Raytheon Company

Robert T Moore

Andrew B Facciano

Gregg J Hlavacek

Craig D Seasly

Michael S Alkema

Daniel Chasman

Michael A Leal

Richard A McClain

Juan Gonzalez

Michael D Do

Kelly J Sinnock

Scott T Caldwell

Raymond J Spall

James E Parry

John Terry White

Richard A Mcclain

A projectile for firing from a launcher includes a propulsion stage having non-axisymmetric boosters arranged about a longitudinal axis of the propulsion stage. The propulsion stage may further include a central booster about which the non-axisymmetric boosters are arranged.

Cluster rocket motor boosters

A projectile includes a propulsion booster for producing pressurized gases, a nozzle for expelling the pressurized gases produced by the booster, and a supplementary integrated actuation system. The integrated actuation system selectively directs propellant from a storage reservoir of the integrated actuation system through an interiorly-located outlet of the integrated actuation system located at the nozzle and into the nozzle, thus changing a direction of the pressurized gases expelled by the booster. The integrated actuation system also selectively directs propellant from the storage reservoir through a peripherally-located outlet of the integrated actuation system, to produce thrust at an external periphery of the projectile, thus diverting the projectile. The integrated actuation system may also selectively direct propellant to a nozzle actuation system for positioning the nozzle, to a stage separation system for separating portions of the projectile, or to a power generator for generating electric power for the projectile.

Integral injection thrust vector control with booster attitude control system

A rocket is provided and includes booster stages at a rear of the nose cone, the booster stages being configured for propelling the nose cone in a propulsion direction and a divert control system housed entirely in the nose cone for controlling an orientation of the propulsion direction.

Rocket propelled payload with divert control system within nose cone

Embodiments of a missile, an airframe and a structure comprising piezoelectric fibers and a method for active structural response control are generally described herein. In some embodiments, a housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure to provide low frequency stiffness and strength performance while attenuating high frequency vibrations.

Missile airframe and structure comprising piezoelectric fibers and method for active structural response control

Methods and apparatus for a missile having an external system operate in conjunction with an airframe and a fluid transfer system. The airframe includes an interior surface defining a substantially enclosed internal chamber. The fluid transfer system selectively connects the internal chamber to the external system, for example to provide pressurant or coolant to the external system.

Methods and apparatus for transferring a fluid

An integral composite rocket motor nozzle. The novel nozzle includes a first layer of a first reinforcement material, a second layer of a second reinforcement material, and a common matrix material surrounding the first and second reinforcement materials such that the reinforcement materials and matrix material form a single integral composite structure. In an illustrative embodiment, the first reinforcement material includes graphite fibers for providing structural support, and the second reinforcement material includes glass or quartz fibers for providing thermal insulation on a first side of the first layer. The nozzle may also include a third layer of a third reinforcement material for providing thermal insulation on a second side of the first layer. In a preferred embodiment, the first layer is shaped to form an integrated dome and nozzle structure.

Integral composite rocket motor dome/nozzle structure

A separable structure includes composite material that is separated or severed by a reactive pyrotechnic material. According to one embodiment, the structure includes a pair of composite laminate structural portions, each including multiple layers of composite material. The portions each extend into an overlap region, within which the composite layers of the two structural portions may be alternately placed, overlapping one another. A reactive material is also placed within this overlap region, for instance being in layers between pairs of the composite material layers. The reactive material may be ignited to cause destruction of the pyrotechnic material, and a matrix or resin material of the composite materials layers in the overlap region. This causes the structure to sever or separate along a line of separation within the overlap region. The separation may occur without need to sever fibers of the composite material.

Separable structure material method

Provided is a detachable aerodynamic missile stabilizing system for a missile flying at low flight speeds. The system includes a housing adapted to couple to couple to the missile. Extending outward from the housing is at least one grid fin. Specifically the grid fin extends from the housing such that it is transverse to a longitudinal axis of the housing and the missile. The grid fin provides a plurality of apertures. The apertures are parallel to the longitudinal axis of the housing and the missile. A coupler is adapted to detachably couple the housing to the missile. A method of use is also provided.

Detachable aerodynamic missile stabilizing system

A vibration controlled housing. The novel housing includes a housing structure and a mechanism for receiving a control signal and in accordance therewith electronically tuning a structural response of the structure. In an illustrative embodiment, the housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure in response to an electrical signal applied thereto. A control circuit receives the sensed signal from the fibers and generates an excitation signal that is applied to the fibers to increase the stiffness or compliance of the fibers at predetermined frequencies. In an illustrative embodiment, the control signal is adapted to provide low frequency stiffness and strength performance while attenuating high frequency vibrations to protect electronics housed within the structure.

Piezoelectric fiber, active damped, composite electronic housings

A missile includes a radome-seeker airframe assembly that has a single-piece composite material forebody. The forebody is made of a high-temperature composite material that can withstand heat with little or no ablation. The forebody has a front part with an ogive shape and an aft part that has a cylindrical shape. The front part acts as a radome for a seeker located within the forebody. Patch antennas are attached to an inside surface of the cylindrical aft part. The aft part acts as a radome for the patch antennas, allowing signals to be sent and received by the patch antennas without a need for cutouts. A single seal may be used to seal the guidance system and seeker within the forebody, allowing the equipment to be hermetically sealed within the forebody.

Composite missile nose cone

Separable structure material

A missile includes a payload assembly that has a pair of nosecones. The nosecones may be optimized for different environments and/or phases of flight, for example, having different shapes, different shell materials, different types of seals, and/or different separation mechanisms. The first (outer) nosecone may have a more streamlined shape, be made of more thermally-protective material, and may meet less stringent sealing requirements, than the second (inner) nosecone. Separation of the outer nosecone from the payload assembly may cause backward movement of a center of pressure of the payload assembly, bringing the center of pressure of the assembly closer to a center of gravity of the assembly. This may make the payload assembly easier to maneuver, for example, reducing or eliminating the need for intervention by an attitude control system, to maintain the payload assembly on a desired course.

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Tucson, AZ, United States of America

Robert T Moore