Rosemount Aerospace Limited

Benjamin John Langemo

Brian Brent Naslund

Andrew Sherman

Matthew Paul Anderson

Joel Boelke

Jaime Sly

Kevin J Benning

Marcus Allen Childress

Michael Robert Daup

Ronald Fritz Liffrig

Peter Mann-Lai Chong

Kevin Benning

An air data system with a digital interface includes least one air data component, a receiving system and at least one digital connection. The at least one digital connection is between the receiving system and the air data component. A method for transmitting data in an air data system with a digital interface includes measuring at least one air data parameter with at least one air data component. The method includes generating a digital signal representative of the at least one air data parameter with the at least one air data component, sending the digital signal to a receiving system, and processing the at least one air data parameter with the receiving system.

Digital air data systems and methods

An air data system includes a laser emitter, a laser receiver, and an electronics module. The electronics module includes a processor and computer-readable memory encoded with instructions that, when executed by the processor, cause the laser to emit a coherent light pulse into a target volume locating within an exhaust flow aft of an aircraft. The laser receiver detects backscatter produced by the coherent light pulse interacting with the aft target volume, and the electronics module determines an air data parameter based on the backscatter and at least one of an engine parameter indicative of an engine condition of the aircraft and an aircraft parameter indicative of a state of the aircraft before outputting the air data parameter to a consuming system of the aircraft.

Laser airspeed measurement sensor incorporating reversion capability

A system and method of augmenting an existing air data system includes a multi-function probe (MFP) having a portion extending into an oncoming airflow about an exterior of an aircraft. A plurality of pressure sensing ports in the portion includes at least first and second static pressure ports. A first electronics channel of the MFP includes pressure sensors communicating with the first and second static pressure ports and is configured to determine first and second altitude values based on sensed static pressures at the first and second static pressure ports, respectively, that are independent of the existing air data system.

Architecture for providing enhanced altitude functionality to aircraft air data system

A device for use in a leak check test of an air data system includes a device body, an opening extending into the device body with the opening being configured to allow a probe to be at least partially inserted into the opening, and walls surrounding the opening with the walls being situated to seal a port in the probe such that air is prevented from flowing into or out of the port while the probe is inserted into the opening. A method of performing a leak check test includes covering the port with the device to seal the port, heating air within a gas path in the air data system, measuring the change in pressure of the air resulting from an increase in temperature of the air, and determining whether the air data system is sealed depending on the change in pressure of the air.

Method and device for leak check of air data system

A system includes an air data computer (ADC) having a single pneumatic port for receiving a pneumatic input, a plurality of electrical inputs for receiving one or more electrical signals, and an output. The ADC can transmit, via the output, air data parameters based on the received pneumatic input and the received one or more electrical signals. In a further example embodiment, the system includes a first pressure sensing probe discrete from the ADC and a pneumatic connection joining a pressure sensing port of the first probe to the pneumatic input of the ADC. Second and third pressure sensing probes pneumatically coupled to respective pressure modules, which output electrical signals to the ADC, the electrical signals being representative of pressures sensed by the second and third pressure sensing probes, respectively.

Advanced air data system architecture with air data computer incorporating enhanced compensation functionality

A sensor is configured to attach to a main body and includes a sensor body, a transducer, a transmitter, and a power source. The sensor body is configured to provide a smooth transition with a surface of the main body. The transducer is positioned within the sensor body and is configured to provide a sensed output. The transmitter is positioned within the sensor body and is configured to transmit the sensed output. The power source is positioned within the sensor body and is configured to provide electrical power to the transducer and the transmitter.

Low profile pressure sensor on the body of a vehicle

An aircraft probe includes a base, a strut that extends from the base, at least one port, and an electronics assembly insertable into the strut and removable from the strut. The electronics assembly includes at least one pressure sensor that is pneumatically connected to the at least one port to sense a first pressure when in the inserted position.

Aircraft probe with removable and replaceable embedded electronics

A system includes a probe, a transducer, and a sealing feature. The probe is detachable and includes a first gas path extending from a head to a mount. The transducer is configured to mate with the mount and includes a second gas path with an inlet configured to be in fluid communication with the outlet of the first gas path when the transducer is mated with the mount and at least one sensor disposed along the second gas path. The sealing feature includes a first membrane configured to allow pressure to be conveyed from the first gas path to the second gas path when the transducer is mated with the mount while preventing contaminants from entering the second gas path when the transducer is distant from the probe.

Detachable probe and sealing of an integrated air data sensor

A system includes a probe and a transducer. The probe is detachable and includes a mount having an outlet of a first gas path extending through the probe and a protrusion extending away from the mount. The transducer is configured to mate with the mount and includes a sealing feature adjacent an inlet of the second gas path in fluid communication with the first gas path. When the mount of the probe is adjacent the transducer, the protrusion interacts with the sealing feature such that the sealing feature is in an open position to allow air to flow from the first gas path into the second gas path. When the mount of the probe is distant from the transducer, the sealing feature is in a closed position to prevent contaminants from entering the second gas path.

A system for an aircraft includes a pneumatic sensor, an optical sensor, and a computer system. The pneumatic sensor is configured to sense a value external to the aircraft. The optical sensor is configured to emit an optical signal external to the aircraft and receive an optical response. The computer system is configured to receive the value and the optical response. The pneumatic sensor and the optical sensor do not extend beyond a boundary layer of the aircraft.

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Shakopee, MN, United States of America

Benjamin John Langemo