公开(公告)号：GB1196563A

公开(公告)日：1970-07-01

申请号：GB713568

申请日：1968-02-13

Applicant: NORRIS INDUSTRIES

Inventor： CHOATE PAUL VINCENT ,  SPINALE FRANK ANTHONY

IPC: F41A1/08 ,  F41A33/00 ,  F41F3/04 ,  F41F3/045

Abstract: 1,196,563. Rocket launcher. NORRIS INDUSTRIES Inc. 13 Feb., 1968, No. 7135/68. Heading F3C. A rocket launcher comprises two telescopic sections 10, 11 one 10 of which forms the breech end of the rocket launcher. The section 10 has a rigid member 20 attached thereto which member 20 overlies the section 11. A firing mechanism comprises a firing member 34 which is movable relative to the section 10 between a cocked forward position and a firing position. The cocking is effected during extension of the sections 10, 11 when the rigid and firing members 20, 34 are interconnected for movement with the section 10 by a pivoted latch 42. Towards the end of the extension movement of the two sections the firing member 34 is releasably connected to a trigger 22 so that the firing member is locked to the section 11 and a cocking spring (Figs. 1, 9, not shown) is compressed. A safety 30 is movable to disengage the latch 42 from the members 20, 34. In the construction shown the firing member is provided with a firing pin portion which cooperates with an igniter mounted in a pocket of the section 10. The latch is urged in an anticlockwise direction by one end of a spring 46, the other end thereof engaging a lock 47 which locks the sections in their telescoped conditions. The rocket launcher is shown as adjusted to discharge subcalibre rockets. To this end a tubular member 74 is mounted in the section 10 by three discs 75 (Fig. 9, not shown), 76, 77. The disc 75 includes an electric terminal for firing the rocket, the impulse being generated by a magneto 91 mounted on the disc 75. The magneto 91 which comprises a spring-loaded, slidable actuator 92 is actuated through a linkage 102, 103, 99 by a part 106 depending from the firing member 34. A lost motion connection is provided between the rod 102 of the linkage and the depending part 106 such that the part 106 is accelerated before it engages the rod in its firing stroke. A firing impulse is not imparted to a rocket in the launcher on cocking of the firing mechanism as the output of the segments is earthed through a switch 112 which is controlled by an arm 113 of the latch 42. A foresight and a backsight 51 are folded within the rocket launcher in the telescoped condition thereof but are spring-loaded to an erect position on extension of the rocket launcher.

公开(公告)号：GB1185656A

公开(公告)日：1970-03-25

申请号：GB1436767

申请日：1967-03-29

Applicant: NORRIS INDUSTRIES

Inventor： CHOATE PAUL VINCENT ,  ANTHONY-NEE MICHAEL

IPC: F42B10/66

Abstract: 1,185,656. Jet propulsion nozzles. NORRIS INDUSTRIES Inc. March 29, 1967, No.14367/67. Heading F1J. [Also in Division F3] An annular nozzle 39B, Fig.3 for the propellant gases from a flight sustaining solid fuel rocket motor 11B is defined in part by an internal plug 48A which is in engagement with threads 49 on a launching motor 10B to enable its position to be varied relative to a shoulder 38B of the housing 28B of the motor 11B. The shoulder 38B may be shaped as shown, or may be conical. Fins (60, Fig. 5 not shown) for rotating the rocket at a rate which is below that useful in spin stabilization is located within the annular nozzle. The launching motor 10B may have a rearwardly opening axial nozzle (17, Fig.1 not shown). In a modification, Fig.8 the annular nozzle is defined between the casing 28C and a member 52 formed on an axial rod 51. When the rocket is in a launcher 50, the launcher serves as a casing for a launching motor 10C, and defines with a second member 53, formed on the rod, its nozzle. In another modification, Fig.9 (not shown) the second member 53 of the previous modification is omitted and the launcher (55) is provided with a nozzle (56) at its rear end.

公开(公告)号：GB1100515A

公开(公告)日：1968-01-24

申请号：GB2452066

申请日：1966-06-01

Applicant: NORRIS INDUSTRIES

Inventor： CHOATE PAUL VINCENT ,  WEEKS CHARLES BAILEY ,  SPINALE FRANK ANTHONY

IPC: F41F3/045 ,  F41F3/077

Abstract: 1,100,515. Rocket launcher. NORRIS INDUSTRIES Inc. 1 June, 1966, No. 24520/66. Heading F3C. A rocket launcher comprises telescopically connected first and second sections, the first section having at one end the breech and being housed, in the inoperative position of the launcher, within the second section. The first section is provided with a rigid member 26 of channel section overlying the second section and, when the sections are extended to the operative position of the launcher, moves relative thereto. The member 26 has attached thereto a spring-loaded latching member 51 which keeps the sections locked either in the inoperative or operative positions of the launcher (Figs. 1, 2, not shown). The first section also includes a firing member 28 comprising a spring-loaded firing pin 29, the firing member 28 being, in the inoperative position of the launcher, connected to the rigid member 26 by a spring latch 34 engaging in apertures in both members and held in position by a sleeve like lock 35. The second section is provided with a firing mechanism which includes a pivoted, spring-loaded trigger 37 associated with a slidable safety device 45 and trigger sears 42. On extension of the two sections the members 26, 28 move together relatively to the second section until a depending stop 51 attached to the second section urges the lock 35 away from the latch 34 and the trigger sears 42 engage laterally projecting shoulders of the firing member 28. Further extension of the two sections causes the rearward edge of the retaining aperture of the member 28 to engage the rearward end of the latch 34 and cam the latch upwardly thus disconnecting the two members. The firing member 28 is thus cocked by the final relatively short movement of the two sections. The safety device 45 when urged away from the trigger 37 in the operative position of the launcher has a portion which is engaged by the latch 34 to lock the safety device in its inoperative position (Fig. 6, not shown). In the inoperative position of the two sections a foresight 55 and a rear sight 58 of the second section are kept in a depressed state against spring loading by the latching member 51 and a housing 18 of the first section.

公开(公告)号：GB1098118A

公开(公告)日：1968-01-03

申请号：GB1497766

申请日：1966-04-04

Applicant: NORRIS INDUSTRIES

Inventor： CHOATE PAUL VINCENT ,  CARR ALTON FRANK

IPC: F41G1/00 ,  F41G1/08 ,  F41G3/08

Abstract: 1,098,118. Sights for weapons. NORRISINDUSTRIES Inc. April 4, 1966, No. 14977/66. Heading F3C. A sight for a weapon comprises a mount 14 and a sighting unit housed within the mount and including a vertically movable sight member 22 to which one end of a thermally responsive means 24 is connected. The other end of the thermally responsive means 24 is connected to the mount and is made of such a material, e.g. bi-metallic strip, that in the case of a back sight, the sighting member is lowered in the mount for a decrease in temperature and raised for an increase in temperature. The sight is for a weapon firing rocket having solid fuel propellent, the efficiency of the propellant depending upon its initial firing temperature. Hence as the propellant temperature increases the trajectory of the associated projectile becomes lower, the sight compensating for this energy variation (Fig. 1, not shown). The thermally responsive means may comprise a helix formed from helically wound bi-metallic strip, a spiral bi-metallic strip (Fig. 6, not shown) on a U-shaped bi-metallic strip one end of which is connected to the mount and the other end carrying a forked member, a pin, joining the free end of the forked member, working in a diagonal slot in the sight member (Fig. 7, not shown). The sight member 22 is provided with a peep aperture 23 viewed through windows 21 in the mount. The thermally responsive means 24 is a free fit within a sleeve 26 of heat reflecting material such as aluminium.