Raytheon Company

Jeff L Vollin

Kenneth William Brown

Frederick B Koehler

Jeremy C Danforth

Matt H Summers

Paul M Lyons

Mark J Meisner

Frederick A Ahrens

James D Kueneman

Robert A Mauss

A solid rocket motor uses at least one thermally conductive wire or at least one pair of electrically conductive wires to increase a burn surface area of a propellant grain and thus a thrust of the rocket motor. The rocket motor includes a pulse chamber containing a burnable propellant grain, a propellant inhibited center bore bonded to surfaces of the burnable propellant grain, and at least one conductive wire coupled to the burnable propellant grain and arranged in variable regions along the propellant inhibited center bore. The conductive wire is configured for passive or active activation to ignite the propellant inhibited center bore that subsequently burns in the variable regions. The thermally conductive wire is formed of a refractory metal or refractory alloy material that enables the entire length of the wire to be heated simultaneously or nearly simultaneously when the wire is passively activated.

Variable burn-rate solid rocket motor ignition method

An open-loop thermal control system and method for components that generate heat includes a reservoir for containing a pressurized working fluid, a first heat exchanger in thermal communication with the working fluid, a Joule-Thomson expansion valve in fluid communication with the reservoir, and a second heat exchanger in fluid communication with the valve. The first heat exchanger is configured to transfer heat from the components to the fluid in the reservoir. The valve is configured to expand the working fluid into a two-phase fluid having a primary use of cooling. The second heat exchanger is configured to receive heat from the components and receive the two-phase fluid. The second heat exchanger provides a single-phase working fluid for at least one secondary use before the working fluid is expelled from the thermal control system.

Multifunctional aerodynamic, propulsion, and thermal control system

A method for controlling a power converter that includes a first cell having an output connected at a first node in parallel with a second cell includes sensing a voltage signal at the first node, defining a current set point associated with the converter, processing the current set point associated with the converter to define a current set point associated with the first cell, sensing a current output by the first cell, controlling the first cell such that the first cell outputs a current substantially similar to the current set point associated with the first cell, processing the current set point associated with the converter to define a current set point associated with the second cell, sensing a current output by the second cell, and controlling the second cell such that the second cell outputs a current substantially similar to the current set point associated with the second cell.

Multiphase power converter

The disclosed system, device, and method for diverting a guided missile generally includes a ground-based sensor array generating tracking data of a guided missile tracking a target. A control node in communication with the ground-based sensor array generates targeting data from the tracking data. A phased array directed-energy unit in communication with the control node radiates the guided missile with variable beam width microwave radiation based on the targeting data received from the control node, where the microwave radiation disrupts an electronic component of the guided missile such that the guided missile discontinues tracking the target.

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Tucson, AZ, United States of America

Jeff L Vollin