Air data module

Abstract: An air data module is provided that is relatively small, lightweight, low cost, uses relatively low power, and is relatively easy to install, test, and maintain. The air data module includes a housing that is adapted to be mounted to an external surface of an aircraft, and includes at least a sensor compartment and an interface electronics compartment formed therein. A pitot-static probe is coupled to the housing and extends therefrom, and has a static pressure passageway that is in fluid communication with the sensor compartment. A plurality of static pressure ports are formed in the pitot-static probe and are in fluid communication with the static pressure passageway. A pitot pressure inlet port is formed in a distal end of the pitot-static probe. A static pressure sensor and a differential impact or absolute pitot pressure sensor, for example, may be mounted within the module and used to sense static pressure and impact or pitot pressure, respectively. The disclosed configuration makes the module less sensitive to a relatively high pressure pulse.

Abstract: In this paper, the design and fabrication techniques of a differential pressure sensor used in precision air data module (ADM) are described, and its performance test results are presented. A differential pressure senor for an ADM detects the differential pressure between static and total pressure, which can cover differential pressure of 0~20psi range with less than 1% accuracy. In order to satisfy these requirements, the piezoresistive Wheatstone bridge on the silicon diaphragm is used as a strain gauge. The p-type piezoresistors are implanted on the diaphragm under high doping concentration level for achieving smaller temperature sensitivity, and each resistor is designed to have same shape to compensate common errors. A constant current is applied to the bridge, which makes the temperature effects on piezoresistive coefficients and resistors compensate each other. The proposed differential sensor is designed through FEM analysis in order to satisfy nonlinearity requirements for an ADM. The repeatability and nonlinearity of the sensor are less than 0.09% and 0.27%, respectively, and the pressure hysteresis is less than 0.63%, which contributes to the root sum square (RSS) accuracy of 0.69%.

Abstract: An acoustic airspeed sensor system can include at least one acoustic transmitter configured to provide an acoustic pulse, a plurality of acoustic receivers including at least a first acoustic receiver positioned at a first radial distance from the at least one acoustic transmitter and a second acoustic receiver positioned at a second radial distance from the at least one acoustic transmitter. The first acoustic receiver is configured to receive the acoustic pulse at a first time and output a first receiver signal. The second acoustic receiver is configured to receive the acoustic pulse at a second time and output a second receiver signal. The sensor system can include an air data module operatively connected to the first acoustic receiver and the second acoustic receiver. The air data module is configured to determine true air speed (TAS) based upon a first signal delay, a second signal delay, and a wind angle.

Abstract: The present invention provides a serial communication processing device using standard software for multiple kinds of unmanned aerial vehicles. The serial communication processing device includes: a flight control computer electrically connected to all kinds of equipment loaded on an aircraft to monitor the operation status, controls a sub system including a control-surface driver loaded on the aircraft, receives a data link task from a ground remote control facility, and fulfills the task; a navigation device unit electrically connected to the flight control computer, operates in an integrated GPS/INS/air data module (ADM) navigation mode, generates a data signal to compensate the posture error and velocity error of INS, and transmits the signal to the flight control computer; and a data link module loaded on the flight control computer, processes data link messages, and executes an interface function for loaded communication equipment by performing functions such as processing ground commands, transmission of flight data to the ground, and monitoring the status of the wireless communication equipment, communication quality, and communication blockage. As described above, in the present invention, by connecting a navigation sensor (NSU), a data link (ADTC), and a task control sensor (EO/IR) to the flight control computer, serial communication interfaced with multiple kinds of unmanned aerial vehicles is performed, such that the posture error and velocity error of an unmanned aerial vehicle can be quickly corrected through serial communication. As a result, the unmanned aerial vehicle can continue a safe flight, and the system stability of the unmanned aerial vehicle can be maximized.