GB771851A - Improvements relating to projectiles, particularly rocket projectiles or bombs - Google Patents

Improvements relating to projectiles, particularly rocket projectiles or bombs

Info

Publication number
GB771851A
GB771851A GB19499/55A GB1949955A GB771851A GB 771851 A GB771851 A GB 771851A GB 19499/55 A GB19499/55 A GB 19499/55A GB 1949955 A GB1949955 A GB 1949955A GB 771851 A GB771851 A GB 771851A
Authority
GB
United Kingdom
Prior art keywords
rocket
support
bar
recess
wing
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
GB19499/55A
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.)
Saab Bofors AB
Original Assignee
Bofors AB
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 Bofors AB filed Critical Bofors AB
Publication of GB771851A publication Critical patent/GB771851A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

771,851. Rocket projectiles ; discharging from aircraft. AKTIEBOLAGET BOFORS. July 6, 1955 [July 9, 1954], No. 19499/55. Class 9 (2). Relates to rockets which are adapted to be fired electrically and suspended horizontally beneath an aircraft wing in vertical rows, the topmost rocket in a row being attached to the wing and each succeeding rocket being suspended from the rocket immediately above. Each rocket is provided with two projecting members and a recess so arranged that, when a second rocket is attached, the recess of the first rocket receives a shearable portion of a projecting member of the second rocket. The body 4 of the rocket 1 is provided with grooved guides 14, 15 which receive flanges of a support 11 fixed to the wing, similar flanges 17, 18 being provided on the rocket to engage the guides of rocket 2. Through a non-conducting body 32 extends a bar 33 biased by springs to project from each side of the rocket before attachment to the aircraft. On attachment to the support 11 the upper projecting end of the bar enters a recess in the support, the weakened portion of the bar being coincident with the junction of the rocket and the support. On attachment of the rocket 2, the bar 32 of rocket 1 is moved further into the recess of the support 11, so locking rocket 1 to the support. As the rocket 1 is attached to the support 11, the electrical circuit from a control device 23 within the aircraft is completed through contacts 26, 27 to an ignition device 44 for the rocket motor 5. When rocket 2 is put in position, movement of the bar 33 breaks the circuit to the ignition device 44 of rocket 1 and completes the circuit to the device 44 of rocket 2, so that rocket 2 must be fired before rocket 1. The rockets have a nozzle portion 6 from which project vanes 7, each vane being slotted so that the two upper vanes can engage the lower vanes of the rocket immediately above to support the rocket tail. The upper vanes of rocket 1 engage a device 10 depending fromthe wing 9. Specification 771,852 is referred to.
GB19499/55A 1954-07-09 1955-07-06 Improvements relating to projectiles, particularly rocket projectiles or bombs Expired GB771851A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE771851X 1954-07-09

Publications (1)

Publication Number Publication Date
GB771851A true GB771851A (en) 1957-04-03

Family

ID=20333374

Family Applications (1)

Application Number Title Priority Date Filing Date
GB19499/55A Expired GB771851A (en) 1954-07-09 1955-07-06 Improvements relating to projectiles, particularly rocket projectiles or bombs

Country Status (1)

Country Link
GB (1) GB771851A (en)

Similar Documents

Publication Publication Date Title
US2824496A (en) Electric control system for singly and sequentially firing ballistic missiles
GB846246A (en) Improvements in rockets carried in clusters by a launching machine and in particular by an aircraft
GB869410A (en) Improvements relating to projectiles and rockets
GB771851A (en) Improvements relating to projectiles, particularly rocket projectiles or bombs
GB1179804A (en) Illuminating projectiles
US2792756A (en) Rocket launching support structure
US3122058A (en) Systems comprising a cluster of rockets carried by a launching machine
GB715928A (en) A rocket projectile and a launching device therefor
US3059541A (en) Rockets carried in clusters by a launching machine and in particular an aircraft
GB1016030A (en) A new or improved apparatus for controlling aircraft
GB854015A (en) Improvements in firing systems for rockets carried in clusters by a launching machine, and in particular an aircraft
FINELLI Flight controls of subroc, a rocket-propelled nuclear armed missile to be used on submarines
Chernyi et al. Supersonic flow of a combustible gas mixture past a sphere with allowance for the ignition delay time(Supersonic flow of combustible gas mixture past sphere with allowance for ignition delay time)
LEE Description of a facility to test the shock- isolation system of the launch control center for the minuteman missile
MILLS et al. Guided weapons aerodynamic study- Characteristics of aft mounted all-moving rectangular control surfaces on a slender cruciform missile at Mach numbers from 0. 6 to 2. 8(Aerodynamic characteristics of aft mounted all-moving rectangular control surfaces on slender cruciform missile at Mach numbers from 0. 6 to 2. 8)
GB925415A (en) Improvements in parachute apparatus
GB1000272A (en) Improvements relating to rocket launchers
MAZET Critical transitory velocity of a supersonic engine determined by subjecting the engine to an infrared beam which simulates the kinetic heating of accelerated flight
GB946700A (en) Improvements in or relating to rocket projectiles
CONNER An airline approach to reliability(Airline reliability, including turbine engine reliability alert concept, applied to subsystems of douglas dc-8)
FIEDLER et al. Missile environment simulation for rocket engine test facility(Test facility design for large rocket engines under simulated altitude conditions)
FERRE et al. Gas turbine engine analog simulation for acceleration sensing fuel control studies(Gas turbine engine analog simulation for acceleration sensing fuel control studies, comparing results with actual engine performance)
PREININGER Effects of specific engine weight, reynolds number, fuel consumption and safe flying time on the choice of optimum thrust levels for turbojets
JAMES Flight demonstration of a nose-mounted rotating-solid-propellant rocket control system and a comparison with analog studies(Flight test of nose mounted rotating solid propellant rocket attitude control system for space vehicle second stage)
GRAY An approach to and results of a formal reliability program in connection with the minuteman flight control system