A kinetic energy vehicle (or warhead) has a divert thruster system and an attitude control system, both operatively coupled to receive pressurized gasses from a solid rocket motor that is operatively coupled to both systems. The divert thruster system may have three divert thrusters evenly spaced around a circumference of the vehicle, offset 120 degrees from each other. The divert thrusters are located at a longitudinal (axial) location along the vehicle at or close to a center of gravity of the vehicle. In addition the vehicle may have an aft axial thrusters that may be used in maneuvering the vehicle.

A kinetic energy vehicle (or warhead) has a divert thruster system and an attitude control system, both operatively coupled to receive pressurized gasses from a solid rocket motor that is operatively coupled to both systems. The attitude control system may have two pairs of attitude control thrusters, with one of the pairs diametrically opposed from the other pair, on opposite sides of an end (such as a rear end) of the vehicle. The attitude control thrusters all have radial and circumferential components to their thrust, and various combinations of the attitude control thrusters may be used to achieve desired roll, pitch, and/or yaw.

Apparatus for trajectory control and/or position control of a missile (99), comprising a controllable gas generator (109, 200) with a fuel flow control valve (124, 213), an injector head (112, 202), a combustion chamber (111) and at least one outflow nozzle (103, 204) or at least one throttle.

A kinetic energy vehicle (or warhead) has a divert thruster system and an attitude control system, both operatively coupled to receive pressurized gasses from a solid rocket motor that is operatively coupled to both systems. The divert thruster system may have three divert thrusters evenly spaced around a circumference of the vehicle, offset 120 degrees from each other. The divert thrusters are located at a longitudinal (axial) location along the vehicle at or close to a center of gravity of the vehicle. In addition the vehicle may have an aft axial thrusters that may be used in maneuvering the vehicle.

A kinetic energy vehicle (or warhead) has a divert thruster system and an attitude control system, both operatively coupled to receive pressurized gasses from a solid rocket motor that is operatively coupled to both systems. The attitude control system may have two pairs of attitude control thrusters, with one of the pairs diametrically opposed from the other pair, on opposite sides of an end (such as a rear end) of the vehicle. The attitude control thrusters all have radial and circumferential components to their thrust, and various combinations of the attitude control thrusters may be used to achieve desired roll, pitch, and/or yaw.

An in-flight side force steering and attitude control system for a vehicle includes a thruster body and a plurality of valves distributed in first and second valve sets. The system further includes a first tank defined by a first cylindrical enclosure present at the center of the thruster body, the first tank containing a first solid propellant charge having at least one combustion face exposed at one end of the first tank, the first tank being in communication with the first valve set; and a second tank defined between the first cylindrical enclosure and a second cylindrical enclosure present around the first enclosure, the second tank containing a second solid propellant charge having at least one combustion face exposed at one end of the second tank, the second tank being in communication with the second valve set.

The present invention provides a thrust flow powered vehicle comprising a first thrust flow expeller for expelling a first thrust flow in a first direction, a second thrust flow expeller for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow deflector surface at an angle to the plane of the first and second directions, and an outlet portion for providing an output thrust flow, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of that plane.

A method for controlling the attitude and/or flight path of a flight vehicle includes burning propellant in a gas generator to produce hot gas, storing the hot gas in an accumulator, and releasing the hot gas in the accumulator through one or more thrusters to control the attitude and/or flight path of the flight vehicle.

A projectile is disclosed, having: a longitudinal axis, a steering assembly, a shell body, an attitude control system, a despin module, an electromagnetic receiver and/or emitter system, and a controller. The attitude control system includes a ram air inlet in selective open fluid communication with an exhaust assembly, which includes a plurality of exhaust outlets to selectively generate each of a plurality of thrust jets from a ram air inflow provided by the ram air inlet, each thrust jet being selectively controllable via the controller. The despin module is configured for selectively de-spinning the steering assembly with respect to the shell body about the longitudinal axis. The electromagnetic receiver and/or emitter system is configured for receiving and/or emitting electromagnetic energy, and for cooperating with the controller for operating the exhaust assembly to thereby selectively provide steering control moments. Systems and methods for steering the projectile are also disclosed.

A projectile, such as a railgun-launched projectile, includes a single-piece body that is additively manufactured. The single piece body includes fuel within it, and one or more cavities for receiving an oxidizer. The body also defines one or more combustion chambers therein for combustion of the fuel and oxidizer as part of a divert thruster system. Thus the projectile is able to fully contain the divert thruster system within the single-piece body without using any hot gas seals as part of the system. The body may also define a cavity for receiving a pressurized fluid, used as part of a cold-gas attitude control system of the projectile. The body may also define passages between the pressurized fluid cavity and other parts of the attitude control system, such as valves and/or nozzles that are outside of the body, for example being aft of the one-piece body.