Abstract: A delivery system for feeding particulate matter to a target location at a well site, including a transportable conveyor belt assembly; one or more silos in fluid communication with a particulate supply line, each of the silo inlets extending through a side wall of the respective silo and disposed at a different location from the others along a longitudinal axis of the respective silo; and for each silo an enclosed chute detachably attachable thereto so as to receive into the chute particulate matter gravity fed out of the respective silo and convey such matter into the housing of the conveyor belt assembly. The silos, the chutes and the housing enclose the particulate matter as it passes from the silos through the chutes and conveyor belt assembly to the target location, to inhibit the release of dust generated from movement of the particulate matter from the silos to the target location.

Abstract: A first air data system for providing first aircraft air data parameter outputs is formed by a first electronics channel of a first multi-function probe (MFP) that is electrically coupled with a first electronics channel of a second MFP to receive static pressure data from the second MFP. A second air data system for providing second aircraft air data parameter outputs is formed by a second electronics channel of the second MFP that is electrically coupled with a second electronics channel of the first MFP to receive static pressure data from the first MFP. A third air data system for providing third aircraft air data parameter outputs is formed by a laser air data sensor that is configured to emit directional light into airflow about the aircraft exterior and to generate the third aircraft air data parameter outputs based on returns of the emitted directional light.

Abstract: A method can include generating image data of an interior of a fuel tank disposed within a wing of an aircraft, and determining, by a processing device, an amount of wing bending of the wing of the aircraft based on the generated image data of the interior of the fuel tank. The method can further include producing, by the processing device, a fuel measurement value representing an amount of fuel contained in the fuel tank based on the amount of wing bending of the wing of the aircraft, and outputting, by the processing device, an indication of the fuel measurement value.

Abstract: A delivery system for feeding particulate matter to a target location at a well site, including a transportable conveyor belt assembly; one or more silos in fluid communication with a particulate supply line, each of the silo inlets extending through a side wall of the respective silo and disposed at a different location from the others along a longitudinal axis of the respective silo; and for each silo an enclosed chute detachably attachable thereto so as to receive into the chute particulate matter gravity fed out of the respective silo and convey such matter into the housing of the conveyor belt assembly. The silos, the chutes and the housing enclose the particulate matter as it passes from the silos through the chutes and conveyor belt assembly to the target location, to inhibit the release of dust generated from movement of the particulate matter from the silos to the target location.

Abstract: A method can include transmitting, from a light source, light through a fuel tank ullage, and determining, by a processing device, an amount of absorption of at least one wavelength of the transmitted light. The method can further include determining, by the processing device based on the amount of absorption of the at least one wavelength of the transmitted light, a chemical composition of the fuel tank ullage.

Abstract: Apparatus and associated methods relate to determining, based on a detected portion of a projected pulse of quasi-optical energy backscattered by water particles within a divergent projection volume of a cloud atmosphere, properties of the backscattering water particles. The pulse of quasi-optical energy is projected into the divergent projection volume of the cloud atmosphere. The divergent projection volume is defined by an axis of projection and an angle of projection about the axis of projection. The portion of the projected pulse of optical energy backscattered by water particles within the divergent projection volume of the cloud atmosphere is received and detected. Various properties of the backscattering water particles, which can be determined from the detected portion of the projected pulse backscattered by water particles can include particle density and/or particle size.

Abstract: An aircraft ice detection system is configured to determine a condition of a cloud and includes a radar transmitter, a radar receiver, optics and a splitter. The radar transmitter is configured to produce quasi-optical radiation. The optics are configured to direct the quasi-optical radiation from the radar transmitter to the cloud and receive reflected quasi-optical radiation from the cloud. The radar receiver is configured to receive the reflected quasi-optical radiation from the optics and the splitter is configured to direct the reflected quasi-optical radiation from the optics to the radar receiver.

Abstract: An aircraft ice detection system is configured to determine a condition of a cloud and includes a radar system, a lidar system, optics and a dichroic filter. The radar system is configured to project quasi-optical radiation to the cloud and receive reflected quasi-optical radiation from the cloud. The lidar system is configured to project optical radiation to the cloud and receive reflected optical radiation from the cloud. The optics are configured to direct the quasi-optical radiation and the optical radiation to the cloud and receive the reflected quasi-optical radiation and the reflected optical radiation from the cloud. The dichroic filter is configured to direct the quasi-optical radiation from the radar system to the optics, direct the optical radiation from the lidar system to the optics, direct the reflected quasi-optical radiation from the optics to the radar system and direct the reflected optical radiation from the optics to the lidar system.

