A method including operating a vehicle in a medium. The vehicle is subject to advection due to movement of the medium. The method also includes measuring, using a navigation system, positions of a vehicle over time. The method also includes measuring, using a directional sensor, a course-through-medium over the time. The method also includes calculating, using the positions and the course-through-medium, a variation of a speed-over-ground of the vehicle over the time as a function of the course-through-medium over the time. The method also includes concurrently estimating, using the variation, 1) an average speed-through-medium for the vehicle over the time, and 2) an advection rate of the medium, and 3) an advection direction of the medium.

A computer-implemented method, a system, and a computer program product for detecting objects are disclosed. The method can include receiving, by a computer communicatively connected to a plurality of anemometers positioned throughout the space, first sensor data from the plurality of anemometers, creating a baseline profile of airflow in the space based on the first sensor data, and receiving second sensor data from the plurality of anemometers at a different time than the first sensor data. The method can include comparing the second sensor data with the first sensor data to determine first different data, rendering, in response to determining that the second sensor data is different from the first sensor data, a representation of the object using the first different data and first location data related to the first different data, and calculating a vector associated with the object using the first different data and the first location data.

A non-nulling gas velocity measurement apparatus performs a non-nulling measurement of gas velocity parameters and includes: a non-nulling pitot probe; gas valves in fluid communication with a different entrant aperture of the non-nulling pitot probe via a different pressure channel; receives stagnant gas from the respective entrant aperture; receives a reference gas; receives a valve control signal; and produces a valve-selected gas based on the valve control signal, the valve-selected gas consisting essentially of the reference gas or the stagnant gas; and a plurality of differential pressure transducers, such that each differential pressure transducer: is separately and independently in fluid communication with a different gas valve, and that gas valve communicates the valve-selected gas to the differential pressure transducer; receives the valve-selected gas from the gas valve; and produces a differential pressure signal from comparison of the pressure of the valve-selected gas to a reference gas pressure.

The present invention relates to a synchronous sampling and measuring system and a method thereof for flue gas partition. The system includes a detection device arranged at an SCR outlet for simultaneous detection of flue gas from the pipelines in different areas, wherein the detection device is connected to a speed measurement device for measuring the speed of flue gas, the speed measurement device is connected to a central control unit and one end of a valve group, respectively, the other end of the valve group is connected to an air extracting device and a dilution unit, respectively, the control end of the valve group and the control end of the air extracting device are connected to a central control unit, respectively, the dilution unit is connected to a CEMS analyzer.

Systems and aircraft are provided. An avionics system includes a storage device and one or more data processors. The storage device stores instructions for monitoring an actual performance of the aircraft. The one or more data processors are configured to execute the instructions to: determine a first measured value of a flight characteristic of the aircraft at a first position of the aircraft; execute at least one flight maneuver between the first position and a second position of the aircraft; generate a predicted energy change between the first position and the second position based on the at least one flight maneuver and an energy state model; determine a second measured value of the flight characteristic of the aircraft at the second position; and generate an adjustment to the energy state model based on the first measured value, the second measured value, and the predicted energy change.

A method of inspecting an air data probe for damage or misalignment on a mounting surface includes retrieving reference data for the air data probe from a database, capturing images of the air data probe via a camera and generating dimensions from the captured images of the air data probe via a feature extractor. An alignment calculator analyzes the generated dimensions from the captured images of the air data probe and the reference data for the air data probe from the database to identify misalignment of the air data probe, and analyzes the generated dimensions from the captured images of the air data probe and the reference data for the air data probe from the database to identify damage of the air data probe. A maintenance recommendation for the air data probe is generated and outputted, based on the identified misalignment or damage of the air data probe.

A wind speed detection system and a wind speed detection method are provided. The wind speed detection system includes a pipe body, a pressure sensing module, a suction pump, and a controller. The pressure sensing module is connected to a first opening through a first pipe and connected to a second opening through a second pipe. The first pipe has a main pipe. Two ends of a first alternative pipe are connected to two ends of the main pipe. When the controller performs a self-checking operation, the main pipe is closed and the first alternative pipe is opened. The controller starts the suction pump to perform forward suction. The controller measures a first air pressure through the first pipe and measures a second air pressure through the second pipe by the pressure sensing module. The controller calculates a reference wind speed value according to the first and second air pressures.

The present invention relates to a method for self-testing an angle-of-attack probe comprising the steps of controlling an angular excitation of a rotary element that is rotatable about its equilibrium position according to known excitation characteristics; acquiring angular measurements relating to the rotation of the rotary element, determining a parasitic torque applied to the rotary element on the basis of the angular measurements and of the excitation characteristics; comparing at least one component of the parasitic torque with at least one predetermined threshold and detecting an operating fault in the probe when said component exceeds the predetermined threshold.

A system and method for automatically estimating a speed of an aircraft during a flight of the aircraft includes a determining module to determine at least one quantity which is representative of a force exerted on at least one control surface of the aircraft, a calculating module to calculate at least one speed of the aircraft and a transmitting module to transmit the one or more speeds of the aircraft which are calculated by the calculating module to a user device. The system makes it possible to estimate a speed of the aircraft without having to use the total pressure.

A method of health management and assessment for an air data probe comprises performing a calibration process for the air data probe prior to installation of the air data probe on a vehicle; performing an operational process after the air data probe is installed on the vehicle; computing residuals for individual pressure channels of the air data probe and an aggregated response function, based on outputs from the calibration process and the operational process; storing and trending the residuals over time; evaluating a trendline for the residuals against one or more threshold values; and announcing a message when one or more of the threshold values is exceeded, indicating that the health of the air data probe is compromised.