Bae Systems Information and Electronic Systems Integration Inc.

Jason H Batchelder

Matthew F Chrobak

Michael J Choiniere

David J Schorr

James H Steenson, Jr

Jeremy B Gibson

Richie Spitsberg

Robert D Frey, Jr

Kenneth D Cleveland

Ryan Dippel

Joseph P Cullen

Matthew H Robichaud

Maxwell L Affleck

Peter J Evans

Joseph D Vasile

Samantha Kirsh

Tyler Nickerson

Gregory R Hallerman

James H Steenson Jr

Jr James H Steenson

A guidance kit for a projectile and method for suppressing a point-of-interest (POI) at a desired location away from the POI. The guidance kit includes at least one processor in the guidance kit. The guidance kit also includes a guidance protocol operatively in communication with the guidance kit and the at least one processor and having a set of angular offset modes. The guidance protocol of the guidance kit is configured to guide the projectile to at least one location relative to a desired point-of-interest (POI) upon or in response to activation of at least one angular offset mode of the set of angular offset modes.

Guidance kit with variable angular offset for undetected ground suppression and methods thereof

A feed forward guidance kit for a ballistic device that includes at least one optical imaging sensor, a processor that is operatively in communication with the at least one optical imaging sensor, and a feed forward guidance protocol that is stored on a computer readable medium and that is operatively in communication with the processor. When the at least one optical imaging sensor initially intercepts an aircraft at an initial location during combat, the feed forward guidance protocol instructs the processor to proactively calculate an anticipated second position of the aircraft as an orientation of the aircraft changes from an initial orientation to a translated orientation.

Feed forward image based guidance

The system and method of a steering a moving object using a control plate-based control actuation system on the moving object. The control plate-based control actuation system having a control plate with at least four fin linkages for connecting at least four fins to the control plate; and three actuators configured to move the control plate to produce movement in two or more of the at least four fins. The system produces roll, pitch, and yaw moments for the moving object using three actuators acting on the control plate and thus moving two or more of the at least four fins all with no loss of performance as compared to systems with four actuators.

Control plate-based control actuation system

[A system and method for dynamic autopilot control comprising providing input to a guidance and control autopilot comprising Mach and dynamic pressure; tailoring parameters of the autopilot, the parameters comprising: roll gain; a pitch/yaw gain; a pitch/yaw loop compensator frequency; a guidance filter bandwidth; a guidance filter lead compensator frequency; and a navigation gain.

Dynamic autopilot

The system and method of weapon on-board range and velocity tracking using a synchronized clock and a pulse beacon on a fire control system, or the like, coupled with an on-board rear-facing detector and processor. A round or a UAS may use this system to accurately estimate range with respect to the fire control system, over time, and the round's or UAS's velocity at various times along its flight path. The system provides for smaller miss distances, and the like.

Weapon on-board velocity and range tracking

Techniques are provided for determination of a guided-munition orientation during flight based on lateral acceleration, velocity, and turn rate of the guided-munition. A methodology implementing the techniques, according to an embodiment, includes obtaining a lateral acceleration vector measurement and a velocity of the guided-munition, and calculating a ratio of the two, to generate an estimated lateral turn vector of the guided-munition. The method also includes integrating the estimated lateral turn vector, over a period of time associated with flight of the guided-munition, to generate a first type of predicted attitude change. The method further includes obtaining and integrating a lateral turn rate vector measurement of the guided-munition, over the period of time associated with flight of the guided-munition, to generate a second type of predicted attitude change. The method further includes calculating a gravity direction vector based on a difference between the first and second types of predicted attitude change.

Determination of guided-munition roll orientation

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.

Wing mounted seeker

An ordnance includes a nose cone configured to be attached to a fuze or a warhead. The nose cone, when attached or coupled to the fuze or warhead, covers the fuze and at least a portion of the warhead to provide the ordnance with an aerodynamic profile. The nose cone has a shape that improves the aerodynamic profile of the ordnance as compared to ordnance that does not include a cover over the fuze. The improved aerodynamic profile enables the ordnance to achieve a greater range (approximately 20% or more) than ordnance that does not have a separate nose cone covering the fuze.

Ordnance nose cone

The system and method of attitude determination by pulse beacon and extremely low cost inertial measuring unit. A pulse beacon is used to generate a plurality of pulses detected by a detector or receiver located on the rear of a projectile such that direction of arrival can be determined. A synchronized clock proved for velocity and range information. Altitude can also be determined and may use an altimeter or the like. The use of a low cost IMU is possible with internal calibration by the system. Real-time attitude information provides for correction for crosswind and other drift enabling the system to have less down range dispersion.

Attitude determination by pulse beacon and low cost inertial measuring unit

A mid-body which a cylindrical housing which defines a longitudinal axis and has an interior compartment. A guidance controller is housed within the mid-body for controlling flight. A plurality of wings are connected to the housing and each of the wings is movable into a deployed position to provide guidance during flight. The mid-body has an access window which facilitates communication between the interior compartment of the housing and an external environment. A normally door covers the access window, but when the door is moved, relative to the access window, into an open position, communication between the interior compartment and the external environment is established. An optical sensor is accommodated within the interior compartment and the optical sensor, once the door is moved relative to the access window, can view the external environment and supply data to the guidance controller for controlling operation of the plurality of wings during flight.

Growing community of inventors

Lyndeborough, NH, United States of America

Jason H Batchelder