US3377954A - Explosive-started generator - Google Patents

Explosive-started generator Download PDF

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Publication number
US3377954A
US3377954A US269321A US26932152A US3377954A US 3377954 A US3377954 A US 3377954A US 269321 A US269321 A US 269321A US 26932152 A US26932152 A US 26932152A US 3377954 A US3377954 A US 3377954A
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Prior art keywords
detonator
ogive
duct
generator
ring
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Expired - Lifetime
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US269321A
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Rabinow Jacob
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US Department of Army
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Army Usa
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/28—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids
    • F42C15/295—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids operated by a turbine or a propeller; Mounting means therefor

Definitions

  • This invention relates to electronic proximity fuses for explosive missiles and more particularly to fuses of the class in which are incorporated air turbine means for driving an electrical generator.
  • a longitudinal duct is formed in the nose of the fuse through which air passes while the missileis in flight to drive a turbine coupled to an electrical generator. It is essential that the generator be brought up to speed immediately upon firing or launching the missile.
  • the prime object of the invention is a new and novel means for instantly bringing the generator up to operating speed upon firing or launching of the missile.
  • 1 generally indicates an electronic type of fuse having an ogive 2 of nonconductive material affixed to a conductive base member 3 which is in threaded engagement with the missile body 4 containing an explosive charge 5.
  • a metallic tubular member 7 Fixed in a longitudinal bore 6 of the ogive is a metallic tubular member 7 having one end 7b threaded and in engagement with turbine housing 18 as indicated by 8.
  • the housing 18 is provided with exhaust ports 30 which are sealed by an annular ring 21, preferably made of plastic.
  • a high pressure gas explosive means 9 and a detonator 10 Positioned in the forward end of member 7 is a high pressure gas explosive means 9 and a detonator 10 therefor.
  • the forward opening of the tubular member 7 is sealed by means of a protective cap 31.
  • the rearward opening of said member opens into a turbine chamber 18a.
  • One lead 11 of the detonator is connected to the member 7 and the other lead 12 is threaded through a perforation 7a in the tubular member and a channel 13 in the ogive to a metallic contact ring 14 embedded in the peripheral surface of the ogive.
  • the lead 12 is soldered or otherwise fixed to the ring in a conventional manner.
  • base member 3 The forward end of base member 3 is provided with a recess 15 in which is fixed a housing 16 containing an electric generator and associated electronic means.
  • the generator is coupled to a turbine 17 in housing 18 by means of a shaft 19.
  • the rearward end of the base member is provided with 3,377,954 Patented Apr. 16, ISfiS a recess 22, separated from recess 15 by means of a partition 23 having a perforation 24 formed centrally therein.
  • a housing 25 containing a detonator 25a and booster 25b is placed in the recess 22.
  • Leads 26-27 passing through the perforation 24 connect the output of the electronic means with the detonator in housing 25.
  • the launching means 29 is provided with a resilient contact member 32 for engagement with the ring 14 upon launching of the missile.
  • the resilient member 32 is insulated from the launching means and is connected to one terminal of an electric energy supply 28. The other terminal of the electric energy supply is connected to the launching means 29.
  • resilient member 32 momentarily contacts the ring 14 to close the circuit formed by the detonator 10, tubular member 7, housing 18, base 3 and body 4 in contact with the launching means 29. As this circuit is completed, current flows through it to actuate the detonator 10 which fires the means 9. The expanding gases from the means 9 expel cap 31 and annular seal 21 and at the same time impart rapid initial rotation to turbine 17.
  • a turbo-generator powered fuse for explosive missiles means for causing rapid initial rotation of the turbine of said turbo-generator, said means comprising a nonconductive ogive, a longitudinal bore in said ogive, said bore open to the air at its forward end and to a turbogenerator housing at its rearward end, a metallic duct in said bore, an annular metallic ring embedded in the peripheral surface of said ogive, an electric detonator and high pressure gas producing means positioned in the forward end of said duct, one lead of the detonator being affixed to said duct, the other lead of said detonator being affixed to said annular ring, said ring upon firing of the projectile making contact with the electrical contact means on a launcher to cause actuation of the detonator, the actuation of said detonator firing the high pressure gas producing means whereupon the high pressure gas flows through said duct to cause initial rotation of said turbine.
  • said high pressure gas producing means comprises an explosive charge.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Automotive Seat Belt Assembly (AREA)

