US2661691A - Projectile - Google Patents

Projectile Download PDF

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Publication number
US2661691A
US2661691A US136824A US13682450A US2661691A US 2661691 A US2661691 A US 2661691A US 136824 A US136824 A US 136824A US 13682450 A US13682450 A US 13682450A US 2661691 A US2661691 A US 2661691A
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US
United States
Prior art keywords
projectile
nozzles
blades
combustion chamber
tail
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
US136824A
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English (en)
Inventor
Brandt Edgar William
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.)
Anstalt Fuer die Entwicklung von Erfindungen und Gewerblichen Anwendungen ENERGA
Original Assignee
Anstalt Fuer die Entwicklung von Erfindungen und Gewerblichen Anwendungen ENERGA
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
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Application filed by Anstalt Fuer die Entwicklung von Erfindungen und Gewerblichen Anwendungen ENERGA filed Critical Anstalt Fuer die Entwicklung von Erfindungen und Gewerblichen Anwendungen ENERGA
Application granted granted Critical
Publication of US2661691A publication Critical patent/US2661691A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/30—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants with the propulsion gases exhausting through a plurality of nozzles
    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • 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
    • 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
    • F42B10/26—Stabilising arrangements using spin
    • F42B10/28—Stabilising arrangements using spin induced by gas action
    • F42B10/30—Stabilising arrangements using spin induced by gas action using rocket motor nozzles
    • 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

