US2972933A - Missile hand launching system - Google Patents

Missile hand launching system Download PDF

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Publication number
US2972933A
US2972933A US704560A US70456057A US2972933A US 2972933 A US2972933 A US 2972933A US 704560 A US704560 A US 704560A US 70456057 A US70456057 A US 70456057A US 2972933 A US2972933 A US 2972933A
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Prior art keywords
missile
gripstock
launch tube
grip
tube
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Expired - Lifetime
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US704560A
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John M Guthrie
Jr George D Harkey
Donald I Smith
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General Dynamics Corp
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General Dynamics Corp
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    • 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
    • F41F3/045—Rocket or torpedo launchers for rockets adapted to be carried and used by a person, e.g. bazookas
    • F41F3/0455—Bazookas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A19/00—Firing or trigger mechanisms; Cocking mechanisms
    • F41A19/58—Electric firing mechanisms

Definitions

  • the present invention relates to a missile hand launching system and more particularly to a system for launching target homing missiles.
  • This invention is designed to be carried and operated by individual field personnel. Little comparison can be made with existing systems because they are used to fire ballistic projectiles whose eifectiveness is entirely dependent on the accuracy of the operator.
  • a unique feature of this invention is the positive manner in which the launching system mechanically and electrically engages the missile to be fired. Another feature is that it permits a missile packaging technique which allows final missile checkout at the originating facility. It also permits relatively rapid cyclic launching of missiles with a high degree of operational reliability.
  • the invention is compact with its own replaceable power supply, requiring no other equipment than that enclosed within the launcher.
  • the launching system and configuration disclosed herein could be adapted to applications other than shown in the preferred embodiment.
  • the launching system has two prime mechanical components.
  • the two components are the launch tube and the gripstock.
  • the launch tube also serves as the shipping container for the missile to be launched.
  • An object of the present invention is to provide individual field personnel with a means for launching missiles.
  • Another object is to provide individual field personnel with a missile container which can be used as the missile launch tube.
  • Figure 1 is a side elevation view of the launch tube with gripstock attached.
  • Figure 2 is an exploded view of Figure 1 showing the launch tube and gripstock separated and the launch tube and end caps separated.
  • Figure 3 is a cross section of a portion of Figure 1.
  • Figure 4 is a schematic of the launching systems electrical circuitry for a representative missile.
  • the launch tube shown in Figure l is an expendable item.
  • the launch tube is a phenolic impregnated, laminated paper tube.
  • the missile is not removed from the tube at any time after final packaging.
  • the tube can be sealed as an airtight package or filled with an inert gas for better corrosion protection.
  • the tube has two end caps 11 and 12 which are held in place by a close fit pin and slot arrangement 13. This arrangement lends itself to safety wiring during storage periods.
  • the end caps may contain cushions or pads to protect the missile.
  • the tube alignment lugs 14 and 15 are shown in Figure 2. These lugs fit into slots 14a and 15a in the gripstock 21.
  • the gripstock 21 is shown as a curved trough having a rear grip 22 with trigger 38, and a pinned, springloaded forward grip 23.
  • the forward grip 23 is swung forward about the pin 24. The tube is placed on the gripstock and then moved to the rear. The forward grip is then swung back into place, locking the tube to the gripstock.
  • the rear lug 15 is used only for alignment and fits into an alignment socket 50 when the tube is in locked position.
  • the forward lug 14, however, contains one half of a quick-disconnect electrical plug 16 which mates with a plug 17 in the missile.
  • the plug 16 is held by a pin 20.
  • the forward lug also has an electrical contact plate 19 for making contact with the gripstock.
  • the contact plate has a plurality of contact points or terminals 51 which are connected to the quick-disconnect plug by the electrical wiring 37.
  • the terminals in plate 19 are forced against spring loaded contact points 31 of the gripstock. In the locked position a portion of the forward lug protrudes into the tubular retainer 30, making the mechanical lock complete.
