Abstract: Systems and methods for transferring electric power to an aircraft during flight. Power transfer to the receiver aircraft is effected by means of a donor aircraft using a wired electrical connection. The method for transferring electric power includes: establishing an electrical connection between a receiver aircraft and a donor aircraft during flight; and transferring electric power from the donor aircraft to the receiver aircraft via the electrical connection. In one embodiment, electric power is transferred by way of a power cable deployed by the donor aircraft, a drogue attached to a trailing end of the power cable, and a probe mounted to the fuselage of the receiver aircraft, The probe and drogue are configured to form an electrical connection when fully engaged.

Abstract: A system for inspecting a wire segment includes an inspection apparatus and a visual imaging device. The apparatus includes an array of mirrors positioned about a centerline of the apparatus, wherein each mirror in the array is oriented such that a reflection of a first inspection zone of the wire segment in the array of mirrors forms a circumferential view of the first inspection zone of the wire segment, and the reflection from each mirror is within a field of view from a single vantage point. The visual imaging device is positioned at the single vantage point and oriented towards the wire segment such that the reflection from each mirror of the array of mirrors is within a field of view of the visual imaging device, the visual imaging device configured to capture at least one image of the reflection of the wire segment from the array of mirrors.

Abstract: A transmitter for providing energy to a beam-powered aircraft includes an energy source that outputs an energy beam having an elongated cross-section, and a mount. The mount is operable to vary an azimuth and an elevation of the energy beam, and operable to rotate the energy beam about a central axis of the energy beam.

Abstract: A system for inspecting a wire segment includes an inspection apparatus and a visual imaging device. The apparatus includes an array of mirrors positioned about a centerline of the apparatus, wherein each mirror in the array is oriented such that a reflection of a first inspection zone of the wire segment in the array of mirrors forms a circumferential view of the first inspection zone of the wire segment, and the reflection from each mirror is within a field of view from a single vantage point. The visual imaging device is positioned at the single vantage point and oriented towards the wire segment such that the reflection from each mirror of the array of mirrors is within a field of view of the visual imaging device, the visual imaging device configured to capture at least one image of the reflection of the wire segment from the array of mirrors.

Abstract: An apparatus for use in inspecting a wire segment is provided. The apparatus includes a guide tube sized to receive the wire segment, and an array of mirrors positioned about the guide tube. Each mirror in the array is oriented such that a reflection of the wire segment in the array of mirrors forms a circumferential view of at least a portion of the wire segment, and such that the reflection from each mirror is within a field of view from a single vantage point.

Abstract: Methods and systems according to one or more examples are provided for avoiding foreign object strikes on rotorcraft vehicles. In one example, a vehicle comprises a rotor comprising a rotor blade, a first sensor configured to provide first sensor information associated with an object proximate the vehicle, and a second sensor configured to provide second sensor information associated with the rotor. The vehicle further comprises a processor coupled to the first sensor and the second sensor configured to selectively control the rotor to minimize damage to the vehicle by the object based on the first and second sensor information.

Abstract: Pre-flight and episodic aircraft inspections to ensure operational safety and effectiveness are made faster, less costly and more effective by utilizing mobile model and data-driven sensor platforms inspecting known-state target vehicles. For autonomous aircraft, an inspection unmanned aerial vehicle (I-UAV) containing sensors inspects a utility unmanned aerial vehicle (U-UAV). Failure and system models of the U-UAV and the flight history of the U-UAV carried in the sensor data captured by the U-UAV's aircraft health management system are combined to guide the I-UAV to appropriately attend to the systems of the U-UAV and to drive the U-UAV systems into target states that will reveal otherwise hidden or latent failures.

Abstract: Systems and methods for transferring electric power to an aircraft during flight. Power transfer to the receiver aircraft is effected by means of a donor aircraft using a wired electrical connection. The method for transferring electric power includes: establishing an electrical connection between a receiver aircraft and a donor aircraft during flight; and transferring electric power from the donor aircraft to the receiver aircraft via the electrical connection. In one embodiment, electric power is transferred by way of a power cable deployed by the donor aircraft, a drogue attached to a trailing end of the power cable, and a probe mounted to the fuselage of the receiver aircraft, The probe and drogue are configured to form an electrical connection when fully engaged.

Abstract: Systems and methods for transferring electric power to an aircraft during flight. Power transfer to the receiver aircraft is effected by means of a donor aircraft using a wired electrical connection. The method for transferring electric power includes: establishing an electrical connection between a receiver aircraft and a donor aircraft during flight; and transferring electric power from the donor aircraft to the receiver aircraft via the electrical connection. In one embodiment, electric power is transferred by way of a power cable deployed by the donor aircraft, a drogue attached to a trailing end of the power cable, and a probe mounted to the fuselage of the receiver aircraft, The probe and drogue are configured to form an electrical connection when fully engaged.

Abstract: A methane transportation system is provided. The system may include a methane source configured to dispense methane at a first location, and an underwater vehicle. The underwater vehicle may include a propulsion system configured to transport the underwater vehicle underwater from the first location to a second location and a vessel defining a storage chamber configured to receive water and the methane from the methane source. The storage chamber of the vessel may have a pressure exceeding one atmosphere and a temperature during transport from the first location to the second location sufficient to form methane clathrate in the storage chamber. The system may further include a methane receiver configured to receive the methane released from the storage chamber at the second location. Related methods are also provided.

