A Projectile Continuous Power Module (PCMP) is configured to take incoming or oncoming airflow of an inflight projectile and direct the airflow to a turbine for converting the airflow into electrical power. The PCMP is mounted within or otherwise coupled to an airframe of the projectile. The PCMP is coupled to the projectile in a manner such that an air inlet of the projectile is positioned to capture incoming or oncoming boundary layer airflow as the projectile travels.

A Projectile Continuous Power Module (PCMP) is configured to take incoming or oncoming airflow of an inflight projectile and direct the airflow to a turbine for converting the airflow into electrical power. The PCMP is mounted within or otherwise coupled to an airframe of the projectile. The PCMP is coupled to the projectile in a manner such that an air inlet of the projectile is positioned to capture incoming or oncoming boundary layer airflow as the projectile travels.

Inertial measurement units (IMUs) and methods with adaptations to eliminate or minimize sensor error, offset, or bias shift are presented. More particularly, the IMUs and methods for gun-fired projectiles herein are particularly adapted to accurately measure forces and to prevent or minimize the error, offset, or bias shift associated with events exhibiting high g shock, and/or high levels of vibration, and/or rotation. Even more particularly, the IMUs and methods herein utilize novel IMU packaging adapted to prevent or minimize sensor error, offset, or bias shift, and recalibration adaptations and methods adapted to correct or reset the error, offset, or bias shift from such an event. The IMUs are adapted to provide accurate measurements prior to, during and after such event, and to provide continuous accurate measurements during flight of gun-fired projectiles.

A closed, self-contained ballistic apogee detection module for use in a projectile, such as a rocket, mortar round, or artillery round, fuses data from multiple built-in sensors, such as an accelerometer, a magnetometer, and a gyroscope, and processes the data using a microprocessor through a custom quaternion extended Kalman filter to provide accurate state and orientation information about the projectile so as to accurately predict apogee. The module outputs a signal indicating apogee detection or prediction which they projectile uses to initiate fuze arming, targeting control, airbody transformation, maneuvering, flow effector deployment or activation, payload exposure or deployment, and/or other mission activity. Because the system and method of the invention does not rely on external environmental data to detect apogee, it need not use a pressure sensor and can be completely sealed in and closed without requiring access to air from outside the projectile for barometric readings.

Presented herein are systems and methods using inertial measurement units (IMUs) for providing location and guidance, and more particularly for providing location and guidance in environments where global position systems (GPS) are unavailable or unreliable (GPS denied and/or degraded environments), and for such location and guidance being provided to projectiles, munitions, or rounds that are released, fired, or deployed from vehicles or weapons systems. More particularly, this disclosure relates to the use of a series of low-accuracy or low-resolution IMUs, in combination, to provide high-accuracy or high-resolution location and guidance results. This further relates to an electronics-control system for handing off control of the measurement and guidance of a body in flight between groups or subgroups of IMUs to alternate between high dynamic range/lower resolution and lower dynamic range/higher resolution measurement and guidance as the environment dictates.