  • the contact points 31 are set in a plug 45.
  • a spring 46 is compressed between the plug and the screw 47.
  • the screw 48 is positoned through a slot 49 in the plug. The slot allows fore and aft movement of the plug as a launch tube is locked into position or removed from the gripstock.
  • the screws 47 and 48 also hold the tubular retainer 30 to the gripstock.
  • the wires 52 electrically connect the contact points 31 to the electrical connector 53.
  • the connector 53 engages pins 54 which have lead wires attached to them.
  • One of the lead wires is soldered to the pin 55 for making electrical contact with the battery.
  • the remaining wires run to the rear grip area to perform the functions shown in Figure 4.
  • the tubular retainer with its plug, spring, and electrical connecter assembly is an easily removed and replaceable item. Although this is not necessary it is a desirable feature since. the contact points 3 1 can become worn.
  • a battery 27 for supplying electrical power is located in the rear grip. It is inserted from the aft end and held in place by a spring loaded cap 28 which acts as an electrical ground for the battery.
  • An arming switch 32 shown in Figures 1 and 2 is used to connect the battery to the pin 55 and thus to the contact points 31. This is accomplished, as shown in Figure 3, by a contact spring 33 and a contact rod 34 which rotates with the arming switch. When the arming switch is on safe the rod 34 is in the position shown. When the arming switch is on armed the rod 34 has been rotated to make contact with the battery 27 and contact spring 33.
  • the present invention is a launching system for target homing missiles, no precision accuracy in aiming the missile is required. However, some means must be provided for notifying the operator that the missile target sensing or seeking apparatus has acquired the target.
  • the acquisition of the target usually produces an electrical signal (or signals) somewhere in the missile that is transformed into a missile flight control signal. This signal (or signals) may also be used to notify the operator that the target has been acquired.
  • the signal may be monitored and sent through the quick-disconnect plug to the gripstock where it may be suitably transformed and used to energize a light, a hell or the like.
  • the target acquisition signals produced are audio frequency signals. If this is the case, then the electrical signal may be sent to a. small speaker in.
  • the gripstock whereupon an audible tone from the speaker notifies the operator that the target has been acquired. Loss of the target by the missile seeking apparatus terminates the speaker tone. Thus, the missile may be fired whenever the speaker tone'is audible.
  • FIG 4 is a schematic of the launching systems electrical circuitry for a representative missile having an audio frequency target acquisition signal.
  • This schematic shows an amplifier for the speaker.
  • the amplifier 35 and speaker 36 are located in the rear grip of the gripstock as shown in Figure 3.
  • the wiring for the amplifier, speaker, and fire switch is shown in Figure 4.
  • This signal is transmitted to the speaker from the missiles electronics section 41 which has its own battery lar retainer, said launch tube having a plurality of alignment lugs, one of said lugs corresponding to said positioned hole, said cam surface on said forward grip contacting the forward end of said lug when said launch tube is positioned on said gripstock, and the rearward movement of said forward grip forcing said lug and launch tube rearwardly until said lug engages said tubular retainer thereby mechanically locking said launch tube to tact points being located near said open end with a spring therebehind, said trough having a plurality of alignment 42.
  • the missile may be fired at any time during a sustained audio signal. is depressed. This closes the fire switch 39 which is located in the rear grip behind the trigger. As shown in Figure 4 this energizes a control actuator ignitor 43 and.
  • a rocket engine ignitor 44 If the missile does not use a hot gas control actuator then the connection to the control actuator ignitor 43 may not be needed.
