초록 ▼

In a seeker head for target tracking missiles or projectiles, an imaging optical system with an optical axis is mounted on a rotor. The rotor is mounted for universal swivelling motion in the missile. It rotates about its geometrical axis. Thereby, the rotor is stabilized in inertial space as a gyro

In a seeker head for target tracking missiles or projectiles, an imaging optical system with an optical axis is mounted on a rotor. The rotor is mounted for universal swivelling motion in the missile. It rotates about its geometrical axis. Thereby, the rotor is stabilized in inertial space as a gyro. The optical system images an object scene on a circular array of detector elements. The rotor can be caused to make controlled precession and nutation movements by control loops with attitude pick-offs and a torquer coil such that the optical axis of the optical system makes a cyclic spiral movement over an extended field of view, in a seeking and target acquisition mode, is then precessed towards a detected target, the nutation amplitude, in a pre-phase mode, being made equal to the target deviation, and, eventually, in a target-tracking mode, makes a circling movement within a limited area in the field of view containing the target. In the target-tracking mode, the target image circles on the circular array of detector elements.

대표청구항 ▼

[ We claim:] [1.] A seeker head for a target tracking missile or projectile, comprising:an imaging optical system with an optical axis;a rotor defining a geometrical axis, said imaging optical system being mounted on said rotor;mounting means for mounting said rotor for universal swivelling movement

[ We claim:] [1.] A seeker head for a target tracking missile or projectile, comprising:an imaging optical system with an optical axis;a rotor defining a geometrical axis, said imaging optical system being mounted on said rotor;mounting means for mounting said rotor for universal swivelling movement in said missile or projectile, said rotor rotating about said geometrical axis such that said rotor is stabilized in inertial space and is de-coupled from the angular movements of the missile;detector means in the form of a circular array of detector elements for providing detector signals; said imaging optical system being arranged to image an object scene on said detector means;attitude pick-off means for detecting the angular orientation of said rotor and for providing signals indicative of said orientation;torque generating means for exerting torques on said rotor;control loop means including said torque generating means, wherein signals from said attitude pick-off means and detector signals are applied for causing said optical axis of said optical systemto carry out a cyclic, spiral movement over an extended field of view during a seeking and catching mode,to be precessed towards a target recognized within said field of view, if a target image is generated on said detector means, and,after the target has been caught, to carry out a circling movement within a limited area of said field of view containing said target, in a target-tracking mode,said control loop means being controlled, in said target tracking mode, to cause said target image to circle on said circular array of detector elements;and change-over means for changing said torque generating means over to a pre-phase mode, when a target has been detected in said seeking and catching mode, said rotor, in said pre-phase mode, being caused to nutate with a nutation amplitude which substantially is equal to the deviation of said target from said optical axis, said nutation amplitude continuously decaying when said optical axis is precessed towards said target, the target image sweeping, during each cycle of said nutation, across said circular array of detector elements, andfor changing said torque generating means over to said target-tracking mode, when a minimum value of said nutation amplitude substantially equal to the diameter of the circular array of detector elements has been reached.