Abstract: A miniature lightweight high-maneuverability missile (10) has a missile body (12) with three sets of at least two aerodynamic control surfaces (14, 16, 18) for independent control of roll, pitch and yaw of the missile. Each set of control surfaces (14, 16, 18) is independently controlled by a corresponding actuator (20) deployed within the missile body (12). Other preferred features include selection of an elevation angle of incidence at a target, and switching between explosive and kinetic modes of operation.

Abstract: A miniature lightweight high-maneuverability missile (10) has a missile body (12) with three sets of at least two aerodynamic control surfaces (14, 16, 18) for independent control of roll, pitch and yaw of the missile. Each set of control surfaces (14, 16, 18) is independently controlled by a corresponding actuator (20) deployed within the missile body (12). Other preferred features include selection of an elevation angle of incidence at a target, and switching between explosive and kinetic modes of operation.

Abstract: A method for adjusting the flight path of an unguided projectile, which comprises the steps of: (a) Measuring the magnitude and direction of the jittering of a projectile launch tube, at an ejection time of a projectile from the launch tube; (b) Measuring a velocity deviation of the projectile from a nominal velocity; (c) Measuring an angular deviation of the sight of the launch tube, being equal to the angular deviation between a line coinciding with the direction of gravity and a line passing through the center of the launch tube and the center of the sight; (d) Determining a compensating impulse vector to be applied to the projectile during an initial flight path thereof based on the magnitude and direction of the jittering, velocity deviation and angular deviation; and (e) Applying the compensating impulse vector to the projectile by activating a flight correction unit, the thrust developed by the flight correction unit suitable for adjusting the flight path of the projectile by a magnitude and direction

Abstract: A method for adjusting the flight path of an unguided projectile, which comprises the steps of: (a) Measuring the magnitude and direction of the jittering of a projectile launch tube, at an ejection time of a projectile from the launch tube; (b) Measuring a velocity deviation of the projectile from a nominal velocity; (c) Measuring an angular deviation of the sight of the launch tube, being equal to the angular deviation between a line coinciding with the direction of gravity and a line passing through the center of the launch tube and the center of the sight; (d) Determining a compensating impulse vector to be applied to the projectile during an initial flight path thereof based on the magnitude and direction of the jittering, velocity deviation and angular deviation; and (e) Applying the compensating impulse vector to the projectile by activating a flight correction unit, the thrust developed by the flight correction unit suitable for adjusting the flight path of the projectile by a magnitude and direction

Abstract: An ultrasound therapy system utilizes a mechanical positioning assembly to locate and aim an ultrasonic transducer. The positioner provides for roll and pitch control as well as control in the lateral and longitudinal directions. The positioner uses piezo-electric vibrational motors that can effectively operate within the field of an MRI system without interfering with its operation. The motors are capable of providing a breaking force to the drive shafts while de-energized and thus aid in preventing motor slippage or backlash. Since the motors do not affect the operation of an MRI system, the ultrasonic therapy system can be made more compact. Two sets of position encoders are used to align the positioner. Course absolute encoders and fine relative encoders are both coupled to the positioning motors and allow for precise control over the position and orientation of the ultrasonic transducer.

Abstract: A system for intercepting targets having predictable flight trajectory, the system comprising a platform carrying an interceptor missile which includes a seeker unit, propulsion system steering system and destruction capability system, all communicating with a processor device. The processor device is further coupled to a data link for communicating with the platform.

Abstract: A device, particularly a missile, includes a body having an appendage, e.g., a wing, normally folded in an inoperative position and to be unfolded to an operative position when the body is accelerated in the direction of the longitudinal axis of the body. The appendage is pivotally mounted about a first pivot axis extending perpendicularly to the longitudinal axis of the body, and also about a second pivot axis extending parallel to the longitudinal axis of the body. The center of gravity of the appendage is outwardly of the first pivot axis in the folded condition of the appendage such that the acceleration of the body produces a moment pivotting the appendage about the first pivot axis.

Abstract: A clamp for joining a pair of elements having generally circular flanges, the clamp including an inner flange engaging portion arranged to provide generally axially extending forces to said flanges for retaining them against one another when substantially radial forces are applied to the inner flange, an outer circumferential strap element and at least one bolt. The clamp also includes a coupler engaging the strap element adapted to provide substantially circumferential tension thereto, whereby substantially radial forces are applied to the inner flange without urging non-circumferential bending of the strap element.