  • Av hand launching system for missiles comprising a gripstock, an expendable launch tube, said gripstock forming a curved open ended trough with a rear grip and a fore and aft pivotably connected forward grip on its underside, said forward grip having a cam surface on its rear side, a tubular retainer adjacent to said rear grip and between said rear grip and said forward grip, said trough having a plurality of alignment holes, one of said holes positioned between said forward grip and said tubu- To fire the missile the trigger 38 holes with one of said holes between the open end of said tubular retainer and said pivotable forward grip, said launch tube having a plurality of alignment lugs,- one of said lugs'having a rearwardly facing contact plate with a plurality of electrical terminals thereon for making contact with said contact'points' of said gripstock,-
  • said forward grip of said gripstock having a cam surface for forcing said lug rearwardly against said spring held contact points, said launch tube and said gripstock being mechanically and electrically interconnected when said launch tube is positioned on said gripstock and said forward grip is pivoted to the rear.
  • a hand launching system for missiles comprising a gripstock and an expendable launch tube, said gripstock forming a substantially longitudinal trough having a rear-hand grip and forward hand grip attached thereto,
  • said trough having a plurality of alignment receptacles
  • said launch tube having a plurality-of alignment lugs adapted for locking engagement with said alignment receptacles, and said forward hand grip pivotally movable to contact said launch tube and coerce said alignment lugs into locking engagement with said alignment receptacles when said gripstock and launch tube are placed together.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Description

Feb. 28, 1961 Filed Dec. 23, 1957 J. M. GUTHRIE ETAL MISSILE HAND LAUNCHING SYSTEM 2 Sheets-Sheet l INVENTORS JOHN M. GUTHRIE GEORGE 0. HARKEY, JR. BY DONALD I. SMITH ATTORNEY Patented Feb. 28, 1961 MISSILE LAUNCHING SYSTEM- John M. Guthrie, Pomona, George D. Harkey, Jr., La 'Verne, and Donald. I. Smith, La Mesa, Califl, assignors to General Dynamics Corporation, San Diego, Calitl, a corporation of Delaware Filed Dec. 23, 1957, Ser. No. 704,560
3 Claims. (CI. 89-15) The present invention relates to a missile hand launching system and more particularly to a system for launching target homing missiles.
This invention is designed to be carried and operated by individual field personnel. Little comparison can be made with existing systems because they are used to fire ballistic projectiles whose eifectiveness is entirely dependent on the accuracy of the operator.
A unique feature of this invention is the positive manner in which the launching system mechanically and electrically engages the missile to be fired. Another feature is that it permits a missile packaging technique which allows final missile checkout at the originating facility. It also permits relatively rapid cyclic launching of missiles with a high degree of operational reliability. The invention is compact with its own replaceable power supply, requiring no other equipment than that enclosed within the launcher. The launching system and configuration disclosed herein could be adapted to applications other than shown in the preferred embodiment.
The launching system has two prime mechanical components. The two components are the launch tube and the gripstock. The launch tube also serves as the shipping container for the missile to be launched.
An object of the present invention is to provide individual field personnel with a means for launching missiles.
Another object is to provide individual field personnel with a missile container which can be used as the missile launch tube.
Other objects and features of the present invention will be readily apparent to those skilled in the art from the following specification and appended drawings wherein is illustrated a preferred form of the invention, and in which:
Figure 1 is a side elevation view of the launch tube with gripstock attached.
Figure 2 is an exploded view of Figure 1 showing the launch tube and gripstock separated and the launch tube and end caps separated.
Figure 3 is a cross section of a portion of Figure 1.
Figure 4 is a schematic of the launching systems electrical circuitry for a representative missile.
The launch tube shown in Figure l is an expendable item. In the preferred embodiment disclosed herein the launch tube is a phenolic impregnated, laminated paper tube. The missile is not removed from the tube at any time after final packaging. The tube can be sealed as an airtight package or filled with an inert gas for better corrosion protection. The tube has two end caps 11 and 12 which are held in place by a close fit pin and slot arrangement 13. This arrangement lends itself to safety wiring during storage periods. The end caps may contain cushions or pads to protect the missile.
The tube alignment lugs 14 and 15 are shown in Figure 2. These lugs fit into slots 14a and 15a in the gripstock 21. The gripstock 21 is shown as a curved trough having a rear grip 22 with trigger 38, and a pinned, springloaded forward grip 23. In preparing to load the launch tube on the gripstock, the forward grip 23 is swung forward about the pin 24. The tube is placed on the gripstock and then moved to the rear. The forward grip is then swung back into place, locking the tube to the gripstock.
