US2114214A - Self-propelling projectile - Google Patents

Self-propelling projectile Download PDF

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Publication number
US2114214A
US2114214A US67403A US6740336A US2114214A US 2114214 A US2114214 A US 2114214A US 67403 A US67403 A US 67403A US 6740336 A US6740336 A US 6740336A US 2114214 A US2114214 A US 2114214A
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US
United States
Prior art keywords
charge
powder
combustion
elements
envelope
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
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US67403A
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English (en)
Inventor
Damblane Louis
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Individual
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Individual
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Publication of US2114214A publication Critical patent/US2114214A/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

Definitions

  • the present invention relates to self-propelling projectiles,.that is to say projectiles which are l provided, in addition to their specic charge,
  • the invention is more especially, al- 10 though not exclusively, concerned, among projectiles of this kind, with rockets.
  • the object of the present invention is to provide a projectile of the kind above referred to which is better adapted to meet the requirements of practice, and in which, in particular, the combustion of the propelling charge contained in the projectile isutilized with an improved efficiency.
  • the essential feature of the present invention consists in devising the envelope of a projectile of the type above referred to in such manner that the length of said envelope is gradually reduced as the propelling charge is being gradually burnt.
  • Other features of the present invention will result from the following detailed description of 25 some specific embodiments thereof.
  • Fig. 1 is anelevatlonal view, partly in section, of a rocket made according to an embodiment of the present invention
  • Figs. 2 and 3 are views, similar to Fig. 1, relating to other embodiments.
  • I further provide, in the direction of the axis of each chamber I, 2, 3, or 4, a nozzle 5, consisting of a cavity or recess, preferably of the shape of a frustum of a cone, the dimensions of which will be moreparticularly referred to in what follows, said nozzleubeing intended to facilitate the propagation of combustion in the charge.
  • the 4respective chambers i, 2, 3 and 4 are separated from one another by means of annular elements 6, made for instance of cardboard, which prevent premature ignition of the successive charges of -said chambers.
  • the charges may consist of any 4suitable matters, for instance powder.
  • said envelope or cartridge is devised in such manner that its length is gradually reduced as the propelling charge that it contains is being burnt.
  • the cartridge or envelope is constituted by the mere juxtaposition of annular elements 1, of copper for instance, said elements being kept in position owing to the cohesion of the charge of powder they surround.v
  • the combustion of the charge of powder produces the successive elimination of annular elements 1.
  • Rose's metal (1 part of tin, 1 of lead, 2 of bis- -muth) the melting point of which is 110;
  • Woods metal (4 parts of tin, 8 of lead, 15' of bismuth and 4 of cadmium), the melting point of which is 70 C.;
  • Lipowitz metal (4 parts of tin, 2 of lead, 16
  • I may, fo
  • annular parts separating the envelope into a plurality of elements said annular separating parts being made of one of these metals.
  • the elements 8, 9, I0 and Il ofthe envelope are made of Woods metal.
  • elements of the cartridge or envelope made of any metal consisting, as shown by Fig. 3, of four sleeves 8', 9', I0', Il' of copper, ⁇ or preferably of magnesium or of a light alloy oi.' this metal, said sleeves being connected with one another and with the nose of the rocket by annular elements made, at least partly, of Woods metal.
  • Nozzle 5 must then be given a size .such that the particles of powder in contact with ring I4' given oiby the vvexhaust gases ensure a continuous or discontinuous elimination of these elements.
  • the projectile above described may further includel any suitable stabilizing device, such for instance as ribs or ns which are carried either by the elements intended to be eliminated, or by the portion of said projectile that is intended to remainas long as said projectile is moving along its path oi.'I travel.
  • any suitable stabilizing device such for instance as ribs or ns which are carried either by the elements intended to be eliminated, or by the portion of said projectile that is intended to remainas long as said projectile is moving along its path oi.'I travel.
  • combustion chambers may include a number of combustion chambers as high as it is desired;
  • a rocket according to the present invention may be combined with various devices, such, for example
  • the projectile might include not l.
  • a rocket having a charge of powder divided into a plurality of parts, each of such parts having a recess therein, a casing surrounding said parts and formed of a plurality of metallic elements associated with the respective charge 'parts I may also, according to another embodiment.
  • a rocket having a. charge, of powder dividedr into a vplurality of parta-each of such parts having a recess therein, a casing surrounding said parts and formed of a plurality of metallic eleausgew o! the powder forming the charge. and iniusible rings joining said elements, said recesses being so located in each part-oi' the charge that between the recess and thewall of the fusible metallic element there is a layer of powder of suiicient thickness to prevent the melting of each fusible metallic element until the part of the charge ring there is a. layer of powder oi suicient thickness to prevent the melting of leach fusible ring until the part of the charge which is contained in the corresponding influsible section has been substantially completely burned.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US67403A 1935-03-09 1936-03-05 Self-propelling projectile Expired - Lifetime US2114214A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE2114214X 1935-03-09