  • This invention relates to a self-propelled pro- .iectile which is stabilized during its trajectory by the provision of a tail.
  • the projectile according to the present invention includes a self-propelling device consisting of a tubular combustion chamber containing the propellant and including at its end a nozzle assembly, its external terminal part acting as a tail carrier for stabilizing blades of the same calibre as the projectile.
  • the blades are arrange in pairs, each pair of blades being arranged obliquely and symmetrically with respect to the longitudinal axis of the projectile.
  • this arrangement of the blades by alternate inclination, imparts to the projectile a far greater stabilizing power than that which would result from an ordinary straight tail. This phenomenon is accounted for by the carrying effect arising from the contraction of the air streams between two converging blades and by the vacuum created between the diverging ones.
  • At least one nozzle of the self-pro-' pelling device includes on its internal face an eccentric conical recess so directed as to impart to the projectile a slow rotation in relation to its linear speed.
  • This rotation prevents any deviation of the projectile, such as might be caused by manufacturing irregularities, machining tolerances, as well as by a variation of the discharge of the nozzles as between themselves, because the ei'iect of these asymmetries on a tailed projectile tends systematically to cause it to deviate from the trajectory imparted to it so that a rotation or gyraticn, even a slow one, corrects these errors by causing the projectile to follow a helicoidal movement around its theoretical trajectory.
  • this gyration still further increases the action and the stabilizing power of the tail.
  • experience shows that the best stabilizing effect on the one hand and the smallest dispersion on the other hand, result from an inclination of 2 to of the blades as between themselves for an initial speed of the projectile ranging from to 300 metres per second.
  • the tail is made as a single unit and secured on the projectile by the nozzle carrier.
  • the tail and the nozzle carrier should constitute a single unit; the direction of the nozzles always remaining the same in relation to the stabilizing blades.
  • the gyration of the projectile is started at the beginning of the self-propulsion, i. e. in the weapon which fires said projectile, and in accordance with still a further feature of the invention, the blades which are inclined in the direction of rotation of the projectile are formed of a height greater than that of the other blades so that only the former have the calibre of the firing weapon.
  • the nozzles are arranged in known manner, obliquely in relation to the longitudinal axis of the projectile. The result is that the gases diverge on ejection and it is thus possible, without danger to the firer, to propel the projectile after its exit from the weapon.
  • each of the nozzles by closing each of the nozzles by a membrane which collapses only when the pressure of the ases inside the tubular combustion chamber reaches a predetermined value, which is itself a function of the thickness of the said membranes which, for equal resistances, collapse simultaneously. It is, however, advantageous to provide two or more additional safety nozzles arranged symmetrically on the periphery of the nozzle carrier and closed by a membrane having a resistance greater than that of those which close the other nozzles.
  • the safety nozzles are intended for opening only in case of abnormal rise of pressure.
  • this precaution will enable the wall of the combustion chamber to be of a thickness smaller than that of ordinary projectiles of the same type required to work in similar conditions.
  • the result will be a decrease in weight of the rear of the projectile and, consequently, an increase of the stabilizing power. This decrease in weight will also cause an increase in speed of the projectile.
  • the membranes closing the safety nozzles may be covered, on their inside face, by insulating washers, for example, of cork, which are intended to keep constant the resistance of the said membranes, which are insulated from the high rise in temperature taking place inside the combustion chamber as soon as the propulsion agent is ignited.
  • each membrane is kept on its seat, provided in the corresponding nozzle, by means of a part made of a heat-resistant material which constitutes the collar of the nozzle.
  • a heat-resistant material which constitutes the collar of the nozzle.
  • the self-propelling device preferably includes, between the propellant (sticks of powder, for instance) and the nozzles, a grid adapted to act as a filter to damp the jet of fire.
  • This grid constitutes an annulus, the section of which is in the shape of a double-vault, the convex portion of which is preferably turned towards the front of the projectile.
  • FIG. 1 shows a general view of one embodiment of projectile in accordance with the invention
  • Fig. 2 is a rear view representing the arrangement of the nozzles and of the tail;
  • Fig. 3 is a cross section on the line 3-3 of Fig. 2;
  • Fig. 4 is a longitudinal section of the self-propelling device on the line 4-4 of Fig. 2;
  • Fig. 5 is a transverse section taken along the line 5-5 of Fig. 1;
  • Fig. 6 is a longitudinal section showing the front part of the propellent combustion chamber
  • Figs. 7 and 8 illustrate, in cross section, the
  • Figs. 9 and 10 show the closing of the safety nozzles.
  • the projectile includes a nose fuze I, a casing 2 which contains the explosive charge and the usual devices and a tail 3 designed as a tubular combustion chamber carrying the tail blades 4, 5.
  • the tail blades are grouped in pairs and arranged in such a way that each of the blades 4 is at a constant angle with respect to the adjoining blade 5, this angle be ing a function of the speed of the projectile along its trajectory.
  • the diameter of the tubular combustion chamber 3 is greater than half the calibre of the projectile, so that the height of the blades is necessarily limited.
  • Fig. 2 is an end view of the projectile seen from the rear.
  • the part 6 carries peripheral nozzles I closed internally by membranes 8.
  • Each of the nozzles 1 includes, in addition, a conical milled recess 9 (Fig. 3), imparting to the projectile a slow rotation in the direction of the arrow. This feature of the construction facilitates machining and leads to an appreciable saving in weight.
  • the membranes 8 are held between a seat formed on the inside periphery of the nozzle 1' and a collar I0 constructed of a material of high heat resistance, such, for example, as steel, whilst the nozzle carrier is machined or cast in aluminum or any other light alloy.
