Abstract: An unmanned vehicle includes at least one navigation sensor configured to measure navigation data indicative of an environment, at least one status sensor configured to measure status data indicative of operating parameters of a hardware system and a computing system. The computing system includes a navigation engine configured to receive the navigation data and status data and plan a path through the environment and a security engine. The security engine is configured to detect that an unauthorized user is attempting to access the navigation data or the status data, send an alert to an authorized user indicating that the unauthorized user is attempting to access navigation data or status data, and send, to the unauthorized user, simulated data including one or both of simulated navigation data and simulated status data.

Abstract: An unmanned vehicle includes at least one navigation sensor configured to measure navigation data indicative of an environment, at least one status sensor configured to measure status data indicative of operating parameters of a hardware system and a computing system. The computing system includes a navigation engine configured to receive the navigation data and status data and plan a path through the environment and a security engine. The security engine is configured to detect that an unauthorized user is attempting to access the navigation data or the status data, send an alert to an authorized user indicating that the unauthorized user is attempting to access navigation data or status data, and send, to the unauthorized user, simulated data including one or both of simulated navigation data and simulated status data.

Abstract: Methods and apparatus for calibrating a gyroscope without rotating the instrument. In one example, a calibration method includes operating the gyroscope in a self-oscillation loop to generate x-axis and y-axis drive signals, adding forcing signals to the x-axis and y-axis drive signals to produce pick-off x-axis and y-axis signals, measuring the pick-off x-axis and y-axis signals to produce measurement data, determining a relative phase between the pick-off x-axis and y-axis signals, based on the measurement data and the relative phase, estimating parameters of the gyroscope, based on the measurement data and the estimated parameters, calculating estimated position signals to calibrate the gyroscope.

Abstract: Methods and apparatus for calibrating a gyroscope without rotating the instrument. In one example, a calibration method includes operating the gyroscope in a self-oscillation loop to generate x-axis and y-axis drive signals, adding forcing signals to the x-axis and y-axis drive signals to produce pick-off x-axis and y-axis signals, measuring the pick-off x-axis and y-axis signals to produce measurement data, determining a relative phase between the pick-off x-axis and y-axis signals, based on the measurement data and the relative phase, estimating parameters of the gyroscope, based on the measurement data and the estimated parameters, calculating estimated position signals to calibrate the gyroscope.

Abstract: The present invention relates to the field of optical imaging and therapeutics. More particularly, embodiments of the present invention provide minimally-invasive Fiberoptic Microneedle Devices (FMDs) for light-based therapeutics, which physically penetrate tissue and deliver light directly into the target area below the skin surface (FIG. 1). A preferred embodiment of the invention is a fiberoptic microneedle device comprising: (a) one or more silica-based needles capable of guiding light and comprising a length of about 0.5-6 mm, a base having an outer diameter in the range of about 100-150 micron, and a tip having an outer diameter in the range of about 5-20 micron; (b) a support member to which the needles are secured; (c) a ferrule comprising one or more holes for each of the needles, wherein the ferrule is operably configured to provide mechanical support to each needle at all or some portion of the length of the needle.

Abstract: The present invention relates to the field of optical imaging and therapeutics. More particularly, embodiments of the present invention provide minimally-invasive Fiberoptic Microneedle Devices (FMDs) for light-based therapeutics, which physically penetrate tissue and deliver light directly into the target area below the skin surface (FIG. 1). A preferred embodiment of the invention is a fiberoptic microneedle device comprising: (a) one or more silica-based needles capable of guiding light and comprising a length of about 0.5-6 mm, a base having an outer diameter in the range of about 100-150 micron, and a tip having an outer diameter in the range of about 5-20 micron; (b) a support member to which the needles are secured; (c) a ferrule comprising one or more holes for each of the needles, wherein the ferrule is operably configured to provide mechanical support to each needle at all or some portion of the length of the needle.

