An inertial measurement system for a spinning projectile comprising: first (roll), second and third gyros with axes arranged such that they define a three dimensional coordinate system; at least a first linear accelerometer; a controller, arranged to: compute a current projectile attitude comprising a roll angle, a pitch angle and a yaw angle; compute a current velocity vector from the accelerometer; combine a magnitude of said velocity vector with an expected direction for said vector to form a pseudo-velocity vector; provide the velocity vector and the pseudo-velocity vector to a Kalman filter that outputs a roll gyro scale factor error calculated as a function of the difference between the velocity vector and the pseudo-velocity vector; and apply the roll gyro scale factor error from the Kalman filter as a correction to the output of the roll gyro.

An ordnance munition is included in an intelligent ordnance projectile delivery system and equipped with targeting and guidance systems that allow the ordnance munition to collaborate with other devices to intelligently select targets and/or to guide the ordnance munition to its selected target. The ordnance munition may be configured to generate first location information based on its determined approximate location, send the generated first location information to a wireless transceiver in proximity to the first ordnance munition, and receive location information from the wireless transceiver in response. The ordnance munition may determine its more precise location based on the received location information, and generating second location information based on the more precise location. The ordnance munition may change or adjust its flight path or trajectory based on the generated second location information.

A Vehicle Based Independent Range System (VBIRS) (10) comprised of individual stacked chambered modules that function as a single integrated system that provides a self-contained space based range capability, and is comprised of a power module (12), an artificial intelligence/autonomous engagement/flight termination system module (20), a satellite data modem module system (30) and a navigation, communications and control module system (40), all of which interface with a VBIRS test and checkout system (52) and a weather data system (116). The artificial intelligence/autonomous engagement/flight termination system module (20) is comprised of an inherent artificial intelligence capability that envelopes and interchanges data with an autonomous engagement controller (22) that contains all missile/rocket autonomous cooperative engagement, destruct decision software and range safety algorithm parameters required for optimum mission planning. VBIRS employed aboard an aircraft or between any combination of launching systems allows that aircraft to launch a missile/rocket from any location on earth, whether the missile/rocket is singularly launched by itself or as a larger group of missiles/rockets launched in a salvo arrangement, while providing collaborative real-time targeting to occur directly between missiles/rockets in conjunction with other missile/rocket launch platforms or stand-alone mission control centers.

A Vehicle Based Independent Range System (VBIRS) (10) comprised of individual stacked chambered modules that function as a single integrated system that provides a self-contained space based range capability, and is comprised of a power module (12), an artificial intelligence/autonomous engagement/flight termination system module (20), a satellite data modem module system (30) and a navigation, communications and control module system (40), all of which interface with a VBIRS test and checkout system (52) and a weather data system (116). The artificial intelligence/autonomous engagement/flight termination system module (20) is comprised of an inherent artificial intelligence capability that envelopes and interchanges data with an autonomous engagement controller (22) that contains all missile/rocket autonomous cooperative engagement, destruct decision software and range safety algorithm parameters required for optimum mission planning. VBIRS employed aboard an aircraft or between any combination of launching systems allows that aircraft to launch a missile/rocket from any location on earth, whether the missile/rocket is singularly launched by itself or as a larger group of missiles/rockets launched in a salvo arrangement, while providing collaborative real-time targeting to occur directly between missiles/rockets in conjunction with other missile/rocket launch platforms or stand-alone mission control centers.

