Stone Aerospace, Inc.

Piedra-sombra Corporation, Inc.

Other

Bartholomew P Hogan

William C Stone

A power conversion module for use with optical energy transfer and conversion system has a hemi-spherically configured housing, an array of photovoltaic chips mounted on the interior thereof, and inlet and outlet ports connected thereto. An end plate connected to the housing defines a cavity. An actively cooled high-power connector has one end connected to a fiber optic cable and the opposite end traversing the end plate and extending within the cavity. Beam forming optics within the cavity are in optical communication with the connector to disburse received optical energy in a hemispherical emission pattern of uniform flux toward an array of photovoltaic chips mounted in complementary configuration to the housing within the cavity, each chip spaced equidistantly from the beam forming optics. A heat sink within the housing has a plurality of fluid channels therethrough through which a work fluid removes heat via the outlet port. In alternative embodiments, the power conversion module includes a housing having a spherical configuration and a plurality of power conversion modules.

Power conversion module for use with optical energy transfer and conversion system

A method of recovery of optical fiber expended during a parabolic launch trajectory of a spacecraft is disclosed. An optical fiber adapted for transmission of high optical energy sufficient to launch the spacecraft is connected at one end to the spacecraft and is released during launching of the spacecraft. The optical fiber expended from the spacecraft is then engaged by a drum spooler following launch of the spacecraft and the fiber has been fully spooled out by the spacecraft. The optical fiber is then reeled in prior to the fiber contacting the Earth. The recovered optical fiber is then collected for processing, cleaning and rewinding for future use of subsequent series of launches for as many times as possible.

Method of recovery of optical fiber expended during launch of a spacecraft into low earth orbit using a non-line-of-sight optical power transfer system

A power conversion system for converting optical energy received from a fiber optic line to electrical energy, the system comprises a housing, a heat sink within the housing, a high power connector coupled to the line and having an end positioned within the housing, beam forming optics within the interior space positioned proximal to the connector, and a partially spherical end array and annular arrays of photovoltaic chips.

An optical energy transfer and conversion system comprising a fiber spooler and an electrical power extraction subsystem connected to the spooler with an optical waveguide. Optical energy is generated at and transferred from a base station through fiber wrapped around the spooler, and ultimately to the power extraction system at a remote mobility platform for conversion to another form of energy. The fiber spooler may reside on the remote mobility platform which may be a vehicle, or apparatus that is either self-propelled or is carried by a secondary mobility platform either on land, under the sea, in the air or in space.

Optical energy transfer and conversion system for planetary rover having drum configured fiber spooler mounted thereon

Optical energy transfer and conversion system for unmanned aerial vehicle having drum configured fiber spooler mounted thereon

Optical energy transfer and conversion system for autonomous underwater vehicle having drum configured fiber spooler mounted thereon

Optical energy transfer and conversion system for planetary rover having axially configured fiber spooler mounted thereon

Optical energy transfer and conversion system for remotely operated vehicle having axially configured fiber spooler mounted thereon

Optical energy transfer and conversion system for unmanned aerial vehicle having axially configured fiber spooler mounted thereon

A method of launching a spacecraft into low Earth orbit using a non-line-of-sight optical power transfer system. The method includes generating optical power at a base station and using an optical fiber to transmit the optical power generated to a launch vehicle via an actively cooled fiber spooler thereon. The optical power received by the launch vehicle is converted to another form of energy usable by the launch vehicle. The optical power is optically focused into a reaction chamber to impinge on a refractory target. A working fluid is regeneratively fed to a heat exchanger contained within the actively cooled fiber spooler. The working fluid is pre-heated within the heat exchanger and injected into the reaction chamber where the working fluid heats and expands. The exhaust is channeled through a rocket nozzle to produce thrust. In an alternative embodiment, the optical fiber expended during launch of a spacecraft is recovered.

Method of launching a spacecraft into low earth orbit using a non-line-of-sight optical power transfer system

Optical energy transfer and conversion system for remotely operated vehicle having drum configured fiber spooler mounted thereon

A fiber optic rotary joint for use in an optical power transfer system. The fiber optic rotary joint comprising a first housing element and a second housing element rotatable with respect to the first housing element. The first and second housing elements define a chamber. Optical connectors are disposed through the housing elements and have a beam expansion block positioned in the chamber. A laser is optically connected with the fiber optic rotary joint and transmits optical energy therethrough. Collimating optics aligned with the beam expansion blocks are orientated to direct the received optical energy to a position. The optical connectors and housing elements define a continuous coolant communication path with a coolant inlet and outlet. A rotary water coupling traverses through the housing elements. In an alternative embodiment, the fiber optic rotary joint also contains an actively cooled mirror positioned optically between the collimating optics.

Fiber optic rotary joint for use in an optical energy transfer and conversion system

An optical power transfer system for launching a spacecraft into low Earth orbit comprising a ground-based laser power generation station and a launch vehicle optically connected thereto. The generation station is capable of generating high optical power in the range of kilowatts to tens of megawatts and transferring the optical power generated to a launch vehicle to generate thrust. The generation station comprises a high power source, a chilling station, a laser, optical fiber, and at least one coupler. The launch vehicle comprises an actively cooled fiber spooler mounted thereon with a length of fiber for transmission of high optical energy circumscribing at least part thereof. The launch vehicle also contains a working fluid and fluid reservoir, a thruster assembly, an air intake and a storage chamber. In alternative embodiments, the launch vehicle may contain a beam switch assembly, multiple fiber spoolers and multiple thruster assemblies wherein at least one thruster assembly is gimbaled.

Non-line-of-sight optical power transfer system for launching a spacecraft into low earth orbit

An optically powered system for rapid, focused heating and melting of water ice. The optical wavelength is chosen to fall in a range where transmissivity through liquid water is higher than through ice. An alternative embodiment of the invention further comprises a length of fiber optic tether between source and output to allow for motion of the melt head. A further embodiment includes probing the ice using various sensing modalities exploiting the presence of the fiber in the ice, searching for biomarkers and characterizing the radiation/light environment for subsurface habitability, including photosynthetic potential and radiation environment as a source for energy.

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Rockville, MD, United States of America

Bartholomew P Hogan