US3089390A - Launching apparatus for guided missiles - Google Patents

Launching apparatus for guided missiles Download PDF

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Publication number
US3089390A
US3089390A US93980A US9398061A US3089390A US 3089390 A US3089390 A US 3089390A US 93980 A US93980 A US 93980A US 9398061 A US9398061 A US 9398061A US 3089390 A US3089390 A US 3089390A
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US
United States
Prior art keywords
receiver
missiles
launching
launching apparatus
missile
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
US93980A
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English (en)
Inventor
Wilson Mervyn Francis
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.)
Short Brothers PLC
Original Assignee
Short Brothers and Harland Ltd
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 Short Brothers and Harland Ltd filed Critical Short Brothers and Harland Ltd
Application granted granted Critical
Publication of US3089390A publication Critical patent/US3089390A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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

Definitions

  • the invention is concerned with launching apparatus for guided missiles of the type which depend for their propulsion upon the thrust of the efilux gases from a rocket motor incorporated in the after end thereof; such apparatus incorporates a stand or platform on which a missile may be mounted in the attitude appropriate to discharge, and which will be provided with such services and power connections as are necessary for aiming and firing. It is found in practice that where missiles are operated under visual command guidance of an operator situated in an adjacent direction installation and provided with optical and other means for controlling the course of a missile, the operator may be distracted and even temporarily blinded by the flash and smoke produced by the rocket motor at the instant of launching and immediately thereafter. This disadvantage may be more especially evident in operations during hours of darkness, when the eyes have greater difliculty in accommodating a sudden hash of light.
  • a receiver for the efilux gas flame and smoke including means for cooling and extinguishing the gases, together with means for expelling said gases into the at niosphere in a safe direction.
  • a receiver for the efilux gas flame and smoke including means for cooling and extinguishing the gases, together with means for expelling said gases into the at niosphere in a safe direction.
  • such apparatus will include means for filtering out any solid particles from the gases before their expulsion.
  • the apparatus is intended to serve a plurality of missiles mounted in ganged formation upon a common stand or support
  • the mountings for the individual missiles are connected to said receiver by manifold ducts.
  • two or more receivers may be provided, each receiver being used for a group of mountings.
  • the constructional arrangement of the launching apparatus will preferably be such that reaction torques due to the thrust of the propulsive rocket-motors will be eliminated or balanced until the missile is released from its supports, to avoid disturbance of the aiming control. This can be achieved by ensuring that the thrust vector of the gas which is being exhausted to atmosphere lies in the plane containing the launcher pivot axis.
  • FIG. 1 is a front elevation partly in section of the launching apparatus
  • FIG. 2 is a plan thereof
  • FIG. 3 is a section on the line III-4H of FIG. 1.
  • the launching apparatus shown in the drawings is intended to support fourteen missiles, arranged in two oppositely disposed sets of seven which are respectively carried on opposite inclined platforms 10, .11 in back-toback relationship.
  • the missiles are indicated by the numerals 12, and in the plan view of FIG. 2 only the missiles of one set are shown, the other set being omitted to show the spigot members 13 upon which the missiles are mounted and through which electrical services to the missiles are connected.
  • Said two platforms 1t 11 form part of a central structure 14 which is carried by a turn-table 1411 upon a base 142.
  • Said structure 14 carries an internal spur ring gear l5 meshing with a pinion 16 on the shaft 17 connected by gearing enclosed in the casing 18 and driven by an electric motor 1? which is governed for aiming purposes by a r mote director installation; trailing cables 2% lead from the respective missile sp-igots i3, and through the hollow axle of the turn-table, and are passed to the director installation.
  • an enclosed receiver chamber 21 which is connected to the rear of each missile mounting on each platform by a duct 22, the mouth 22d of which will receive the gas flame from the rocket motor when the particular missile is fired, and which will conduct the gases into said chamber 21.
  • a sump 23 will receive solid particles filtered out of the gases by passage through a suitable screen 24 situated on the inner side of a heat exchanger 25 by which the gases are cooled and any flame is extinguished before expulsion into the atmosphere through the outlet 26.
  • the chamber outlet 26 is provided exteriorly with a louvered deflector 27 for taking the gases to atmosphere in a direction such as to avoid damage to the apparatus or inconvenience to the operator.
  • the constructional arrangement of the apparatus is such that the thrust vector of the gas eiiiuent discharged from outlet lies in the plane containing the launcher pivot axis until the missile is released from its supports on discharge. By these means it is ensured that the rocketmotor thrust reaction torque is eliminated or balanced.
  • a missile launching apparatus a stationary base, a receiver for missile efflux gas flame and smoke, means for mounting said receiver upon said base for rotation about a vertical axis, launching means mounted on said receiver offset from said axis, duct means connecting said launching means to said receiver, means in said receiver for cooling and extinguishing the gases, and a receiver outlet which has its axis in a plane containing the said vertical axis so that the said thrust vector of gas as it is exhausted through said outlet lies substantially in said plane.
  • Apparatus as in claim 1 including means in said receiver ror separating solid particles from the gases.
  • Missile launching apparatus comprising a stationary base, a structure carrying two oppositely inclined platforms mounted in back-to-back relationship, means for mounting said structure upon said base for rotation about a vertical axis, means on each platform for supporting a gang of missiles in side-by-side disposition, means for controlling the angle of rotation of said structure for purposes of aiming said missiles, a receiving chamber within said structure and ducts therein for connecting said chamber to the mountings of the respective missiles for conduction of the efllux gases therefrom to said chamber, an outlet in said chamber, and a heat exchanger in said outlet for cooling and extinguishing gases expelled from the chamber to said outlet, said outlet having its axis in a plane containing the said vertical axis so that the thrust vector of gas exhausted through said outlet lies substantially in said plane.
  • said receiving chamber includes a solids screen and a sump respectively for filtering gases entering said heat exchanger and for collecting the solid particles separated by said screen.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Separation By Low-Temperature Treatments (AREA)
US93980A 1960-03-11 1961-03-07 Launching apparatus for guided missiles Expired - Lifetime US3089390A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB8705/60A GB900140A (en) 1960-03-11 1960-03-11 Improvements in launching apparatus for guided missiles