The locking operation is more clearly illustrated in Figure 3. Here the launch tube is shown in the prelock position after the lugs 14 and 15 have just been inserted into the slots. The tube is then moved to the rear, in the direction of the arrows, so that the cam 25 on the forward grip can be placed in position to force the launch tube further to the rear. Thus, when the forward grip is swung back into place the launch tube is locked to the gripstock. The forward grip is held in the lock position by spring 44.
The rear lug 15 is used only for alignment and fits into an alignment socket 50 when the tube is in locked position. The forward lug 14, however, contains one half of a quick-disconnect electrical plug 16 which mates with a plug 17 in the missile. The plug 16 is held by a pin 20. The forward lug also has an electrical contact plate 19 for making contact with the gripstock. The contact plate has a plurality of contact points or terminals 51 which are connected to the quick-disconnect plug by the electrical wiring 37. When the launch tube is moved to the rear, the terminals in plate 19 are forced against spring loaded contact points 31 of the gripstock. In the locked position a portion of the forward lug protrudes into the tubular retainer 30, making the mechanical lock complete. The contact points 31 are set in a plug 45. A spring 46 is compressed between the plug and the screw 47. The screw 48 is positoned through a slot 49 in the plug. The slot allows fore and aft movement of the plug as a launch tube is locked into position or removed from the gripstock. The screws 47 and 48 also hold the tubular retainer 30 to the gripstock. The wires 52 electrically connect the contact points 31 to the electrical connector 53. The connector 53 engages pins 54 which have lead wires attached to them. One of the lead wires is soldered to the pin 55 for making electrical contact with the battery. The remaining wires run to the rear grip area to perform the functions shown in Figure 4. The tubular retainer with its plug, spring, and electrical connecter assembly is an easily removed and replaceable item. Although this is not necessary it is a desirable feature since. the contact points 3 1 can become worn.
A battery 27 for supplying electrical power is located in the rear grip. It is inserted from the aft end and held in place by a spring loaded cap 28 which acts as an electrical ground for the battery. An arming switch 32 shown in Figures 1 and 2 is used to connect the battery to the pin 55 and thus to the contact points 31. This is accomplished, as shown in Figure 3, by a contact spring 33 and a contact rod 34 which rotates with the arming switch. When the arming switch is on safe the rod 34 is in the position shown. When the arming switch is on armed the rod 34 has been rotated to make contact with the battery 27 and contact spring 33.
Since the present invention is a launching system for target homing missiles, no precision accuracy in aiming the missile is required. However, some means must be provided for notifying the operator that the missile target sensing or seeking apparatus has acquired the target. The acquisition of the target usually produces an electrical signal (or signals) somewhere in the missile that is transformed into a missile flight control signal. This signal (or signals) may also be used to notify the operator that the target has been acquired. The signal may be monitored and sent through the quick-disconnect plug to the gripstock where it may be suitably transformed and used to energize a light, a hell or the like.
3 In some missiles the target acquisition signals produced are audio frequency signals. If this is the case, then the electrical signal may be sent to a. small speaker in.
the gripstock whereupon an audible tone from the speaker notifies the operator that the target has been acquired. Loss of the target by the missile seeking apparatus terminates the speaker tone. Thus, the missile may be fired whenever the speaker tone'is audible.
Figure 4 is a schematic of the launching systems electrical circuitry for a representative missile having an audio frequency target acquisition signal. This schematic shows an amplifier for the speaker. The amplifier 35 and speaker 36 are located in the rear grip of the gripstock as shown in Figure 3. The wiring for the amplifier, speaker, and fire switch is shown in Figure 4.
To launch a missile a certain sequence is followed.
