Abstract: Solar thermal and chemical hybrid rocket configurations for mining and other space applications are disclosed. One aspect is a rocket propulsion system configured to provide rocket thrust, including a solar absorber, a rocket nozzle, and a solar power collection system configured to collect solar energy from the sun, generate an energy beam from the collected sunlight, heat the solar absorber to transfer heat to one or more pressurized propulsive gases, and expel the heated pressurized propulsive gases through a rocket nozzle. A solar absorber can be formed from a granular collection or agglomeration of solids (e.g., of beads), which can be layered with more transparent layer(s) above and more absorbing layer(s) below to create a temperature profile in propellant(s) flowing through the absorber. A hybrid motor can provide an energy (e.g., solar) absorber for absorbing and transferring radiative energy as well as a combustion area.

Abstract: Pneumatically supported towers for low gravity applications are disclosed herein. In one aspect, an inflatable tower for use in vacuum environments can have a membrane configured to support a load when inflated with an inflation gas to a pressures less than 100,000 pascals and greater than 0.01 pascal. The inflation gas can be chosen to have a sufficiently low boiling temperature at the inflation pressure of the membrane that the gas will not condense to a liquid or solid within a defined range of temperatures in which the tower is designed to operate. The membrane can be configured to be packaged for transport in deflated condition and rolled onto cylinders from which the membrane can be later unfurled and inflated as part of the tower inflation process. The membrane can be further configured to progressively inflate beginning at a bottom or lowest level of the membrane during the tower inflation process.

Abstract: Systems and methods for fabrication of ceramics from celestial materials using microwave sintering and mechanical compression for space mining applications are disclosed. In one aspect, a chamber for sintering loose mineral material into solid ceramic shapes includes a plurality of zirconia insulting plates configured to clamp the mineral material and forming a cavity in which the mineral loose material is contained, and at least one dipole array configured to generate microwave energy and apply the microwave energy to the mineral material.

Abstract: Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.

Abstract: Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, a rocket propulsion system is configured to produce thrust for a spacecraft and includes: one or more optical elements configured to receive solar energy. The optical elements include: a first window configured to allow energy to enter the rocket propulsion system and form a concentrated energy beam, and a second window positioned to allow the concentrated energy beam to pass to the heat exchanger. The second window is spaced away from the first window to form a pressurized plenum chamber therebetween. The system further includes: a heat exchanger configured to receive the energy and use it to heat and pressurize a propulsion gas, and a rocket nozzle configured to expel the pressurized propulsion gas.

Abstract: Systems and methods are disclosed for mining lunar and Martian polar permafrost to extract gas propellants. The method can comprise identifying a plurality of near-polar landing sites in craters in which the surface comprises permafrost in perpetual darkness, wherein such landing sites have perpetual sunlight available at altitudes of about 100 to 200 m. A mining outpost can be established in at least one of the sites and a high altitude solar array deployed at the landing site using a lightweight mast tall enough to generate near continuous power for the outpost. Systems and apparatus are disclosed for mining the permafrost at the landing sites using radiant gas dynamic mining procedures. The systems can comprise a rover vehicle with an integrated large area dome for cryotrapping gases released from the surface and multi-wavelength radiant heating systems to provide adjustable heating as a function of depth.

Abstract: Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, an apparatus for collecting solar energy and simultaneously protecting against damage from a resulting energy beam includes a solar energy collection system including at least one concentrator and a target configured to use, store, or convert the solar energy, the collection system configured to cause solar energy to focus on the target, at least one sensor configured to detect misalignment of the concentrator by determining that some or all of the collected solar energy is offset from the target, and a safety system configured to redirect the energy or interpose a safety structure for shielding other non-target systems from receiving too much solar energy from the collection system.

Abstract: Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.

Abstract: An optical communication system is provided which includes an optical signal transmitter which communicates high bandwidth, high power frequencies. The optical signal transmitter includes a high efficiency/high power optical source such as an optical magnetron or a phased array source of electromagnetic radiation, and a modulator element. The modulator element may be within a resonance cavity of the high efficiency/high power optical source (intra cavity) or external to the cavity (extra cavity). The modulator element serves to modulate output radiation of the high efficiency/high power optical source to produce a modulated high frequency optical signal which may be transmitted through the air. The optical signal transmitter is particularly useful in providing the last mile connection between cable service operators and end users.

Abstract: An electromagnetic radiation source is disclosed that produces a single mode operation at a desired operating frequency. The electromagnetic radiation source is included in a wide variety of applications including a wireless power transmission system, a system for providing wireless/high-bandwidth communications in accordance with the present invention, a lighting system, an irradiation system, a weapons system, etc.

Abstract: An electromagnetic radiation source is disclosed that produces a single mode operation at a desired operating frequency. The electromagnetic radiation source is included in a wide variety of applications including a wireless power transmission system, a system for providing wireless/high-bandwidth communications in accordance with the present invention, a lighting system, an irradiation system, a weapons system, etc.