Publications (1)

Publication Number Publication Date
US3089390A true US3089390A (en) 1963-05-14

Family

ID=9857656

Family Applications (1)

Application Number Title Priority Date Filing Date
US93980A Expired - Lifetime US3089390A (en) 1960-03-11 1961-03-07 Launching apparatus for guided missiles

Country Status (5)

Country Link
US (1) US3089390A (enrdf_load_stackoverflow)
CH (1) CH385073A (enrdf_load_stackoverflow)
DE (1) DE1142532B (enrdf_load_stackoverflow)
GB (1) GB900140A (enrdf_load_stackoverflow)
NL (2) NL112367C (enrdf_load_stackoverflow)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3228296A (en) * 1963-05-23 1966-01-11 Milton C Neuman Arrangement for venting blast gases and for water injection
US3754497A (en) * 1970-08-06 1973-08-28 Sarmac Sa Transporting and firing chest for self-propelled projectiles
FR2458678A1 (fr) * 1979-05-22 1981-01-02 Gen Dynamics Corp Collecteur de gaz d'echappement a deux voies, notamment pour lanceurs de fusees

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1539027A (en) * 1919-04-03 1925-05-26 American Ordnance Corp Projectile for use with depth-charge projectors
US2685936A (en) * 1950-08-08 1954-08-10 Lockheed Aircraft Corp Sound reduction equipment for use with jet-propulsion units
US2925012A (en) * 1953-06-02 1960-02-16 Justin W Malloy Antisubmarine warfare projector mount
US2925013A (en) * 1956-05-01 1960-02-16 North American Aviation Inc Rocket engine assembly testing and launching apparatus
US3001452A (en) * 1959-01-28 1961-09-26 John A Urban Rotary exhaust deflector

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH316189A (de) * 1953-05-07 1956-09-30 Schoenenberger Paul Rakete mit Abschusseinrichtung für dieselbe
US2958261A (en) * 1953-05-12 1960-11-01 Henig Seymour Predetermined target dispersal rocket launcher
US2802399A (en) * 1953-11-30 1957-08-13 Steven M Little Rocket launcher
DE1054879B (de) 1956-12-01 1959-04-09 Ernst Heinkel Fahrzeugbau G M Raketengeschuetz

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1539027A (en) * 1919-04-03 1925-05-26 American Ordnance Corp Projectile for use with depth-charge projectors
US2685936A (en) * 1950-08-08 1954-08-10 Lockheed Aircraft Corp Sound reduction equipment for use with jet-propulsion units
US2925012A (en) * 1953-06-02 1960-02-16 Justin W Malloy Antisubmarine warfare projector mount
US2925013A (en) * 1956-05-01 1960-02-16 North American Aviation Inc Rocket engine assembly testing and launching apparatus
US3001452A (en) * 1959-01-28 1961-09-26 John A Urban Rotary exhaust deflector

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3228296A (en) * 1963-05-23 1966-01-11 Milton C Neuman Arrangement for venting blast gases and for water injection
US3754497A (en) * 1970-08-06 1973-08-28 Sarmac Sa Transporting and firing chest for self-propelled projectiles
FR2458678A1 (fr) * 1979-05-22 1981-01-02 Gen Dynamics Corp Collecteur de gaz d'echappement a deux voies, notamment pour lanceurs de fusees

Also Published As

Publication number Publication date
CH385073A (de) 1965-02-26
NL262078A (enrdf_load_stackoverflow)
DE1142532B (de) 1963-01-17
NL112367C (enrdf_load_stackoverflow)
GB900140A (en) 1962-07-04

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