Rosemount Aerospace Limited

Michael Robert Daup

Brian Brent Naslund

Andrew Sherman

David Patrick Potasek

Brian Daniel Matheis

Benjamin John Langemo

Joel Boelke

Richard Zhongmin Li

Andrew Edmund Sherman

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 aircraft pressure measurement device includes a pressure sensor, a pressure measurement path, a valve, and a fluid port. The pressure measurement path extends between an aircraft skin and the pressure sensor, and the valve is positioned within the pressure measurement path between the aircraft skin and the pressure sensor. The valve is configured to regulate airflow through the pressure measurement path, and the fluid port is configured to allow a pressurized fluid into the pressure measurement path to clear the pressure measurement path of debris. The improved pressure measurement device allows the aircraft to automatically clear debris from the pressure measurement path both during flight and while on the ground, removing the need for manual cleaning processes.

Aircraft pressure measurement device including an enhanced cleaning system

A micromechanical piezoresistive pressure sensor includes a diaphragm configured to mechanically deform in response to an applied load, a sensor substrate located on the diaphragm, and a number of piezoresistive resistance devices located on the sensor substrate. The piezoresistive resistance devices are arranged in a first planar array defining a grid pattern having two or more rows, each row being aligned in a first direction. The piezoresistive resistance devices are configured to be electrically connected in a number of bridge circuits, whereby the piezoresistive resistance devices in each row is electrically connected in an associated bridge circuit. A method of using the micromechanical piezoresistive pressure sensor is also disclosed.

Micromechanical redundant piezoresistive array pressure sensor

Apparatus and associated methods relate to determining altitude of an aircraft during flight based on properties of vortex shedding. A vortex-shedding projection is projected into the airstream adjacent to the exterior surface of the aircraft so as to cause vortex-shedding turbulence of the airstream. One or more downstream sound-pressure detectors, which are attached to the exterior surface of the aircraft downstream from the vortex-shedding projection, detect(s) a vortex-shedding frequency f of the vortex-shedding turbulence caused by the vortex-shedding projection. A processor determines the altitude of the aircraft based, at least in part, on the vortex-shedding frequency f of the vortex-shedding turbulence as detected by the one or more downstream sound-pressure detectors.

Determining altitude of an aircraft during flight based on vortex shedding

A tuned sensor system is disclosed. The tuned sensor system may receive an unsteady pressure from an external environment via a pressure inlet port. The pressure may have a first component that is substantially static and a second component that varies at a relatively high frequency. The pressure inlet port may conduct the unsteady pressure to a tuned path. The tuned path may filter the unsteady pressure, blocking the second component and communicating the first component, such as for use by a pressure sensor. The tuned sensor system may be compact and may include one or more turn in the tuned path so that the distance between the pressure inlet port and the sensor is less than the length of the tuned path. The tuned path may be entirely within the supporting structure of the tuned sensor system, easing installation, removal, and maintenance of the compact and modular system.

Pneumatic filter

A vane for dynamic flow angle measurements may have improved performance for time lag responsiveness over a prior art delta-shaped vane. In various embodiments, a gust sensing vane may have a cropped-delta shape and configured to align to a fluid flow direction, where the gust sensing vane comprises a forward portion having a leading edge and an aft portion having a first trailing edge and a second trailing edge. A cross-sectional area of the forward portion may have a triangular shape. Furthermore, a cross-sectional area of the aft portion has two substantially parallel sides to form the cropped-delta shape of the gust sensing vane. The gust sensing vane may be coupled to, and extend away from, a rotary hub.

Growing community of inventors

Minneapolis, MN, United States of America

Michael Robert Daup