Abstract: A fuel filter inspection method includes capturing an image of a fuel filter sample using an imaging device and sending the captured image to an image processor. The method further includes the image processor receiving the captured image, thresholding the captured image to generate a binary image, determining sizes for a plurality of particles present in the binary image, comparing the size of each of particle of the plurality of particles to a particle size threshold, and quantifying the number of particles of the plurality of plurality of particles with a size greater than the particle size threshold. The method further includes the image processor comparing the number of particles of the plurality of particles with a size greater than the particle size threshold to a particle count threshold, and modifying a graphical user interface to indicate a state of the fuel filter sample based on the comparison.

Abstract: In certain embodiments, an apparatus comprises a laser detector, a lens, a Global Positioning System (“GPS”) receiver, a digital ground map, a tilt measurement device, and one or more processors. The laser detector is operable to detect a laser light emitted from a laser source, the lens is operable to pass the laser light to the laser detector, the GPS receiver is operable to determine a GPS location of an aircraft, and the tilt measurement device is operable to determine a tilt angle of the aircraft. The one or more processors of the apparatus are operable to determine a line of sight based on the detected laser light, the GPS location, and the tilt angle. The one or more processors are further operable to determine a location of the laser source from an intersection of the line of sight and the digital ground map.

Abstract: A system includes a first optical fiber having a first fiber face at a first end. The system further includes a second optical fiber having a second fiber face at a second end. The first end and the second end are separated by a distance. The system also includes a first lens coupled to the first fiber face at the first end, and a second lens coupled to the second fiber face at the second end.

Abstract: A fuel filter inspection method includes capturing an image of a fuel filter sample using an imaging device and sending the captured image to an image processor. The method further includes the image processor receiving the captured image, thresholding the captured image to generate a binary image, determining sizes for a plurality of particles present in the binary image, comparing the size of each of particle of the plurality of particles to a particle size threshold, and quantifying the number of particles of the plurality of plurality of particles with a size greater than the particle size threshold. The method further includes the image processor comparing the number of particles of the plurality of particles with a size greater than the particle size threshold to a particle count threshold, and modifying a graphical user interface to indicate a state of the fuel filter sample based on the comparison.

Abstract: A fuel filter inspection method includes capturing an image of a fuel filter sample using an imaging device and sending the captured image to an image processor. The method further includes the image processor receiving the captured image, thresholding the captured image to generate a binary image, determining sizes for a plurality of particles present in the binary image, comparing the size of each of particle of the plurality of particles to a particle size threshold, and quantifying the number of particles of the plurality of plurality of particles with a size greater than the particle size threshold. The method further includes the image processor comparing the number of particles of the plurality of particles with a size greater than the particle size threshold to a particle count threshold, and modifying a graphical user interface to indicate a state of the fuel filter sample based on the comparison.

Abstract: In certain embodiments, a gimbal assembly includes an enclosure, a window, and a pivot assembly. The enclosure is centered on a first axis and the window is coupled to the enclosure. The pivot assembly is coupled to an interior portion of the enclosure and configured to pivot within the enclosure about a second axis, the second axis being perpendicular to the first axis. The pivot assembly includes a base portion, a mirror coupled at an angle to the base portion and configured to reflect light received through the window, and a sensor configured to receive the light reflected by the mirror. The pivot assembly is further configured to move within the enclosure in a direction that is perpendicular to the first axis and rotate about the first axis.

Abstract: In certain embodiments, a gimbal assembly includes an enclosure, a window, and a pivot assembly. The enclosure is centered on a first axis and the window is coupled to the enclosure. The pivot assembly is coupled to an interior portion of the enclosure and configured to pivot within the enclosure about a second axis, the second axis being perpendicular to the first axis. The pivot assembly includes a base portion, a mirror coupled at an angle to the base portion and configured to reflect light received through the window, and a sensor configured to receive the light reflected by the mirror. The pivot assembly is further configured to move within the enclosure in a direction that is perpendicular to the first axis and rotate about the first axis.

Abstract: In certain embodiments, an apparatus comprises a laser detector, a lens, a Global Positioning System (“GPS”) receiver, a digital ground map, a tilt measurement device, and one or more processors. The laser detector is operable to detect a laser light emitted from a laser source, the lens is operable to pass the laser light to the laser detector, the GPS receiver is operable to determine a GPS location of an aircraft, and the tilt measurement device is operable to determine a tilt angle of the aircraft. The one or more processors of the apparatus are operable to determine a line of sight based on the detected laser light, the GPS location, and the tilt angle. The one or more processors are further operable to determine a location of the laser source from an intersection of the line of sight and the digital ground map.

Abstract: A fuel filter inspection method includes capturing an image of a fuel filter sample using an imaging device and sending the captured image to an image processor. The method further includes the image processor receiving the captured image, thresholding the captured image to generate a binary image, determining sizes for a plurality of particles present in the binary image, comparing the size of each of particle of the plurality of particles to a particle size threshold, and quantifying the number of particles of the plurality of plurality of particles with a size greater than the particle size threshold. The method further includes the image processor comparing the number of particles of the plurality of particles with a size greater than the particle size threshold to a particle count threshold, and modifying a graphical user interface to indicate a state of the fuel filter sample based on the comparison.