A guided projectile including a precision guidance munition assembly utilizes at least one maneuver envelope to optimally control movement of at least one canard to steer the guided projectile during flight. The maneuver envelopes optimize movements of the at least one canard that effectuate movement in either the range direction or the cross-range direction, or both. The maneuver envelope enables optimal timing such that maneuvering in one direction does not come at the expense of maneuver authority in the other direction.

A guided projectile including a precision guidance munition assembly utilizes at least one maneuver envelope to optimally control movement of at least one canard to steer the guided projectile during flight. The maneuver envelopes optimize movements of the at least one canard that effectuate movement in either the range direction or the cross-range direction, or both. The maneuver envelope enables optimal timing such that maneuvering in one direction does not come at the expense of maneuver authority in the other direction.

A precision guided munition (PGM) system is disclosed. The PGM system comprises a body including a nose portion. The nose portion includes an aperture. A window is attached, secured, or adhered to the body at the nose portion. One or more antenna substrates is attached, secured, or adhered to the window. A plurality of radiating elements is attached, secured, or adhered to the one or more antenna substrates. An image sensor configured to capture an image in front of the body. The image sensor is behind the aperture and is configured to focus at an infinity focus in front of the body. The one or more antenna substrates include unpopulated areas configured to let photons pass through the antenna substrates from the window to the image sensor. The photons are parallel or collimated and the captured image does not include features of the antenna substrates.

A precision guided munition (PGM) system is disclosed. The PGM system comprises a body including a nose portion. The nose portion includes an aperture. A window is attached, secured, or adhered to the body at the nose portion. One or more antenna substrates is attached, secured, or adhered to the window. A plurality of radiating elements is attached, secured, or adhered to the one or more antenna substrates. An image sensor configured to capture an image in front of the body. The image sensor is behind the aperture and is configured to focus at an infinity focus in front of the body. The one or more antenna substrates include unpopulated areas configured to let photons pass through the antenna substrates from the window to the image sensor. The photons are parallel or collimated and the captured image does not include features of the antenna substrates.

A non-uniformity correction (NUC) calibration method comprises obtaining image data for a plurality of images with an image sensor, wherein each image in the plurality of images is obtained at a different respective global pixel gain setting and global expose in the image sensor; and using the image data for non-uniformity correction calibration to compute pixel NUC values for the pixels in the image sensor. The method can further include storing the pixel NUC values and obtaining further image data corrected by the stored pixel NUC values. In embodiments, the method can include moving a platform based on the further image data. In certain embodiments, the platform can be a guided munition.

A non-uniformity correction (NUC) calibration method comprises obtaining image data for a plurality of images with an image sensor, wherein each image in the plurality of images is obtained at a different respective global pixel gain setting and global expose in the image sensor; and using the image data for non-uniformity correction calibration to compute pixel NUC values for the pixels in the image sensor. The method can further include storing the pixel NUC values and obtaining further image data corrected by the stored pixel NUC values. In embodiments, the method can include moving a platform based on the further image data. In certain embodiments, the platform can be a guided munition.

In accordance with at least one aspect of this disclosure, a thermoelectric generator (TEG) system can include a TEG conversion element configured to be in thermal communication with a leading edge surface subject to hypersonic flow and a heatsink to generate a temperature differential across the TEG conversion element mounted between the leading edge surface and heatsink, and an electrical conductor configured to connect between the TEG conversion element and a powered unit to supply electrical energy from the TEG conversion element to the powered unit.

In accordance with at least one aspect of this disclosure, a thermoelectric generator (TEG) system can include a TEG conversion element configured to be in thermal communication with a leading edge surface subject to hypersonic flow and a heatsink to generate a temperature differential across the TEG conversion element mounted between the leading edge surface and heatsink, and an electrical conductor configured to connect between the TEG conversion element and a powered unit to supply electrical energy from the TEG conversion element to the powered unit.

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.

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.