Rosemount Aerospace Limited

Other

Roger Duane Foster

Dennis J Cronin

Thomas Jerome Bachinski

Timothy Thomas Golly

Brian Daniel Matheis

Brian Alan Gilkison

Steve F Alwin

Charles Jae Doolittle

David George Owens

Thomas D Amerson

Mark Charles Skarohlid

Patrick John Moynihan

Paul F Heine

An air data probe includes a probe head defining a longitudinal axis with a forward tip, and a turbulence inducing surface defined in the probe head aft of the forward tip. The turbulence inducing surface is configured and adapted to trip a fluid boundary layer passing over the probe head to transition from laminar to turbulent to control or reduce boundary layer separation resulting in consistent readings at high altitudes.

Air data probes

An air data probe includes a probe head and a raised portion. The probe head defines a longitudinal axis and includes a forward tip and a probe head surface. The raised portion is defined in the probe head surface aft of the forward tip. The raised portion is raised radially relative to the probe head surface. The raised portion is configured and adapted to trip a fluid boundary layer passing over the probe head to transition from laminar to turbulent for reducing boundary layer separation for consistent readings at high altitudes and/or high mach numbers. A method of manufacturing an air data probe includes forming a probe head and applying a raised portion to a surface of the probe head aft of the forward tip. Applying the raised portion to the surface of the probe head includes using brazing, additive manufacturing, adhesives and/or any other suitable technique.

A static pressure sensing probe has an aerodynamically shaped cross section, and extends laterally from an aircraft surface sufficiently so that an outer end of the probe is a short distance outside the boundary layer on the aircraft surface on which the probe is mounted. The probe has surface corrugations or ridges along the probe, and the ridges include an upstream ridge adjacent the leading edge, and a downstream ridge spaced rearwardly from the upstream ridge. The ridges cause pressure disturbances along the probe surfaces. Static pressure sensing ports are positioned on the surfaces of the probe relative to the ridges in regions of pressure disturbances caused by the ridges. The probes can be mounted on opposite sides of the aircraft and pneumatically or electrically connected to average the pressures from selected sets of ports.

Aerodynamically shaped static pressure sensing probe

A method of detecting errors in air data sensing systems having multi-function probes being used in combinations to define probe systems includes a step (A) of, for each probe system, making a first prediction of an aircraft parameter as a function of local angles of attack at two member probes of the particular system, and making a second prediction of the aircraft parameter as a function of local pressure ratios at the two member probes of the particular system. A step (B) is performed in which, for each of the probe systems, the first and second predictions of the aircraft parameter are compared to determine whether the first and second predictions are within a predetermined threshold of each other. Then, a step (C) is performed in which, for each of the probe systems, if the first and second predictions of the aircraft parameter are not within the predetermined threshold of each other, then the particular probe system is identified as having a malfunctioning member probe.

Error detection and fault isolation for multi-function air data probes and systems

An air data sensing probe such as a multi-function probe includes a barrel having multiple pressure sensing ports for sensing multiple pressures. Instrumentation coupled to the pressure sensing ports provides electrical signals indicative of the pressures. An inertial navigation system input of the probe receives electrical signals indicative of inertial navigation data for the aircraft. A neural network of the probe receives as inputs the electrical signals indicative of the multiple pressures and the electrical signals indicative of the inertial navigation data. The neural network is trained or configured to provide as an output, electrical signals indicative of an air data parameter.

Multi-function air data probes using neural network for sideslip compensation

In an iterative method of determining aircraft flight data parameters using first and second multi-function probes, an assumed value of a first aircraft parameter is defined to be equal to an initial value. Using the assumed value of the first aircraft parameter together with the respective local angles of attack determined at first and second multi-function probes, first and second estimates of a second aircraft parameter are calculated and compared. If the first and second estimates of the second aircraft parameter are within tolerance of each other, then the first aircraft parameter is approximately equal to the assumed value, and the second aircraft parameter is determined from the first and second estimates. If the first and second estimates of the second aircraft parameter are not within tolerance of each other, then an iterative process is continued to correctly determine the first and second parameters.

Iterative method of aircraft sideslip compensation for multi-function probe air data systems

A semi-flush air data sensing probe is formed as an elongated bubble housing directly supported on an aircraft surface having a generally longitudinally extending rounded outer edge surface with a rounded contoured leading end. The housing has top and bottom wall surfaces extending from the supporting surface to the rounded outer surface. The trailing end of the housing is smaller than the leading end and is contoured to provide for smooth airflow past the housing. A central longitudinally extending plane that bisects the housing and which is perpendicular to the supporting surface, forms a reference. A forwardly facing port is at the leading end and centered on the central plane, and a pair of angle of attack sensing ports are on the leading end and are symmetrically located on opposite sides of the longitudinally extending plane. A static pressure sensing port also is provided on the housing at a position along the rounded outer edge surface and spaced downstream from the leading end.

Semi-flush air data sensor

A method of and apparatus for obtaining angle of attack, local static pressure and local pitot pressure from measured pressure values at ports of a probe having angle measuring ports with angle measuring axes lying in a plane and a pitot port having an axis lying along an axis in the plane bisecting the angle between the measuring ports. A table of known values of angle of attack relative to measured pressure ratio at measured Mach numbers determined by P,/P,is stored in memory and used when P,is greater than the pressure sensed at the pitot port (P,), P,is the pressure measured at the one of the angle measuring ports that is higher than the pressure measured at the other angle measuring port, and P,is an average of the pressures at the angle measuring ports. The correlation of the ratio of measured pressures on the probe relative to angle of attack is determined using the known values P,/P,at different angles of attack either in wind tunnel tests or by computer simulation. The known values are stored in a look-up table in an onboard air data computer. The values that have been stored then can be retrieved to solve for the correct angle of attack, using the measured pressures P,, P,and P,. The angle of attack values are used with an algorithm to determine local pitot and static pressure.

Method of and apparatus for using an alternate pressure to measure mach number at high probe angles of attack

A removable auxiliary spool device is provided including a spool having a pair of end plates maintained fixed in parallel planes via a central portion about which a string of material may be stored. Further provided is a pair of end assemblies each having an end face and an engagement portion coupled to the end face for being removably coupled to an associated one of the end plates of the spool thereby allowing convenient dispensing of the string of material.

Growing community of inventors

Burnsville, MN, United States of America

Roger Duane Foster