Raytheon Company

Jaylan S Jones

Donald G Messitt

Paul S MacDonald

Shawn P Burke

Frederick B Koehler

Ronald L Roncone

Brian Hodge

Gabe Harris

Andrew J Lotti

Donald M Jones

Jessie A Polanco

A projectile includes a wing structure to form both an inlet that intakes air for combustion by a propulsion system of the projectile during an initial range of flight, and a lift surface for the projectile after the propulsion engine of the propulsion system burns out. The wing structure acts as both the inlet and the lift surface to enable both a long range and an optimal time of flight for the projectile to the target. The wing structure includes at least one wing that is movable from a folded position, in which the wing extends along a propulsion body section of the projectile to define the inlet, to a deployed position, in which the wing extends outwardly from the propulsion body section to form the lift surface. Any number of wings may be provided and the wings may be simultaneously deployed or sequentially deployed depending on the application.

Articulating inlet for airbreathing extended range projectiles and missiles

A submunition assembly to be stored and deployed from an aerial vehicle, particularly a supersonic vehicle, includes a container having at least first and second walls that are joined at one end by a hinge that together define a volume along an axis perpendicular to the hinge that contains a submunition. The submunition assembly is suitably axially-shaped with a rigid parachute panel positioned around the hinge to separate and deploy a parachute. The container may have an internal volume that is conformal to the submunition. The container may have an exterior shape that is either optimized for free-fall or has a portion that provides a conformal surface for the aerial vehicle. The submunition assembly may be configured so that all processing, memory and data resides with the submunition, which issues any and all commands to control the container including separation of the rigid parachute panel and opening of the container to release the submunition.

Submunition assembly

A dual-mode roll/nod gimballed seeker is configured to provide an unobstructed path for a forming-warhead penetrator. A nod assembly includes first and second seekers separately offset from the roll axis whose FOV overlap within a stand-off range to a target. A roll gimbal rotates the dome and nod assembly around the roll axis. A nod gimbal rotates the nod assembly about a nod axis over a nod FOR that causes the seekers to cross the roll axis and obstruct a path along the roll axis. At terminal, the nod gimbal rotates the nod assembly to a nominal nod angle at which the path is unobstructed to detonate the forming warhead and project a penetrator along the path through the dome. This alleviates the need for a precursor charge and saves precious volume in the airframe, which is of particular import for small diameter warheads, in particular those having a diameter of no more than 8 inches.

Dual-mode roll/nod gimballed seeker for a forming warhead

Embodiments of a system for simulating a radio frequency (RF) scene associated with a moving maritime surface are generally described herein. An RF scene is generated using an RF scene generation model and a moving maritime surface is generated using a maritime surface model. The RF scene is integrated with the moving maritime surface model. The RF scene generation model is configured to apply a radar model to generate and update the RF scene based on simulated radar returns at a radar pulse repetition frequency (PRF) and the maritime surface model is configured to update the moving maritime surface at a maritime surface update rate, access previous and current maritime surfaces, and interpolate surface facet properties to pulse times of the radar model. The maritime surface model is configured to update the moving maritime surface once every subdwell.

RF scene generation simulation with external maritime surface

An integrated propulsion and warhead system for an artillery round includes a propulsion, such as a solid rocket motor and/or an air-breathing jet engine, and an annular explosive concentrically arranged around at least a portion of the propulsion system. The integrated propulsion and warhead system is included in a propulsion section of the artillery round so that space in an adjacent guidance section is increased and the space allocation for the propulsion system and annular explosive is optimized.

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Tucson, AZ, United States of America

Jaylan S Jones