Abstract: A laser alignment system for determining received pulse shape characteristics is provided. An exemplary laser alignment system may include a multi-channel optical detector including a plurality of light sensitive regions, each light sensitive region being associated with a respective one of a plurality of channels of the multi-channel optical detector and being configured to detect energy of an incident laser pulse. The system may include a signal processing unit configured to determine a plurality of data points associated with a detected laser pulse and determine whether the plurality of data points correspond to an expected laser pulse response of a designator laser. The signal processing unit may then perform other post-processing operations and in some embodiments may output an alignment command based at least in part on the plurality of data points associated with the laser pulse when the detected laser pulse corresponds to the expected laser pulse response.

Abstract: An apparatus comprising, inter alia, gyroscope feedback circuitry which aw scanning the rotor magnet of a gyroscope disposed in an associated guided missile system so as to increase the seeker field thereof is disclosed. A signal from the cage coil of the gyroscope having an amplitude approximating a sine function of the angular position of the spin axis of the rotor magnet portion of the gyroscope with respect to the body axis of the associated guided missile is used to generate a constant amplitude drive signal for driving the precession coil of the gyroscope. Scanning, so as to drive the rotor magnet in a predetermined scan pattern is accomplished by phase shifting the signal from the cage coil as a function of its amplitude and then driving the precession coil with the aforementioned constant amplitude drive signal which is phased-locked to the phase shifted or processed cage coil signal.

Abstract: A circuit for applying rate feedback to the pitch and yaw canard commands a guided projectile or missile to stabilize the airframe. The circuit demodulates and differentiates the signal from the gyro cage coil to obtain a signal representative of the airframe movement at its natural frequency. Phase detectors provide a phase reference by comparing the cage signal carrier with the output of hall effect elements in the speed sensing circuitry. The rate amplitude from the differentiator is then multiplied by the phase references to resolve the rate into pitch and yaw command components. Summation circuits then scale and subtract the rate commands from the guidance commands to provide negative rate feedback.

Abstract: An electronic phase shifter for shifting the phase of a sine wave at an input terminal, as measured at an output terminal, without affecting the magnitude thereof and having the ability to operate over a wide range of input voltages is disclosed. The electronic phase shifter comprises, inter alia, an operational amplifier and a unique variable output resistance device. A control signal, in the form of a current, for controlling the phase shift of the sine wave is applied to the input of the variable output resistance device. Buffering of the electronic phase shifter from preceding stages is controlled by matched resistors operatively connected between its output and input terminals and the inverting input terminal of the operational amplifier. The operating frequency range of the electronic phase shifter, and, accordingly, the phase shift range, is controlled by a capacitor connected from its input terminal to the non-inverting input terminal of the operational amplifier.

Abstract: A gain controllable amplifier wherein a plurality of signal paths are proed with each of the signal paths having predetermined different gain characteristics. The gain of the total amplifier is selected by application of power supply voltages to amplying stages of the different signal paths with the combination of the level of the voltages determining which signal path will be operational and the total gain of the amplifier.