Abstract: An alignment system for sensor or other electrical device filters rate data from gyroscopes and integrates the same to determine an alignment error state that is populated into a direction cosine matrix that pre-rotates measurement from a first electrical device into an estimated coordinate frame to determine a static alignment between first and second electrical devices or sensors. The system may be part of a countermeasure system on an aircraft. A first electrical device may be an inertial navigation system (INS), and a second electrical device may be an inertial measurement unit (IMU). The attitude of the IMU is used to translate the detected threats from the countermeasure system into a common reference frame of the INS.

Abstract: The system and method of a dual mode semi active laser seeker and imaging system using pulse detection and angle determination as applied to quad detectors to properly identify a correct designator spot. The angle performance is driven by the field of view of the imaging system. The imaging system resolution provides the required angle accuracy for guidance as cued by pulse detection apertures. The imaging system eliminates the need to designate until impact thus eliminating exposure to counter fire against the designator. The elimination of designation until impact also opens up the opportunity rapid engagement of multiple targets from a single designator.

Abstract: An optical seeker assembly having an optical detector located within the wing or canards of a precision guided munition. The optical seeker provides on-wing processing that generates low bandwidth detection data that can be easily transferred to a primary CPU located within the main body or fuselage of the precision guided munition. The on-wing processing reduces or eliminates the need for optical fibers extending between an optical wedge and an optical detector to reduce the likelihood of optical fibers from impeding in the mechanical deployment of the wing and reduces losses. The reduction or elimination of optical fibers between the optical wedge and the optical detector further enables the optical detection assembly to have a higher pixel ratio or transmitting raw data between the wedge and the detector by sending sampled detection data across a low bandwidth link to a CPU in the main body.

Abstract: An alignment system for sensor or other electrical device filters rate data from gyroscopes and integrates the same to determine an alignment error state that is populated into a direction cosine matrix that pre-rotates measurement from a first electrical device into an estimated coordinate frame to determine a static alignment between first and second electrical devices or sensors. The system may be part of a countermeasure system on an aircraft. A first electrical device may be an inertial navigation system (INS), and a second electrical device may be an inertial measurement unit (IMU). The attitude of the IMU is used to translate the detected threats from the countermeasure system into a common reference frame of the INS.

Abstract: An alignment system for sensor or other electrical device filters rate data from gyroscopes and integrates the same to determine an alignment error state that is populated into a direction cosine matrix that pre-rotates measurement from a first electrical device into an estimated coordinate frame to determine a static alignment between first and second electrical devices or sensors. The system may be part of a countermeasure system on an aircraft. A first electrical device may be an inertial navigation system (INS), and a second electrical device may be an inertial measurement unit (IMU). The attitude of the IMU is used to translate the detected threats from the countermeasure system into a common reference frame of the INS.

Abstract: An optical seeker assembly having an optical detector located within the wing or canards of a precision guided munition. The optical seeker provides on-wing processing that generates low bandwidth detection data that can be easily transferred to a primary CPU located within the main body or fuselage of the precision guided munition. The on-wing processing reduces or eliminates the need for optical fibers extending between an optical wedge and an optical detector to reduce the likelihood of optical fibers from impeding in the mechanical deployment of the wing and reduces losses. The reduction or elimination of optical fibers between the optical wedge and the optical detector further enables the optical detection assembly to have a higher pixel ratio or transmitting raw data between the wedge and the detector by sending sampled detection data across a low bandwidth link to a CPU in the main body.

Abstract: A system and method for a semi-active laser seeker combining a temporal and a spatial sensor to form a seeker with a wide angle FOV and low angle error for use with spinning projectiles with spin rates of up to 300 Hz. The FOV is about 40 degrees and the angle error is less than 0.1 degrees. The seeker utilizes a CCA and fits into a small, low cost package, of about 1.5 in3 or less.

Abstract: A system for calculating airspeed and dynamic pressure comprises a system body, an internal accelerometer, located within the system body, an internal pressure sensor, located in the system body, the internal pressure sensor being not hermetically sealed within the system body and capable of measuring the static pressure of the ambient atmosphere, and a processor in reception of the internal accelerometer, and the internal pressure sensor, capable of calculating Mach number via an axial acceleration, and capable of calculating a dynamic pressure and a true airspeed via the Mach number.

Abstract: An inertial sensor system according to one embodiment having a platform with an x axis and a y axis, a rotational table that is free to rotate about the x axis, a rotational table gyroscope mounted onto the rotational table to measure p, q, and r rotation rates referenced to the rotational table and at least one platform gyroscope mounted off the rotational table, wherein the rotational table gyroscope and the platform gyroscope provide sense rotation used to process gyroscope biases that are used to correct measurements for the inertial sensing system.

Abstract: A system and method of determining a pointing vector using two GPS antennas and a single GPS receiver is disclosed. Two stationary GPS antennas, with a separation preferably less than half of a wavelength (˜100 mm) may use a single receiver to determine the pointing vector of the system. Incorporation of a three axis angular rate measurement allows pointing determination during system rotation. Incorporation of three axis gyroscope system allows pointing determination while in motion. The system provides the ability to sense multipath and jamming. Also the system can potentially eliminate the impact and certainly alert the user that the measurement may not be reliable.

