Abstract: 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.

Abstract: A modulation device for modulating a gas ejection section, the device being for placing in a nozzle upstream from the throat of the nozzle, the modulation device including a plug having a downstream end forming a member for partially obstructing the nozzle throat; and a plug guide having an internal housing in which the upstream end of the plug is present. The upstream end of the plug is suitable for sliding in the internal housing of the plug guide between a first position in which the upstream end of the plug is present in an upstream portion of the internal housing, and a second position in which the upstream end is present in a downstream portion of the internal housing. The upstream end of the plug is held in the first position by at least one retaining element for breaking under the effect of heat.

Abstract: A modulator device for modulating a gas ejection section, which device is for placing in a nozzle upstream from the throat of the nozzle and includes a plunger. The plunger has both a proximal portion connected to a control guide and also a distal portion in the form of a body of revolution, the plunger being movable between a retracted position and an extended position. The plunger presents, in its distal portion, a first section of concave shape and a second section of concave shape situated downstream from the first section.

Abstract: 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.

Abstract: A modulator device for modulating a gas ejection section, which device is for placing in a nozzle upstream from the throat of the nozzle and includes a plunger. The plunger has both a proximal portion connected to a control guide and also a distal portion in the form of a body of revolution, the plunger being movable between a retracted position and an extended position. The plunger presents, in its distal portion, a first section of concave shape and a second section of concave shape situated downstream from the first section.

Abstract: A modulation device for modulating a gas ejection section, the device being for placing in a nozzle upstream from the throat of the nozzle, the modulation device including a plug having a downstream end forming a member for partially obstructing the nozzle throat; and a plug guide having an internal housing in which the upstream end of the plug is present. The upstream end of the plug is suitable for sliding in the internal housing of the plug guide between a first position in which the upstream end of the plug is present in an upstream portion of the internal housing, and a second position in which the upstream end is present in a downstream portion of the internal housing. The upstream end of the plug is held in the first position by at least one retaining element for breaking under the effect of heat.

Abstract: A combined steering and drag reduction device for a missile is disclosed. The device includes a base and an upper part which are arranged in succession along a main axis of navigation of the missile. Advantageously, the device also includes a pressurized-gas generator and at least one lateral thruster having at least one nozzle configured to deliver a thrust, by expanding gas transmitted by the generator and oriented along an axis substantially perpendicular to the main axis. The at least one lateral thruster also has at least one stabilizing chamber configured to expand the gas transmitted by the generator and expel it through an outlet section of the base substantially perpendicular to the main axis.

Abstract: A system for in-flight attitude control and side-force steering includes a thruster body and a plurality of valves capable of generating side thrusts put into communication with the thruster body. The valves are arranged in two sets of valves spaced apart from each other towards the front and towards the rear of the thruster body in substantially symmetrical manner relative to the center of gravity of the vehicle situated on a longitudinal axis (A) of the vehicle. Each set comprises a first pair of valves generating thrust in opposite directions along axes that are not in alignment and are parallel to a first axis, and a second pair of valves generating thrust in opposite directions along axes that are not aligned and are parallel to a second axis. The first and second axes are distinct and perpendicular to the longitudinal axis of the vehicle.

Abstract: A combined steering and drag reduction device for a missile is disclosed. The device includes a base and an upper part which are arranged in succession along a main axis of navigation of the missile. Advantageously, the device also includes a pressurized-gas generator and at least one lateral thruster having at least one nozzle configured to deliver a thrust, by expanding gas transmitted by the generator and oriented along an axis substantially perpendicular to the main axis. The at least one lateral thruster also has at least one stabilizing chamber configured to expand the gas transmitted by the generator and expel it through an outlet section of the base substantially perpendicular to the main axis.

Abstract: A system for in-flight attitude control and side-force steering includes a thruster body and a plurality of valves capable of generating side thrusts put into communication with the thruster body. The valves are arranged in two sets of valves spaced apart from each other towards the front and towards the rear of the thruster body in substantially symmetrical manner relative to the center of gravity of the vehicle situated on a longitudinal axis (A) of the vehicle. Each set comprises a first pair of valves generating thrust in opposite directions along axes that are not in alignment and are parallel to a first axis, and a second pair of valves generating thrust in opposite directions along axes that are not aligned and are parallel to a second axis. The first and second axes are distinct and perpendicular to the longitudinal axis of the vehicle.