Rosemount Aerospace Limited

Matthew Michael Webb

Jason Lee Skoglund

Vincent R LoPresto

Jamison K Roman

Harold Edward Garnett

Brian Brent Naslund

Alexander Nathan Reid

Darren Glenn Jackson

Jeremiah Schweitzer

Jeremy S Burns

Peter Mann-Lai Chong

Jeremiah Schweizer

Vincent R Lopresto

Harold E Garnett

An ice detection sensor apparatus includes a strut body extending along a longitudinal axis. The strut body includes an axially extending wall extending around the longitudinal axis to surround an interior space, and an axial-facing end wall connected to an axial end of the axially extending wall. The axial-facing end wall partially bounds the interior space. A magneto strictive oscillator sensing element extends from the interior space, through the axial-facing end wall. The sensing element is engaged to the axial-facing end wall for oscillation along the longitudinal axis relative to the axial-facing end wall. A permanent magnet (PMG) element is integral with, e.g., monolithic with, the strut body.

Additive manufactured permanent magnets in magneto strictive oscillating ice detector sensors

A strut of a magnetostrictive oscillator includes a strut body which includes an airfoil with a first end, a second end, a leading edge, a trailing edge, a first side, and a second side. The strut further includes a heater element within the first side and second side, wherein the heater element connects from the first side to the second side. The strut further includes an electrically insulative layer between the heater element and the strut body. The heater element and the electrically insulative layer are integral with the strut body.

Additive material integrated heater deposited or embedded within an ice detector

A method of monitoring an ice protection system of a rotorcraft or an aircraft includes applying heat to rotating blades of the rotorcraft or the aircraft according to a heater duty cycle and determining an anticipated ice shed time for ice to shed from the rotating blades. Torque of the rotating blades is sensed, and an actual ice shed time for ice to shed from the rotating blades is determined based on the sensed torque. A status of the ice protection system is determined based on the anticipated ice shed time and the actual ice shed time, and the status of the ice protection system is output for consumption by a consuming system.

Heating prognostics system for ice protection system

A method for managing icing conditions on a rotary aircraft via one or more ice protection controllers. The method includes steps for receiving an icing condition signal from an icing rate sensor at an ice protection controller, determining, in response to the icing condition signal, a de-icing signal based at least in part a liquid water content (LWC). The method further includes steps for transmitting, via a digital communication bus disposed in at least part of a slip ring assembly, the de-icing signal to a upper distributor to cause the upper distributor to transmit power to one or more heating elements for a respective rotor blade.

Rotor ice protection systems and methods

Apparatus and associated methods relate to differentiating ice accretion caused by different supercooled water droplets on an airfoil of an aircraft. A sensor having a sensing surface region is mounted at a mounting location of the airfoil such that the sensing surface region is flush with a surrounding adjacent surface of the airfoil. Water particles of sizes less than or equal to a predetermined threshold do not impinge the sensor surface region at the mounting location when the aircraft is in flight. A sensor driver provides an excitation signal to the sensor. A signal detector detects a sensor signal responsive to the provided excitation signal. The sensor signal is indicative of water particles exceeding the predetermined threshold impinging the sensing surface region. In some embodiments, the sensing surface region is mechanically coupled to a resonant cavity. In other embodiments, the sensor is a surface resistance sensor configured to sense surface resistance.

Surface sensing for droplet size differentiation

A wiper arm assembly has a load member, a wiper arm, and a blade load cam with a cam slot. The load member mates with a joint disposed between first and second ends of the wiper arm. Changes in length of the load member impose a force in a lengthwise direction of the load member. The wiper arm is configured to rotate relative to the blade load cam about an axis proximate to the first end of the wiper arm. The cam slot is configured to vary the length of the load member as a function of a wiper angle in which the wiper angle is defined as the angle between the wiper arm and a starting position of the wiper arm.

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Burnsville, MN, United States of America

Matthew Michael Webb