US3853058A - Improvements in or relating to rockets - Google Patents

Improvements in or relating to rockets Download PDF

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Publication number
US3853058A
US3853058A US00311717A US31171772A US3853058A US 3853058 A US3853058 A US 3853058A US 00311717 A US00311717 A US 00311717A US 31171772 A US31171772 A US 31171772A US 3853058 A US3853058 A US 3853058A
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US
United States
Prior art keywords
chamber
sheath
missile
explosive charge
charge
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
US00311717A
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English (en)
Inventor
J Tartault
A Minot
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.)
Luchaire SA
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Luchaire SA
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Filing date
Publication date
Application filed by Luchaire SA filed Critical Luchaire SA
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Publication of US3853058A publication Critical patent/US3853058A/en
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Classifications

    • 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
    • F42B12/201—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 characterised by target class
    • F42B12/204—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 characterised by target class for attacking structures, e.g. specific buildings or fortifications, ships or vehicles
    • 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
    • F02K9/36—Propellant charge supports

Definitions

  • ABSTRACT This self-propelling projectile or missile, or rocket, comprises a fixed explosive charge and a movable explosive charge adapted, at the end of the combustion of the propulsive charge, to be transferred by the action of the combustion gases of the propellant toward the propelling body of the missile.
  • the present invention relates to improvements in or relating to self-propelled missiles or like projectiles, notably rockets, and its primary object is to increase the efficiency of such missiles.
  • rockets comprise essentially an explosive charge and a propelling charge, the latter occupying a portion, frequently of considerable dimensions, of the missile body, which constitutes the propulsive body.
  • This propulsive body is useful during only a very short period of the missile flight; thus, when the propellant combustion is completed, this section of the rocket constitutes a dead weight without any military efficiency, for during the explosion of the missile, as the propulsive body is not exposed to the action of the explosive charge, it will not exert any effective function since it cannot be transformed into fragments or splinters.
  • missiles usually referred to as conventional, a far from negligible and completely useless mass is conveyed to the target contemplated, at the expense of an increment in the flight duration and a reduction in the permissible range.
  • the self-propelled missile comprises, in addition to the conventional fixed explosive charge, a movable explosive charge which, at the end of the combustion of the propellant charge, will be transferred into the propulsive body.
  • FIGS. 1 and 2 are longitudinal sections of the improved rocket according to this invention, FIG. 1 showing the missile ready for the launching operation, and FIG. 2 the same missile at the end of the propellant combustion phase;
  • FIG. 3 is a section taken along the line III-III of FIG. 1.
  • the rocket comprises:
  • a charge body comprising the double military charge according to this invention, and to be described in detail presently;
  • the combustion gases are ejected through the divergent 14 comprising blades 15.
  • the stability along the desired trajectory is ensured by means of a fin-type spread-out set of vanes 16.
  • the brush type propelling charge is ignited by means of an electric igniter 17.
  • the military charge consists of two portions, namely a fixed portion 18 and a movable portion 19.
  • the former consists in the selected example of two frustoconical blocks assembled by their major bases. This shape permits of raising the cone of dispersion of the splinters, and therefore of increasing its efficient range.
  • the splinter effect is obtained, in this example, by using balls 20 distributed along the outer periphery of the charge in light-alloy sheaths 21 and embedded in epoxy resin.
  • the charge is primed by a pair of detonators 22.
  • This assembly is housed in the charge body 23 streamlinedby a plastic fairing or shell 24 fitted to the front and rear cross members 25 and 26, respectively.
  • the movable portion 19 comprises an explosive sausage or bar enclosed in a light-alloy sheath 27 adapted to move backwards and fitted in the fixed portion of the charge specially shaped to this endf
  • the sheath 27 is provided with guide grooves 28 and locking grooves 29.
  • the locking action is obtained by means of three collapsible studs 30 each urged by a spring 31.
  • This explosive block is adapted to be primed through a pair of ports 32 formed in the front portion of bar 19 and opening into the fixed portion 18 of the charge.
  • annular cavity 33 is formed which, as will be explained presently, acts as an accumulator chamber in which recesses are provided for said three locking studs 30.
  • the brush type charge 13 of the propulsive section is anchored to a suspension block consisting, according to this invention, of a base plate 34 adapted to move in the propulsive body 12 and rigidly connected to the sheath 27 in which the movable charge 19 is contained, for example, in this example, by means of a projection fitted in said sheath.
  • a passage 36 is formed through the base plate 34 for receiving a gas supply; this passage 36 opens into the accumulator chamber 33.
  • a non-return valve 36a is provided at the outlet end of passage 36 in chamber 33 which comprises, on the other hand, a pressure-release port 37.
  • the fixed charge 18 receives therethrough a tube 38 having a front extension extending through the front cross member 25 in which it is bent to direct the combustion gas from the propellant towards the front end face of the sheath 27 enclosing the movable charge 19.
  • Another non-return valve 39 prevents any untimely return of gases towards said chamber 33.
  • This rocket operates as follows:
  • the pressure actuates a piston in fuse ll, shearing a lock pin therein and permitting arming of the fuse in a conventional manner. Since the fuse is conventional, its internal structure has not been shown in the drawing.
  • This kinetic phase (see FIG. 2) is started when the forceexerted on the sheath 27 exceeds that exerted on base plate 34 of propulsive body 12, so as to cause the sheath 27 and the charge 19 contained therein towards the rear of the missile.
  • the sheath uncovers the orifice 37, thus causing the accumulator chamber to communicate (see FIG. 2) with the propulsive chamber in which the combustion is now completed, that is, with the atmospheric pressure.
  • the non-return valve 39 isolates the accumulator chamber 33 from the expansion chamber 41 consisting of the space now freed, in the fixed charge, by the sheath having moved to the rear, so that a constant force can be maintained on this sheath 27 and thus ensure the proper positioning and locking thereof.
  • the explosive bar 19 is primed by the main charge, due to the presence of said ports 32.
  • a self-propelled missile having a front end and a rear end, first and second chambers, the first chamber being positioned rearwardly of the second chamber, a combustible propellant charge contained in said first chamber, an explosive charge contained in said second chamber, said explosive charge comprising a fixed portion and a movable portion, and means for moving said movable portion of said explosive charge into said first chamber upon completion of combustion of said propellant charge, the means for moving the movable portion of the explosive charge comprising means for transmitting the pressure of the propulsive gases generated by combustion of said propellant charge to said movable portion and further comprising means for delaying movement of the movable portion of the explosive charge until shortly before completion of the combustion of the propellant charge, the delaying means comprising an accumulator chamber, means connecting said accumulator chamber with the first chamber and means connecting said accumulator chamber with that portion of the second chamber containing the movable portion of the explosive charge.
  • the sheath housing the second portion of the explosive charge comprises guide grooves and locking grooves, and wherein the missile comprises locking studs engaging said guide and locking grooves and means for transmitting the pressure of the propulsive gases to said studs for disengaging said studs from said grooves.
  • the missile claimed in claim 5' wherein the sheath has a forward face and wherein the missile comprises an accumulator chamber, first duct means in the movable block connecting said accumulator chamber to the propellant charge and second duct means in the fixed portion of the explosive charge and connecting said accumulator chamber with the forward face of said sheath.
  • the missile claimed in claim 1 wherein the first chamber is positioned rearwardly of the second chamber, and wherein the missile comprises a sheath enclosing the movable portion of said explosive charge, said sheath having a forward face, a movable block at the rear end of said sheath, said block forming the forward wall of the first chamber enclosing the propellant charge, locking studs normally engaging said sheath, an accumulator chamber, valved duct means for transmitting propulsive gases from said first chamber to said accumulator chamber but blocking transmission of gases from said accumulator chamber to said second chamber, means for transmitting the pressure of propulsive gases from said accumulator chamber to said locking studs to disengage said studs from said sheath and means for transmitting the pressure of propulsive gases from said accumulator chamber to the forward face of said sheath to cause rearward movement of said sheath and said block into said first chamber when the pressure in said accumulator chamber exceeds the pressure in said first chamber, and means for vent

