Accessories may be mounted using a quick-detachable multi-purpose accessory mounting platform. The platform may include one or more clamps to receive an object, such as a firearm. The platform also may include at least one recessed mounting pad, at least one rear shelf, and other surfaces to provide different mounting points for accessories.

Accessories may be mounted using a quick-detachable multi-purpose accessory mounting platform. The platform may include one or more clamps to receive an object, such as a firearm. The platform also may include at least one recessed mounting pad, at least one rear shelf, and other surfaces to provide different mounting points for accessories.

A ballistic descent vehicle comprises an airframe, one or more control surfaces for controlling a descent of the vehicle, a controller, and a sensor suite to estimate both relative position, velocity, and flight path angle. Such a controller guides the vehicle, via the control surfaces, based on the estimated vehicle states, and a preprogrammed equivalent airspeed versus flight path angle two dimensional surface. During flight, the controller periodically consults the pre-computed equivalent airspeed versus flight path angle surface to obtain a desired flight path angle such that the vehicle asymptotically approaches a desired terminal approach angle while successfully navigating to the target. The use of this preprogrammed surface allows for the control of such vehicles with significantly lower computational resources, smaller control surfaces, and/or without relative airflow sensors onboard.

A ballistic descent vehicle comprises an airframe, one or more control surfaces for controlling a descent of the vehicle, a controller, and a sensor suite to estimate both relative position, velocity, and flight path angle. Such a controller guides the vehicle, via the control surfaces, based on the estimated vehicle states, and a preprogrammed equivalent airspeed versus flight path angle two dimensional surface. During flight, the controller periodically consults the pre-computed equivalent airspeed versus flight path angle surface to obtain a desired flight path angle such that the vehicle asymptotically approaches a desired terminal approach angle while successfully navigating to the target. The use of this preprogrammed surface allows for the control of such vehicles with significantly lower computational resources, smaller control surfaces, and/or without relative airflow sensors onboard.

An archery broadhead air flow interrupter or an attachment for a broadhead configured to fit over the point of the broadhead and prior to the primary cutting blades; the air flow interrupter creating a turbulent low pressure zone around the cutting blades, preventing broadhead planing, and improving the accuracy of the broadhead archery point.

A system to deploy a parachute is disclosed. In various embodiments, a plurality of rockets are attached to a perimeter of the parachute. Each of the rockets is configured to fly initially in a first direction substantially in a direction of deployment of the parachute and to fly subsequently along a trajectory that includes a component that is substantially perpendicular to the direction of deployment and extends radially from a center of the parachute.

A system to deploy a parachute is disclosed. In various embodiments, a plurality of rockets are attached to a perimeter of the parachute. Each of the rockets is configured to fly initially in a first direction substantially in a direction of deployment of the parachute and to fly subsequently along a trajectory that includes a component that is substantially perpendicular to the direction of deployment and extends radially from a center of the parachute.

A projectile (10) for firing from a barrel (12) of a firearm has an elongated tubular body (14) with a leading end (16), a trailing end (18) and a passage (100) extending through the body (14) and opening onto the leading end (16). An insert (102) is disposed in the passage (100). A cavity (20) is formed in the body (14) between the insert (102) and the trailing end (18) for holding a volume of propellant. A seal arrangement (22) is formed on the body (14) and located between and in-board of the leading end (16) and the trailing end (18). The seal arrangement (22) extends circumferentially about body to form a substantial seal against an inner circumferential surface of the barrel (12). A driving band (28) is supported on the body (14) between the seal arrangement (22) and the trailing end (18) and arranged to maintain substantial coaxial alignment of the body (14) of the projectile and the barrel (12) of the firearm while the projectile travels along the barrel (12). The driving band (28) has one or more flow paths (38) that enable fluid communication between opposite axial ends of the driving band (28).

A projectile (10) for firing from a barrel (12) of a firearm has an elongated tubular body (14) with a leading end (16), a trailing end (18) and a passage (100) extending through the body (14) and opening onto the leading end (16). An insert (102) is disposed in the passage (100). A cavity (20) is formed in the body (14) between the insert (102) and the trailing end (18) for holding a volume of propellant. A seal arrangement (22) is formed on the body (14) and located between and in-board of the leading end (16) and the trailing end (18). The seal arrangement (22) extends circumferentially about body to form a substantial seal against an inner circumferential surface of the barrel (12). A driving band (28) is supported on the body (14) between the seal arrangement (22) and the trailing end (18) and arranged to maintain substantial coaxial alignment of the body (14) of the projectile and the barrel (12) of the firearm while the projectile travels along the barrel (12). The driving band (28) has one or more flow paths (38) that enable fluid communication between opposite axial ends of the driving band (28).

A method for controlling a flying projectile which rotates during flight, comprising: determining an angle of rotation of an inertial mass spinning about an axis during flight; and controlling at least one actuator for altering at least a portion of an aerodynamic structure, selectively in dependence on the determined angle of rotation and a control input, to control aerodynamic forces during flight. An aerodynamic surface may rotate and interact with surrounding air during flight, to produce aerodynamic forces. A sensor determines an angular rotation of the spin during flight. A control system, responsive to the sensor, produces a control signal in dependence on the determined angular rotation. An actuator selectively alters an aerodynamic characteristic of the aerodynamic surface in response to the control signal.