Publications (1)

Publication Number Publication Date
US2114214A true US2114214A (en) 1938-04-12

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ID=3895609

Family Applications (1)

Application Number Title Priority Date Filing Date
US67403A Expired - Lifetime US2114214A (en) 1935-03-09 1936-03-05 Self-propelling projectile

Country Status (3)

Country Link
US (1) US2114214A (no)
BE (1) BE408330A (no)
FR (1) FR803021A (no)

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2424934A (en) * 1944-11-17 1947-07-29 Melvin E Kasper Projectile
US2454096A (en) * 1943-05-11 1948-11-16 Schermuly Pistol Rocket App Means for discharging rockets
US2600678A (en) * 1949-03-11 1952-06-17 Olin Ind Inc Rocket powder
US2749705A (en) * 1951-01-03 1956-06-12 Gen Electric Fusible link jet motor control
US2920443A (en) * 1955-05-25 1960-01-12 Higginson John Rocket propellant grain with helically grooved perforation
US2956401A (en) * 1959-06-12 1960-10-18 Ernest M Kane Variable thrust rocket motor
US3000597A (en) * 1951-08-15 1961-09-19 Alfred J Bell Rocket-propelled missile
US3017746A (en) * 1958-06-16 1962-01-23 Phillips Petroleum Co Disposable elastic rocket case
US3032970A (en) * 1957-01-25 1962-05-08 Phillips Petroleum Co Disposable rocket motor
US3043221A (en) * 1958-06-02 1962-07-10 Frank H Swanser Rocket propulsion method and means
US3067575A (en) * 1959-01-02 1962-12-11 Thompson Ramo Wooldridge Inc Disposable rocket motor
US3122884A (en) * 1961-05-19 1964-03-03 Atlantic Res Corp Rocket motor
US3137126A (en) * 1961-01-11 1964-06-16 North American Aviation Inc Method and means for forming a gaseous passage
US3142959A (en) * 1959-09-11 1964-08-04 Phillips Petroleum Co Range control of self propelled missile
US3151559A (en) * 1961-06-20 1964-10-06 Schermuly Pistol Rocket App Pyrotechnic propellant charge
US3172255A (en) * 1961-09-26 1965-03-09 United Aircraft Corp Ignition device
US3175497A (en) * 1962-02-20 1965-03-30 United Aircraft Corp Segmented rocket engine
US3199406A (en) * 1961-06-21 1965-08-10 Mb Assoc In-line launching
US3250216A (en) * 1960-01-26 1966-05-10 Zissimos A Typaldos Autophage rocket
US3292302A (en) * 1964-09-14 1966-12-20 Estes Ind Multistage model rocket
US3319520A (en) * 1965-06-23 1967-05-16 Trw Inc High speed low shock separation system
US3369365A (en) * 1965-10-18 1968-02-20 Henry A. Olson Solid propellant rocket motor
US3397638A (en) * 1961-03-08 1968-08-20 Mb Assoc Rocket launcher
US3517615A (en) * 1961-07-14 1970-06-30 Us Navy Explosive wave shaper
US3554078A (en) * 1969-02-10 1971-01-12 Joseph S Horvath Spherical missile and launching means therefor
US3611935A (en) * 1969-10-31 1971-10-12 Us Navy Small caliber dual colored signal flare
US3811380A (en) * 1958-01-30 1974-05-21 Cava Ind Rocket and propellant therefor
US4723736A (en) * 1986-08-18 1988-02-09 Todd Rider Rocket staging system
US4930421A (en) * 1988-07-11 1990-06-05 The Boeing Company Partitioned, fluid supported, high efficiency traveling charge for hyper-velocity guns
US5172875A (en) * 1988-03-30 1992-12-22 Israel Fried Space launcher and method for launching objects into space
US6148610A (en) * 1997-06-16 2000-11-21 Aerospatiale Societe Nationale Industrielle Solid propellant charge for a propulsion unit and propulsion unit equipped with such a charge
WO2001038711A1 (en) * 1999-11-23 2001-05-31 Technanogy, Llc End-burning rocket motor
US7254936B1 (en) * 2004-04-26 2007-08-14 Knight Andrew F Simple solid propellant rocket engine and super-staged rocket
WO2013001267A1 (en) * 2011-06-28 2013-01-03 Mbda Uk Limited A bomb for deployment from an air vehicle
EP2602466A1 (en) * 2011-12-07 2013-06-12 MBDA UK Limited A bomb for deployment from an air vehicle
RU2509909C1 (ru) * 2012-07-10 2014-03-20 Юрий Дмитриевич Сасов Реактивный двигатель

