Patents Assigned to BAE Systems Rokar International Ltd.
  • Publication number: 20180245895
    Abstract: 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.
    Type: Application
    Filed: March 30, 2018
    Publication date: August 30, 2018
    Applicant: BAE Systems Rokar International Ltd.
    Inventors: Assaf MALUL, Ziv MOSHKOVITZ
  • Patent number: 9945649
    Abstract: 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.
    Type: Grant
    Filed: August 24, 2011
    Date of Patent: April 17, 2018
    Assignee: BAE SYSTEMS ROKAR INTERNATIONAL LTD.
    Inventors: Assaf Malul, Ziv Moshkovitz
  • Patent number: 9587923
    Abstract: 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.
    Type: Grant
    Filed: March 1, 2016
    Date of Patent: March 7, 2017
    Assignee: BAE SYSTEMS ROKAR INTERNATIONAL LTD.
    Inventors: Gil Wurzel, Assaf Malul
  • Patent number: 9303964
    Abstract: 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.
    Type: Grant
    Filed: October 29, 2013
    Date of Patent: April 5, 2016
    Assignee: BAE SYSTEMS ROKAR INTERNATIONAL LTD.
    Inventors: Gil Wurzel, Assaf Malul
  • Publication number: 20150247715
    Abstract: 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.
    Type: Application
    Filed: October 29, 2013
    Publication date: September 3, 2015
    Applicant: BAE Systems Rokar International Ltd.
    Inventors: Gil WURZEL, Assaf MALUL