  • a sensitive primer cap II fixed in the primer carrier I2, serves to ignite the powder l3 and a relay charge I3a contained in a socket I4, laterally drilled to give access to the propellant I5, shown in Figs. 4 and 5 in the form of hollow cylindrical sticks.
  • the openings H of this grid are distributed laterally and prevent the ejection into the nozzles of unburnt particles of propulsive powder.
  • the front end of the combustion chamber 3 is screwed to the coupling I8 which, in turn, is screwed to the body I9 of the projectile, a part of which is shown at 29.
  • the propellant I5 does not fill the combustion chamber completely but that an extension of the latter forms a complementary chamber H.
  • the volume of this is so determined as to prevent an excessive increase of the internal pressure, for instance under the influence of a high outside temperature which, but for the safety nozzles, might go as far as to cause the tail of the projectile to explode.
  • the securing ring 22 holds the sticks It in place at their front ends.
  • the tail blades :i, 5 are made as a single unit, for instance, of plastic material, the low density of which advantageously reduces the weight of the rear of the projectile.
  • the tail is forced onto the tubular combustion chamber 3 or is secured by gluing by means of a suitable coating, and is held at the rear by the nozzle carrier 6.
  • Another feature of the invention consists in the use of an auxiliary striker 23 operating after the fashion of a valve and protected at the rear by a membrane 24. This improved arrangement prevents the rearward ejection of the jet of fire created by the powder I 3, the effect of which is then solely devoted to the ignition of the propellant 55.
  • Fig. 8 differs from that of Fig. 7 in that the nozzle carrier 5 is formed as a single unit with the tail blades t, 5, which advantageously simplifies the construction.
  • Figs. 9 and 16 show the safety nozzles symmetrically arranged either in pairs or in groups of three in accordance with the total number of peripheral nozzles provided on the projectile; the membranes 8a are more resistant than those which adjoin them and only give way when the internal pressure in the combustion chamber exceeds the permitted limit.
  • tubular combustion chamber 3 with an internal insulating lining 25 (a cardboard sheet, for instance) and with an external coating decreasing the absorption of heat by radiation (for instance, a coat of white paint).
  • an internal insulating lining 25 a cardboard sheet, for instance
  • an external coating decreasing the absorption of heat by radiation for instance, a coat of white paint
  • the striker of the fire-arm hits the primer H (eventually the membrane 21; and the striker 23, Figs. 7 and 8) which fires the ignition powder 13, 13a which, in turn, uniformly fires the sticks 15.
  • the self-propulsion of the projectile then starts in the gun barrel under the reaction effect of the gases ejected by the nozzles E, and the projectile at the same time acquires a gyratory movement, obtained either by the asymmetrical action of the gases acting inside the nozzles and provided for this purpose, or by the suitable inclination of said nozzles.
  • the propellent charge, the rate of combustion of the powder and the discharge of the nozzles are so combined that the linear speed and the gyratory speed of the projectile, at the gun muzzle, are at least equal to half of the corresponding speeds achieved at the end of the combustion of the said charge.
  • a combustion chamber for a propelling charge stabilizing fins on said chamber, each two successive fins being arranged obliquely and symmetrically with respect to an intermediate plane containing the longitudinal axis of said projectile.
  • a combustion chamber for a propelling charge stabilizing fins on said chamber, each two successive fins being arranged obliquely and symmetrically with respect to an intermediate plane containing the longitudinal axis of said projectile, any pair of two successive fins presenting between themselves a constant angle, greater than two and smaller than ten degrees, for an initial speed of the projectile ranging from 100 to 300 meters per second.
  • a combustion chamber for a propelling charge stabilizing fins on said chamber, each two successive fins being arranged obliquely and symmetrically with respect to an intermediate plane containing the longitudinal axis of said projectile, one fin of each pair of two successive fins having a greater radial height than the other fin of said pair.
  • a combustion chamber for a propelling charge stabilizing fins on said chamber, each two successive fins being arrange obliquely and symmetrically with respect to an intermediate plane containing the longitudinal axis of said projectile, one fin of each pair of two successive fins having a greater radial height than the immediately adjacent one, said greater fin being inclined in the direction of rotation of the projectile.
  • a combustion chamber for a propelling charge for a propelling charge, stabilizing fins on said chamber, a plug at the rear of said chamber, and a series of nozzles in said plug, each of said nozzles including on its internal face a rearwardly directed conical recess, said recess being located on the part of said internal face opposite to that which is directed in the sense of rotation of the projectile, said recess imparting a rotation to the projectile.
  • a combustion chamber for a propelling charge for a propelling charge, stabilizing fins on said chamber, a plug at the rear of said chamber, and
  • each of said nozzles including on its internal face a rearwardly directed conical recess, said recess being located on the part of said internal face opposite to that which is directed in the sense of rotation of the projectile, the axis of said recess being parallel to the axis of the projectile in order to impart a rotation to the projectile.
  • a rocket projectile a combustion chamher, a propelling charge in said chamber, said charge being constituted by cylindrical powder grains, an annular grid inside said chamber at the rear of the propelling charge, said grid having in the axial section the form of a double vault, the convex portion of said double-vault being directed toward the front of the projectile, said convex portion acting externally as a support for each of said powder grains.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • Fluid Mechanics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Testing Of Engines (AREA)
  • Oxygen, Ozone, And Oxides In General (AREA)
  • Fire-Extinguishing Compositions (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US136824A 1949-01-17 1950-01-04 Projectile Expired - Lifetime US2661691A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH681916X 1949-01-17