Abstract: Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power unit, with the controller being configured to automatically stop the auxiliary power unit while the auxiliary power unit is functioning normally. The controller can also be configured to automatically start the auxiliary power unit in-flight when power supplied or expected to be supplied to a subsystem of the aircraft has a non-zero value at or below a threshold value. The controller may also be configured to start the auxiliary power unit when a load or expected load on the subsystem meets or exceeds a threshold value.

Abstract: Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power unit, with the controller being configured to automatically stop the auxiliary power unit while the auxiliary power unit is functioning normally. The controller can also be configured to automatically start the auxiliary power unit in-flight when power supplied or expected to be supplied to a subsystem of the aircraft has a non-zero value at or below a threshold value. The controller may also be configured to start the auxiliary power unit when a load or expected load on the subsystem meets or exceeds a threshold value.

Abstract: Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.

Abstract: Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power unit, with the controller being configured to automatically stop the auxiliary power unit while the auxiliary power unit is functioning normally. The controller can also be configured to automatically start the auxiliary power unit in-flight when power supplied or expected to be supplied to a subsystem of the aircraft has a non-zero value at or below a threshold value. The controller may also be configured to start the auxiliary power unit when a load or expected load on the subsystem meets or exceeds a threshold value.

Abstract: Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.

Abstract: The present invention provides systems and methods for quantifying, purifying and separating fullerenes, such as single wall carbon nanotubes (SWNTs). The purification/separation combination provides nearly 100% carbonaceous impurity-free SWNT content from a given impure sample and provides a desired chirality and diameter from a given non-separated sample. Nanometrological validation of the success of purification and separation uses a pyroelectric detector and Raman spectroscopy in a single system, thus providing a critical aspect for the nanomanufacturing environment. The purification/separation and nanometrological validations may be performed in a feedback loop to provide a satisfactorily refined sample and optimized purification/separation settings.

Abstract: Methods and systems for starting aircraft turbofan engines are disclosed. A system in accordance with one embodiment includes an electrically-powered starter motor coupled to a turbofan engine to provide power to the turbofan engine during an engine start procedure. The system can further include an on-board, deployable, ram air driven turbine coupled to an electrical generator, which is in turn coupled to the starter motor to provide electrical power to the starter motor. In other embodiments, the ram air driven turbine can be replaced with a fuel cell or a battery. In still further embodiments, a single controller can control operation of both the engine starter and other motors of the aircraft.

Abstract: Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power unit, with the controller being configured to automatically stop the auxiliary power unit while the auxiliary power unit is functioning normally. The controller can also be configured to automatically start the auxiliary power unit in-flight when power supplied or expected to be supplied to a subsystem of the aircraft has a non-zero value at or below a threshold value. The controller may also be configured to start the auxiliary power unit when a load or expected load on the subsystem meets or exceeds a threshold value.

Abstract: Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.

Abstract: Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power unit, with the controller being configured to automatically stop the auxiliary power unit while the auxiliary power unit is functioning normally. The controller can also be configured to automatically start the auxiliary power unit in-flight when power supplied or expected to be supplied to a subsystem of the aircraft has a non-zero value at or below a threshold value. The controller may also be configured to start the auxiliary power unit when a load or expected load on the subsystem meets or exceeds a threshold value.

Abstract: Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.

Abstract: Integrated axially varying engine mufflers, and associated methods and systems. An arrangement in accordance with one embodiment of the invention includes a tailcone having a tapering external surface, a cavity disposed within the surface, and an engine muffler disposed within the cavity. The engine muffler can have a tapering outer surface, a porous inner surface disposed inwardly from the outer surface, and a plurality of cells disposed between the outer surface and the inner surface in fluid communication with the perforations of the inner surface. The inner surface can be positioned adjacent to an exhaust gas flow path having an entrance aperture and an exit aperture. Cells positioned toward the entrance aperture can have a first dimension extending away from the gas path, and cells positioned toward the exit aperture can have a second, different, dimension extending away from the exhaust gas path.

Abstract: Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.