An inertial measurement system (200) for a longitudinal projectile, comprising a first, roll gyro to be oriented substantially parallel to the longitudinal axis of the projectile; a second gyro and a third gyro with axes arranged with respect to the roll gyro such that they define a three dimensional coordinate system. The system further comprises a controller (225, 250), arranged: —to compute a current projectile attitude from the outputs of the first, second and third gyros, the computed attitude comprising a roll angle, a pitch angle and a yaw angle; —for at least two time points, to compare the computed pitch and yaw angles with expected values for the pitch and yaw angles; —for each of said at least two time points, to calculate a roll angle error based on the difference between the computed pitch and yaw angles and the expected pitch and yaw angles; —to calculate a roll angle error difference between said at least two time points; —to calculate the total roll angle subtended between said at least two time points; —to calculate a roll angle scale factor error based on said computed roll angle error difference and said total subtended roll angle and apply the calculated roll angle scale factor error to the output of the roll gyro.

An inertial measurement system (200) for a longitudinal projectile, comprising a first, roll gyro to be oriented substantially parallel to the longitudinal axis of the projectile; a second gyro and a third gyro with axes arranged with respect to the roll gyro such that they define a three dimensional coordinate system. The system further comprises a controller (225, 250), arranged: —to compute a current projectile attitude from the outputs of the first, second and third gyros, the computed attitude comprising a roll angle, a pitch angle and a yaw angle; —for at least two time points, to compare the computed pitch and yaw angles with expected values for the pitch and yaw angles; —for each of said at least two time points, to calculate a roll angle error based on the difference between the computed pitch and yaw angles and the expected pitch and yaw angles; —to calculate a roll angle error difference between said at least two time points; —to calculate the total roll angle subtended between said at least two time points; —to calculate a roll angle scale factor error based on said computed roll angle error difference and said total subtended roll angle and apply the calculated roll angle scale factor error to the output of the roll gyro.

A method for aligning a missile with a target in a laser beam riding missile guidance system, the system including a laser transmitter for generating and projecting a laser information field towards the target and an optical sight for aiming the laser beam towards the target, the method comprising: determining a point in the laser information field with which the missile is currently aligned; determining a distance of the target from the missile; determining an angular displacement between the missile's current direction of travel and the direction in which the target lies from the missile; determining, based on said distance and angular displacement, a new point in the laser information field with which the missile should be aligned to reach the target; and controlling missile guidance systems on board the missile to bring the missile into alignment with the new point in the laser information field.

An automated weapons system is comprised of a human transported weapon having munitions for firing and a computational subsystem, responsive to a targeting subsystem for determining where the chosen target is located, positioning means, adjusting the aim when firing the munitions responsive to the computational subsystem; and, a firing subsystem. An external drone subsystem comprises a drone with a sensing subsystem that communicates to the targeting subsystem, the external drone subsystem located remotely to the human transported weapon subsystem and provides communications between the external drone subsystem and the human transported weapon subsystem. The targeting subsystem selects a chosen target from available targets. The computational subsystem is responsive to the targeting subsystem for determining where the chosen target is located, and then determines where to aim so that the munitions will strike the chosen target. Positioning means, adjusts the aim when firing the munitions responsive to the computational subsystem. A firing subsystem fires the munitions at the chosen target responsive to the positioning means.

An automated weapons system is comprised of a human transported weapon having munitions for firing and a computational subsystem, responsive to a targeting subsystem for determining where the chosen target is located, positioning means, adjusting the aim when firing the munitions responsive to the computational subsystem; and, a firing subsystem. An external drone subsystem comprises a drone with a sensing subsystem that communicates to the targeting subsystem, the external drone subsystem located remotely to the human transported weapon subsystem and provides communications between the external drone subsystem and the human transported weapon subsystem. The targeting subsystem selects a chosen target from available targets. The computational subsystem is responsive to the targeting subsystem for determining where the chosen target is located, and then determines where to aim so that the munitions will strike the chosen target. Positioning means, adjusts the aim when firing the munitions responsive to the computational subsystem. A firing subsystem fires the munitions at the chosen target responsive to the positioning means.

The system and method of projectile flight management using a combination of radio frequency orthogonal interferometry for the long range navigation and guidance of one or more projectiles and a short range navigation and guidance system to provide for more accurate targeting, especially in GPS-denied and GPS-limited environments.