The present invention belongs to the field of ship engineering, and provides a ship real wind measuring device calibration method. In this method a ship sway simulator is build using a 2-axis ganged platform, natural wind is simulating generated using a wind tunnel flow field. Then the ship sway simulator is controlled to simulate the ship spatial motion under the disturbance of stormy waves. Furthermore, the data of the wind speed and direction is obtained under different sway angles and speeds. So that the database of wind direction and speed measurement, attitude measurement, actual wind direction and speed measurement is formed. Subsequently, a calibration model based on BP neural network is constructed using this database, a ship real wind direction and speed calibration algorithm is formed, which can calibrate a ship real wind measuring device.

An industrial process field device includes a piezoelectric transducer, a sensor circuit, a test circuit, a controller and a communications circuit. The sensor circuit generates a sensor signal indicating a process variable based on a voltage across the piezoelectric transducer. The test circuit is configured to apply a voltage pulse having a pulse voltage to the piezoelectric transducer that induces a response signal, and capture peak positive and negative voltages of the response signal. The controller calculates a current condition value of the piezoelectric transducer based on the peak positive voltage, the peak negative voltage and the pulse voltage, and generates a diagnostic test result based on a comparison of the current condition value to a reference condition value corresponding to a properly operating piezoelectric transducer. The communications circuit communicates the process variable and the diagnostic test result to an external control unit over a process control loop.

A method for determining airspeed of an aircraft that includes determining a rotor model relating a power coefficient of a propeller of the aircraft to an axial inflow velocity through the propeller as a function of a set of rotor operating parameters; determining the set of rotor operating parameters by sampling an electronic control signal associated with an electric motor actuating the propeller; computing the axial inflow velocity through the propeller based on the set of rotor operating parameters using the rotor model; and determining the airspeed based on the axial inflow velocity.

A flight control system for an aircraft is disclosed. The flight control system includes one or more processors and a memory coupled to the processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive as input a plurality of first operating parameters that each represent an operating condition of the aircraft. The flight control system is further caused to determine a drag coefficient and a lift coefficient based on the plurality of first operating parameters. The flight control system is also caused to determine an estimated dynamic pressure based on both the drag coefficient and the lift coefficient.

Method and systems of determining when to replace an air data probe are provided. The method includes estimating air data probe temperatures based at least in part on available vehicle sensor data; tracking an amount of time an estimated temperature of the heating element is within at least one temperature range; and providing an air data probe replacement indication when a replacement threshold is met that is at least in part based on reaching a cumulative amount of time the heating element has an estimated temperature within the at least one temperature range.

A test fixture for determining calibration accuracy of an aircraft angle of attack sensor vane includes an outer disc, configured to be transiently fixed to an aircraft exterior portion surrounding the sensor vane, and an inner disc that includes a spring-loaded plunger configured to physically engage the sensor vane during tests. The inner disc is rotatable relative to the outer disc to accommodate rotation of the sensor vane when engaged with the inner disc. The outer disc includes a ring gear fixed thereto; the inner disc includes a manually operated knob containing a spur gear that reacts with the ring gear to rotate the inner disc when the knob is rotated. The outer disc is a clamshell structure formed of an upper annular disc and a lower annular disc rigidly secured together, and the inner disc is rotatably retained between the upper and lower annular discs.

Various implementation described herein are directed to a method for identifying a blockage in a pitot-static system. A pressure signal is received. Pressure fluctuations in the pressure signal are identified. A determination is made as to whether a blockage has occurred in the pitot-static system based on the identified pressure fluctuations.

A yaw auto-calibration method configured to calibrate an anemometer of a yaw control system to correct for yaw misalignment, includes collecting wind speed and wind direction data from the anemometer over a plurality of time periods. The method includes determining from the collected data a wind direction compensation signal associated with a plurality of wind speed ranges. The step of determining a wind direction compensation signal includes determining from a plotted performance value, a maximum performance value for each wind speed range and the step of determining further includes correlating the maximum performance value for each wind speed range with the associated average generator speed and plotting the maximum performance wind direction against average generator speed for each wind speed range. The maximum performance wind direction associated with the average generator speed for each wind speed range constitutes the wind direction compensation signal for the wind speed range.

A flight control system for an aircraft is disclosed and includes one or more processors and a memory coupled to the processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive as input a measured angle of attack that is based on a raw angle of attack and an estimated angle of attack based on a total pressure. The flight control system is further caused to compare the measured angle of attack with the estimated angle of attack to determine an error. In response to determining that the error between the measured angle of attack and the estimated angle of attack exceeds a threshold value, the flight control system determines the presence of a fault with an angle of attack value.

Techniques are disclosed for systems and methods to provide proactive directional control for a mobile structure. A proactive directional control system may include a logic device, a memory, one or more sensors, one or more actuators/controllers, and modules to interface with users, sensors, actuators, and/or other modules of a mobile structure. The logic device is adapted to determine a steering angle disturbance estimate based on environmental conditions associated with the mobile structure, and the steering angle disturbance estimate is used to adjust a directional control signal provided to an actuator of the mobile structure. The logic device may also be adapted to receive directional data about a mobile structure and determine nominal vehicle feedback from the directional data, which may be used to adjust and/or stabilize the directional control signal provided to the actuator.