Description

April 16, 1968 J. RABINOW EXPLOSIVE-STARTED GENERATOR Filed Jan. 31, 1952 IN VEN TOR.
LT 11: uh Ruhinuw ATTORNEYS AGE/v7- United States Patent 3,377,954 EXPLOSIVE-STARTED GENERATOR Jacob Rabinow, Takoma Park, Md., assignor to the United States of America as represented by the Secretary 0f the Army Filed Jan. 31, 1952, Ser. No. 269,321 2 Claims. (Cl. 10270.2)
The invention described herein may be manufactured and used by or for the Government for governmental purposes without the payment of any royalty thereon.
This invention relates to electronic proximity fuses for explosive missiles and more particularly to fuses of the class in which are incorporated air turbine means for driving an electrical generator.
In fuses of the above referred to type, a longitudinal duct is formed in the nose of the fuse through which air passes while the missileis in flight to drive a turbine coupled to an electrical generator. It is essential that the generator be brought up to speed immediately upon firing or launching the missile. In view thereof, the prime object of the invention is a new and novel means for instantly bringing the generator up to operating speed upon firing or launching of the missile.
The specific nature of the invention as well as other objects and advantages thereof will clearly appear from the following description and accompanying drawing in which the sole figure is a longitudinal sectional view of a fuse embodying the invention.
Referring now to the drawing wherein 1 generally indicates an electronic type of fuse having an ogive 2 of nonconductive material affixed to a conductive base member 3 which is in threaded engagement with the missile body 4 containing an explosive charge 5. Fixed in a longitudinal bore 6 of the ogive is a metallic tubular member 7 having one end 7b threaded and in engagement with turbine housing 18 as indicated by 8. The housing 18 is provided with exhaust ports 30 which are sealed by an annular ring 21, preferably made of plastic. Positioned in the forward end of member 7 is a high pressure gas explosive means 9 and a detonator 10 therefor. The forward opening of the tubular member 7 is sealed by means of a protective cap 31. The rearward opening of said member opens into a turbine chamber 18a. One lead 11 of the detonator is connected to the member 7 and the other lead 12 is threaded through a perforation 7a in the tubular member and a channel 13 in the ogive to a metallic contact ring 14 embedded in the peripheral surface of the ogive. The lead 12 is soldered or otherwise fixed to the ring in a conventional manner.
The forward end of base member 3 is provided with a recess 15 in which is fixed a housing 16 containing an electric generator and associated electronic means. The generator is coupled to a turbine 17 in housing 18 by means of a shaft 19.
The rearward end of the base member is provided with 3,377,954 Patented Apr. 16, ISfiS a recess 22, separated from recess 15 by means of a partition 23 having a perforation 24 formed centrally therein. A housing 25 containing a detonator 25a and booster 25b is placed in the recess 22. Leads 26-27 passing through the perforation 24 connect the output of the electronic means with the detonator in housing 25. The launching means 29 is provided with a resilient contact member 32 for engagement with the ring 14 upon launching of the missile. The resilient member 32 is insulated from the launching means and is connected to one terminal of an electric energy supply 28. The other terminal of the electric energy supply is connected to the launching means 29.
When the missile is fired, resilient member 32 momentarily contacts the ring 14 to close the circuit formed by the detonator 10, tubular member 7, housing 18, base 3 and body 4 in contact with the launching means 29. As this circuit is completed, current flows through it to actuate the detonator 10 which fires the means 9. The expanding gases from the means 9 expel cap 31 and annular seal 21 and at the same time impart rapid initial rotation to turbine 17.
It will be apparent that the embodiment shown is only exemplary and that various modifications can be made in construction and arrangement within the scope of the invention as defined in the appended claims.
I claim:
1. In a turbo-generator powered fuse for explosive missiles, means for causing rapid initial rotation of the turbine of said turbo-generator, said means comprising a nonconductive ogive, a longitudinal bore in said ogive, said bore open to the air at its forward end and to a turbogenerator housing at its rearward end, a metallic duct in said bore, an annular metallic ring embedded in the peripheral surface of said ogive, an electric detonator and high pressure gas producing means positioned in the forward end of said duct, one lead of the detonator being affixed to said duct, the other lead of said detonator being affixed to said annular ring, said ring upon firing of the projectile making contact with the electrical contact means on a launcher to cause actuation of the detonator, the actuation of said detonator firing the high pressure gas producing means whereupon the high pressure gas flows through said duct to cause initial rotation of said turbine.
2. The invention as set forth in claim 1 wherein said high pressure gas producing means comprises an explosive charge.
References Cited UNITED STATES PATENTS 4/ 1949 Senn 107-70.2 7/ 1951 Clapham -39.47
D. D. DOTY, W. J. CURRAN, T. H. WEBB,
Assistant Examiners.