First, the .launch tube end caps are removed. Then the.
tube, with missile, is placed and locked on the gripstock. The arming switch is turned from safe to armed. By referring to Figure 4 it can be seen that this completes the electrical circuit between the battery 27 and the target detection apparatus 40 of the missile. Next, the missile is aimed at the target. When the missile acquires the target an audible signal is given off by the speaker 36. This signal is transmitted to the speaker from the missiles electronics section 41 which has its own battery lar retainer, said launch tube having a plurality of alignment lugs, one of said lugs corresponding to said positioned hole, said cam surface on said forward grip contacting the forward end of said lug when said launch tube is positioned on said gripstock, and the rearward movement of said forward grip forcing said lug and launch tube rearwardly until said lug engages said tubular retainer thereby mechanically locking said launch tube to tact points being located near said open end with a spring therebehind, said trough having a plurality of alignment 42. The missile may be fired at any time during a sustained audio signal. is depressed. This closes the fire switch 39 which is located in the rear grip behind the trigger. As shown in Figure 4 this energizes a control actuator ignitor 43 and.
a rocket engine ignitor 44. If the missile does not use a hot gas control actuator then the connection to the control actuator ignitor 43 may not be needed.
' After the missile is fired the arming switch is turned to safe, the empty tube is removed and another launch.
be readily apparent to those skilled in the art and the.
invention is to be given its broadest possible interpretation Within the terms of the following claims.
We claim:
1. Av hand launching system for missiles comprising a gripstock, an expendable launch tube, said gripstock forming a curved open ended trough with a rear grip and a fore and aft pivotably connected forward grip on its underside, said forward grip having a cam surface on its rear side, a tubular retainer adjacent to said rear grip and between said rear grip and said forward grip, said trough having a plurality of alignment holes, one of said holes positioned between said forward grip and said tubu- To fire the missile the trigger 38 holes with one of said holes between the open end of said tubular retainer and said pivotable forward grip, said launch tube having a plurality of alignment lugs,- one of said lugs'having a rearwardly facing contact plate with a plurality of electrical terminals thereon for making contact with said contact'points' of said gripstock,-
said forward grip of said gripstock having a cam surface for forcing said lug rearwardly against said spring held contact points, said launch tube and said gripstock being mechanically and electrically interconnected when said launch tube is positioned on said gripstock and said forward grip is pivoted to the rear.
3. A hand launching system for missiles comprising a gripstock and an expendable launch tube, said gripstock forming a substantially longitudinal trough having a rear-hand grip and forward hand grip attached thereto,
said trough having a plurality of alignment receptacles,
said launch tube having a plurality-of alignment lugs adapted for locking engagement with said alignment receptacles, and said forward hand grip pivotally movable to contact said launch tube and coerce said alignment lugs into locking engagement with said alignment receptacles when said gripstock and launch tube are placed together.
References Cited in the file of this patent UNITED STATES PATENTS France Mar. 4, 1953
