The Boeing Company

Other

United Technologies Corporation

Pratt & Whitney Rocketdyne, Inc.

Aerojet Rocketdyne of De, Inc.

Patrick Edward Frye

Joseph P Carroll

William D Otting

Charles T Kudija, Jr

Terrence H Murphy

James M Shoji

Andrew J Zillmer

Cheng-Yi Lu

William Determan

Kenneth John Metcalf

James A McClanahan

Rick L Howerton

Charles Thomas Kudija

A heat rejection system includes a plurality of panel subassemblies and a solid state heat pipe flex joint. Each panel subassembly includes a fin, a solid state heat pipe manifold, a first solid state heat pipe tube operatively connected to the solid state heat pipe manifold and secured to the fin, a second solid state heat pipe tube operatively connected to the solid state heat pipe manifold adjacent to the first solid state heat pipe and secured to the fin. The solid state heat pipe flex joint operably connects the solid state heat pipe manifolds of two of the plurality of panel subassemblies in a hermetically sealed configuration, and is configured to permit repositioning of the two panel subassemblies relative to each other.

Solid state heat pipe heat rejection system for space power systems

A solar power system capable of storing heat energy and converting sun light to electrical power. The solar power system includes a solar collection system which gathers and transmits concentrated solar energy to an absorber/cavity. The thermal energy is extracted from the absorber/cavity via a fluid and transported to a heat conversion system. The heat conversion system uses the thermal energy to create electricity.

Solar dish concentrator with a molten salt receiver incorporating thermal energy storage

A thruster device and associated methods are provided. The thruster device comprises a frustoconical inner layer and a frustoconical outer layer that surrounds the inner layer such that the inner and outer layers cooperate to define a spiral flow passage therebetween. An outlet, such as a nozzle, is attached to an exit end of the thruster device such that the outlet is in fluid communication with the spiral flow passage. In one embodiment, the thruster device includes an end flow cap that is also attached to the exit end and establishes the fluid communication between the spiral flow passage and the outlet. The end flow cap includes at least one channel for directing the propellant from the spiral flow passage to the outlet. The design of the thruster device allows the frustoconical inner and outer layers to be assembled without galling or damaging the spiral flow passage.

Thruster device responsive to solar radiation and associated methods

A solar power collection system capable of operating with a positioning system that provides movement of the system about only a single axis of rotation. The solar power collection system includes a concentrator having at least one parabolic-trough-shaped mirror that focuses sun light reflected therefrom along a longitudinal focus line defined by a focus of the parabolic-trough shaped mirror. An absorber having a heat absorbing tube and a heat absorbing shoe is supported from the mirror such that the tube is positioned coaxially along the focus line to receive reflected sun light. The tube absorbs thermal from the sun light and conductively heats the shoe. The shoe supplies this thermal energy to an energy conversion engine. The engine, in one preferred form, is a Stirling engine that converts the thermal energy into electrical energy. A pointing system moves the concentrator about a single axis of rotation to track the sun across the horizon.

Trough-stirling concentrated solar power system

Method of making a thruster device for solar radiation

A combined generator device for use in a satellite capable of generating electrical power and thrust from an optical solar image. The combined generator includes a first receiver positioned to receive and store the outer, low-intensity region of the optical solar image. An electrical power generator thermally coupled to the first receiver uses the stored thermal energy to produce electricity. The combined generator also includes a thrust generator having a second receiver. The second receiver is positioned to receive and absorb the inner, high-intensity region of the optical solar image. A heat exchanger of the combined generator transfers the thermal energy from the second receiver into a supply of propellant which is vented to a nozzle to produce thrust.

Method of generating thrust and electrical power from an optical solar image

Combined thrust and power generator for a satellite

Thruster device responsive to solar radiation

A solar thermal engine for propelling and powering a craft. The solar thermal engine includes a housing, a propellant annulus, a plurality of static power converters and an electrical energy storage device. The housing has an optical cavity for receiving a beam of concentrated sunlight and converting the beam into ambient thermal energy. The propellant annulus is coupled to the housing and is selectively operable in a heating mode wherein the propellant annulus transmits at least a first portion of the ambient thermal energy to heat a flow of propellant. The plurality of static power converters are coupled to the housing and receive the first portion of the ambient thermal energy when the propellant annulus is not operated in the heating mode. The plurality of static power converters employ the first portion of the ambient thermal energy to generate electrical energy. The electrical energy storage device is coupled to the plurality of static power converters and receives and stores the electrical energy generated by the plurality of static power converters. A method for propelling and powering a craft is also provided.

Integral propulsion and power radiant cavity receiver

Growing community of inventors

Simi Valley, CA, United States of America

Patrick Edward Frye