Abstract: In a method of facilitating flight operations, a payload is coupled to a spacecraft via a payload interface. The relative alignment of the payload and the spacecraft is dynamically adjusted (e.g., for thrust alignment) while the payload remains coupled to the spacecraft.

Abstract: A system for an entertainment venue includes an enclosure comprising a display surface, a light emitter disposed within the enclosure and configured to output a light, and a tube disposed within the enclosure. The tube is configured to receive the light and transmit the light through the display surface of the enclosure to form imagery.

Abstract: Disclosed herein are techniques for reducing the pitch between light-emitting diodes (LEDs) in an array of LEDs. According to an aspect of the invention, a method includes forming a plurality of stacks of layers on a surface of a semiconductor, with a p contact at an interface between each stack and a p-type layer of the semiconductor. The semiconductor is etched to form a plurality of mesa shapes corresponding to the plurality of stacks. A dielectric is formed on at least a portion of each mesa shape and at least a portion of each stack. A reflector is formed on at least a portion of the dielectric and at least a portion of the semiconductor to provide an n contact at an interface between the reflector and an n-type layer of the semiconductor. The reflector is physically separated from the p contact for each stack.

Abstract: Described are light emitting apparatus with self-aligned elements and techniques for manufacturing such light emitting apparatus. In certain embodiments, a method for manufacturing a light emitting apparatus involves forming a plurality of semiconductor layers including a first semiconductor layer, a second semiconductor layer, and a light emission layer between the first semiconductor layer and the second semiconductor layer. The method further involves forming an electrical contact and a spacer. The electrical contact is formed on a surface of the first semiconductor layer. The spacer is formed on the surface of the first semiconductor layer, around the electrical contact. After forming the spacer, the plurality of semiconductor layers is etched to form a mesa with sidewalls that extend from an outer edge of the spacer. The spacer operates as an etch mask that causes the electrical contact to be substantially centered between opposing sidewalls of the mesa.

Abstract: In a spacecraft for operating a thruster that includes a microwave source, a resonant cavity, and a source of propellant which the thruster converts to hot gas and directs via a nozzle to generate thrust, a method includes operating the thruster in an ignition mode in which the microwave source outputs power at a first rate, and operating the thruster in a propulsion mode in which the microwave source outputs power at a second rate higher than the first rate.

Abstract: A multi-mode thruster system for use in a spacecraft includes a microwave source; a cavity coupled to the microwave source and including a first inlet to receive a first fluid and a second inlet to receive a second fluid; and a nozzle provided at one end of the cavity. The thruster operates in a microwave electrothermal thruster (MET) mode to (i) generate a standing wave in the cavity using the microwave source and (ii) raise a temperature of the first fluid to generate a first hot gas that exits the cavity via the nozzle to generate thrust. The thruster operates in a chemical propulsion mode to (i) produce a reduction-oxidation reaction between the first fluid and the second fluid and (ii) generate a second hot gas that exits the cavity via the nozzle to generate thrust.

Abstract: In a method of facilitating flight operations, a payload is coupled to a spacecraft via a payload interface. The relative alignment of the payload and the spacecraft is dynamically adjusted (e.g., for thrust alignment) while the payload remains coupled to the spacecraft.

Abstract: To manage propellant in a spacecraft, the method of this disclosure includes storing propellant in a tank as a mixture of liquid and gas; transferring the propellant out of the tank; converting the mixture of liquid and gas propellant into a single phase, where the single phase is either liquid or gaseous; and supplying the single phase of the propellant to a thruster.

Abstract: A spacecraft structure for transporting propellant to be consumed by a thruster includes storing the propellant in the spacecraft in a solid state during at least a portion of a take-off procedure and supplying the propellant to the thruster in a liquid or vaporous state when the spacecraft is in space.

Abstract: Disclosed herein are techniques for reducing the pitch between light-emitting diodes (LEDs) in an array of LEDs. According to an aspect of the invention, a method includes forming a plurality of stacks of layers on a surface of a semiconductor, with a p contact at an interface between each stack and a p-type layer of the semiconductor. The semiconductor is etched to form a plurality of mesa shapes corresponding to the plurality of stacks. A dielectric is formed on at least a portion of each mesa shape and at least a portion of each stack. A reflector is formed on at least a portion of the dielectric and at least a portion of the semiconductor to provide an n contact at an interface between the reflector and an n-type layer of the semiconductor. The reflector is physically separated from the p contact for each stack.

