GB1256760A - - Google Patents

Info

Publication number
GB1256760A
GB1256760A GB1256760DA GB1256760A GB 1256760 A GB1256760 A GB 1256760A GB 1256760D A GB1256760D A GB 1256760DA GB 1256760 A GB1256760 A GB 1256760A
Authority
GB
United Kingdom
Prior art keywords
rocket
fairings
fairing
nose
firing
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
Application number
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 filed Critical
Publication of GB1256760A publication Critical patent/GB1256760A/en
Expired legal-status Critical Current

Links

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
    • F41F3/077—Doors or covers for launching tubes

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

1,256,760. Rocket launches. THOMAS FRENCH & SONS Ltd. 25 Aug., 1970 [20 June, 1969], No. 31250/69. Heading F3C. A rocket launcher for attachment to an aircraft comprises a plurality of rocket-receiving tubes 11 and a fairing or nose cone 13 acting as a heat shield affixed to the forward end of each rocket-receiving tube 11, each fairing or nose cone being adapted on firing a rocket therethrough to open along predetermined lines whilst remaining attached to the tubes. In the construction shown the lines comprise lines of weakness 17 formed by grooves on the inner face of the fairing 13. The fairings may be of plastics material and the grooves formed during the moulding thereof. Alternatively, sections of the fairings or nose cones may be jointed and locked together so that after firing of the rockets therethrough the fairings or nose cones may be re-usable.
GB1256760D 1969-06-20 1969-06-20 Expired GB1256760A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3125069 1969-06-20

Publications (1)

Publication Number Publication Date
GB1256760A true GB1256760A (en) 1971-12-15

Family

ID=10320291

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1256760D Expired GB1256760A (en) 1969-06-20 1969-06-20

Country Status (1)

Country Link
GB (1) GB1256760A (en)

Similar Documents

Publication Publication Date Title
GB1443626A (en) Radar-augmented sub-target
GB868408A (en) Improvements in and relating to an improved nozzle and tailplane device for a self-propelling missile
GB1103580A (en) Fairing
GB884128A (en) Improvements in or relating to flying bodies for supersonic speeds
GB1279102A (en) Improvements in or relating to assemblable missiles
GB907244A (en) Improvements in launching racks for flying bodies
GB1389950A (en) Target directed projectile
GB988318A (en) Frangible fairings for rocket launchers
GB939806A (en) Improvements in rocket-bomb firing apparatus
GB1256760A (en)
GB1024103A (en) Aircraft with flexible wings
US3106863A (en) Casing for transporting rocket-bombs from an aircraft
GB1198989A (en) Improvements in Pyrotechnic Devices
GB1260422A (en) Non-rotating projectile for use with a launching tube
GB1283941A (en) Improvements in fairings for rocket launchers
GB573485A (en) Improvements in or relating to rockets
GB1085045A (en) A projectile or aerial bomb
GB961001A (en) Improvements in propulsion units having a plurality of reaction propulsion nozzles
GB1295629A (en)
GB1173098A (en) Projectile for Supersonic Flight
FAULMANN Study of the interaction of supersonic jets(Supersonic jet interaction for hypersonic flow of Mach 7. 1 and for variable Mach number, noting jet instability, stagnation pressure, drag variation, wind tunnel, etc)
GB951237A (en) Improvements in or relating to rocket propulsion units employing solid propellants
FR1496471A (en) Jet airplane with vertical flight and vertical take-off method for an airplane
GB1000272A (en) Improvements relating to rocket launchers
LUCAS et al. Evaluation of wind tunnel tests on AFMDC monorail cone and spike nose sled configurations at Mach numbers from 2. 0 to 5. 0 Final technical report, 27 Feb.- 23 Apr. 1968(Supersonic wind tunnel tests of monorail nose cone and spike nose rocket propelled sled models)

Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees