Described are spherical projectiles such as used in birdshot, buckshot, or single ball spherical projectiles, including slugs, muzzle loading projectiles, or any close-to-bore diameter projectile, that is auto-segmenting or self-segmenting upon impact with a target. The projectile or shot disclosed herein retains its shape and structure during flight until impact with soft tissue, whereupon its individual sections separate or segment in a controllable manner, each portion of the projectile imparting or depositing a high amount energy to the tissue and target. The auto-segmenting spherical projectiles can be frangible or non-frangible. This disclosure also provides cartridges such as shotshells that are loaded with the projectiles described herein.

Asteroid redirection and soft-landing systems are provided that use cosmic ray and muon-catalyzed micro-fusion. These systems include a micro-fusion propulsion system providing thrust for redirecting a small asteroid, as well as providing a particle cushion at a landing site for a soft-landing. The systems deploy deuterium-containing fuel material as a localized cloud interacting with incoming ambient cosmic rays to generate energetic fusion products. Dust or other particulate matter in the fuel material converts some cosmic rays into muons that also catalyze fusion. The fusion products provide thrusting upon the asteroid. The fusion products also aid deceleration of incoming asteroids to be mined for a soft landing upon a lunar or planetary surface.

A pod assembly which includes a pod and an inertial measurement unit positioned within the pod. The pod assembly further includes deceleration hardware associated with the pod. A method for using a pod assembly, includes a step of securing the pod assembly, which includes a pod and an inertial measurement unit contained within the pod, to an aircraft and a step of operating the aircraft with the inertial measurement unit operating sensing movement and alignment of the pod and storing data corresponding to the sensed movement and alignment of the pod on a data collection assembly connected to the inertial measurement unit. The method further includes a step of releasing the pod assembly from the aircraft and a step of utilizing deceleration hardware associated with the pod to reduce rate of descent of the pod assembly released from the aircraft.

A pod assembly which includes a pod and an inertial measurement unit positioned within the pod. The pod assembly further includes deceleration hardware associated with the pod. A method for using a pod assembly, includes a step of securing the pod assembly, which includes a pod and an inertial measurement unit contained within the pod, to an aircraft and a step of operating the aircraft with the inertial measurement unit operating sensing movement and alignment of the pod and storing data corresponding to the sensed movement and alignment of the pod on a data collection assembly connected to the inertial measurement unit. The method further includes a step of releasing the pod assembly from the aircraft and a step of utilizing deceleration hardware associated with the pod to reduce rate of descent of the pod assembly released from the aircraft.

A penetration device including a casing, a propellant positioned in the casing, and a flyer plate. The flyer plate is coupled to the casing and adjacent to the propellant. The flyer plate includes a center portion having a substantially constant first thickness and includes a peripheral portion around the center portion and defining an edge. The peripheral portion tapers from the first thickness to a second thickness at the edge, where the second thickness is less than the first thickness.

A penetration device including a casing, a propellant positioned in the casing, and a flyer plate. The flyer plate is coupled to the casing and adjacent to the propellant. The flyer plate includes a center portion having a substantially constant first thickness and includes a peripheral portion around the center portion and defining an edge. The peripheral portion tapers from the first thickness to a second thickness at the edge, where the second thickness is less than the first thickness.

A penetration device including a casing, a propellant positioned in the casing, and a flyer plate. The flyer plate is coupled to the casing and adjacent to the propellant. The flyer plate includes a center portion having a substantially constant first thickness and includes a peripheral portion around the center portion and defining an edge. The peripheral portion includes one or more recesses in a first surface of the peripheral portion.

A non-lethal projectile comprises a rear portion in the form of a cylinder (2) coupled to at least two symmetrical petal-like impact elements (1) which are capable of opening upon leaving a bore and are designed to form, in a closed configuration, a cylinder having an outside diameter equal to the diameter of the cylindrical rear portion and also having an axial cylindrical opening which transitions into an axial opening in the cylindrical rear portion of the projectile. The petal-like elements have an asymmetrical cross section and an inner conical groove, the base of which is disposed at the rear portion-end of the projectile, wherein, in the front portion, each petal-like element has a unidirectional relief.

A non-lethal projectile comprises a rear portion in the form of a cylinder (2) coupled to at least two symmetrical petal-like impact elements (1) which are capable of opening upon leaving a bore and are designed to form, in a closed configuration, a cylinder having an outside diameter equal to the diameter of the cylindrical rear portion and also having an axial cylindrical opening which transitions into an axial opening in the cylindrical rear portion of the projectile. The petal-like elements have an asymmetrical cross section and an inner conical groove, the base of which is disposed at the rear portion-end of the projectile, wherein, in the front portion, each petal-like element has a unidirectional relief.

A system for bistatic radar target detection employs an unmanned aerial vehicle (UAV) having a ramjet providing supersonic cruise of the UAV. Deployable antenna arms support a passive radar receiver for bistatic reception of reflected radar pulses. The UAV operates with a UAV flight profile in airspace beyond a radar range limit. The deployable antenna arms have a first retracted position for supersonic cruise and are adapted for deployment to a second extended position acting as an airbrake and providing boresight alignment of the radar receiver. A mothership aircraft has a radar transmitter for transmitting radar pulses and operates with an aircraft flight profile outside the radar range limit. A communications data link operably interconnects the UAV and the tactical mothership aircraft, transmitting data produced by the bistatic reception of reflected radar pulses in the UAV radar antenna to the mothership aircraft.