Abstract: A GaN layer of micro-LEDs is exposed to ion implantation to amorphize one or more regions of the GaN layer. As a result, the GaN layer through which light rays propagate have non-uniform refractive indexes that modify propagation paths of some light rays. Ions are implanted in a region overlapping an active region that emits light to function as a converging GRIN (gradient-index) lens. The ion implanted regions collimate light rays that propagate along predetermined directions. As such, the light extraction from and the focus of the micro-LEDs is increased.

Abstract: Disclosed herein are techniques for reducing the pitch between light-emitting diodes (LEDs) in an array of LEDs. According to an aspect of the invention, a device includes an array having a plurality of LEDs and a reflector that is in Ohmic contact with at least two adjacent LEDs of the plurality of LEDs. Each LED of the plurality of LEDs includes a p contact, and the reflector is physically separated from the p contact of each LED of the plurality of LEDs.

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: Described are light emitting apparatus with self-aligned elements and techniques for manufacturing such light emitting apparatus. In certain embodiments, a light emitting apparatus includes a mesa formed by a plurality of semiconductor layers. The light emitting apparatus further includes an electrical contact on one of the semiconductor layers and a spacer around the electrical contact. The spacer is aligned with respect to the electrical contact, which permits etching around the spacer to define the shape of the mesa in such a way that the mesa is also aligned with respect to the electrical contact. In particular, the electrical contact is substantially centered between opposing sidewalls of the mesa.

Abstract: A multi-mode thruster system for use in a spacecraft includes a microwave source; a cavity coupled to the microwave source and including a first inlet to receive a first fluid and a second inlet to receive a second fluid; and a nozzle provided at one end of the cavity. The thruster operates in a microwave electrothermal thruster (MET) mode to (i) generate a standing wave in the cavity using the microwave source and (ii) raise a temperature of the first fluid to generate a first hot gas that exits the cavity via the nozzle to generate thrust. The thruster operates in a chemical propulsion mode to (i) produce a reduction-oxidation reaction between the first fluid and the second fluid and (ii) generate a second hot gas that exits the cavity via the nozzle to generate thrust.

Abstract: A light assembly can have an array of light sources forming rows and columns, where the array comprises a plurality of chips, and each chip comprises a subarray of light sources forming the rows and columns. A boundary between chips in the array can be configured to extend diagonally across rows and columns of the array such that, for each column across which the boundary extends, the first row of the plurality rows may not have a light source disposed in the respective column, but a second row of the plurality of rows has a light source disposed in the respective column.

Abstract: A thruster system for use in a spacecraft includes a microwave source, a resonant cavity coupled to the microwave source, wherein the microwave source is configured to generate a standing wave field in the resonant cavity, a nozzle provided at one end of the resonant cavity; and at least one injector configured to inject propellant into the resonant cavity so as to create a rotating circumferential flow. The standing wave field raises a temperature of the injected propellant to provide thrust by way of a hot gas exiting the resonant cavity via the nozzle.

Abstract: Disclosed herein are techniques for reducing the pitch between light-emitting diodes (LEDs) in an array of LEDs. According to an aspect of the invention, a device includes an array having a plurality of LEDs and a reflector that is in Ohmic contact with at least two adjacent LEDs of the plurality of LEDs. Each LED of the plurality of LEDs includes a p contact, and the reflector is physically separated from the p contact of each LED of the plurality of LEDs.

Abstract: Techniques related to laser lift-off masks are disclosed. In some embodiments, masking material is applied to a substrate that is attached to a plurality of semiconductor device sets. More specifically, the masking material is applied to one or more regions of the substrate between the semiconductor device sets. When the semiconductor device sets are embedded in a filling material, the masking material may be situated between the substrate and the filling material. Thus, transmitting light through the substrate toward the semiconductor device sets causes the substrate to become detached from the semiconductor device sets. However, the light is at least partially occluded by the masking material.

Abstract: A method in a spacecraft for transporting propellant to be consumed by a thruster includes storing the propellant in the spacecraft in a solid state during at least a portion of a take-off procedure and supplying the propellant to the thruster in a liquid or vaporous state when the spacecraft is in space.