Publications (1)

Publication Number Publication Date
US2661691A true US2661691A (en) 1953-12-08

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ID=4528535

Family Applications (1)

Application Number Title Priority Date Filing Date
US136824A Expired - Lifetime US2661691A (en) 1949-01-17 1950-01-04 Projectile

Country Status (7)

Country Link
US (1) US2661691A (de)
BE (1) BE493192A (de)
CH (3) CH283467A (de)
DE (2) DE831819C (de)
GB (3) GB681977A (de)
LU (1) LU29848A1 (de)
NL (3) NL79093C (de)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2982090A (en) * 1956-08-06 1961-05-02 Phillips Petroleum Co Means to prevent perforation of starter disk during ignition delay
US3020710A (en) * 1956-03-29 1962-02-13 Stephen H Herzog Sealing means for rocket nozzles
US3167912A (en) * 1960-01-04 1965-02-02 United Aircraft Corp Thrust control for solid rocket
US3305194A (en) * 1960-03-08 1967-02-21 Robert G Conard Wind-insensitive missile
DE977712C (de) * 1957-03-03 1968-08-08 Franz Rudolf Dipl-Ing Thomanek Mit einer ausgekleideten Hohlladung ausgeruesteter Flugkoerper mit Raketentriebwerk
US3433437A (en) * 1967-01-18 1969-03-18 John E Reilly Rocket projectile
US3437289A (en) * 1966-04-04 1969-04-08 Mb Assoc Miniature rocket nozzle
FR2474699A1 (fr) * 1980-01-30 1981-07-31 Ruggieri Ets Artifice de signalisation a dipoles electromagnetiques
US6964154B1 (en) * 2003-03-11 2005-11-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Axisymmetric, throttleable non-gimballed rocket engine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH314670A (de) * 1953-04-07 1956-06-30 Bofors Ab Rakete mit Leitflügeln
DE1043875B (de) * 1955-05-02 1958-11-13 Hans Albrecht Verschluss fuer huelsenlose Geschosse, insbesondere Raketengeschosse
DE2553201C2 (de) * 1975-11-27 1984-05-10 Rheinmetall GmbH, 4000 Düsseldorf Rückstoß- und knallfrei abschießbares Geschoß

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US53933A (en) * 1866-04-10 Improvement in rockets
US579035A (en) * 1897-03-16 Projectile
US2145508A (en) * 1937-01-04 1939-01-31 Sageb Sa Bladed projectile
US2412173A (en) * 1944-02-22 1946-12-03 Winslow B Pope Projectile
GB594513A (en) * 1940-09-04 1947-11-13 Charles Dennistoun Burney Improvements in or relating to projectiles operating with rocket propulsion
US2479718A (en) * 1947-01-29 1949-08-23 Carold F Bjork Rocket projectile
US2494026A (en) * 1945-03-28 1950-01-10 Anderson Nelson Projectile

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US53933A (en) * 1866-04-10 Improvement in rockets
US579035A (en) * 1897-03-16 Projectile
US2145508A (en) * 1937-01-04 1939-01-31 Sageb Sa Bladed projectile
GB594513A (en) * 1940-09-04 1947-11-13 Charles Dennistoun Burney Improvements in or relating to projectiles operating with rocket propulsion
US2412173A (en) * 1944-02-22 1946-12-03 Winslow B Pope Projectile
US2494026A (en) * 1945-03-28 1950-01-10 Anderson Nelson Projectile
US2479718A (en) * 1947-01-29 1949-08-23 Carold F Bjork Rocket projectile

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3020710A (en) * 1956-03-29 1962-02-13 Stephen H Herzog Sealing means for rocket nozzles
US2982090A (en) * 1956-08-06 1961-05-02 Phillips Petroleum Co Means to prevent perforation of starter disk during ignition delay
DE977712C (de) * 1957-03-03 1968-08-08 Franz Rudolf Dipl-Ing Thomanek Mit einer ausgekleideten Hohlladung ausgeruesteter Flugkoerper mit Raketentriebwerk
US3167912A (en) * 1960-01-04 1965-02-02 United Aircraft Corp Thrust control for solid rocket
US3305194A (en) * 1960-03-08 1967-02-21 Robert G Conard Wind-insensitive missile
US3437289A (en) * 1966-04-04 1969-04-08 Mb Assoc Miniature rocket nozzle
US3433437A (en) * 1967-01-18 1969-03-18 John E Reilly Rocket projectile
FR2474699A1 (fr) * 1980-01-30 1981-07-31 Ruggieri Ets Artifice de signalisation a dipoles electromagnetiques
US6964154B1 (en) * 2003-03-11 2005-11-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Axisymmetric, throttleable non-gimballed rocket engine

Also Published As

Publication number Publication date
BE493192A (de)
NL78976C (de)
GB681916A (en) 1952-10-29
DE831819C (de) 1952-02-18
NL79093C (de)
GB681978A (en) 1952-10-29
NL84170C (de)
CH283093A (fr) 1952-05-31
DE850277C (de) 1952-09-22
CH283466A (fr) 1952-06-15
CH283467A (fr) 1952-06-15
GB681977A (en) 1952-10-29
LU29848A1 (de)

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