Abstract: Higher Order Sliding Mode (HOSM) control techniques are applied to the Guidance Control (G&C) of interceptor missile in which velocity may be steered by combination of main thrust, aerodynamic lift and lateral on-off divert thrusters, and attitude may be steered by continuous or on-off actuators. Methods include the pointing of the seeker, its associated estimation processes, a guidance law that uses concurrent divert mechanisms, and an attitude autopilot. The insensitivity of the controller to matched disturbances allows the concurrent usage of the divert mechanisms without adverse effect on the accuracy. The controller also allows the de-coupling of the control of roll, pitch and yaw channels, and usage quaternions to represent body attitude and it provides control perfect robustness. While it conceivable to design separately the components of the G&C method, it is widely accepted that designing them in an integrated fashion usually produces a better result.

Abstract: A magnetic field having an alternate component in a predetermined direction is produced in a zone and electrons are injected into this zone perpendicularly to said direction. To this end a winding is connected to a source for supplying current pulses having a predetermined duration. A split tube is placed coaxially within the winding and has an inner wall which provides periodic or nearly periodic variations. The split tube is formed of material having good electrical conductivity and has a skin thickness which is considerably smaller than the tube thickness at the frequency corresponding to the reciprocal of the time-duration of the current pulses.