Abstract: An apparatus for deploying stowed control surfaces of a projectile is disclosed. The apparatus for deploying stowed control surfaces of a projectile includes a first and second hot gas generators, a first and second gas chambers, a piston wedge, a piston and a barrel. Initially, the first hot gas generator discharges a surge of hot gas into the first gas chamber. In response to the surge of hot gas being discharged into the first gas generator, the piston wedge displaces at least one of the control surfaces to break an environmental seal covering the projectile. After a predetermined amount of time has lapsed, the second hot gas generator discharges a surge of hot gas into the second gas chamber. The surge of hot gas displaces the piston and barrel for deploying the control surfaces completely.

Abstract: A method for controlling autopilot roll capture of a rocket comprising adapting the start time and the rate of roll capture such that regardless of the initial rocket spin rate, the roll capture process is completed at a predetermined time.

Abstract: An apparatus for deploying stowed control surfaces of a projectile is disclosed. The apparatus for deploying stowed control surfaces of a projectile includes a first and second hot gas generators, a first and second gas chambers, a piston wedge, a piston and a barrel. Initially, the first hot gas generator discharges a surge of hot gas into the first gas chamber. In response to the surge of hot gas being discharged into the first gas generator, the piston wedge displaces at least one of the control surfaces to break an environmental seal covering the projectile. After a predetermined amount of time has lapsed, the second hot gas generator discharges a surge of hot gas into the second gas chamber. The surge of hot gas displaces the piston and barrel for deploying the control surfaces completely.

Abstract: An accurate and rapid method for characterizing the performance of an APD and setting its operating voltage Vop to an optimal value uses an on-board LED or other pulsed light source to measure APD responses at different operating voltages Vop. An estimated breakdown voltage Vb is determined by comparing the measured responses, and the Vop is adjusted to a new value at a fixed offset from the estimated Vb. The fixed offset is selected according to ambient light conditions, including the presence or absence of light background noise, and whether the sun is partially or fully in the field of view. The method is iterated until convergence, or until a maximum number of iterations is reached. In embodiments, a plurality of APD's having a common Vop can be adjusted, and the Vop is never set below a minimum value VopBW necessary to meet timing requirements for a missile guidance system.

Abstract: An apparatus and method improves the fault tolerance of a rocket or missile guidance system which includes a resonant sensor. When improper initialization is detected, the resonant sensor is reinitialized, repeatedly if necessary, until normal operation is achieved. Improper initialization is detected by comparing data from the guidance system with pre-specified physical limits to roll, pitch, yaw, and/or other features of the flight scenario. Embodiments can also detect a fault condition due to an error signal from a “Built-in-Test” (BIT) module. The initialization sequence initiated by the invention can be identical to the power-on sequence, or it can be a separate, reinitiating sequence. Subsequent resets are initiated as needed, for example until the burn of the rocket fuel and the associated vibrations have ceased and the resonant sensor has been successfully initialized.

Abstract: An apparatus and method improves the fault tolerance of a rocket or missile guidance system which includes a resonant sensor. When improper initialization is detected, the resonant sensor is reinitialized, repeatedly if necessary, until normal operation is achieved. Improper initialization is detected by comparing data from the guidance system with pre-specified physical limits to roll, pitch, yaw, and/or other features of the flight scenario. Embodiments can also detect a fault condition due to an error signal from a “Built-in-Test” (BIT) module. The initialization sequence initiated by the invention can be identical to the power-on sequence, or it can be a separate, reinitiating sequence. Subsequent resets are initiated as needed, for example until the burn of the rocket fuel and the associated vibrations have ceased and the resonant sensor has been successfully initialized.

Abstract: A method for controlling autopilot roll capture of a rocket comprising adapting the start time and the rate of roll capture such that regardless of the initial rocket spin rate, the roll capture process is completed at a predetermined time.

Abstract: An accurate and rapid method for characterizing the performance of an APD and setting its operating voltage Vop to an optimal value uses an on-board LED or other pulsed light source to measure APD responses at different operating voltages Vop. An estimated breakdown voltage Vb is determined by comparing the measured responses, and the Vop is adjusted to a new value at a fixed offset from the estimated Vb. The fixed offset is selected according to ambient light conditions, including the presence or absence of light background noise, and whether the sun is partially or fully in the field of view. The method is iterated until convergence, or until a maximum number of iterations is reached. In embodiments, a plurality of APD's having a common Vop can be adjusted, and the Vop is never set below a minimum value VopBW necessary to meet timing requirements for a missile guidance system.

Abstract: The invention provides a method and apparatus for correcting for gain changes in detectors in a guided vehicle. In one version of the invention, an on board light source is used to generate a reference set of detector gains, which are stored in computer memory. The on board light source is then pulsed at subsequent times and the signals generated by the detectors are compared to the reference set of detector gains to determine whether any gains have changed.

Abstract: The invention provides a method and apparatus for correcting for gain changes in detectors in a guided vehicle. In one version of the invention, an on board light source is used to generate a reference set of detector gains, which are stored in computer memory. The on board light source is then pulsed at subsequent times and the signals generated by the detectors are compared to the reference set of detector gains to determine whether any gains have changed.

Abstract: Methods and apparatuses for determining angular information from a target. A plurality of sensors on an image plane are used to obtain measured amplitude data. An azimuth and elevation may be estimated using this measured amplitude data. A residual error between the measured amplitude data and calibrated amplitude data may then be determined. The angular information corresponding to the azimuth and elevation at which the residual error is minimized may then be outputted as representing or corresponding to the angular information of the target.

Abstract: Methods and apparatuses for determining angular information from a target. A plurality of sensors on an image plane are used to obtain measured amplitude data. An azimuth and elevation may be estimated using this measured amplitude data. A residual error between the measured amplitude data and calibrated amplitude data may then be determined. The angular information corresponding to the azimuth and elevation at which the residual error is minimized may then be outputted as representing or corresponding to the angular information of the target.

Abstract: A directional control system for ballistic projectiles, including a projectile capable of being fired from a gun, a tracking device within the projectile capable of sensing and identifying a preferred target direction, a moveable mass located within the projectile, an electromagnetic mass-shifting device within the projectile capable of reversibly moving the mass from a first position to a second position whereby the flight path of the projectile is controlled. The directional control system may be used with a projectile which has no externally protruding bodies. The system includes at least one microprocessor programmed to obtain input from the tracking device and to perform calculations to determine movements of the mass. The moveable mass is positioned to shift the momentum vector perpendicular to the central longitudinal spin axis of the projectile when in motion.