This application discloses a calibration method for navigation of an UAV including a vector sensor. The calibration method includes: collecting, during a flight of the UAV, a current correction value and current data during a current measurement performed by the vector sensor; acquiring previous data during a previous measurement performed by the vector sensor; acquiring an adjustment quantity according to the current data and the previous data; acquiring a next correction value according to the current correction value and the adjustment quantity; and acquiring next original data during a next measurement performed by the vector sensor, acquiring next valid data according to the next original data and the next correction value , and controlling headings and postures of the UAV according to the next valid data. With the calibration method of this application, the next valid data V.sub.k+1 more closely approximated to a true value can be obtained.

This application discloses a calibration method for navigation of an UAV including a vector sensor. The calibration method includes: collecting, during a flight of the UAV, a current correction value and current data during a current measurement performed by the vector sensor; acquiring previous data during a previous measurement performed by the vector sensor; acquiring an adjustment quantity according to the current data and the previous data; acquiring a next correction value according to the current correction value and the adjustment quantity; and acquiring next original data during a next measurement performed by the vector sensor, acquiring next valid data according to the next original data and the next correction value , and controlling headings and postures of the UAV according to the next valid data. With the calibration method of this application, the next valid data V.sub.k+1 more closely approximated to a true value can be obtained.

The system, configured for being on board an aircraft, includes a probe for collecting samples of contrail, a chamber for collecting the samples, a collecting conduit for conducting the samples from the collecting probe the collecting chamber and at least one device for measuring at least one parameter characterizing the samples in the collecting conduit while they are conducted from the collecting probe to the collecting chamber. By virtue of the system, it is not necessary to use a second aircraft that follows the aircraft for collecting samples of contrail.

The system, configured for being on board an aircraft, includes a probe for collecting samples of contrail, a chamber for collecting the samples, a collecting conduit for conducting the samples from the collecting probe the collecting chamber and at least one device for measuring at least one parameter characterizing the samples in the collecting conduit while they are conducted from the collecting probe to the collecting chamber. By virtue of the system, it is not necessary to use a second aircraft that follows the aircraft for collecting samples of contrail.

A system for an aircraft includes an optical sensor, at least one aircraft sensor, and a controller. The optical sensor is configured to emit a laser outside the aircraft, and the at least one aircraft sensor is configured to sense at least one aircraft condition. The controller is configured to determine a first operational state of the aircraft based upon the at least one aircraft condition and determine a second operational state of the aircraft based on the at least one aircraft condition, and operate the optical sensor to emit the laser at a first intensity during the first operational state and a second intensity during the second operational state, wherein the second intensity is greater than the first intensity.

A system for an aircraft includes an optical sensor, at least one aircraft sensor, and a controller. The optical sensor is configured to emit a laser outside the aircraft, and the at least one aircraft sensor is configured to sense at least one aircraft condition. The controller is configured to determine a first operational state of the aircraft based upon the at least one aircraft condition and determine a second operational state of the aircraft based on the at least one aircraft condition, and operate the optical sensor to emit the laser at a first intensity during the first operational state and a second intensity during the second operational state, wherein the second intensity is greater than the first intensity.

Radar, lidar, and other active 3D imaging techniques require large, heavy sensors that consume lots of power. Passive 3D imaging techniques based on feature matching are computationally expensive and limited by the quality of the feature matching. Fortunately, there is a robust, computationally inexpensive way to generate 3D images from full-motion video acquired from a platform that moves relative to the scene. The full-motion video frames are registered to each other and mapped to the scene coordinates using data about the trajectory of the platform with respect to the scene. The time derivative of the registered frames equals the product of the height map of the scene, the projected angular velocity of the platform, and the spatial gradient of the registered frames. This relationship can be solved in (near) real time to produce the height map of the scene from the full-motion video and the trajectory.

Method for monitoring the operation of a pair of turboprop engines of an aircraft comprising the steps of: detecting the sound pressure generated by the first or second turboprop engine generating a respective first or second signal x(t); iteratively calculating by means of a function Rx/Ry the similarity between the first/second signal x(t)/y(t) at a time T1 and at a time T2 subsequent to time T1; and storing the degrees of similarity calculated in successive iterations in order to detect situations of normal operation of the engines when the degrees of similarity fall in successive iterations within the interval of a first value and to detect a potential fault situation in the engines when the degrees of similarity depart from this interval.

Method for monitoring the operation of a pair of turboprop engines of an aircraft comprising the steps of: detecting the sound pressure generated by the first or second turboprop engine generating a respective first or second signal x(t); iteratively calculating by means of a function Rx/Ry the similarity between the first/second signal x(t)/y(t) at a time T1 and at a time T2 subsequent to time T1; and storing the degrees of similarity calculated in successive iterations in order to detect situations of normal operation of the engines when the degrees of similarity fall in successive iterations within the interval of a first value and to detect a potential fault situation in the engines when the degrees of similarity depart from this interval.

A connector includes a shell, an insert that fits within the shell, and a socket that extends within the insert. The socket includes a hood, a body within the hood, an annular tine extending from the body within the hood, an annular lip extending around the tine adjacent an end of the tine, and a cavity formed within the tine.