US704560A 1957-12-23 1957-12-23 Missile hand launching system Expired - Lifetime US2972933A (en)

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Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3138064A (en) * 1961-11-13 1964-06-23 Hesse Eastern Inc Rocket launcher and sight
US3145619A (en) * 1961-05-15 1964-08-25 Ozanne Jean-Claude Rocket package assembly
US3198072A (en) * 1959-09-24 1965-08-03 Bolkow Entwicklungen Kg Portable missile carrier and launcher
US3251301A (en) * 1962-09-12 1966-05-17 Lockheed Aircraft Corp Missile and launcher system
DE1228535B (en) * 1964-04-09 1966-11-10 Diehl Fa Launch tube for a recoilless weapon
US3302522A (en) * 1964-10-12 1967-02-07 Laureys Pierre Weapons for firing self-propelled missiles
US3313207A (en) * 1965-04-02 1967-04-11 Arthur T Biehl Underwater weapon
US3357305A (en) * 1965-12-15 1967-12-12 Garland W Clutz Expendable dual-purpose rocket launcher shipping container
US3459100A (en) * 1967-05-24 1969-08-05 Bolkow Gmbh Mechanism for locking a missile retainer to a launching apparatus
US3494250A (en) * 1967-05-19 1970-02-10 Bolkow Gmbh Support member for a missile launching and guiding device
US3495497A (en) * 1967-05-19 1970-02-17 Bolkow Gmbh Coupling member for a missile firing and guiding device
US3754497A (en) * 1970-08-06 1973-08-28 Sarmac Sa Transporting and firing chest for self-propelled projectiles
US3774499A (en) * 1971-10-29 1973-11-27 D Applic Techn Soc Et Repeating weapon
US3811360A (en) * 1972-11-28 1974-05-21 Us Army Rocket hold back and tube closure
US3916759A (en) * 1968-10-29 1975-11-04 Us Navy Rocket launcher
US4091710A (en) * 1977-03-18 1978-05-30 The United States Of America As Represented By The Secretary Of The Army Thermal battery firing mechanism
FR2374613A1 (en) * 1976-12-16 1978-07-13 Walther Carl ELECTRONICALLY CONTROLLED TRIGGER FOR PORTABLE FIREARMS
EP0022430A2 (en) * 1979-07-06 1981-01-14 Förenade Fabriksverken Expendable type weapon system
US4298914A (en) * 1978-06-23 1981-11-03 Long Alvin L Electric firing device
US4417498A (en) * 1981-09-14 1983-11-29 General Dynamics, Pomona Division Firing mechanism for rocket launchers
US4491054A (en) * 1984-01-30 1985-01-01 General Dynamics, Pomona Division Pivotal pistol grip firing mechanism
EP0221783A1 (en) * 1985-10-31 1987-05-13 British Aerospace Public Limited Company Clamping mechanisms
US5956879A (en) * 1997-10-30 1999-09-28 Zerega; James E. Apparatus for aiming a handgun
US7226031B1 (en) 2004-03-09 2007-06-05 James Richard Warner Collapsible bookstand
US20090313875A1 (en) * 2006-07-27 2009-12-24 Steve Hines Stock interface
WO2016188869A1 (en) * 2015-05-26 2016-12-01 MYHRE, Tito Waage Device for launching hand grenades
WO2017123904A1 (en) * 2016-01-17 2017-07-20 Wilcox Industries Corp. Combined launch and storage tube for missile

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US194489A (en) * 1877-08-21 Improvement in revolving fire-arms
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US1397698A (en) * 1919-12-20 1921-11-22 Auto Ordnance Corp Gun
US2095490A (en) * 1935-09-30 1937-10-12 Joseph B Decker Rocket assembly
US2337145A (en) * 1940-05-09 1943-12-21 Albree George Norman Firearm
US2383471A (en) * 1942-06-27 1945-08-28 Joseph M Colby Firing grip
US2435217A (en) * 1945-05-02 1948-02-03 Jr Cleves H Howell Firearm and stock structure therefor
US2496316A (en) * 1943-09-22 1950-02-07 Leslie A Skinner Rocket projector
US2568455A (en) * 1945-03-28 1951-09-18 Frederick C Lindvall Rocket launcher
FR1029435A (en) * 1949-02-22 1953-06-02 Apparatus for launching signal rockets and others
US2742820A (en) * 1952-12-15 1956-04-24 Brown Robinson Contact and stop mechanism for launchers

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Publication number Priority date Publication date Assignee Title
