Rosemount Aerospace Limited

Derrick David Hongerholt

Greg Allen Seidel

Dennis J Cronin

Charles George Huss

Eric David Haugen

Kaare Josef Anderson

Brian Daniel Matheis

William Kunik

Jeffrey P Danicich

Mark R Koosmann

Stephen R Meyer

Karl Gable Drutowski

Gary A Willms

Krishna M Rajana

Travis Jon Schauer

Timothy J Matuseski

In one example, a method includes receiving, over an aircraft data communications bus, a plurality of non-pneumatic inputs corresponding to aircraft operational parameters. The method further includes processing the plurality of non-pneumatic inputs through an artificial intelligence network to generate an air data output value, and outputting the air data output value to a consuming system for use when a pneumatic-based air data output value is determined to be unreliable.

Synthetic air data output generation

A method providing fault isolation, in an air data system which uses artificial intelligence to generate an air data parameter, includes generating the air data parameter as a function of a plurality of measured values such as static pressures. Then, estimates of each of the plurality of measured values is generated as a function of the generated air data parameter. Each measured value can then be compared to its corresponding estimate to determine if a difference between the measured value and its corresponding estimate exceeds a threshold and therefore indicates a fault in a device which provides the measured value.

Fault isolation method and apparatus in artificial intelligence based air data systems

A method of calculating a system level air data parameter for an aircraft, for example aircraft angle-of-attack (AOA) and/or angle-of-sideslip (AOS), includes measuring a plurality of local static pressures p. Next, a plurality of non-dimensional pressure ratios are each generated as a function of one of the plurality of local static pressures p, a predicted system static pressure Ps, and a predicted impact pressure q. Then, the system level air data parameter is calculated as a function of the generated plurality of non-dimensional pressure ratios. Air data systems having air data computers configured to implement the method are also disclosed. The air data systems can be Flush Air Data Systems (FADS), or other types of air data systems.

Method and apparatus for obtaining improved accuracy and range for air data parameters inferred from independent measurements of interdependent pressures

A system for determining physical characteristics of an incident flow stream over a surface of a vehicle includes a plurality of acoustic sensors mounted to the surface and configured to sense pressure fluctuations caused by the incident flow stream. The plurality of acoustic sensors provide output signals indicative of the sensed pressure fluctuations. Processing circuitry coupled to the plurality of acoustic sensors, measures flow velocity in a first direction as a function of the output signals of at least two of the plurality of acoustic sensors, and measures flow velocity in a second direction as a function of the output signals of at least two of the plurality of acoustic sensors. The processing circuitry is configured to calculate an angular direction of flow as a function of the first and second measured flow velocities.

System for and method of acoustic and through skin air data measurement

A built-in test system for an ultrasonic liquid level sensor that includes a transducer assembly having an ultrasonic transducer, and a switch that will be actuated when the ultrasonic transducer is in intimate contact with a surface of a tank in which level is to be determined. Once the switch is actuated to indicate that the ultrasonic transducer is properly coupled to the surface, a test sequence is initiated to determine that the level of ultrasonic transmissions are above a certain desired threshold for a selected period of time, and after which the circuit looks for echoes to determine the depth of the liquid in the tank. Thereafter, the test sequence is repeated for each cycle of level sensing.

Built-in test procedure for non-intrusive ultrasonic level sensing

A contaminant sensor is provided which has an ultrasonic guided wave transducer that is bonded to a wall in which the ultrasonic energy is transmitted. A detector reflector is provided at a selected distance from the transducer, which will reflect signals that are affected or changed by contaminants collecting on an exposed surface of the wall. A self test reflector is positioned closely adjacent to the transducer and provides a reflected signal that is substantially unaffected by contaminants on the exposed surface of the wall, but which reflects signals only when the transducer assembly is functioning properly, and is properly bonded to the wall. The signal that is reflected by the self test reflector changes when the bond loosens. The receiver is activated right after transmission ceases to determine if the transmitter is operating.

Ultrasonic sensor self test for integrity/performance verification

A liquid level sensor used for determining liquid levels in a sealed container includes a heat source bonded to the container, a first temperature sensor mounted on the container adjacent the heat source, and a second temperature sensor mounted on the container spaced from the heat source. The temperatures at the first and second temperature sensors are sensed while the heat source is operating, and the differential in the temperatures is measured and used to control power to the heater. Changes in the differential in temperature between the first and second temperature sensors indicates when the heat conductivity between the first and second temperature sensors changes, due to presence or absence of a liquid in the container at the level of the temperature sensors.

Apparatus and method to non-intrusively measure the level of liquid in a sealed container

A sensor for measuring the height of fluid in a vessel, the sensor including a mounting base shaped to be coupled to an exterior surface of a vessel. The sensor further includes a transducer having a pulse source for sending pulses into the vessel and an echo detector for detecting echoes of pulses emitted by the pulse source. The sensor further has a dry couplant located between the transducer and the mounting base, and a processor connected to the transducer for calculating the height of fluid in the vessel based at least in part upon the time elapsed between the pulses sent by the transducer and echoes detected by the echo detector.

Fluid level sensor with dry couplant

An ultrasonic ice detector that can be mounted directly to the skin of an aircraft includes a transducer that is coupled to the interior surface of the skin, and transmits acoustic vibrational energy through the skin. A reflector bar having a reflector surface is mounted on the interior surface of the skin at a location spaced from the transducer and is effective to reflect acoustic energy back to the transducer. The reflector bar is raised from the interior surface and preferably has a width equal to the width of the acoustic wave that is generated by the transducer at the reflector location. The transducer and reflector are non-intrusive and do not alter the aircraft skin structural integrity. The arrangement provides an accurate, responsive sensor for determining presence of ice or other contaminants on the exterior surface of the skin.

Growing community of inventors

Eagan, MN, United States of America

Derrick David Hongerholt