Abstract: An artillery projectile is configured to have a trajectory comprising a ballistic phase and a piloted phase. This projectile has at least one means ensuring its aerodynamic stabilization on part or all of its trajectory and a means configured to ensure a piloting during the piloted phase. This projectile is characterized in that the aerodynamic stabilization means comprises a wing system having at least two wings which are able to be positioned with respect to the axis of the projectile, at least during the piloted phase, with their sweepback angles being negative, that is, with the free ends of the wings being oriented towards the front of the projectile.

Abstract: An artillery projectile is configured to have a trajectory comprising a ballistic phase and a piloted phase. This projectile has at least one means ensuring its aerodynamic stabilization on part or all of its trajectory and a means configured to ensure a piloting during the piloted phase. This projectile is characterized in that the aerodynamic stabilization means comprises a wing system having at least two wings which are able to be positioned with respect to the axis of the projectile, at least during the piloted phase, with their sweepback angles being negative, that is, with the free ends of the wings being oriented towards the front of the projectile.

Abstract: The invention relates to an artillery projectile (1) which is intended to have a trajectory comprising a ballistic phase and a piloted phase. This projectile (1) has at least one means ensuring its aerodynamic stabilization on part or all of its trajectory and a means (9) intended to ensure a piloting during the piloted phase. This projectile is characterized in that the aerodynamic stabilization means comprises a wing system having at least two wings (16) which are able to positioned with respect to the axis (26) of the projectile, at least during the piloted phase, with their sweepback angles being negative, that is, with the free ends (16b) of the wings (16) being oriented towards the front of the projectile (1).

Abstract: The invention relates to an artillery projectile (1) which is intended to have a trajectory comprising a ballistic phase and a piloted phase. This projectile (1) has at least one means ensuring its aerodynamic stabilization on part or all of its trajectory and a means (9) intended to ensure a piloting during the piloted phase. This projectile is characterized in that the aerodynamic stabilization means comprises a wing system having at least two wings (16) which are able to positioned with respect to the axis (26) of the projectile, at least during the piloted phase, with their sweepback angles being negative, that is, with the free ends (16b) of the wings (16) being oriented towards the front of the projectile (1).

Abstract: A simultaneous deployment device for the control surfaces of a projectile for which each control surface is intended to be pivoted by a motor after its deployment to ensure the piloting, each control surface being held within the projectile and deployed towards the exterior of the projectile by the expansion of elastic means, each control surface being deployed by a rotation with respect to a control surface support and following a deployment axis that is crosswise to that of the projectile, wherein the elastic means are common means to ensure the deployment of all the control surfaces, the expansion of the elastic means generating a push stress directed along the axis of the projectile and being exerted on a push plate which transmits the push stress to as many slides as there are control surfaces to be deployed, each slide cooperating without slipping with a matching profile integral with a base of the control surface to make this pivot with respect to its support and first releasable locking means that mai

Abstract: A simultaneous deployment device for the control surfaces of a projectile for which each control surface is intended to be pivoted by a motor after its deployment to ensure the piloting, each control surface being held within the projectile and deployed towards the exterior of the projectile by the expansion of elastic means, each control surface being deployed by a rotation with respect to a control surface support and following a deployment axis that is crosswise to that of the projectile, wherein the elastic means are common means to ensure the deployment of all the control surfaces, the expansion of the elastic means generating a push stress directed along the axis of the projectile and being exerted on a push plate which transmits the push stress to as many slides as there are control surfaces to be deployed, each slide cooperating without slipping with a matching profile integral with a base of the control surface to make this pivot with respect to its support and first releasable locking means that mai