Abstract: A guidance system for a missile or other vehicle utilizing a gyro stabilized seeker which is arranged in such a manner with respect to the missile as not to be servo controlled, but rather to follow the missile air-frame by means of passive coupling between seeker and airframe, as the airframe is steered to turn in response to seeker error signals. As a result of this arrangement the missile velocity vector is steered to point toward fixed targets or to lead moving targets. A further result of this arrangement is that the servo loop used to point the seeker toward the target in the conventional arrangement is not required and accordingly my missile guidance arrangement can achieve greater accuracy with less complexity than in the prior art.