US2989919A - Depth charge having rocket motor propulsion - Google Patents

Depth charge having rocket motor propulsion Download PDF

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Publication number
US2989919A
US2989919A US16370A US1637060A US2989919A US 2989919 A US2989919 A US 2989919A US 16370 A US16370 A US 16370A US 1637060 A US1637060 A US 1637060A US 2989919 A US2989919 A US 2989919A
Authority
US
United States
Prior art keywords
charge
rocket motor
depth charge
depth
propellant
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
US16370A
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English (en)
Inventor
Engborg Nils Harry
Gustafsson Lars Erik
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.)
Saab Bofors AB
Original Assignee
Bofors AB
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 Bofors AB filed Critical Bofors AB
Application granted granted Critical
Publication of US2989919A publication Critical patent/US2989919A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/22—Missiles having a trajectory finishing below water surface
    • 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
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/92—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control incorporating means for reversing or terminating thrust
    • 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
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/663—Steering by varying intensity or direction of thrust using a plurality of transversally acting auxiliary nozzles, which are opened or closed by valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/20—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B19/00—Marine torpedoes, e.g. launched by surface vessels or submarines; Sea mines having self-propulsion means
    • F42B19/12—Propulsion specially adapted for torpedoes
    • F42B19/26—Propulsion specially adapted for torpedoes by jet propulsion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B21/00—Depth charges

Definitions

  • This invention relates to depth charges and, more particularly, to a depth charge propelled by a rocket motor having at least two operating speeds.
  • the greatest horizontal range of a depth charge is determined by the energy content of the rocket motor, so that the rocket motor should, preferably, contain the greatest possible quantity of fuel in relation to the internal weight.
  • the rocket motor In launching such depth charges against targets near the launching site, it is often desir able or necessary to fire the depth charge at a rate of speed lower than the maximum rate of speed provided by the motor. This can be achieved, for example, by having the motor divided into two sections and igniting only one section thereof. In such an arrangement, the maximum rate of speed is attained by igniting both sections. It is evident, however, that with the same total weight, such a rocket motor will contain less propellant than a motor with a single section, as walls are required between the separate sections as well as an extra nozzle.
  • Another object of the present invention is to provide a rocket motor propelled depth charge of the type described which is extremely simple in construction, efliciently arranged in terms of fuel-capacity-to-overall-weight, and which employs rocket motor parts that are substantially foolproof in operation.
  • FIGURE 1 is a longitudinal cross sectional view of a depth charge made in accordance with the present invention.
  • FIGURE 2 is an enlarged fragmentary cross sectional view of certain parts of the present invention shown in FIGURE 1;
  • FIGURE 3 is a view similar to FIGURE 2, with the parts in an adjusted position.
  • a depth charge made in accordance with the present invention is shown to include an outer casing 1 within which a bursting charge 2, such as TNT, a fuse 3, and a rocket motor 4, are encased.
  • a bursting charge 2 such as TNT, a fuse 3, and a rocket motor 4 are encased.
  • the rocket motor 4 contains two propellant charges 5, 6, one such charge 5 generating propellant gases which flow outwardly through a nozzle 7, and the other charge 6 generating propellant gases which flow out through an inner nozzle 8 concentrically arranged with respect to 2,989,919 Patented June 27, 1961 Ice the nozzle 7 of the first propellant charge.
  • a rocket motor wall 9 separates the two propellant charges 5, 6, thus providing for the ignition of either one or both of such charges 5, 6, to obtain different firing rates of speed.
  • a relief valve housing 11 is mounted upon the front wall of a firing chamber 10 enclosing the nose end of one of the propellant charges 5.
  • the relief valve housing .11 has four radially acting valve plates 12, each of which is normally radially outwardly extended to close a relief aperture 12a in the firing chamber 10, each such valve plate 12 being secured in the aperture closing position and prevented from moving radially inwardly by a guide piston 13 slidably supported within the relief valve housing 11 for movement between the normally rearwardly disposed position shown in FIGURE 2 and a forwardly extended position as shown in FIGURE 3.
  • each set of relief conduits opens forwardly through the nose end of the depth charge, and each such relief conduit includes an inner tube 15, 16.
  • the tubes are insulated from the TNT charge 2 by means of air spaces between the inner tubes 15, -16 and outer tubular walls 17, 18, respectively.
  • each of the inner tubes 15, 16 is provided with a nozzle 19, 20 respectively.
  • control means may be provided for selecting the particular propellant charges 5, 6 to be ignited as well as the bursting charge 14 controlling the operation of the relief valve.
  • a depth charge comprising, in combination, an outer casing having a forward nose end and a rear tail end, a rocket motor mounted within said casing having a propellant charge storage chamber, a nozzle assembly having one end in communication with said chamber and an opposite end opening outwardly through said rear end of said casing, a relief valve carried by said motor communicating with said chamber, said relief valve including a housing having at least one aperture, a valve plate overlying said aperture, -a guide piston slidably supported within said housing for movement relative to said valve plate normally maintaining said valve plate in a closed position with said aperture, a propellant gas relief conduit communicating at one end with said relief valve and at the opposite end opening outwardly through said nose end of said casing, and a positioning busting charge acting between said housing and said guide piston of the valve for dislodging said piston from said plate upon firing to release said valve plate from closing engagement with said housing aperture to provide communication between said chamber of the casing and said relief conduit through said aperture, said relief valve controlling the flow of propellant gases through said relief conduit to adjust the
  • a depth charge as set forth in claim 1, wherein said nozzle assembly comprises a set of concentrically arranged rearwardly opening nozzles each having a separately controlled firing chamber, said relief valve being associated with at least one of said nozzles.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Testing Of Engines (AREA)
  • Portable Nailing Machines And Staplers (AREA)
US16370A 1959-03-21 1960-03-21 Depth charge having rocket motor propulsion Expired - Lifetime US2989919A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE273659 1959-03-21