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Portable Nailing Machines And Staplers (AREA)
US00311717A 1972-01-05 1972-12-07 Improvements in or relating to rockets Expired - Lifetime US3853058A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7200202A FR2166713A5 (enrdf_load_stackoverflow) 1972-01-05 1972-01-05

Publications (1)

Publication Number Publication Date
US3853058A true US3853058A (en) 1974-12-10

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Application Number Title Priority Date Filing Date
US00311717A Expired - Lifetime US3853058A (en) 1972-01-05 1972-12-07 Improvements in or relating to rockets

Country Status (3)

Country Link
US (1) US3853058A (enrdf_load_stackoverflow)
DE (1) DE2262416A1 (enrdf_load_stackoverflow)
FR (1) FR2166713A5 (enrdf_load_stackoverflow)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4353305A (en) * 1978-11-23 1982-10-12 Etat Francais Represente Par Le Delegue General Pour L'armement Kinetic-energy projectile
US4643098A (en) * 1983-10-20 1987-02-17 A/S Raufoss Ammunisjonsfabrikker Rocket with tracer charge and gunpowder rods
RU2134860C1 (ru) * 1998-04-07 1999-08-20 Открытое акционерное общество Научно-производственное объединение "Искра" Ракета
US20060243153A1 (en) * 2005-05-02 2006-11-02 Skinner Anthony T Impact initiated venting system and method of using same
RU2292009C1 (ru) * 2005-08-17 2007-01-20 Открытое акционерное общество "Вятскополянский машиностроительный завод "Молот" Управляемая ракета
RU2293283C1 (ru) * 2005-08-08 2007-02-10 Открытое акционерное общество Научно-производственное объединение "Искра" Ракета
RU2319106C1 (ru) * 2006-06-13 2008-03-10 Федеральное Государственное унитарное предприятие "Государственное научно-производственное предприятие "Сплав" Ракета
RU2595070C2 (ru) * 2014-12-01 2016-08-20 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг РФ) Неуправляемый реактивный снаряд
CN106121862A (zh) * 2016-08-11 2016-11-16 西北工业大学 一种固体火箭发动机药柱固定装置