Abstract: An inertial sensor system according to one embodiment having a platform with an x axis and a y axis, a rotational table that is free to rotate about the x axis, a rotational table gyroscope mounted onto the rotational table to measure p, q, and r rotation rates referenced to the rotational table and at least one platform gyroscope mounted off the rotational table, wherein the rotational table gyroscope and the platform gyroscope provide sense rotation used to process gyroscope biases that are used to correct measurements for the inertial sensing system.

Abstract: A system for calculating airspeed and dynamic pressure comprises a system body, an internal accelerometer, located within the system body, an internal pressure sensor, located in the system body, the internal pressure sensor being not hermetically sealed within the system body and capable of measuring the static pressure of the ambient atmosphere, and a processor in reception of the internal accelerometer, and the internal pressure sensor, capable of calculating Mach number via an axial acceleration, and capable of calculating a dynamic pressure and a true airspeed via the Mach number.

Abstract: Disclosed is a system for determination of attitude for a projectile in flight. The system includes at least one antenna mounted on the projectile. Each antenna is configured to receive Global Positioning System (GPS) signals. Further, the system includes a signal receiving unit communicably coupled to the each antenna to receive the GPS signals and to ascertain the earth referenced velocity vector. The system also includes a plurality of magnetometers for ascertaining a projectile referenced earth's magnetic field vector. Moreover, the system includes a processing unit. The processing unit is configured to utilize a known projectile referenced velocity vector and a stored prediction of the earth referenced earth's magnetic field vector along with the measured earth referenced velocity vector and the measured projectile referenced earth's magnetic field vector to determine the attitude of the projectile. Further disclosed is a method for determination of attitude for a projectile in flight.

Abstract: A system and method for guiding a projectile is presented. A method for guiding a projectile includes storing a gas in a chamber that is attached to the projectile. The projectile has an explosive front end and a rear guidance kit consisting of a body extension and a tail boom. The chamber is located in the body extension with the control electronics. Two or more fins that are configured to stabilize the projectile while the projectile is in flight. Pulses of gas are released out of the chamber through a nozzle at the end of the tail boom to control an angle of attack to control the lift of the projectile to guide the projectile to a target while the projectile is in flight.

Abstract: A system and method for guiding a projectile is presented. A nozzle system includes a boom assembly body that can be attached to a rear end of a projectile. A gas tank in the boom assembly contains pressurized gas. Fins are attached to the boom assembly body to guide the projectile. A valve lets a pulse of gas out of the gas tank. A nozzle expels the pulse of gas to control an angle of attack and lift of the projectile to guide the projectile to a target.

Abstract: A system and method of determining a pointing vector using two GPS antennas and a single GPS receiver is disclosed. Two stationary GPS antennas, with a separation preferably less than half of a wavelength (˜100 mm) may use a single receiver to determine the pointing vector of the system. Incorporation of a three axis angular rate measurement allows pointing determination during system rotation. Incorporation of three axis gyroscope system allows pointing determination while in motion. The system provides the ability to sense multipath and jamming. Also the system can potentially eliminate the impact and certainly alert the user that the measurement may not be reliable.

Abstract: A system is provided for semi-active laser designation, the system comprising: a guidance and control system having a plurality of wings disposed at an aerodynamically advantageous angle; a plurality of linear sensor arrays configured to measure location of a target, each the sensor array being disposed on a wing of the plurality of wings; and each the linear sensor array providing independent data to the guidance and control system as to the location of the target.

Abstract: A system is provided for the remote control of a spinning projectile, the system comprising: a polarized radiation source emitting polarized radiation wherein commands are encoded; a projectile round; a polarized radiation receiver disposed on the projectile round and configured to receive the polarized radiation; and a projectile steering mechanism, the mechanism directing movement of the projectile according to the commands communicated by means of rotation of polarization of the polarized radiation source.

Abstract: Disclosed is a system for determination of attitude for a projectile in flight. The system includes at least one antenna mounted on the projectile. Each antenna is configured to receive Global Positioning System (GPS) signals. Further, the system includes a signal receiving unit communicably coupled to the each antenna to receive the GPS signals and to ascertain the earth referenced velocity vector. The system also includes a plurality of magnetometers for ascertaining a projectile referenced earth's magnetic field vector. Moreover, the system includes a processing unit. The processing unit is configured to utilize a known projectile referenced velocity vector and a stored prediction of the earth referenced earth's magnetic field vector along with the measured earth referenced velocity vector and the measured projectile referenced earth's magnetic field vector to determine the attitude of the projectile. Further disclosed is a method for determination of attitude for a projectile in flight.

Abstract: The system includes a mobile vessel having a body axis and a steering mechanism. A three-axis gyroscope is mounted within the vessel. A three-axis magnetometer is mounted within the vessel. A programmable device communicates with the three-axis gyroscope, the three-axis magnetometer, and the steering mechanism. The three-axis gyroscope may include three single axis gyroscopes.