US3835749A - Weapon launching rockets and method to use the same - Google Patents

Weapon launching rockets and method to use the same Download PDF

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Publication number
US3835749A
US3835749A US00319074A US31907463A US3835749A US 3835749 A US3835749 A US 3835749A US 00319074 A US00319074 A US 00319074A US 31907463 A US31907463 A US 31907463A US 3835749 A US3835749 A US 3835749A
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United States
Prior art keywords
rocket
tracer
launcher
cells
projectile
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Expired - Lifetime
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US00319074A
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English (en)
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P Joneaux
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Individual
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Individual
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/226—Semi-active homing systems, i.e. comprising a receiver and involving auxiliary illuminating means, e.g. using auxiliary guiding missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/14—Indirect aiming means
    • F41G3/142—Indirect aiming means based on observation of a first shoot; using a simulated shoot
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/222—Homing guidance systems for spin-stabilized missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
    • 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
    • F42B15/01—Arrangements thereon for guidance or control

Definitions

  • ABSTRACT A weapon including in combination, a rocket launcher and a gun attached to said launcher with its axis parallel to that of the launcher to move with said rocket launcher, an artillery tracer projectile for firing from said gun constructed to be crushed upon impact with a target to deposit tracer material thereon which continues to burn, and a rocket provided with guidance means for following said tracer projectile through the entirety of its path to impact the position of said deposited tracer material, wherein said guidance means comprises means rotating the rocket about its axis through its trajectory and at least two guidance devices each including a pair of aerodynamic flaps externally and symmetrically arranged on the rocket about an axial plane and independently movable, a lens positioned on said rocket with its optical axis parallel to the axis of the rocket to receive radiant energy from said tracer material as the rocket is launched to follow the path of said projectile, two radiant energy detector cells each symmetrically placed upon two equal sectors of one circle located
  • the invention relates to a weapon launching a selfpropelled projectile which is guided by a more precise projectile fired through an auxiliary gun.
  • the invention also relates to the combination of the weapon with the said projectiles and to methods for using the same.
  • Rockets and some other self-propelled projectiles are not usually guided.
  • artillery projectiles even if they concern small size bullets, they have the great advantage not to require heavy launching equipment, but they also have the great disadvantage to be much less accurate than self-propelled projectiles. This defect greatly limits the use of rockets.
  • the invention consists of firing, at the same time as a self-propelled projectile or at a determined interlapse, an artillery projectile, termed a pilot projectile, which preferably precedes the self-propelled projectile and issues a signal, luminous for instance, towards which a guidance system, borne by the self-propelled projectile, leads the latter.
  • a pilot projectile which preferably precedes the self-propelled projectile and issues a signal, luminous for instance, towards which a guidance system, borne by the self-propelled projectile, leads the latter.
  • the principal object of my invention is to give the rockets a firing accuracy approaching that of artillery projectiles or bullets, that is to say, exactly, a firing accuracy near that of the pilot projectile fired through an auxiliary gun.
  • FIG. 1 is a schematic view in elevation of the weapon, the rocket and the bullet in flight and the target.
  • FIG. 2 is a schematic view in elevation of the rocket.
  • FIG. 3 is a diagrammatical drawing of one form of a guidance system for the rocket.
  • FIG. 4 is a front view of a group of photoelectric cells being a part of the rocket guidance system.
  • FIG. 5 is a curve of the voltage issued from one of the photoelectric cells.
  • FIG. 6 shows a device for the rotation of a rocket guidance flap.
  • the weapon according to the invention consists of a rocket launcher 1 and a gun 2 fastened with the launcher l.
  • the rocket is generally referenced as 3.
  • the pilot projectile is a tracer bullet or a bullet with a rear pyrotechnic flare, fired through the gun 2, visible from the departure out of the gun.
  • the trajectories of the rocket and the tracer bullet are respectively referenced 6 and 7.
  • the target is referenced 5.
  • rocket and the pilot projectile are selected, according to the known teaching of ballistics, in order that both projectiles, simultaneously fired or with a determined time stagger, have neighbouring flights, the tracer bullet being before the rocket, at least in the useful range limits of the weapon.
  • the rocket is provided with a known system guiding it from the light of the tracer bullet, as conventional for guidance of missiles towards the light or the heat issued by plane motors. It may also be provided with the guidance system described below, as an example.
  • the rocket comprises from rear to fore parts: a tail fin 8, a powder propellant 9, a fore body 10 bearing a bursting charge, for example a shaped charge 11, and a known booster device not drawn on the figures (striker, primer, booster).
  • a rocket is selected with low rotation around its axis (a few rotations per second).
  • rotation is given from thestart of the rocket by known means, either by means of the launching tube, or by means of the rocket tuyeres.
  • the rotation is maintained by the tailfin.
  • the guidance system is located in the head 12, and arranged so as practically not disturb the acting of the bursting charge. In the particular case described, the neighbouring of the axis is not obstructed before the bursting hollow charge.
  • the rocket guidance system includes the following parts: aerodynamic flaps or movable vanes, a detector or sensor unit, a flaps control, an electric battery and amplifiers for electric currents issued from the sensor unit.
