Brunswick Corporation

Kdi Precision Products, Inc.

Michael F Steele

William Marc Schmidt

William D Bowers

Raymond L Chuan

Ezra Stearns Waller

Nathan N Shiovitz

John G Maloney

George M Dobson

Scott R Langer

John E Lambright

In one aspect, an artillery projectile apparatus is provided that includes a carrier projectile containing a payload, and a fuze disposed at an ogive of the projectile and which is configured to eject the payload when the fuze is detonated. The fuze includes a receiver configured to receive location information from a radionavigation source and a processor configured to acquire position data from the receiver. The processor is also configured to estimate a projectile flight path using the position data, to determine intercept parameters of the artillery projectile relative to an ejection plane of its payload cargo, and to adjust an ejection event initiation command time of the payload in accordance with the determined intercept parameters. In some configurations, the present invention dramatically decreases range errors typically associated with delivering artillery payloads to specific targets.

Accuracy fuze for airburst cargo delivery projectiles

A fuze for a munition adapted to prevent unintended arming thereof. The fuze incorporates an arming screw having a keyed portion and a centrifugal locking mechanism for preventing rotation of the arming screw unless the fuze mechanism is in a rapidly spinning condition such as that experienced when the fuze and its associated munition are deployed from an airborne rocket or artillery shell, and thus spinning at a rate of at least several thousand rpm. The centrifugal locking mechanism includes a pair of locking members which are biased by biasing elements into engagement with the keyed portion of the arming screw. This prevents the arming screw from being accidentally unscrewed from an inertia weight within the fuze, thus placing the fuze in an unintended armed condition. However, when the munition is deployed from an airborne rocket or artillery shell, and thus reaches a spinning rate of several thousand rpm or higher, the centrifugal force acting on the locking members forces them out of engagement with the keyed portion. This allows the arming screw to unscrew from the inertia weight and arm the fuze.

Fuzes having centrifugal arming lock for a munition

A munition incorporating a fuze mechanism adapted to prevent momentary disarming of the mechanism once same is placed in an armed state. The fuze mechanism incorporates a fuze housing having a slide member movable slidably longitudinally between an unarmed position and an armed position. In an unarmed position, a firing pin tip of an arming screw engages a lock post disposed within an opening in the slide member to hold the slide member in the unarmed position. When the arming screw is unscrewed during airborne deployment of the munition, the firing pin tip is withdrawn from the lock post. This enables a spring to urge the slide member into a laterally extended position. As the slide member moves into its laterally extended position, the lock post drops partially out of the slide member into abutting engagement with a bottom cover of the fuze mechanism, thus preventing the slide member from moving back towards its unarmed position. Thus, the lock post prevents momentary movement of the slide member back towards its unarmed position regardless of the orientation at which the munition strikes the ground surface or a target, thus eliminating the possibility of undetonated yet armed munitions remaining on a ground surface or target.

Fuze mechanism for a munition

A system is disclosed for relieving excessive pressure within a combustion chamber of a spin-stabilized, jet-propelled missile launching system. An annular passage surrounds an exhaust nozzle, the passage being in communication with the chamber. A unitary valve ring closes the passage. Frangible pins hold the unitary valve ring in its closing position. An exhaust vent slaving cavity is provided for capturing the unitary valve ring upon rupture of the frangible pins. Exhaust vent ports communicate the slaving cavity with atmosphere, whereby the slaving cavity operates to capture the entire unitary valve ring bodily upon rupture of the frangible pins in response to excessive pressure within the chamber to relieve the pressure as the exhaust vent ports exhaust the chamber.

Pressure relief means for jet-propelled missiles

A release mechanism for facilitating launching a spin-stabilized self-propelled missile, which includes a rotary missile support and a launching support for supporting the rotary missile support for rotation about a spin axis and for movement axially of the spin axis. A nozzle assembly extends between the rotary missile support and the missile coaxial with the spin axis. A separable portion of the nozzle assembly moves axially in an aft direction under the influence of exhaust gases expelled by the missile. The separable portion strikes an abutment on the rotary missile support to effect rapid movement of the rotary missle support axially away from the missile on separation of the separable portion of the nozzle assembly. A low friction bearing is provided for engagement by the rotary missile support at its aft limit position of travel away from the missile to reduce spin momentum induced forces caused by the rotary missile support. Another low friction bearing surrounds the rotary missile support between the support and the launching support to further reduce spin momentum induced forces. A time release mechanism is provided for preventing aft movement of the rotary missile support during a given number of initial revolutions and for releasing the rotary missile support to allow aft movement thereof after the given number of initial revolutions. A prescribed clearance is provided between the missile and the launching support to prevent post-separation collisions between the missile and the lauching support.

Release mechanism for spin-stabilized self-propelled missiles

The gas detection apparatus for detecting chemical agents in an air stream includes a radioactive source to ionize the air stream and an electrostatic field to increase the efficiency of the apparatus by neutralizing undesired ions, which allows a radioactive source with a lower radiation level to be used than would be required without such neutralization. A diffusion chamber including a baffle device is then used for an ion selection processes. Additional undesired ions are diffused into the walls of the diffusion chamber while the remaining ions, which are the ones sought to be detected, pass from the diffusion chamber into a collection chamber. Detection of the chemical agent ions is achieved when the remaining ions collide with the walls of a collection chamber, transferring their charge to thereby generate a current.

Gas detection apparatus and related method

For use with a launching apparatus for a spin-stabilized self-propelled missile, which includes a rotary missile support defining a spin axis and receiving the missile with a missile axis of rotation, and a spring operative to hold the missile on the missile support, a method and apparatus are provided for aligning the missile axis of rotation with the spin axis. The rotary missile support and missile are supported on a fixture for rotation about the spin axis. The rotary missile support and missile then are rotated relative to the fixture about the spin axis. The amount of eccentricity between the missile axis of rotation and the spin axis is determined. The missile is restrained for single plane motion and is adjustably moved relative to the rotary support to coincidently align the missile axis of rotation with the spin axis. The spring then is tightened to maintain the coincident alignment of the axes.

Method and apparatus for aligning spin-stabilized self-propelled missiles

A release mechanism for facilitating launching a spin-stabilized self-propelled missile. A missile support includes a rotary turbine having a receptacle defining a spin axis, and a fixed support for supporting the rotary turbine for rotation about the spin axis and for movement axially of the spin axis. A nozzle assembly extends from the missile into the receptacle and includes a fusible joint for heating by high temperature exhaust gases expelled by the missile to release the missile, and an aft nozzle section movable away from the missile on fusing and separation of the fusible joint. An abutment on the rotary turbine is disposed in the path of movement of the aft nozzle section for striking by the aft nozzle section to effect rapid movement of the rotary turbine and receptacle axially away from the missile on fusing and separation of the fusible joint.

Release apparatus for spin stabilized self-propelled projectiles

A device for gas detection through ion mobility segregation by mobility ranges includes a flow tube through which a sample of atmospheric air with possible contaminant gases flow. Ions formed of gases in the air and the possible contaminant gases are segregated by ion mobility range in either a first, second or subsequent electric field positioned along the flow tube. The ions are collected on an anode or cathode of each electric field. The ions of the gases striking an anode or cathode by charge transfer induce a detection current, the measure of which indicates the presence of gases of interest. A method for detecting a gas by ion mobility segregation is also described.

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Cincinnati, OH, United States of America

Michael F Steele