Projectile guiding assemblies, caps and methods of delivering power for testing and optionally data over spring-mounted fin(s) of the guiding assembly are provided. The guiding assemblies are configured to have continuous electrically conductive path(s) from the fin(s), through the respective spring(s) on which the fin(s) are mounted, and into the electronics module, which may receive power for testing and guiding data from external source(s) over the electrically conductive path(s). In the testing state, cap mechanically secures the fin(s) to contact(s) thereupon to assure continuous power and data transfer, sparing surface area that was previously dedicated to power and data transfer and simplifying these processes, especially under field conditions.
A device for improving the aerodynamic feature of a projectile is disclosed. The projectile has a front part and a rear part. The external diameter of the front part of the projectile is larger than the external diameter of the front end of a rear part of the projectile. The front end of the rear part of the projectile is conical having larger diameter at locations behind the front end. The device comprises an annular cut-off cone sleeve slidably disposable over the front part of the projectile. The diameter of the narrower end of the annular cone sleeve is slightly larger than the diameter of the front part of the projectile and the length of the annular cut-off cone sleeve is larger than the distance between the front end of the rear part of the projectile and a location on rear part having a diameter equal to the diameter of the rear end of the annular cut-off cone sleeve.
F42B 10/00 - Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missilesArrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
A device for improving the aerodynamic feature of a projectile is disclosed. The projectile has a front part and a rear part. The external diameter of the front part of the projectile is larger than the external diameter of the front end of a rear part of the projectile. The front end of the rear part of the projectile is conical having larger diameter at locations behind the front end. The device comprises an annular cut-off cone sleeve slidably disposable over the front part of the projectile. The diameter of the narrower end of the annular cone sleeve is slightly larger than the diameter of the front part of the projectile and the length of the annular cut-off cone sleeve is larger than the distance between the front end of the rear part of the projectile and a location on rear part having a diameter equal to the diameter of the rear end of the annular cut-off cone sleeve.
F42B 10/46 - Streamlined nose conesWindshieldsRadomes
F42B 10/00 - Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missilesArrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
F42B 10/64 - Steering by movement of flight surfaces of fins
4.
Projectile fuze assembly and methods of assembling and use
A guiding kit for guiding a projectile to a target comprises a front part and a rear part. The front part and the rear part are rotatably connected to each other to enable relative rotation about a common central longitudinal axis of rotation. The front part comprises a front transceiver (T/X) unit that is disposed next to the rear end of the front part and coinciding with the longitudinal central axis of rotation and adapted to transmit signals towards the rear part. A rear transceiver unit is disposed against the front transceiver unit and adapted to communicate with front transceiver unit when the front part and the rear part are rotating with respect to each other.
F42B 10/64 - Steering by movement of flight surfaces of fins
F42C 15/42 - Arming-means in fuzesSafety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected electrically from a remote location, e.g. for controlled mines or mine fields
F42C 13/00 - Proximity fuzesFuzes for remote detonation
A device for sealing a projectile guiding kit may be used with any kit having a rear unit and a front unit rotatably connectable to the rear unit thereof. The device may include an annular body adapted to envelope at least a front portion of the rear unit and at least a rear portion of the front unit of the kit. The device may include a flexible ring-shaped strip attached to an inner side and at a front end of the annular body and adapted to seal a gap between the rear unit and the front unit of the kit. The annular body may be adapted to slide towards the rear unit of the kit when subjected to a longitudinal acceleration that exceeds a predetermined acceleration value, thereby uncovering the gap and enabling uninterrupted rotation of the front unit with respect to the rear unit of the kit.
F42B 12/02 - Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
F42B 15/00 - Self-propelled projectiles or missiles, e.g. rocketsGuided missiles
6.
System and method for guiding a cannon shell in flight
A method for guiding an artillery projectile to a target. In one embodiment, the method includes providing control commands to change an angle of attack of one or more roll stabilizing fins and providing control commands to change an angle of attack of one or more lift guiding fins; and controlling the roll angle to provide a lift force to guide the projectile along a trajectory, wherein the projectile is configured to spin about its longitudinal axis during flight.
A guiding assembly is adapted to be connected to a projectile and comprising a rear main unit adapted to be connected to the front end of the projectile, and a front main unit rotatably connected at its rear end to the front end of the rear main unit. The front main unit is adapted to rotate about a central longitudinal axis. A relative speed control unit is operable between the rear main unit and the front main unit and capable of providing spin braking force to slow the relative speed of rotation of the front main unit. An at least one guiding fin radially extends from the front main unit. The pitch angle of the fin is controllable by a return spring connected to the fin so that the pitch angle of the fin is growing as the aerodynamic pressure on the fin lowers and it is growing smaller as the aerodynamic pressure on the fin gets bigger.
A guiding assembly is adapted to be connected to a projectile and comprising a rear main unit adapted to be connected to the front end of the projectile, and a front main unit rotatably connected at its rear end to the front end of the rear main unit. The front main unit is adapted to rotate about a central longitudinal axis. A relative speed control unit is operable between the rear main unit and the front main unit and capable of providing spin braking force to slow the relative speed of rotation of the front main unit. An at least one guiding fin radially extends from the front main unit. The pitch angle of the fin is controllable by a return spring connected to the fin so that the pitch angle of the fin is growing as the aerodynamic pressure on the fin lowers and it is growing smaller as the aerodynamic pressure on the fin gets bigger.
An apparatus and method for guiding a cannon shell accurately are disclosed. The apparatus includes two main parts adapted to be installed on the leading end of the cannon shell. The front main part of the apparatus is equipped with at least one pair of fins and is rotatable with respect to the rear main part. The pair of fins is controlled to hold the front main part substantially stable with respect to an external reference frame when the cannon shell rotates as it flies towards its target. Control system is comprised within the apparatus that receives location signals and is adapted to provide guiding control commands to the cannon shell via the fins so as to guide the shell accurately to its preprogrammed target. The control system is adapted to activate the detonation chain of the shell according to preprogrammed mode.
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