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3205431A1 (de) * 1982-02-16 1983-08-25 Licentia Patent-Verwaltungs-Gmbh, 6000 Frankfurt Raketengeschoss
US5535679A (en) * 1994-12-20 1996-07-16 Loral Vought Systems Corporation Low velocity radial deployment with predetermined pattern
US5691502A (en) * 1995-06-05 1997-11-25 Lockheed Martin Vought Systems Corp. Low velocity radial deployment with predeterminded pattern

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2145507A (en) * 1936-12-31 1939-01-31 Sageb Sa De Gestion Et De Expl Percussion fuse for rocketprojectiles
US2440271A (en) * 1944-06-26 1948-04-27 Us Sec War Rocket projectile
US2773448A (en) * 1954-01-21 1956-12-11 Brandt Soc Nouv Ets Rocket projectile
US3234878A (en) * 1962-10-05 1966-02-15 Soc Tech De Rech Ind Powder-fuelled rocket
US3256817A (en) * 1951-10-17 1966-06-21 Rabinow Jacob Piezoelectric fuse
US3490373A (en) * 1968-05-09 1970-01-20 Thiokol Chemical Corp Self-destructing rocket propelled grenade
US3585419A (en) * 1968-12-19 1971-06-15 France Etat Impact-operated electricity generator for projectiles
US3677179A (en) * 1966-09-29 1972-07-18 Lester A Potteiger Telescoping ordnance device

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2145507A (en) * 1936-12-31 1939-01-31 Sageb Sa De Gestion Et De Expl Percussion fuse for rocketprojectiles
US2440271A (en) * 1944-06-26 1948-04-27 Us Sec War Rocket projectile
US3256817A (en) * 1951-10-17 1966-06-21 Rabinow Jacob Piezoelectric fuse
US2773448A (en) * 1954-01-21 1956-12-11 Brandt Soc Nouv Ets Rocket projectile
US3234878A (en) * 1962-10-05 1966-02-15 Soc Tech De Rech Ind Powder-fuelled rocket
US3677179A (en) * 1966-09-29 1972-07-18 Lester A Potteiger Telescoping ordnance device
US3490373A (en) * 1968-05-09 1970-01-20 Thiokol Chemical Corp Self-destructing rocket propelled grenade
US3585419A (en) * 1968-12-19 1971-06-15 France Etat Impact-operated electricity generator for projectiles

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4353305A (en) * 1978-11-23 1982-10-12 Etat Francais Represente Par Le Delegue General Pour L'armement Kinetic-energy projectile
US4643098A (en) * 1983-10-20 1987-02-17 A/S Raufoss Ammunisjonsfabrikker Rocket with tracer charge and gunpowder rods
RU2134860C1 (ru) * 1998-04-07 1999-08-20 Открытое акционерное общество Научно-производственное объединение "Искра" Ракета
US20060243153A1 (en) * 2005-05-02 2006-11-02 Skinner Anthony T Impact initiated venting system and method of using same
US8307767B2 (en) * 2005-05-02 2012-11-13 Lockheed Martin Corporation Impact initiated venting system and method of using same
RU2293283C1 (ru) * 2005-08-08 2007-02-10 Открытое акционерное общество Научно-производственное объединение "Искра" Ракета
RU2292009C1 (ru) * 2005-08-17 2007-01-20 Открытое акционерное общество "Вятскополянский машиностроительный завод "Молот" Управляемая ракета
RU2319106C1 (ru) * 2006-06-13 2008-03-10 Федеральное Государственное унитарное предприятие "Государственное научно-производственное предприятие "Сплав" Ракета
RU2595070C2 (ru) * 2014-12-01 2016-08-20 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг РФ) Неуправляемый реактивный снаряд
CN106121862A (zh) * 2016-08-11 2016-11-16 西北工业大学 一种固体火箭发动机药柱固定装置

Also Published As

Publication number Publication date
DE2262416A1 (de) 1973-07-12
FR2166713A5 (enrdf_load_stackoverflow) 1973-08-17

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