Abstract: Overheat and fire detection for aircraft systems includes an optical controller and a fiber optic loop extending from the optical controller. The fiber optic loop extends through one or more zones of the aircraft. An optical signal is transmitted through the fiber optic loop from the optical controller and is also received back at the optical controller. The optical controller analyzes the optical signal to determine the temperature, strain, or both experienced within the zones.

Abstract: Overheat and fire detection for aircraft systems includes an optical controller and a fiber optic loop extending from the optical controller. The fiber optic loop extends through one or more zones of the aircraft. An optical signal is transmitted through the fiber optic loop from the optical controller and is also received back at the optical controller. The optical controller analyzes the optical signal to determine the temperature, strain, or both experienced within the zones.

Abstract: Overheat and fire detection for aircraft systems includes an optical controller and a fiber optic loop extending from the optical controller. The fiber optic loop extends through one or more zones of the aircraft. An optical signal is transmitted through the fiber optic loop from the optical controller and is also received back at the optical controller. The optical controller analyzes the optical signal to determine the temperature, strain, or both experienced within the zones.

Abstract: Overheat and fire detection for aircraft systems includes an optical controller and a fiber optic loop extending from the optical controller. The fiber optic loop extends through one or more zones of the aircraft. An optical signal is transmitted through the fiber optic loop from the optical controller and is also received back at the optical controller. The optical controller analyzes the optical signal to determine the temperature, strain, or both experienced within the zones.

Abstract: A delivery system for feeding particulate matter to a target location at a well site, including a transportable conveyor belt assembly; one or more silos in fluid communication with a particulate supply line, each of the silo inlets extending through a side wall of the respective silo and disposed at a different location from the others along a longitudinal axis of the respective silo; and for each silo an enclosed chute detachably attachable thereto so as to receive into the chute particulate matter gravity fed out of the respective silo and convey such matter into the housing of the conveyor belt assembly. The silos, the chutes and the housing enclose the particulate matter as it passes from the silos through the chutes and conveyor belt assembly to the target location, to inhibit the release of dust generated from movement of the particulate matter from the silos to the target location.

Abstract: A method can include generating reference image data representing a field of view of an interior of a fuel tank, and generating active image data representing the field of view of the interior of the fuel tank when the fuel tank contains fuel. The method can further include producing, by a processing device, a fuel measurement value representing an amount of fuel contained in the fuel tank based on the reference image data and the active image data, and outputting, by the processing device, an indication of the fuel measurement value.

Abstract: A method can include illuminating an interior of a fuel tank with one or more light pulses, and receiving reflected returns of the one or more light pulses at a light sensor array. The method can further include producing, by a processing device, three-dimensional image data of the interior of the fuel tank based on the received reflected returns, producing, by the processing device, a fuel measurement value representing an amount of fuel contained in the fuel tank based on the three-dimensional image data, and outputting, by the processing device, an indication of the fuel measurement value.

Abstract: A method can include transmitting, from a light source, light through a fuel tank ullage, and determining, by a processing device, an amount of absorption of at least one wavelength of the transmitted light. The method can further include determining, by the processing device based on the amount of absorption of the at least one wavelength of the transmitted light, a chemical composition of the fuel tank ullage.

Abstract: A method can include generating image data of an interior of a fuel tank disposed within a wing of an aircraft, and determining, by a processing device, an amount of wing bending of the wing of the aircraft based on the generated image data of the interior of the fuel tank. The method can further include producing, by the processing device, a fuel measurement value representing an amount of fuel contained in the fuel tank based on the amount of wing bending of the wing of the aircraft, and outputting, by the processing device, an indication of the fuel measurement value.

Abstract: A method can include emitting, from a light source, directional light through fuel contained in a fuel tank, and determining a refraction angle of the directional light after the directional light passes through an interface with the fuel. The method can further include determining, by a processing device, an index of refraction of the fuel based on the determined refraction angle, and determining, by the processing device, a density of the fuel based on the determined index of refraction of the fuel.

Abstract: A fluid powered circuit for a gearbox and a method for protecting a gearbox are disclosed. The fluid powered circuit includes a control circuit operatively connected to a clutch engagement circuit. The fluid powered circuit is selectively operable to either flow a fluid from a fluid supply source to the clutch or vent the fluid to the atmosphere. The method for protecting the gearbox includes flowing the fluid from the fluid supply source to the fluid powered circuit, measuring the speed of the shaft, measuring the pressure of the fluid entering the clutch engagement circuit, and flowing the fluid from the fluid powered circuit to the clutch upon detecting one or more conditions.

Abstract: A method of optically detecting the presence of a bimodal droplet size distribution in the atmosphere. The method comprising monitoring statistical fluctuations in a backscattered signal received from a series of pulsed laser light beams directed into a cloud and analyzing the statistics of the fluctuations of the backscattered signals to identify the presence of larger diameter droplets.