Abstract: An orbital transfer vehicle system for cargo delivery is described herein. An orbital transfer vehicle (OTV) resides in space at a staging orbit. The OTV is configured for interfacing with a cargo pod at an insertion orbit to form a mated stack including the OTV and the cargo pod. The OTV is further configured for providing propulsion and rendezvous operations for transporting the mated stack to an intended target destination. Upon completion of delivery of the cargo pod to its intended target destination, the OTV then releases the cargo pod and returns to the staging orbit.

Abstract: Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a housing with a solid propellant positioned within the housing, and an injector ring positioned at a proximal end of the housing. The injector ring can include a plurality of angled injector units each including a first injector and a second injector angled towards an impingement point. A first fluid stream of a liquid propellant dispensed from the first injector can collide with a second fluid stream of the liquid propellant dispensed from the second injector to atomize the liquid propellant and form a spray fan formation. At least one of the first injector and the second injector can be positioned at an injection angle relative to the sidewall to create a swirl flow of the atomized injector fluid.

Abstract: Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.

Abstract: An energy conversion and transmission system includes a thermal energy converter configured to convert thermal blackbody radiation energy to thermal infrared (IR) energy and to output a thermal IR energy stream. The system further includes a transmission device configured to receive the thermal IR energy stream from the thermal energy converter at a first location and output the thermal IR energy stream at a second location. The transmission device supplies the thermal IR energy stream to a thermal IR energy destination at the second location.

Abstract: Systems and methods of manufacture of radiator fins. In one embodiment, a radiator fin made of carbon fiber is provided. In one aspect, the radiator fin is made of carbon fibers forming an interlaced pattern. In another aspect, the interlaced carbon fiber radiator fin is attached directly to a heat pipe, the heat pipe connected to a heat source.

Abstract: Various embodiments of a vortex hybrid motor system are described herein. In some embodiments, the vortex hybrid motor system can include a control system, a vortex hybrid motor, and an oxidizer injector. The oxidizer injector can be in fluid communication with a combustion zone defined by a fuel core and/or housing of the vortex hybrid motor. In some embodiments, at least one material regression sensor can be positioned along the fuel core and sensed data from the material regression sensors can be provided to the control system for determining one or more characteristics associated with the fuel core. The control system can control, based on the analyzed sensed data, the oxidizer injector for modulating an oxidizer flow rate delivered to the combustion zone to achieve a desired oxidizer-to-fuel ratio.

Abstract: A modular space reactor includes a plurality of sections, each section containing a component of an assembled reactor. Each section contains contents configured to be unable to sustain a fission chain reaction as an individual section and is configured to be separately launched into space from each other section. The sections are configured for assembly in space to form the assembled reactor configured for sustaining an active fission chain reaction only when all of the sections are assembled together. In embodiments, contents of a section include at least one of fissile fuel, reactivity control devices, neutron reflectors, neutron moderators, radiation shielding mechanisms, cooling systems, power conversion systems. In embodiments, the sections are further configured for disassembly in space for being separable for at least one of refueling, decommissioning, and disposal of the system so disassembled.

Abstract: Examples described herein include methods and computing systems which may include examples of calculating risk scores for certain natural disasters perils based on machine learning model outputs. For example, a machine learning model may weight each of the pixels of a map in accordance with the set of weights associated with a structure, to calculate a risk score for a particular natural disaster peril associated with that structure. A plurality of risk selections may be provided to a user computing device for selection by a user, with those risk selections being associated with that risk score. Advantageously, the computing system facilitates the interaction of datasets with different measurement parameters in a machine learning model. In normalizing datasets before providing the datasets to input nodes of a machine learning model, a computing system may efficiently provide hazard and vulnerability outputs of the machine learning model.

Abstract: A surface heating device and related method includes a heater assembly having a layer of dielectric material, thermal insulation material positioned adjacent to the heater assembly, an encapsulation layer surrounding the thermal insulation material and connected to the heater assembly, and a controller configured to control power delivered to the heater assembly to activate the dielectric material to generate heat.

Abstract: A method of moving a spacecraft from an initial orbit to a final orbit includes providing a spacecraft with thrusters traveling in an initial orbit that has a first RAAN. Thrusters are activated to move the spacecraft into a transfer orbit having more eccentricity than the initial orbit. A RAAN of the transfer orbit changes over time toward a target RAAN. The spacecraft enters an aerobraking orbit wherein the spacecraft is exposed to increased atmospheric drag to reduce orbit energy and reduce an apoapsis radius. Thrusters may be activated to increase the periapsis radius of the aerobraking orbit and cause the spacecraft to move into the final orbit, the final orbit having a final RAAN different from the first RAAN.

