Abstract: A launcher for launching a projectile includes a launch piston for engaging and driving the projectile from the launcher and a launch brake that constrains the piston to enable separation of the piston from the projectile. The launch brake is configured to have minimal to no effect on projectile exit velocity and exit trajectory from the launcher. The launch brake is also configured to reduce the velocity of the launch piston via coupling of the masses of the launch piston and the launch brake. The coupling allows, separation of the projectile from the launch piston and reduces or prevents a negative effect on stabilization of the projectile upon exit from the launcher.

Abstract: A launcher for launching a projectile includes a launch piston for engaging and driving the projectile from the launcher and a launch brake that constrains the piston to enable separation of the piston from the projectile. The launch brake is configured to have minimal to no effect on projectile exit velocity and exit trajectory from the launcher. The launch brake is also configured to reduce the velocity of the launch piston via coupling of the masses of the launch piston and the launch brake. The coupling allows, separation of the projectile from the launch piston and reduces or prevents a negative effect on stabilization of the projectile upon exit from the launcher.

Abstract: A control actuation system for an air-breathing rocket motor propelled guided missile positions the drive motors and input gears in an inlet fairing extending aft of the air inlet towards the tail of the missile. The output gears are positioned coincident with and mechanically coupled to their respective tail fins spaced around the circumference of the missile. At least one of the tail fins is offset in a circumferential direction of the missile from its corresponding input gear and the inlet fairing. At least one ring gear is positioned around the exhaust tube to rotate in the circumferential direction of the missile. The ring gear comprises input and output teeth that engage the input and output gears, respectively, to actuate the tail fin.

Abstract: A control actuation system for an air-breathing rocket motor propelled guided missile positions the drive motors and input gears in an inlet fairing extending aft of the air inlet towards the tail of the missile. The output gears are positioned coincident with and mechanically coupled to their respective tail fins spaced around the circumference of the missile. At least one of the tail fins is offset in a circumferential direction of the missile from its corresponding input gear and the inlet fairing. At least one ring gear is positioned around the exhaust tube to rotate in the circumferential direction of the missile. The ring gear comprises input and output teeth that engage the input and output gears, respectively, to actuate the tail fin.

Abstract: The disclosed system, device and method for deploying a sub-module from a carrier vehicle generally includes: a sub-module projectile (100) housed within a carrier vehicle; a rolling diaphragm (115) sealed between a first pressure chamber volume (145) and a second sub-module containment volume (e.g., substantially formed on the opposing side of rolling diaphragm 115 relative to pressure chamber 145); and a release mechanism (500), wherein the sub-module projectile (100) is secured until releasable deployment from the carrier vehicle. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve ejection, deployment and/or dispersal of a variety of sub-modules from a variety of carrier modules. Exemplary embodiments of the present invention generally provide for the ejection and dispersal of kinetic energy rod warheads from a kill-vehicle.

Abstract: The disclosed system, device and method for deploying a sub-module from a carrier vehicle generally includes: a sub-module projectile (100) housed within a carrier vehicle; a rolling diaphragm (115) sealed between a first pressure chamber volume (145) and a second sub-module containment volume (e.g., substantially formed on the opposing side of rolling diaphragm 115 relative to pressure chamber 145); and a release mechanism (500), wherein the sub-module projectile (100) is secured until releasable deployment from the carrier vehicle. Disclosed features and specifications may be variously controlled, adapted or otherwise optionally modified to improve ejection, deployment and/or dispersal of a variety of sub-modules from a variety of carrier modules. Exemplary embodiments of the present invention generally provide for the ejection and dispersal of kinetic energy rod warheads from a kill-vehicle.

Abstract: The disclosed system and method for improving aerodynamic stability of aeronautic vehicles generally includes an ejectable grid fin adapted for releasable engagement with aeronautic vehicles. The grid fin is generally configured to optimize the flight performance characteristics of the aeronautic vehicle taken in engaged combination with the grid fin as compared with the flight performance of the aeronautic vehicle taken alone. Disclosed features and specifications may be controlled, adapted or otherwise optionally modified to improve the aerodynamic stability and/or control of a variety of deployed aeronautic vehicles. Exemplary embodiments of the present invention generally provide ejectable grid fins that may be used in conjunction with missiles mounted on an eject rail of an aircraft.