Abstract: Systems, methods, and apparatus for magnetic maneuvering for satellites are disclosed. In one or more embodiments, a method for maneuvering satellites comprises applying, by a current source in a first satellite, current to an electromagnet in the first satellite. The method further comprises generating, by the electromagnet in the first satellite in response to the current, a magnetic field. Further, the method comprises maneuvering, by the first satellite, a second satellite via the magnetic field. In one or more embodiments, the electromagnet comprises a torque rod, an electric motor coil, and/or a solar array. In one or more embodiments, the second satellite comprises a ferromagnetic or ferrimagnetic material, a conductive material, or a combination thereof. In some embodiments, the second satellite comprises an electromagnet.

Abstract: An example method includes determining, by a flight planning system, a perceived noise at a surface location based on acoustic noise emitted by an aerial vehicle at an aerial location. The aerial location corresponds to a waypoint along a proposed trajectory. Further, determining the perceived noise includes estimating propagation of the acoustic noise from the aerial location to the surface location based on environmental features of the environment or weather data. The flight planning method also includes determining, by the flight planning system using a noise-abatement function, a noise-abatement value of the proposed trajectory for the aerial vehicle based on the perceived noise at the surface location. In addition, the flight planning method includes determining, by the flight planning system, a flight plan for the aerial vehicle based on the noise-abatement value of the proposed trajectory, and outputting the flight plan for use in navigating the aerial vehicle.

Abstract: A method of measuring air data of an aircraft is provided. The method includes emitting, by a laser disposed on the aircraft, laser light into air outside the aircraft, the laser tuned to induce a laser-induced plasma channel (LIPC) in the air. The method also includes sensing, by a sensor system disposed on the aircraft, at least one property of the LIPC. The method further includes computing, by a computing device disposed on the aircraft, the air data of the aircraft based on the at least one property of the LIPC.

Abstract: A radioisotope power source is disclosed. In one embodiment, the power source includes a dielectric liquid held within a vessel, a radioisotope material dissolved as an ionic salt within the dielectric liquid thereby forming an ionic salt solution, and a thermal-to-electric power conversion system configured to receive thermal heat generated from the decay of the radioisotope material and to generate electrical power.

Abstract: In an example, a drop tank for an aerial vehicle includes a body having an internal fuel reservoir configured to store fuel. The drop tank also includes an outlet coupled to the internal fuel reservoir for supplying the fuel from the internal fuel reservoir to a propulsion system of the aerial vehicle. Additionally, the drop tank includes a plurality of flight control surfaces extending outwardly from the body. The flight control surfaces are actuatable to adjust a flight attitude of the drop tank. The drop tank further includes a flight control system including a processor and configured to actuate the plurality of flight control surfaces to fly the drop tank to a target location when the drop tank is jettisoned from the aerial vehicle.

Abstract: An air data system for measuring an airspeed includes a pair of electrodes, and one or more magnets arranged relative to the pair of electrodes. The pair of electrodes includes a first electrode and a second electrode spaced apart from the first electrode along a first dimension by an air gap. The one or more magnets produce a magnetic field within the air gap. The air data system further includes an electronic circuit interfacing with the pair of electrodes. The electronic circuit outputs a voltage difference measured between the pair of electrodes across the air gap. A magnitude of the voltage difference indicates a magnitude of an air stream velocity through the air gap.

Abstract: A spacecraft includes a body defining an interior payload region and a particle dispersion layer disposed between the interior payload region and one or more exterior surfaces of the body. The particle dispersion layer is formed of one or more magnets having a persistent magnetic field. The spacecraft including the particle dispersion layer may be manufactured by obtaining a particle dispersion layer having a persistent magnetic field, identifying a directionality of the persistent magnetic field of the particle dispersion layer, and installing the particle dispersion layer between an interior payload region formed by a body of a spacecraft and one or more exterior surfaces of the body according to the identified directionality of the persistent magnetic field.

Abstract: Implementations provide an aircraft synthetic vision system (“SVS”) giving passengers an exterior view. Omitting windows reduces costs, lowers weight, and simplifies hypersonic aircraft design and construction. Unlike contemporary SVSs, no lag exists between the exterior view and actual aircraft motion. Passengers experience no airsickness associated with a visual and vestibular system feedback mismatch. Lag is eliminated by predicting aircraft interior motion based on sensor feedback, and (b) displaying video camera images transformed to match the predicted aircraft orientation when the images get through the display system latency. Implementations predict aircraft orientation and pre-transform—through the use of dead reckoning to adjust a video signal based on sensed aircraft dynamics and an aircraft electronic model—an image captured from a video camera to match that orientation at the image display time.

Abstract: A device to remove moisture from air. The device includes a container with an interior space that contains liquid saline solution. The interior space is configured to prevent the saline solution from escaping into the environment. A saline solution moving device moves the saline solution within the interior space. An air moving device moves air through the interior space. The movement of the air within the interior space exposes the air to the saline solution and enables moisture within the air to be absorbed into the saline solution.

