There is provided a projectile, a system and a related method of operation of a projectile comprising: a front ogive section; an aft section; and a control module; wherein the front ogive section is rotatably connected to the aft section by a coupling device, the front ogive section further comprising an asymmetric surface such that the asymmetric surface exerts an imbalance upon the projectile, where in use, the angular rotation of the front ogive section can be selectively adjusted relative to the aft section by commands from the control module to the coupling device influencing a helical trajectory of the projectile in flight thereby causing a change in direction thereby steering the projectile towards a target.

There is provided a projectile, a system and a related method of operation of a projectile comprising: a front ogive section; an aft section; and a control module; wherein the front ogive section is rotatably connected to the aft section by a coupling device, the front ogive section further comprising an asymmetric surface such that the asymmetric surface exerts an imbalance upon the projectile, where in use, the angular rotation of the front ogive section can be selectively adjusted relative to the aft section by commands from the control module to the coupling device influencing a helical trajectory of the projectile in flight thereby causing a change in direction thereby steering the projectile towards a target.

Controlling an in-flight spin-rate of a spin-stabilized guided projectile is disclosed. In various embodiments, the projectile includes a despun control portion configured for despinning relative to a projectile chassis and for directional control of the projectile. In various embodiments, controlling the in-flight spin-rate includes determining a gyroscopic stability factor for the guided projectile using the in-flight spin rate and a forward velocity of the guided projectile, determining that the gyroscopic stability factor exceeds a stability threshold, and spin-braking the guided projectile, in response to determining that the gyroscopic stability factor exceeds a threshold value, by braking rotation of the despun control portion by which the gyroscopic stability factor of the guided projectile is reduced to a second gyroscopic stability factor.

Methods involve using a guided munition (e.g., a mortar round or a grenade) that utilizes deployable flow effectors, activatable flow effectors and/or active flow control devices to extend the range and enhance the precision of traditional unguided munitions without increasing the charge needed for launch. Sensors such as accelerometers, magnetometers, IR sensors, rate gyros, and motor controller sensors feed signals into a controller which then actuates or deploys the flow effectors/flow control devices to achieve the enhanced characteristics.

Methods involve using a guided munition (e.g., a mortar round or a grenade) that utilizes deployable flow effectors, activatable flow effectors and/or active flow control devices to extend the range and enhance the precision of traditional unguided munitions without increasing the charge needed for launch. Sensors such as accelerometers, magnetometers, IR sensors, rate gyros, and motor controller sensors feed signals into a controller which then actuates or deploys the flow effectors/flow control devices to achieve the enhanced characteristics.

A projectile includes a body and a power generator secured to the body. The power generator includes a stator and a ring including at least one magnet and extending radially around and freely rotatable about at least a portion of the stator. A power generator for a projectile is also provided.

The invention relates to a missile (1) for intercepting alien drones (21), comprising a capturing net (9) and a parachute (18), wherein a plurality of weights (15) are connected to the capturing net (9), wherein the capturing net (9) can be ejected from the missile (1) and the weights (15) can be ejected from the missile (1). The capturing of the alien drone is improved by the fact that the capturing net (9) can be ejected by a first means and the weights (15) can be ejected by a second means, wherein the weights (15) and the capturing net (9) can be ejected at different times from the missile (1).

The invention relates to a missile (1) for intercepting alien drones (21), comprising a capturing net (9) and a parachute (18), wherein a plurality of weights (15) are connected to the capturing net (9), wherein the capturing net (9) can be ejected from the missile (1) and the weights (15) can be ejected from the missile (1). The capturing of the alien drone is improved by the fact that the capturing net (9) can be ejected by a first means and the weights (15) can be ejected by a second means, wherein the weights (15) and the capturing net (9) can be ejected at different times from the missile (1).

A system including a system controller configured to transmit a first amount of commands in order to produce a desired effect by a group of actuators acting in combination. A system controller configured to control a group of at least two actuators in order to produce at least one combined effect, wherein the number of actuators is greater than or equal to the number of effects. A system controller configures to independent and variable bandwidths or responses of the desired effects produced by the actuators acting in combination.

An inflatable dummy target comprising a chassis of inflatable ducts wrapped with a sheet.