, torpedoes, mines and the like
US2299466A (en) * 1935-02-08 1942-10-20 Roscoe A Coffman Power generating unit and igniting means therefor
US2335763A (en) * 1940-01-16 1943-11-30 Imber Jack Safety device for aerial bombs

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB189614000A (en) * 1896-06-24 1897-05-29 Alfred Vincent Newton Improvements in War Rockets.
US2299466A (en) * 1935-02-08 1942-10-20 Roscoe A Coffman Power generating unit and igniting means therefor
US2335763A (en) * 1940-01-16 1943-11-30 Imber Jack Safety device for aerial bombs
GB540559A (en) * 1940-11-08 1941-10-22 Victor George Bull Improvements in or relating to electric primers and detonators for ammunition cartridges, torpedoes, mines and the like

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2801587A (en) * 1953-02-06 1957-08-06 Albert S Gould Folding fins for rockets and missiles
US2836105A (en) * 1953-09-01 1958-05-27 Jr Robert A Doak Contact type latch and firing mechanism for rocket launcher
DE1000718B (en) * 1953-12-01 1957-01-10 Nils Olov Malmstroem Practice bullet for recoilless firearms
US2935843A (en) * 1954-07-01 1960-05-10 Gen Electric Combustion motor starting and signal means
US2960824A (en) * 1955-08-01 1960-11-22 Rohr Aircraft Corp Rocket starter for gas turbine
DE977712C (en) * 1957-03-03 1968-08-08 Franz Rudolf Dipl-Ing Thomanek A missile-powered missile equipped with a lined shaped charge
US2952972A (en) * 1957-09-09 1960-09-20 Norman A Kimmel Rocket motor and method of operating same
US4009661A (en) * 1957-10-24 1977-03-01 Imrie Dodd Missile warheads
US2912903A (en) * 1957-11-25 1959-11-17 James W Crothers Insulator ring
US3088373A (en) * 1958-12-31 1963-05-07 Roger A Robert Apparatus for storing and firing rocket bombs from aircraft
US3091052A (en) * 1959-04-10 1963-05-28 John W Ryan Multiple-stage projectile
US3190033A (en) * 1961-02-13 1965-06-22 Wilburn W Wood Thermally actuated power aerial device
US3139794A (en) * 1962-01-08 1964-07-07 Texaco Experiment Inc Launcher and rocket
US3194119A (en) * 1962-07-17 1965-07-13 Louise Rosemonde Paulette Jacq Closing devices for rocket bomb nozzle
US3358933A (en) * 1962-09-14 1967-12-19 Aerojet General Co Rocket nozzle with automatically adjustable auxiliary nozzle portion
US3229635A (en) * 1964-02-12 1966-01-18 George K Oss Rocket nozzle diaphragm seal
US3228334A (en) * 1964-02-12 1966-01-11 George K Oss Bondless "high performance" rocket nozzle closure
US3699893A (en) * 1971-03-30 1972-10-24 Us Navy Ignition band and cover assembly
US4232843A (en) * 1977-05-25 1980-11-11 Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of National Defence Molded nozzle for rocket motor
RU2513862C1 (en) * 2013-01-30 2014-04-20 Открытое акционерное общество Научно-производственное объединение "Искра" Rocket engine nozzle plug
RU2775891C1 (en) * 2022-01-10 2022-07-11 Акционерное общество "Корпорация "Московский институт теплотехники" (АО "Корпорация "МИТ") Solid-fuel rocket engine

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