The present disclosure provides a payload activation device. The payload activation device comprises a camera having a fixed focal length, arranged to capture an image of an object on a platform for carrying a payload having the payload activation device, wherein, when the payload is in a first position relative to the platform, the image of the object is in a first focused state and, when the payload is in a second position relative to the platform, the image of the object is in a second focused state. The payload activation device also comprises a processor configured to determine whether the image of the object is in the first focused state or the second focused state and to cause actuation of an activation mechanism within the payload when the image of object is in the second focused state to activate the payload. The present disclosure also provides a deployable payload having the payload activation device and an aircraft for carrying the deployable payload.

The system and method for accurately determining range-to-go for the command detonation of a projectile. Using dual laser and/or radio frequency detectors on the tail and on the nose of a spinning projectile to determine the range-to-go, time-to-go, or lateral offset from the projectile to the target.

The system and method for accurately determining range-to-go for the command detonation of a projectile. Using dual laser and/or radio frequency detectors on the tail and on the nose of a spinning projectile to determine the range-to-go, time-to-go, or lateral offset from the projectile to the target.

A projectile including an ejectable aft fin housing assembly. The aft fin housing assembly includes aft fins that increase a distance between a center of gravity and a center of pressure of the projectile, improving passive stabilization of the projectile. Once the projectile has been passively stabilized, the aft fin housing assembly is ejected, decreasing a distance between the center of gravity and the center of pressure, improving active stabilization of the projectile.

A projectile including an ejectable aft fin housing assembly. The aft fin housing assembly includes aft fins that increase a distance between a center of gravity and a center of pressure of the projectile, improving passive stabilization of the projectile. Once the projectile has been passively stabilized, the aft fin housing assembly is ejected, decreasing a distance between the center of gravity and the center of pressure, improving active stabilization of the projectile.

A pivot connection part for a flying machine includes an inner body, an outer body radially surrounding the inner body, and a set of connection elements configured to connect the inner body to the outer body. Breaking the connection elements detaches the inner body from the outer body. A first blocking assembly having a cam and a stop is configured to block relative rotation between the inner and outer bodies in a first rotational direction. A second blocking assembly having a pawl and a resilient stop blade is configured to block relative rotation between the inner and outer bodies in a second rotational direction.

A pivot connection part for a flying machine includes an inner body, an outer body radially surrounding the inner body, and a set of connection elements configured to connect the inner body to the outer body. Breaking the connection elements detaches the inner body from the outer body. A first blocking assembly having a cam and a stop is configured to block relative rotation between the inner and outer bodies in a first rotational direction. A second blocking assembly having a pawl and a resilient stop blade is configured to block relative rotation between the inner and outer bodies in a second rotational direction.

The system and method of spin stabilizing a guided munition where a motor provides necessary de-spinning torque. The despun PGK portion of a guided projectile is already at high rate of spin relative to the projectile body and the motor is operated to maintain that rate.

The system and method of spin stabilizing a guided munition where a motor provides necessary de-spinning torque. The despun PGK portion of a guided projectile is already at high rate of spin relative to the projectile body and the motor is operated to maintain that rate.

A missile including an upper stage and at least one lower stage is provided. The upper stage includes a primary flight computer configured to control a flight of the upper stage along a missile flight path such that, for example, it reaches a predetermined target. The lower stage is mounted to the upper stage and includes a propellant for initially propelling the upper stage along the missile flight path. The lower stage is configured to be jettisoned from the upper stage when the propellant is spent. The lower stage includes a secondary flight computer configured to receive data from the primary flight computer prior to the propellant of the lower stage being spent, and to control a flight of the lower stage along a jettisoned stage flight path of the jettisoned lower stage such that, for example, the jettisoned lower stage glides to a predetermined safe landing zone.