Abstract: In an example, a method of supplying fuel to a fuel tank of a vehicle includes supplying, via a fuel line, fuel to a fuel tank of a vehicle at an initial rate of fuel flow, which causes an electrostatic charge to accumulate on a surface of the fuel in the fuel tank. The method also includes exposing an air medium in the fuel tank to ionizing radiation to increase a level of ionization of an air medium in the fuel tank and increase a rate of dissipation of the electrostatic charge. The method includes determining the level of ionization of the air medium in the fuel tank, and determining an increased rate of fuel flow based on a difference between the determined level of ionization and a baseline level of ionization. The method further includes supplying the fuel to the fuel tank at the increased rate of fuel flow.

Abstract: In an example, a power source for an electric propulsion system of an aerial vehicle includes a body having an electrical energy storage device configured to store electrical energy. The power source also includes a plurality of terminals coupled to the electrical energy storage device for supplying the electrical energy from the electrical energy storage device to the electric propulsion system of the aerial vehicle. The power source further includes a plurality of flight control surfaces extending outwardly from the body. The flight control surfaces are actuatable to adjust a flight attitude of the power source. Additionally, the power source includes a flight control system including a processor and configured to actuate the plurality of flight control surfaces to fly the power source to a target location when the power source is jettisoned from the aerial vehicle.

Abstract: Drag reduction systems and methods for an aircraft include a first vortex generator position on a portion of the aircraft, and a second vortex generator positioned on the portion of the aircraft. The first vortex generator is associated with the second vortex generator. The first vortex generator is asymmetrical to the second vortex generator in relation to a coupling axis in order to offset the longitudinal contribution of the vortex generator to vehicle cross-sectional area.

Abstract: Airflow-dependent deployable fences for aircraft wings are described. An example apparatus includes a fence coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel is configured to impede a spanwise airflow along the wing when the fence is in the deployed position. The fence is configured to move from the deployed position to the stowed position in response to an aerodynamic force exerted on the panel.

Abstract: Airflow-dependent deployable fences for aircraft wings are described. An example apparatus includes a fence of a wing of an aircraft. The fence includes a base that is coupled to the wing and a panel that is movable relative to the base and the wing between a stowed position in which the panel extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel is configured to impede a spanwise airflow along the wing when the panel is in the deployed position. The panel is configured to move from the deployed position to the stowed position in response to an aerodynamic force exerted on the panel.

Abstract: A rotorcraft includes a frame and an engine coupled to the frame. The rotorcraft also includes a rotor hub coupled to the engine and a plurality of rotor blades coupled to the rotor hub. Each rotor blade is configured to be adjusted to a negative pitch angle such that each rotor blade is oriented at a negative angle of attack. The rotation of the plurality of rotor blades at the negative pitch angle generates an updraft that, during a vertical take-off operation, applies an upward force to the rotorcraft to supplement lift generated by the plurality of rotor blades.

Abstract: Airflow-dependent deployable fences for aircraft wings are described. An example apparatus includes a fence coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel is configured to impede a spanwise airflow along the wing when the fence is in the deployed position. The fence is configured to move from the stowed position to the deployed position in response to an aerodynamic force exerted on a deployment vane of the fence.

Abstract: Automated deployable fences for aircraft wings are described. An example apparatus includes a fence, a latching actuator, and a biasing actuator. The fence is coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel impedes a spanwise airflow along the wing when the fence is in the deployed position. The latching actuator is movable between a first position in which the latching actuator maintains the fence in the stowed position, and a second position in which the latching actuator releases the fence from the stowed position. The latching actuator moves from the first position to the second position in response to a control signal received at the latching actuator.

Abstract: Disclosed are methods and systems for measuring concentration of known components in gas samples using an acoustic resonance technique. A system includes a resonant chamber, a sound generator positioned at and acoustically coupled to an opening of the resonant chamber, and an audio sensor positioned proximate to and in sound communication to the opening and configured to measure an acoustic spectrum. During operation, the sound generator produces a white noise such that the soundwaves of the white noise passes through a gas sample positioned in the resonant chamber. As the soundwaves pass through the gas sample, the audio sensor monitors the frequency spectrum and identifies any resonant frequency that, if present, would correspond to a specific component and the concentration of this component. Specifically, the component concentration is determined from the frequency response.

Abstract: Disclosed are methods and systems for measuring concentration of known components in gas samples using an acoustic resonance technique. A system includes a resonant chamber, a sound generator positioned at and acoustically coupled to an opening of the resonant chamber, and an audio sensor positioned proximate to and in sound communication to the opening and configured to measure an acoustic spectrum. During operation, the sound generator produces a white noise such that the soundwaves of the white noise passes through a gas sample positioned in the resonant chamber. As the soundwaves pass through the gas sample, the audio sensor monitors the frequency spectrum and identifies any resonant frequency that, if present, would correspond to a specific component and the concentration of this component. Specifically, the component concentration is determined from the frequency response.

Abstract: A system and method for a diffusing concentrator for efficient extraction of power from a beam of light. The diffusing concentrator may include an optical concentrator, the optical concentrator configured to receive beams of light and focus them towards a defined area at a defined distance, and an optical diffuser, the optical diffuser configured to receive the focused beams of light and spread the focused beams of light substantially uniformly over the defined area. The diffusing concentrator may also include a reflective surface configured to reflect stray light from the diffusing concentrator toward the defined area such as a photovoltaic array.