Claims (1)

1. IN A TURBO-GENERATOR POWERED FUSE FOR EXPLOSIVE MISSILES, MEANS FOR CAUSING RAPID INITIAL ROTATION OF THE TURBINE OF SAID TURBO-GENERATOR, SAID MEANS COMPRISING A NONCONDUCTIVE OGIVE, A LONGITUDINAL BORE IN SAID OGIVE, SAID BORE OPEN TO THE AIR AT ITS FORWARD END AND TO A TURBOGENERATOR HOUSING AT ITS REARWARD END, A METALLIC DUCT IN SAID BORE, AN ANNULAR METALLIC RING EMBEDDED IN THE PERIPHERAL SURFACE OF SAID OGIVE, AN ELECTRIC DETONATOR AND HIGH PRESSURE GAS PRODUCING MEANS POSITIONED IN THE FORWARD END OF SAID DUCT, ONE LEAD OF THE DETONATOR BEING AFFIXED TO SAID DUCT, THE OTHER LEAD OF SAID DETONATOR BEING AFFIXED TO SAID ANNULAR RING, SAID RING UPON FIRING OF THE PROJECTILE MAKING CONTACT WITH THE ELECTRICAL CONTACT MEANS ON A LAUNCHER TO CAUSE ACTUATION OF THE DETONATOR, THE ACTUATION OF SAID DETONATOR FIRING THE HIGH PRESSURE GAS
US269321A 1952-01-31 1952-01-31 Explosive-started generator Expired - Lifetime US3377954A (en)

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3861312A (en) * 1972-07-15 1975-01-21 Messerschmitt Boelkow Blohm Ignition device having an ignition sequence including fuse elements for preventing an unintentional release
US3906862A (en) * 1974-04-23 1975-09-23 Us Army Buckling protective fuze cap
US4248153A (en) * 1977-12-21 1981-02-03 A/S Kongsberg Vapenfabrikk Combination fuze for missiles
FR2495761A1 (en) * 1980-12-09 1982-06-11 Thomson Brandt Ogive shaped fuse for bomb - includes wind vane to load pyrotechnic command chain firing explosive charge in predetermined sequence
US20110041719A1 (en) * 2009-01-29 2011-02-24 Gennadii Ivtsenkov Inertial Accumulator (IA) for onboard power supply of spinning and non-spinning projectiles and Directed Energy Projectiles
US11867487B1 (en) 2021-03-03 2024-01-09 Wach Llc System and method for aeronautical stabilization

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2468120A (en) * 1947-12-17 1949-04-26 Jurg A Senn Air turbine generator for fuses
US2559006A (en) * 1948-04-28 1951-07-03 Power Jets Res & Dev Ltd Rotary starting means for rotary engines with cartridge chamber and surplus gas releasing means

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2468120A (en) * 1947-12-17 1949-04-26 Jurg A Senn Air turbine generator for fuses
US2559006A (en) * 1948-04-28 1951-07-03 Power Jets Res & Dev Ltd Rotary starting means for rotary engines with cartridge chamber and surplus gas releasing means

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3861312A (en) * 1972-07-15 1975-01-21 Messerschmitt Boelkow Blohm Ignition device having an ignition sequence including fuse elements for preventing an unintentional release
US3906862A (en) * 1974-04-23 1975-09-23 Us Army Buckling protective fuze cap
US4248153A (en) * 1977-12-21 1981-02-03 A/S Kongsberg Vapenfabrikk Combination fuze for missiles
FR2495761A1 (en) * 1980-12-09 1982-06-11 Thomson Brandt Ogive shaped fuse for bomb - includes wind vane to load pyrotechnic command chain firing explosive charge in predetermined sequence
US20110041719A1 (en) * 2009-01-29 2011-02-24 Gennadii Ivtsenkov Inertial Accumulator (IA) for onboard power supply of spinning and non-spinning projectiles and Directed Energy Projectiles
US11867487B1 (en) 2021-03-03 2024-01-09 Wach Llc System and method for aeronautical stabilization

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