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: Some embodiments relate to a method of controlling a flight of a flight vehicle according to a first mode of operation and changing the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation. Other embodiments relate to a flight-control system for a flight vehicle configured to control a flight of a flight vehicle according to a first mode of operation and to control the flight of the flight vehicle according to a second mode of operation to use less energy than the first mode of operation. Other embodiments relate to a control actuation system configured to control positions of aerodynamic elements in a flight vehicle in response to commands from a guidance system according to a first mode of operation and to change the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation.

Abstract: Some embodiments relate to a method of controlling a flight of a flight vehicle according to a first mode of operation and changing the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation. Other embodiments relate to a flight-control system for a flight vehicle configured to control a flight of a flight vehicle according to a first mode of operation and to control the flight of the flight vehicle according to a second mode of operation to use less energy than the first mode of operation. Other embodiments relate to a control actuation system configured to control positions of aerodynamic elements in a flight vehicle in response to commands from a guidance system according to a first mode of operation and to change the mode of operation to a second mode of operation having a different bandwidth than the first mode of operation.