Abstract: A spinning, rolling, or roll-stabilized vehicle, such as a projectile, includes a fuselage that rotates about its longitudinal axis (spins) during flight. A collar is positionable relative to the fuselage to steer the projectile, with the collar having ailerons to provide a roll force to position the collar. The collar also has elevators to provide lateral force to steer the projectile. The positioning of the collar may be accomplished by moderating the roll force of the ailerons to hold the position of the collar substantially constant with regard to a longitudinal axis of the projectile. The ailerons passively change angle of attack with changes in the dynamic pressure of the projectile. At low speeds the ailerons have a relatively large angle of attack, and at high speeds, the ailerons resiliently reduce their angles of attack, avoiding large rolling forces on the collar.

Abstract: An interceptor is provided with an integrated propulsion and attitude control system (ACS) in which propellant burn forms a common pressure vessel for high-pressure gas. An aft port in the rocket motor directs gas through one or more main nozzles that expel high-velocity gas in a generally axial direction to propel the interceptor. A forward port directs gas through one or more attitude control nozzles that expel high-velocity gas in a generally radial direction to control the attitude of the interceptor. The main nozzle(s) and stabilization fins are fixed, there is no servo control to the main nozzles or fins to affect attitude control. The use of a common pressure vessel enables an integrated propulsion and ACS that can be compact, lightweight and inexpensive.

Abstract: A spinning, rolling, or roll-stabilized vehicle, such as a projectile, includes a fuselage that rotates about its longitudinal axis (spins) during flight. A collar is positionable relative to the fuselage to steer the projectile, with the collar having ailerons to provide a roll force to position the collar. The collar also has elevators to provide lateral force to steer the projectile. The positioning of the collar may be accomplished by moderating the roll force of the ailerons to hold the position of the collar substantially constant with regard to a longitudinal axis of the projectile. The ailerons passively change angle of attack with changes in the dynamic pressure of the projectile. At low speeds the ailerons have a relatively large angle of attack, and at high speeds, the ailerons resiliently reduce their angles of attack, avoiding large rolling forces on the collar.

Abstract: An interceptor is provided with an integrated propulsion and attitude control system (ACS) in which propellant burn forms a common pressure vessel for high-pressure gas. An aft port in the rocket motor directs gas through one or more main nozzles that expel high-velocity gas in a generally axial direction to propel the interceptor. A forward port directs gas through one or more attitude control nozzles that expel high-velocity gas in a generally radial direction to control the attitude of the interceptor. The main nozzle(s) and stabilization fins are fixed, there is no servo control to the main nozzles or fins to affect attitude control. The use of a common pressure vessel enables an integrated propulsion and ACS that can be compact, lightweight and inexpensive.

Abstract: A multi-stage hyper-velocity kinetic energy missile (HVKEM) uses a ‘missile in a missile’ architecture in which the HVKEM includes a 1st stage flight missile and a 2nd stage kill missile that includes a KE-rod penetrator. The flight missile cruises at a relatively low velocity (less than Mach 1.5, typically less than Mach 1) to conserve propellant (weight) and to allow for effective guidance and maneuvering until the missile is in close proximity to the target. When the missile is within the lethal range of the KE-rod penetrator, the kill missile separates and boosts to a much higher velocity (greater than Mach 3, typically greater than Mach 5) and flies unguided to impact the target in less than a second. Waiting to boost the KE-rod until “the last second” reduces the total propellant (weight) needed to deliver the KE-rod on target and simplifies the guidance.

Abstract: A system, device and method provide an exhaust assembly adapted for use with a mass ejection drive system to produce rotational torque about the principle axis of the drive system. Representative features generally include a vane suitably configured to at least partially engage a mass ejecta stream to apply a net rotational torque about the principal axis of the drive system, and a tailfin coupled to the at least one vane. The tail fin is configured to selectively deploy from an at least partially stowed position in order to decrease the application of net rotational torque about the principal axis of the drive system.

Abstract: A multi-stage hyper-velocity kinetic energy missile (HVKEM) uses a ‘missile in a missile’ architecture in which the HVKEM includes a 1st stage flight missile and a 2nd stage kill missile that includes a KE-rod penetrator. The flight missile cruises at a relatively low velocity (less than Mach 1.5, typically less than Mach 1) to conserve propellant (weight) and to allow for effective guidance and maneuvering until the missile is in close proximity to the target. When the missile is within the lethal range of the KE-rod penetrator, the kill missile separates and boosts to a much higher velocity (greater than Mach 3, typically greater than Mach 5) and flies unguided to impact the target in less than a second. Waiting to boost the KE-rod until “the last second” reduces the total propellant (weight) needed to deliver the KE-rod on target and simplifies the guidance.

Abstract: The present invention discloses a system, device and method for providing an exhaust assembly adapted for use with a mass ejection drive system to produce rotational torque about the principle axis of the drive system. Representative features generally include a vane suitably configured to at least partially engage a mass ejecta stream to apply a net rotational torque about the principal axis of the drive system, and a tailfin coupled to the at least one vane. The tailfin is configured to selectively deploy from an at least partially stowed position in order to decrease the application of net rotational torque about the principal axis of the drive system.