  • flaps 13 -13 There are four flaps 13 -13 they are symetrically arranged near the fore part of the head. Each of them is rotatable around an axis perpendicular with the external surface of the head.
  • the axes of each of two symetrical flaps are joined, by means of universal joints for instance, so as to jointly rotate, as if they have one axis 14 or 15 as in simplified form they are shown on the diagrammatical FIG. 3.
  • the sensor unit consists of a lens 16, the optical axis of which is parallel to the axis of the rocket.
  • the lens glass is preferably selected to let pass the light issued from the bullet tracer and to eliminate the most part of the radiation of the background on which the tracer is to be discriminated.
  • the sensor unit consists also of a group of four photoelectric cells 17, 17, 17", 17 symetrically arranged on one circular disc. The cells are covered with angular sectors 18, opacous to the tracer light, between which are shown active sectors 19. The whole cells are placed in the focus plane of the lens 16 with their center on the optical axis.
  • the optical image of the bullet is located on the cells disc. Since the rocket rotates around its axis, the optical image of the tracer moves on spiral curves, crossing the active sectors 19 of the four photoelectric cells. Thus, the cells give out a current the voltage U of which has a curve in function of time with rectangular shape (FIG. The lower value of voltage corresponds to the light of the background on which appears the tracer bullet. Since this light is preferably filtered in greater part by the glass of the lens, the minimal voltage is not very high. The rectangular supplement of voltage is due to the tracer light.
  • flaps control is diagrammatically shown on FIG. 3. Both flaps 13 and 13 jointly rotate around the same axis 14, rigid with a lever 20. The end of the lever can be magnetised and attracted by one or the other of two electromagnets 21" or 21".
  • the lever actuates with a more improved device, such as that of FIG. 6.
  • the lever 20 When not magnetised at its end, the lever 20 is held in a medium position as shown on FIG. 6, in equilibrium between two springs 24 and 26, settled at one of their ends to a frame rigid with the rocket. The other ends respectively bear the plates and 27 which lean against the thrust 29.
  • the end of the lever 20 is fixed in a medium position in consequence of the simultaneous thrust of the two plates 25 and 27.
  • the two electromagnets 21 and 21" attract the magnetic part of the lever 20.
  • the two other flaps 13 and 13 are respectively provided with the same control means as 13 and 13
  • the electromagnets 21 and 21" respectively receive the currents issued from the photoelectric cells 17 and 17" when respectively amplified by amplifiers 22" and 22". Necessary power is provided by the battery or other convenient electric source 23.
  • All the used electric devices may be ordinary staple articles.
  • Actuation is accomplished in the following manner:
  • the tracer image excites the active sectors of the cells which issue by turns a rectangular current.
  • the current from the cell 17 is amplified by the amplifier 22" and sent on the electromagnet 21 which attracts the lever 20 and rotates the flaps 13 and 13 in a fixed angle, in a determined direction.
  • the direction is selected in such a way that the flaps l3 and 13 incline the head of the rocket towards the tracer direction in come quence of the relative air flow.
  • the two other flaps l3 and 13 are similarly controled by the photoelectric cells 17 and 17".
  • the whole flaps when the tracer image goes through the corresponding photoelectric cells, give the rocket a plurality of short impulses bringing the rocket axis towards the tracer bullet.
  • the rocket is induced to follow the bullet, being drawn nearer the trajectory of the latter, and the rocket hit the target close to the bullet impact.
  • the guidance system may actuate from the time of the rocket launching, during the combustion of the propelling charge, that is when the rocket has the most irregular movements.
  • the tracer keeps its activity upon the impact till the rocket reaches the target.
  • the tracer has no longer an activity which causes the rocket to deviate its flight.
  • Two means, for instance, may permit those results: making the bullet with relatively soft material (lead for instance) which crushes on the target, or making the bullet with a weak material, partially at least (glass for instance), so allowing the bullet to be broken on the target. In any case, the remaining of the tracer keeps stuck on the target, when finishing to burn.
  • the methods for using the weapon so described may be various.
  • the trajectories are nearest as possible; the pilot projectile velocity and that of the missile are equal or almost equal; the projectiles shapes and weights are selected so as the rocket velocity decreases it is equal less they that of the pilot projectile, in the range wanted.
  • the lines of fire of both projectiles are parallel; the tracer bullet muzzle velocity and the velocity acquired by the rocket at the end of the propelling charge combustion are practically the same. At the moment when the rocket begins its free flight, the distance between the tracer bullet and the rocket is due to less rapid acquirement of velocity by the latter.
  • a weapon including in combination, a rocket launcher and a gun attached to said launcher with its axis parallel to that of the launcher to move with said rocket launcher, an artillery tracer projectile for firing from said gun constructed to be crushed upon impact with a target to deposit tracer material thereon which continues to burn, and a rocket provided with guidance means for following said tracer projectile through the entirety of its path to impact the position of said deposited tracer material, wherein said guidance means comprises means rotating the rocket about its axis through its trajectory and at least two guidance devices each including a pair of aerodynamic flaps externally and symmetrically arranged on the rocket about an axial plane and independently movable, a lens positioned on said rocket with its optical axis parallel to the axis of the rocket to receive radiant energy from said tracer material as the rocket is launched to follow the path of said projectile, two radiant energy detector cells each symmetrically placed upon two equal sectors of one circle located in the focal plane of said lens with planes identical to that of the corresponding said aerodynamic flaps, insulating

