A method includes determining a rotational position of a rotating projectile as a function of an orientation of a sensor on the rotating projectile. The method also includes actuating a steering mechanism on the rotating projectile at the determined rotational position. The method also includes altering the trajectory of the rotating projectile.

A method includes determining a rotational position of a rotating projectile as a function of an orientation of a sensor on the rotating projectile. The method also includes actuating a steering mechanism on the rotating projectile at the determined rotational position. The method also includes altering the trajectory of the rotating projectile.

A projectile including an ejectable aft fin housing assembly. The aft fin housing assembly includes aft fins that increase a distance between a center of gravity and a center of pressure of the projectile, improving passive stabilization of the projectile. Once the projectile has been passively stabilized, the aft fin housing assembly is ejected, decreasing a distance between the center of gravity and the center of pressure, improving active stabilization of the projectile.

A proximity sensor for a Laser Guided Bomb (LGB) is provided. A proximity sensor for a Laser Guided Bomb (LGB) includes: an electronics package unit (EPU) configured to be connected to a front end of a warhead; and at least one sensor separate from the EPU and configured to be connected to a forward adapter that is connected to the front end of the warhead. The at least one sensor is configured to obtain data that is used to determine a height above ground of the LGB. The EPU is configured to compare the determined height above ground to a predefined value. The EPU is configured to generate a detonation signal for the warhead based on the determined height above ground being equal to or less than the predefined value.

A proximity sensor for a Laser Guided Bomb (LGB) is provided. A proximity sensor for a Laser Guided Bomb (LGB) includes: an electronics package unit (EPU) configured to be connected to a front end of a warhead; and at least one sensor separate from the EPU and configured to be connected to a forward adapter that is connected to the front end of the warhead. The at least one sensor is configured to obtain data that is used to determine a height above ground of the LGB. The EPU is configured to compare the determined height above ground to a predefined value. The EPU is configured to generate a detonation signal for the warhead based on the determined height above ground being equal to or less than the predefined value.

Techniques and architecture are disclosed for a system that includes a fuze at a leading end of a projectile body and a fuze setter configured to engage the fuze and to program the same prior to launch. The system, in one example, includes a plurality of electrical contact pads on an exterior surface of a fuze radome housing and a plurality of electrical contact pins on the fuze setter. The electrical contact pads are arranged in a rotationally symmetric pattern that enables an electrical interface to be formed with the electrical contact pins, regardless of the rotational orientation of the fuze. Commutation is performed to rotate signals to the electrical contact pins instead of requiring that the fuze be physically rotated to bring the electrical contact pads into alignment with the electrical contact pins.

Controlling an in-flight spin-rate of a spin-stabilized guided projectile is disclosed. In various embodiments, the projectile includes a despun control portion configured for despinning relative to a projectile chassis and for directional control of the projectile. In various embodiments, controlling the in-flight spin-rate includes determining a gyroscopic stability factor for the guided projectile using the in-flight spin rate and a forward velocity of the guided projectile, determining that the gyroscopic stability factor exceeds a stability threshold, and spin-braking the guided projectile, in response to determining that the gyroscopic stability factor exceeds a threshold value, by braking rotation of the despun control portion by which the gyroscopic stability factor of the guided projectile is reduced to a second gyroscopic stability factor.

Controlling an in-flight spin-rate of a spin-stabilized guided projectile is disclosed. In various embodiments, the projectile includes a despun control portion configured for despinning relative to a projectile chassis and for directional control of the projectile. In various embodiments, controlling the in-flight spin-rate includes determining a gyroscopic stability factor for the guided projectile using the in-flight spin rate and a forward velocity of the guided projectile, determining that the gyroscopic stability factor exceeds a stability threshold, and spin-braking the guided projectile, in response to determining that the gyroscopic stability factor exceeds a threshold value, by braking rotation of the despun control portion by which the gyroscopic stability factor of the guided projectile is reduced to a second gyroscopic stability factor.

A system and method to aid in guidance, navigation and control of a guided projectile including a precision guidance munition assembly is provided. The system and method obtain raw position data during flight of the guided projectile, the raw position data including a plurality of position data points from the guiding sensor for determining positions of the guided projectile, establish a window including a portion of the plurality of position data points, smooth the portion of the plurality of position data points in the window, and determine a reduced noise position estimate of the guided projectile, based, at least in part, on the smoothed portion of the plurality of position data points in the window. The system and method may determine a velocity estimate of the guided projectile and predict an impact point of the guided projectile relative to a target.

A system and method to aid in guidance, navigation and control of a guided projectile including a precision guidance munition assembly is provided. The system and method obtain raw position data during flight of the guided projectile, the raw position data including a plurality of position data points from the guiding sensor for determining positions of the guided projectile, establish a window including a portion of the plurality of position data points, smooth the portion of the plurality of position data points in the window, and determine a reduced noise position estimate of the guided projectile, based, at least in part, on the smoothed portion of the plurality of position data points in the window. The system and method may determine a velocity estimate of the guided projectile and predict an impact point of the guided projectile relative to a target.