Publications (1)

Publication Number Publication Date
US2989919A true US2989919A (en) 1961-06-27

Family

ID=20367034

Family Applications (1)

Application Number Title Priority Date Filing Date
US16370A Expired - Lifetime US2989919A (en) 1959-03-21 1960-03-21 Depth charge having rocket motor propulsion

Country Status (6)

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US (1) US2989919A (US06265458-20010724-C00056.png)
BE (1) BE588749A (US06265458-20010724-C00056.png)
DE (1) DE1130734B (US06265458-20010724-C00056.png)
FR (1) FR1251728A (US06265458-20010724-C00056.png)
GB (1) GB868326A (US06265458-20010724-C00056.png)
NL (2) NL110668C (US06265458-20010724-C00056.png)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3251267A (en) * 1963-06-18 1966-05-17 Emerson Electric Co Spin rocket and launcher
US9823053B1 (en) * 2016-08-29 2017-11-21 The Boeing Company Solid-fuel ramjet ammunition

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2850976A (en) * 1955-06-28 1958-09-09 Howard S Seifert Thrust cancellation device for use in solid propellant rocket
US2941470A (en) * 1955-03-02 1960-06-21 Brandt Soc Nouv Ets Self-propelled projectile

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR498378A (fr) * 1915-05-10 1920-01-09 Max De Watteville Projectile
FR525867A (fr) * 1917-06-04 1921-09-28 Louis Ferdinand Bourguignon Obus porte-messages
DE568066C (de) * 1930-08-02 1933-01-13 Elek Sche App M B H Ges Steuerung fuer Raketen- und aehnliche Geschosse
US2856851A (en) * 1955-07-27 1958-10-21 Harold E Thomas Apparatus for zoning rockets

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2941470A (en) * 1955-03-02 1960-06-21 Brandt Soc Nouv Ets Self-propelled projectile
US2850976A (en) * 1955-06-28 1958-09-09 Howard S Seifert Thrust cancellation device for use in solid propellant rocket

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3251267A (en) * 1963-06-18 1966-05-17 Emerson Electric Co Spin rocket and launcher
US9823053B1 (en) * 2016-08-29 2017-11-21 The Boeing Company Solid-fuel ramjet ammunition

Also Published As

Publication number Publication date
BE588749A (fr) 1960-07-18
FR1251728A (fr) 1961-01-20
NL249367A (US06265458-20010724-C00056.png)
NL110668C (US06265458-20010724-C00056.png) 1964-09-15
DE1130734B (de) 1962-05-30
GB868326A (en) 1961-05-17

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