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US00319074A 1962-10-26 1963-10-25 Weapon launching rockets and method to use the same Expired - Lifetime US3835749A (en)

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FR913553A FR1605221A (enrdf_load_stackoverflow) 1962-10-26 1962-10-26

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Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2436360A1 (fr) * 1978-09-13 1980-04-11 Rheinmetall Gmbh Procede pour combattre des cibles, de preference blindees, utilisant un reperage par rayonnement
FR2478294A1 (fr) * 1980-03-14 1981-09-18 Philips Nv Procede pour battre un objectif au moyen de projectiles passifs et systeme de tir pour l'execution de ce procede
US4318329A (en) * 1978-07-29 1982-03-09 Diehl Gmbh & Co. Anti-tank weapon
EP0048068A1 (en) * 1980-09-15 1982-03-24 Philips Norden AB A method for combatting of targets and projectile or missile for carrying out the method
EP0256308A1 (de) * 1986-07-25 1988-02-24 Dynamit Nobel Aktiengesellschaft Verfahren zur Bekämpfung eines gepanzerten Zieles
US4796834A (en) * 1980-09-15 1989-01-10 U.S. Philips Corporation Method for combatting of targets and projectile or missile for carrying out the method
FR2619899A1 (fr) * 1987-08-26 1989-03-03 Stribling Gerald Amelioration des systemes antitanks pour les tanks equipes de blindage actif
EP0388264A1 (fr) * 1989-03-14 1990-09-19 Thomson-Csf Marqueur d'objectif pour attirer des projectiles munis d'un autodirecteur
US4967065A (en) * 1989-08-11 1990-10-30 Ford Aerospace Corporation Integrated reticle and detector
FR2657686A1 (fr) * 1990-01-26 1991-08-02 Thomson Brandt Armements Arme anti-char de courte portee et son procede d'utilisation.
EP0670465A1 (en) * 1994-03-02 1995-09-06 State Of Israel Ministry Of Defence Rafael Armament Development Authority Missile homing system using secondary targets