Abstract: A transmitter for providing energy to a beam-powered aircraft includes an energy source that outputs an energy beam having an elongated cross-section, and a mount. The mount is operable to vary an azimuth and an elevation of the energy beam, and operable to rotate the energy beam about a central axis of the energy beam.

Abstract: Systems and methods for ensuring that resonant inductive power transfer goes only to authorized users using encryption. Resonant inductive power transfer requires near-identical resonant frequencies in the transmitter and the receiver. The frequency of the power transfer signal changes on a schedule known only to the transmitter and receiver so a “power eavesdropper” cannot track the frequency well enough to efficiently receive power. To make the frequency transitions energetically efficient, a capacitive or inductive element is switched in or out of each circuit at moments of zero-crossing: zero charge on a capacitor or zero current in an inductor. To maintain phase alignment, either switching an inductor on the transmit side is nearly simultaneous with switching a capacitor on the receive side, or switching a capacitor on the transmit side is nearly simultaneous with switching an inductor on the receive side.

Abstract: Methods and systems according to one or more examples are provided for controlling a multi-rotor vehicle. In one example, a multi-rotor vehicle comprises an airframe and a plurality of rotors coupled to the airframe. The multi-rotor vehicle further comprises a controller, coupled to the airframe, configured to determine a rotational speed of each of the plurality of rotors, and adjust the rotational speed of each of the plurality of rotors such that the rotors do not dwell within a no-dwell zone comprising rotational speeds associated with one or more frequency aspects of the airframe.

Abstract: An animal-entry protection apparatus and related methods for protecting protected areas from animal entry are described. The animal-entry protection apparatus includes an eye-safe laser and a computing device. The animal-entry protection apparatus determines whether an animal has entered into a protected area. After determining that the animal has entered into the protected area, the animal-entry protection apparatus determines a location of the animal within the protected area and activates the eye-safe laser to emit a pulsed laser beam toward the location of the animal. The pulsed laser beam includes laser pulses having a laser-pulse rate that is between a first laser-pulse rate associated with a flicker-fusion frequency of a human eye and a second laser-pulse rate associated with a flicker-fusion frequency of an animal eye.

Abstract: A spacecraft including a frame including a joint coupling a first frame portion to a second frame portion, and an acoustic communication system configured to transfer acoustic data signals across the joint between the first frame portion and the second frame portion.

Abstract: Pre-flight and episodic aircraft inspections to ensure operational safety and effectiveness are made faster, less costly and more effective by utilizing mobile model and data-driven sensor platforms inspecting known-state target vehicles. For autonomous aircraft, an inspection unmanned aerial vehicle (I-UAV) containing sensors inspects a utility unmanned aerial vehicle (U-UAV). Failure and system models of the U-UAV and the flight history of the U-UAV carried in the sensor data captured by the U-UAV's aircraft health management system are combined to guide the I-UAV to appropriately attend to the systems of the U-UAV and to drive the U-UAV systems into target states that will reveal otherwise hidden or latent failures.

Abstract: Systems and methods for preventing high-radiant-flux light, such as laser light or a nuclear flash, from causing harm to imaging devices, such as a camera or telescope. The optical components of the imaging device have first and second foci. The second focus forms an image on an array of photodetectors and occurs at a large f-number. The first focus occurs at a small f-number in a gas that is dense enough to dissipate most of a femtosecond laser pulse of potentially damaging intensity and conditioned to easily undergo dielectric breakdown when exposed to high-radiant-flux light that is less intense than a femtosecond laser pulse. Dielectric breakdown forms a conductive arc that dissipates or scatters light, blocking high-radiant-flux light from reaching the array of photodetectors. Several methods may be used for conditioning the gas to break down quickly when exposed to laser attack.

Abstract: An optical heat exchanger and an associated system and method are provided to allow a vehicle, such as an unmanned air vehicle, a rocket or the like, to deliver more payload at a lower cost. The optical heat exchanger includes a support surface defining a plurality of tapered openings. Each tapered opening tapers from the first size proximate an outwardly facing end of the opening to a second smaller size proximate an inwardly facing end of the opening. The inwardly facing end of each tapered opening is in communication with the propellant. The optical heat exchanger also includes a plurality of lenses with each lens positioned proximate the outwardly facing end of a respective opening. Each lens is configured to receive an electromagnetic energy beam and concentrate the majority of the electromagnetic energy beam through the inwardly facing end of the respective tapered opening, thereby heating the propellant.

Abstract: An abraded wire detection system (“AWDS”) for detecting an abrasion on a wire in a fuel tank is disclosed. The AWDS includes an electrode on the fuel tank, a power source, and a current sensor in electrical series with the power source, wire, and the electrode. The current sensor includes circuitry that detects a current from the wire to the electrode. Additionally disclosed is an aircraft having a fuel tank, a wire within the fuel tank, and the AWDS.

Abstract: Systems and methods according to one or more embodiments are provided for reducing noise levels in a passenger cabin of an aircraft. In one example, an aircraft includes a wing coupled to a fuselage. The wing is configured to heat air to provide a first stream of air from a central portion of a wing segment of the wing extending between the fuselage and a first engine of an aircraft. The first stream of air is at a higher temperature than an adjacent stream of air from the wing.