US194489A (en) * 1877-08-21 Improvement in revolving fire-arms
US455279A (en) * 1891-06-30 Patrick cunningham
US1397698A (en) * 1919-12-20 1921-11-22 Auto Ordnance Corp Gun
US2095490A (en) * 1935-09-30 1937-10-12 Joseph B Decker Rocket assembly
US2337145A (en) * 1940-05-09 1943-12-21 Albree George Norman Firearm
US2383471A (en) * 1942-06-27 1945-08-28 Joseph M Colby Firing grip
US2496316A (en) * 1943-09-22 1950-02-07 Leslie A Skinner Rocket projector
US2568455A (en) * 1945-03-28 1951-09-18 Frederick C Lindvall Rocket launcher
US2435217A (en) * 1945-05-02 1948-02-03 Jr Cleves H Howell Firearm and stock structure therefor
FR1029435A (en) * 1949-02-22 1953-06-02 Apparatus for launching signal rockets and others
US2742820A (en) * 1952-12-15 1956-04-24 Brown Robinson Contact and stop mechanism for launchers

Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3198072A (en) * 1959-09-24 1965-08-03 Bolkow Entwicklungen Kg Portable missile carrier and launcher
US3145619A (en) * 1961-05-15 1964-08-25 Ozanne Jean-Claude Rocket package assembly
US3138064A (en) * 1961-11-13 1964-06-23 Hesse Eastern Inc Rocket launcher and sight
US3251301A (en) * 1962-09-12 1966-05-17 Lockheed Aircraft Corp Missile and launcher system
DE1228535B (en) * 1964-04-09 1966-11-10 Diehl Fa Launch tube for a recoilless weapon
US3302522A (en) * 1964-10-12 1967-02-07 Laureys Pierre Weapons for firing self-propelled missiles
US3313207A (en) * 1965-04-02 1967-04-11 Arthur T Biehl Underwater weapon
US3323457A (en) * 1965-04-02 1967-06-06 Arthur T Biehl Underwater weapon
US3357305A (en) * 1965-12-15 1967-12-12 Garland W Clutz Expendable dual-purpose rocket launcher shipping container
US3494250A (en) * 1967-05-19 1970-02-10 Bolkow Gmbh Support member for a missile launching and guiding device
US3495497A (en) * 1967-05-19 1970-02-17 Bolkow Gmbh Coupling member for a missile firing and guiding device
US3459100A (en) * 1967-05-24 1969-08-05 Bolkow Gmbh Mechanism for locking a missile retainer to a launching apparatus
US3916759A (en) * 1968-10-29 1975-11-04 Us Navy Rocket launcher
US3754497A (en) * 1970-08-06 1973-08-28 Sarmac Sa Transporting and firing chest for self-propelled projectiles
US3774499A (en) * 1971-10-29 1973-11-27 D Applic Techn Soc Et Repeating weapon
US3811360A (en) * 1972-11-28 1974-05-21 Us Army Rocket hold back and tube closure
FR2374613A1 (en) * 1976-12-16 1978-07-13 Walther Carl ELECTRONICALLY CONTROLLED TRIGGER FOR PORTABLE FIREARMS
US4091710A (en) * 1977-03-18 1978-05-30 The United States Of America As Represented By The Secretary Of The Army Thermal battery firing mechanism
US4298914A (en) * 1978-06-23 1981-11-03 Long Alvin L Electric firing device
EP0022430A2 (en) * 1979-07-06 1981-01-14 Förenade Fabriksverken Expendable type weapon system
EP0022430A3 (en) * 1979-07-06 1981-05-06 Forenade Fabriksverken Expendable type weapon system
US4417498A (en) * 1981-09-14 1983-11-29 General Dynamics, Pomona Division Firing mechanism for rocket launchers
US4491054A (en) * 1984-01-30 1985-01-01 General Dynamics, Pomona Division Pivotal pistol grip firing mechanism
EP0221783A1 (en) * 1985-10-31 1987-05-13 British Aerospace Public Limited Company Clamping mechanisms
US4827828A (en) * 1985-10-31 1989-05-09 British Aerospace Public Limited Company Clamping mechanisms
US5956879A (en) * 1997-10-30 1999-09-28 Zerega; James E. Apparatus for aiming a handgun
US7226031B1 (en) 2004-03-09 2007-06-05 James Richard Warner Collapsible bookstand
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WO2016188869A1 (en) * 2015-05-26 2016-12-01 MYHRE, Tito Waage Device for launching hand grenades
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