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2403387A (en) * 1942-12-19 1946-07-02 Miles A Mclennan Radiant energy responsive directional control
US2752850A (en) * 1952-01-30 1956-07-03 Arthur H Warner Self-propelled missile
US2942118A (en) * 1958-02-12 1960-06-21 Westinghouse Electric Corp Radiant energy angular tracking apparatus
US3010677A (en) * 1957-11-12 1961-11-28 Gen Dynamics Corp Missile control system
US3021096A (en) * 1956-12-07 1962-02-13 North American Aviation Inc Infrared guidance system
US3053984A (en) * 1951-01-05 1962-09-11 Hughes Aircraft Co Star tracking system
US3097564A (en) * 1963-07-16 Spotting rifle ignition for larger caliber gun
US3116039A (en) * 1956-02-29 1963-12-31 Goldberg Michael Method of and system for guiding a missile

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3097564A (en) * 1963-07-16 Spotting rifle ignition for larger caliber gun
US2403387A (en) * 1942-12-19 1946-07-02 Miles A Mclennan Radiant energy responsive directional control
US3053984A (en) * 1951-01-05 1962-09-11 Hughes Aircraft Co Star tracking system
US2752850A (en) * 1952-01-30 1956-07-03 Arthur H Warner Self-propelled missile
US3116039A (en) * 1956-02-29 1963-12-31 Goldberg Michael Method of and system for guiding a missile
US3021096A (en) * 1956-12-07 1962-02-13 North American Aviation Inc Infrared guidance system
US3010677A (en) * 1957-11-12 1961-11-28 Gen Dynamics Corp Missile control system
US2942118A (en) * 1958-02-12 1960-06-21 Westinghouse Electric Corp Radiant energy angular tracking apparatus

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4318329A (en) * 1978-07-29 1982-03-09 Diehl Gmbh & Co. Anti-tank weapon
FR2436360A1 (fr) * 1978-09-13 1980-04-11 Rheinmetall Gmbh Procede pour combattre des cibles, de preference blindees, utilisant un reperage par rayonnement
FR2478294A1 (fr) * 1980-03-14 1981-09-18 Philips Nv Procede pour battre un objectif au moyen de projectiles passifs et systeme de tir pour l'execution de ce procede
US4796834A (en) * 1980-09-15 1989-01-10 U.S. Philips Corporation Method for combatting of targets and projectile or missile for carrying out the method
US4457475A (en) * 1980-09-15 1984-07-03 U.S. Philips Corporation Method for destroying targets and a projectile for carrying out the method
EP0048068A1 (en) * 1980-09-15 1982-03-24 Philips Norden AB A method for combatting of targets and projectile or missile for carrying out the method
EP0256308A1 (de) * 1986-07-25 1988-02-24 Dynamit Nobel Aktiengesellschaft Verfahren zur Bekämpfung eines gepanzerten Zieles
FR2619899A1 (fr) * 1987-08-26 1989-03-03 Stribling Gerald Amelioration des systemes antitanks pour les tanks equipes de blindage actif
EP0388264A1 (fr) * 1989-03-14 1990-09-19 Thomson-Csf Marqueur d'objectif pour attirer des projectiles munis d'un autodirecteur
FR2644575A1 (fr) * 1989-03-14 1990-09-21 Thomson Csf Marqueur d'objectif pour attirer des projectiles munis d'un autodirecteur
US5070790A (en) * 1989-03-14 1991-12-10 Thomson-Csf Target marker to attract projectiles provided with a homing head
US4967065A (en) * 1989-08-11 1990-10-30 Ford Aerospace Corporation Integrated reticle and detector
FR2657686A1 (fr) * 1990-01-26 1991-08-02 Thomson Brandt Armements Arme anti-char de courte portee et son procede d'utilisation.
EP0670465A1 (en) * 1994-03-02 1995-09-06 State Of Israel Ministry Of Defence Rafael Armament Development Authority Missile homing system using secondary targets

Also Published As

Publication number Publication date
FR1605221A (enrdf_load_stackoverflow) 1973-08-31

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