Abstract: An electromagnetic radiation source is disclosed. The electromagnetic radiation source includes an anode having a first conductor, a second conductor positioned relative to the first conductor, a plurality of pole pieces coupled to at least one of the first conductor and the second, and at least one mechanical phase reversal positioned along the first conductor or second conductor. Adjacent pole pieces are separated by a gap. The electromagnetic radiation source also includes a cathode separated from the anode by an anode-cathode space, electrical contacts for applying a dc voltage between the anode and the cathode and establishing an electric field across the anode-cathode space, and at least one magnet arranged to provide a dc magnetic field within the anode-cathode space generally normal to the electric field.

Abstract: An optical communication system is provided which includes an optical signal transmitter which communicates high bandwidth, high power frequencies. The optical signal transmitter includes a high efficiency/high power optical source such as an optical magnetron or a phased array source of electromagnetic radiation, and a modulator element. The modulator element may be within a resonance cavity of the high efficiency/high power optical source (intra cavity) or external to the cavity (extra cavity). The modulator element serves to modulate output radiation of the high efficiency/high power optical source to produce a modulated high frequency optical signal which may be transmitted through the air. The optical signal transmitter is particularly useful in providing the last mile connection between cable service operators and end users.

Abstract: A rotating wing aircraft has a rotating fuselage and wings. The aircraft is configured to rotate with the air passing over the wings because of the rotation providing the lift needed to keep the aircraft aloft. The wings have rudders coupled to them, such as at the tips of the wings, to provide force for laterally moving the aircraft. The aircraft may be able to remain airborne by hovering for a long period of time, on the order of days. Power for the aircraft may be provided by a central diesel electric generator, which provides power for electric motors that turn propellers that are on the wings. The aircraft may be used for any of a variety of applications, such as for surveillance, communications, or as a radar platform.

Abstract: A general purpose system and method for transmitting and coherently detecting UWB waveforms is predicated on the formation of conjugate pair of UWB waveforms. The in-phase and conjugate quadrature waveforms are orthogonal to each other and have the same power spectrum so that when squared and added they sum to the modulation envelope of the waveforms. By defining the waveform pair in this manner, a relatively simple and inexpensive transceiver can be used to transmit and receive the waveforms and yet preserve maximum range resolution and recover all possible energy in the returned waveforms. The transceiver transmits the in-phase UWB waveform and the conjugate quadrature UWB waveform with either a known time delay or orthogonal polarization relation. The time delay may be varied to suppress aliased return signals.

Abstract: A particle mass spectrometer includes a supersonic flow expansion nozzle, and a source of a gas having particles entrained therein. The source is in gas-flow communication with an inlet of the expansion nozzle. The particle mass spectrometer further includes a vacuum chamber in gas-flow communication with an outlet of the expansion nozzle, wherein the vacuum chamber has a sufficient vacuum that a gas flow through the expansion nozzle is supersonic, and a microphone having an active element and an output signal responsive to a movement of the active element. The active element is disposed within the vacuum chamber and is positioned so that particles that flow from the outlet of the expansion nozzle impact upon the active element. The output signal of the active element of the microphone is a measure of the masses of the entrained particles.

Abstract: An electromagnetic radiation source is provided which includes an anode and a cathode separated by an anode-cathode space. The source further includes electrical contacts for applying a dc voltage between the anode and the cathode and establishing an electric field across the anode-cathode space. At least one magnet is arranged to provide a dc magnetic field within the anode-cathode space generally normal to the electric field. A plurality of openings are formed along a surface of the anode which defines the anode-cathode space, whereby electrons emitted from the cathode are influenced by the electric and magnetic fields to follow a path through the anode-cathode space and pass in close proximity to the openings.

Abstract: An electromagnetic radiation source is provided which includes an anode and a cathode separated by an anode-cathode space. The source further includes electrical contacts for applying a dc voltage between the anode and the cathode and establishing an electric field across the anode-cathode space. At least one magnet is arranged to provide a dc magnetic field within the anode-cathode space generally normal to the electric field. A plurality of openings are formed along a surface of the anode which defines the anode-cathode space, whereby electrons emitted from the cathode are influenced by the electric and magnetic fields to follow a path through the anode-cathode space and pass in close proximity to the openings.

Abstract: An optical magnetron is provided which includes a cylindrical cathode having a radius rc, and an annular-shaped anode having a radius ra and coaxially aligned with the cathode to define an anode-cathode space having a width wa=ra−rc. The optical magnetron further includes electrical contacts for applying a dc voltage between the anode and the cathode and establishing an electric field across the anode-cathode space, and at least one magnet arranged to provide a dc magnetic field within the anode-cathode space generally normal to the electric field. A plurality of resonant cavities are provided with each having an opening along a surface of the anode which defines the anode-cathode space. Electrons emitted from the cathode are influenced by the electric and magnetic fields to follow a path through the anode-cathode space and pass in close proximity to the openings of the resonant cavities to create a resonant field in the resonant cavities.

Abstract: An optical magnetron generator is provided which includes an anode and a collector separated by an anode-collector space, a pair of output terminals operatively coupled to the anode and the collector to provide an electrical power output based on an electric field generated across the anode-collector space. The optical magnetron generator further includes one magnet arranged to provide a dc magnetic field within the anode-collector space generally normal to the electric field, and a plurality or resonant cavities each having an opening along a surface of the anode which defines the anode-collector space; an input for receiving electromagnetic radiation from an external source and operatively configured to introduce the optical radiation into the anode-cathode space to establish a resonance electromagnetic field within the resonance cavities.