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2454096A (en) * 1943-05-11 1948-11-16 Schermuly Pistol Rocket App Means for discharging rockets
US2424934A (en) * 1944-11-17 1947-07-29 Melvin E Kasper Projectile
US2600678A (en) * 1949-03-11 1952-06-17 Olin Ind Inc Rocket powder
US2749705A (en) * 1951-01-03 1956-06-12 Gen Electric Fusible link jet motor control
US3000597A (en) * 1951-08-15 1961-09-19 Alfred J Bell Rocket-propelled missile
US2920443A (en) * 1955-05-25 1960-01-12 Higginson John Rocket propellant grain with helically grooved perforation
US3032970A (en) * 1957-01-25 1962-05-08 Phillips Petroleum Co Disposable rocket motor
US3811380A (en) * 1958-01-30 1974-05-21 Cava Ind Rocket and propellant therefor
US3043221A (en) * 1958-06-02 1962-07-10 Frank H Swanser Rocket propulsion method and means
US3017746A (en) * 1958-06-16 1962-01-23 Phillips Petroleum Co Disposable elastic rocket case
US3067575A (en) * 1959-01-02 1962-12-11 Thompson Ramo Wooldridge Inc Disposable rocket motor
US2956401A (en) * 1959-06-12 1960-10-18 Ernest M Kane Variable thrust rocket motor
US3142959A (en) * 1959-09-11 1964-08-04 Phillips Petroleum Co Range control of self propelled missile
US3250216A (en) * 1960-01-26 1966-05-10 Zissimos A Typaldos Autophage rocket
US3137126A (en) * 1961-01-11 1964-06-16 North American Aviation Inc Method and means for forming a gaseous passage
US3397638A (en) * 1961-03-08 1968-08-20 Mb Assoc Rocket launcher
US3122884A (en) * 1961-05-19 1964-03-03 Atlantic Res Corp Rocket motor
US3151559A (en) * 1961-06-20 1964-10-06 Schermuly Pistol Rocket App Pyrotechnic propellant charge
US3199406A (en) * 1961-06-21 1965-08-10 Mb Assoc In-line launching
US3517615A (en) * 1961-07-14 1970-06-30 Us Navy Explosive wave shaper
US3172255A (en) * 1961-09-26 1965-03-09 United Aircraft Corp Ignition device
US3175497A (en) * 1962-02-20 1965-03-30 United Aircraft Corp Segmented rocket engine
US3292302A (en) * 1964-09-14 1966-12-20 Estes Ind Multistage model rocket
US3319520A (en) * 1965-06-23 1967-05-16 Trw Inc High speed low shock separation system
US3369365A (en) * 1965-10-18 1968-02-20 Henry A. Olson Solid propellant rocket motor
US3554078A (en) * 1969-02-10 1971-01-12 Joseph S Horvath Spherical missile and launching means therefor
US3611935A (en) * 1969-10-31 1971-10-12 Us Navy Small caliber dual colored signal flare
US4723736A (en) * 1986-08-18 1988-02-09 Todd Rider Rocket staging system
US5172875A (en) * 1988-03-30 1992-12-22 Israel Fried Space launcher and method for launching objects into space
US4930421A (en) * 1988-07-11 1990-06-05 The Boeing Company Partitioned, fluid supported, high efficiency traveling charge for hyper-velocity guns
US6148610A (en) * 1997-06-16 2000-11-21 Aerospatiale Societe Nationale Industrielle Solid propellant charge for a propulsion unit and propulsion unit equipped with such a charge
WO2001038711A1 (en) * 1999-11-23 2001-05-31 Technanogy, Llc End-burning rocket motor
US7254936B1 (en) * 2004-04-26 2007-08-14 Knight Andrew F Simple solid propellant rocket engine and super-staged rocket
WO2013001267A1 (en) * 2011-06-28 2013-01-03 Mbda Uk Limited A bomb for deployment from an air vehicle
US8910576B2 (en) 2011-06-28 2014-12-16 Mbda Uk Limited Bomb for deployment from an air vehicle
EP2602466A1 (en) * 2011-12-07 2013-06-12 MBDA UK Limited A bomb for deployment from an air vehicle
RU2509909C1 (ru) * 2012-07-10 2014-03-20 Юрий Дмитриевич Сасов Реактивный двигатель

Also Published As

Publication number Publication date
FR803021A (fr) 1936-09-21
BE408330A (no)

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