A guidance system for a projectile having a mid-body. The guidance system having a mid-body semi-active laser seeker. The seeker has an objective lens assembly and a sensor array that reads laser energy and transmits data to determine the direction of the laser energy. A glint management unit is connected to mid-body in such a manner that glint laser energy is prevented from passing to the objective lens assembly and sensor array so as to enhance determination of the location of the target.

An optical seeker assembly having an optical detector located within the wing or canards of a precision guided munition. The optical seeker provides on-wing processing that generates low bandwidth detection data that can be easily transferred to a primary CPU located within the main body or fuselage of the precision guided munition. The on-wing processing reduces or eliminates the need for optical fibers extending between an optical wedge and an optical detector to reduce the likelihood of optical fibers from impeding in the mechanical deployment of the wing and reduces losses. The reduction or elimination of optical fibers between the optical wedge and the optical detector further enables the optical detection assembly to have a higher pixel ratio or transmitting raw data between the wedge and the detector by sending sampled detection data across a low bandwidth link to a CPU in the main body.

A tail kit assembly of a guided munition having a tail kit base connected to a trailing end of a projectile body. The tail kit base is rotatable relative to the projectile body. A trimmable rudder has forward and rearward ends. The forward end is pivotally coupled to the tail kit base, such that the trimmable rudder can, relative to the tail kit base, between retracted and extended orientations. An actuator is fixed between the tail kit base and the rearward end of the trimmable rudder. The actuator is electrically coupled to an onboard guidance system that controls actuation of the actuator to pivot the trimmable rudder between the retracted orientation and the extended orientation.

A guiding kit for guiding a projectile to a target comprises a front part and a rear part. The front part and the rear part are rotatably connected to each other to enable relative rotation about a common central longitudinal axis of rotation. The front part comprises a front transceiver (T/X) unit that is disposed next to the rear end of the front part and coinciding with the longitudinal central axis of rotation and adapted to transmit signals towards the rear part. A rear transceiver unit is disposed against the front transceiver unit and adapted to communicate with front transceiver unit when the front part and the rear part are rotating with respect to each other.

An integrated architecture and its associated sensors and processing software subsystems are defined and developed allowing a conventional unguided bullet to be transformed into a guided bullet without the use of an on-board inertial measurement unit (IMU). Some important SW components of the present disclosure include a target state estimator (TSE); a bullet state estimator (BSE); Multi-Object Tracking and Data Association; NTS GL; and a Data Link. Pre-conversion of two angles and range information of an OI sensor from spherical coordinates into Cartesian coordinates eliminates the Jacobian dependency in the H matrix for the BSE, thus increasing the miss distance performance accuracy of the bullet target engagement system.

A guidance unit system is configured to be used for a ground-launched projectile. The system includes a housing configured to be attached to a ground-launched projectile. The housing is coupled to an attachment region that attaches to the projectile, wherein the housing is configure to rotate relative to the attachment region. A motor is contained within the housing and a bearing surrounding the motor. The bearing is rigidly attached to the housing such that the motor rotates with the housing and shields the motor from inertial loads experienced by the housing.

A guidance unit system is configured to be used for a ground-launched projectile. The system includes a housing configured to be attached to a ground-launched projectile. The housing is coupled to an attachment region that attaches to the projectile, wherein the housing is configure to rotate relative to the attachment region. A motor is contained within the housing and a bearing surrounding the motor. The bearing is rigidly attached to the housing such that the motor rotates with the housing and shields the motor from inertial loads experienced by the housing.

In some example, a method for regulating a trajectory of a projectile comprises adjusting the position of a mass within a cavity defined by a jacket of the projectile, whereby to modify a centre of gravity of the projectile.

In some example, a method for regulating a trajectory of a projectile comprises adjusting the position of a mass within a cavity defined by a jacket of the projectile, whereby to modify a centre of gravity of the projectile.

Attitude of a vehicle may be controlled using movable mass. The movable mass may move inside a vehicle or its outline, outside of the vehicle or its outline, inside-to-outside and/or outside-to-inside of the vehicle or its outline, or any combination thereof. The movable mass may be a solid, liquid, and/or gas. When the center-of-mass of the vehicle is moved relative to the line-of-action of applied forces such as thrust, drag, or lift, a torque can be generated for attitude control or for other purposes as a matter of design choice. In the case of external movable masses that extend from the vehicle or its outline, when operating in endoatmospheric flight, or general travel through a fluid, aerodynamic forces from the atmosphere or general fluid forces may further be leveraged to control the attitude of the vehicle (e.g., aerodynamic flaps).