Home | Links | Contact Us | More About Intellectual Property | Bookmark
Search patents:
Home Telecommunications Self-destructing-impact-fuse

 Vehicle guidance system for guided missiles having adaptive trajectory bias
What is claimed is: 1. In a guided missile system of the type including a seeker for providing ...


 Static vent units
According in one aspect this invention provides a static vent unit for use on a vehicle and which ...


 Differential GPS ground station system
An object of the present invention is to provide a differential GPS ground station having enhanced ...


 Communication system employing space-based and terrestrial telecommunications equipment
To meet the above and other objectives, the present invention provides for a communications system ...


 Ins alignment method using a doppler sensor and a GPS/HVINS
The following description of the preferred embodiments of the invention shown in the FIG. 1 and FIG...


 Method and device for displaying animated navigation information
The present invention satisfies the above described need and other needs by providing a GPS ...


 Bobbin transfer tail retainer
What is claimed is: 1. A yarn bobbin having a transfer tail retainer comprising a cylindrical tube ...


 Yarn carrier
An object of the present invention is to provide an improved yarn carrier. Another object of the ...


 Textile yarn carrier
This invention relates to tubular carriers of textile yarn packages particularly used with winding ...


 Spool for filament winder
It is therefore an object of the present invention to provide an improved spool for use in an ...


 Self-destructing impact fuse

Details
Inventors: Hok, AW Cheng; Soon, EE Guan; Chiow, Tan Chian;
Assignee: Chartered Ammunition Industries PTE LTD (Singapore, SG)
Primary Examiner: Carone; Michael J.
Assistant Examiner: Semunegus; Lulit
Attorney, Agent or Firm: Nikolai, Mersereau & Dietz, P.A.

A self destructing impact fuse including a cylindrical firing pin having a hollow centrifugal chamber for holding a number of spheres and a number of radial openings on its surface for exposing portions of the spheres when the chamber is spun. At one end of the chamber is a spring for exerting compression force along the longitudinal axis of the chamber and at the other end is a self-destructing (SD) firing pin for striking the detonator. A centrifugal lock having a pivot offset from the longitudinal axis holds the chamber in place by mating with a groove on the surface of the centrifugal chamber. The cylindrical firing pin is seated concentrically within a frame and disposed over an escapement assembly featuring the detonator. The detonator is rotated into alignment with the SD firing pin after the projectile, incorporating the fuse, travels the minimum tactical distance. The frame is further coupled with a base, which features a point detonation (PD) firing pin for striking the detonator.

DETAILED DESCRIPTION The present invention includes a cylindrical firing pin having a hollow centrifugal chamber for holding a number of spheres and a number of radial openings on its surface for exposing portions of the spheres when the chamber is spun.
At one end of the chamber is a spring for exerting a compression force along the longitudinal axis of the chamber and at the other end is a self-destructing (hereinafter referred to as "SD") firing pin for striking the detonator.
A centrifugal lock having a pivot, offset from the longitudinal axis, holds the chamber in place by mating with a groove on the surface of the centrifugal chamber.
The cylindrical firing pin is seated concentrically within a frame and disposed over an escapement assembly featuring the detonator.
The detonator is rotated into alignment with the SD firing pin after the projectile incorporating the fuse travels a minimum tactical distance.
The frame is further coupled to a base, which features a point detonation (hereinafter referred to as "PD") firing pin for striking the detonator.


Related patents
  Lock-on-after launch missile guidance system using three dimensional scene reconstruction
In accordance with the present invention, rather than using a two dimensional description of the target (template) to match a two dimensional realization of the target (...
  GPS receiver with extended security
OF THE PREFERRED EMBODIMENT(S) FIG. 1 is an overview illustration of the operation of secure GPS receiver system 10 according to the present invention in which SAASM GPS...
  Burst height compensation
It is an object of the present invention to increase the predictable effectiveness of the reentry body upon the intended target. Another object of the present invention ...
  Shuttle launch system for model rocket
The present invention provides a shuttle launch system for a model rocket which includes a model rocket engine having a propellant charge for propelling the model rocket ...
  Control propulsion unit, especially for exerting transverse forces on a missile
An object of the present invention is to provide a control propulsion unit of the type discussed having a simple design, which will enable the thrust of the propulsion ...
  Venting apparatus for controlling missile underwater trajectory
Accordingly, the present invention relates to apparatus for actively controlling the venting of gas from the interior of a missile in such a manner as to influence the ...
  Discrete impulse spinning-body hard-kill (disk)
DISK is a munition system for intercepting a target wherein the system comprises a base platform dispenser, a right circular cylinder having a circular periphery, ...
  System for steering a missile by means of lateral gas jets
The object of the present invention is to provide a system of the above mentioned type having both valving means with low inertia and valving control without ...
  Forebody nozzle for aircraft directional control
Theoretical considerations and an experimental study of the control of forebody vortex flow fields using forebody pneumatic jets are described in the article by C...
  Device for guiding a missile
The above object is achieved according to the present invention by a device for guiding a missile having a missile tip and a cylindrical section adjoining the tip of the ...

0.004

Archive: All patents - Links

Copyright (c)2006 Eipa-patents.org - All rights reserved