Abstract: An apparatus and related methods to separate liquid from a liquid/gas mixture, particularly in a low gravity environment. The apparatus includes a chamber having a capillary channel around a perimeter of the chamber, a liquid/gas inlet to the chamber, a liquid outlet from the chamber, the liquid outlet being positioned at the perimeter of the chamber to remove liquid from the capillary channel, and a gas outlet from the chamber. The gas outlet is positioned in the chamber, away from the capillary channel, to remove gas from the chamber. The chamber is structured to be readily fabricated using traditional machining techniques or additive manufacturing techniques. The chamber may be fabricated from various materials, including, for example, polymers, metals, composites, and ceramics. The chamber may function as a heat exchanger so that the apparatus can remove condensable vapors from the gas in the mixture in addition to what is already liquid.

Abstract: Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a combustion zone defined by a fuel core and/or motor housing. The combustion zone may include an upper zone and a central zone that each contribute to thrust created by the vortex hybrid motor. In some embodiments, an injection port configuration is described that includes a proximal injection port that may be controlled for modulating a delivery of an amount of oxidizer for adjusting an oxidizer-to-fuel ratio. In some embodiments, a fuel core configuration is described that provides radially varying gradients of fuel in order to achieve desired thrust profiles. In some embodiments, the fuel core may include a support structure and/or a proximal end of a nozzle of the vortex hybrid motor may extend into the fuel core.

Abstract: An apparatus to separate water droplets from an air stream. The apparatus includes an elongated tube, a reservoir, and a helix structure. The elongated tube has a first end, a second end, a longitudinal axis, an inner surface, an inlet opening at the first end of the elongated tube, the inlet opening arranged to accept the air stream tangentially relative to the longitudinal axis, and an outlet opening at the second end of the elongated tube. The reservoir is positioned at a second end of the elongated tube. The helix structure is positioned within the elongated tube and includes an upper surface, a lower surface arranged opposite the upper surface, an outer edge, and a variable pitch along a length of the elongated tube, the variable pitch providing a variable interior angle between an inner wall of the elongated tube and the upper surface of the helix structure.

Abstract: An expanding pin system is described that can provide automated and/or power controlled locking and unlocking of an expanding pin assembly in a mechanical joint. For example, the expanding pin system can include an actuation assembly that includes a single actuator (e.g., motor) to control an expanding pin assembly for locking and unlocking a mechanical joint.

Abstract: An expanding pin system is described that can provide automated and/or power controlled locking and unlocking of an expanding pin assembly in a mechanical joint. For example, the expanding pin system can include an actuation assembly that includes a single actuator (e.g., motor) to control an expanding pin assembly for locking and unlocking a mechanical joint.

Abstract: Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.

Abstract: The disclosure describes various aspects of a space-based radioisotope production system and methods use. In one aspect, a propellant is accelerated by decay energy to yield thrust. The decay energy is provided by activating a target material. In one aspect, a radioisotope rocket thruster may be recharged or “reactivated” in a space-borne charging station. The activated isotopes may also be used generate electricity. The space-borne charging station may also be used for irradiating other items in space for any number of purposes.

Abstract: A modular and scalable system to transfer space articles between space orbits. In one embodiment, the system employs a rendezvous vehicle which docks with a space article in an initial orbit, the connected stack then docking with a locomotive vehicle which maneuvers to a targeted orbit where the space article is detached. In one feature, the rendezvous vehicle and locomotive vehicle use a common propellant and the space article is a satellite.

Abstract: An energy conversion and transmission system includes a thermal energy converter configured to convert thermal blackbody radiation energy to thermal infrared (IR) energy and to output a thermal IR energy stream. The system further includes a transmission device configured to receive the thermal IR energy stream from the thermal energy converter at a first location and output the thermal IR energy stream at a second location. The transmission device supplies the thermal IR energy stream to a thermal IR energy destination at the second location.

Abstract: Systems and methods of manufacture of radiator fins. In one embodiment, a radiator fin made of carbon fiber is provided. In one aspect, the radiator fin is made of carbon fibers forming an interlaced pattern. In another aspect, the interlaced carbon fiber radiator fin is attached directly to a heat pipe, the heat pipe connected to a heat source.