Bell Helicopter Textron Inc.

Textron Innovations Inc.

Matthew Wade Hendricks

Michael Reaugh Smith

Maurice D Griffin

Taeoh Lee

David E Heverly, Ii

Joshua Allan Edler

Jon Damon Bennett

Sung Kyun Kim

Jillian Samantha Alfred

Thomas Parham

Mark E Wasikowski

Christopher Mike Bothwell

Marko Vuga

David E Heverly Ii

Michael R Smith

David E Heverly

One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.

Mount for supporting a component and attenuating noise

A for providing control input adjustment for an aircraft, including one or more mode sensors disposed on an aircraft, a mode analysis system, the mode analysis system operable to receive mode sensor data from the one or more mode sensors, and operable to decompose the mode sensor data into decomposed mode data associated with fundamental modes of structural elements of the aircraft associated with the one or more mode sensors, and a flight control computer (FCC) disposed on the aircraft and connected to one or more actuators, the FCC operable to provide a control signal to the one or more actuators according to an association between the decomposed mode data and one or more rotorcraft parameters associated with the one or more actuators.

System and method for frequency domain rotor mode decomposition

In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes receiving a measured yaw rate from a yaw rate sensor or a measured lateral acceleration from a lateral acceleration sensor of the rotorcraft, filtering the measured yaw rate or the measured lateral acceleration using a filter to form a filtered measured yaw rate or a filtered measured lateral acceleration, and regulating a yaw rate or a lateral acceleration of the rotorcraft based on the measured yaw rate or the measured lateral acceleration. The filter includes a bandpass characteristic or a notch characteristic, and the filtering is configured to reduce lateral vibrations caused by airflow in a tail section of the rotorcraft.

System and method for rotorcraft active lateral shuffle filter

The vibration suppression system includes a vibration isolator located in each corner in a four corner pylon mount structural assembly. The combination of four vibration isolators, two being forward of the transmission, and two being aft of the transmission, collectively are effective at isolating main rotor vertical shear, pitch moment, as well as roll moment induced vibrations. Each opposing pair of vibration isolators can efficiently react against the moment oscillations because the moment can be decomposed into two antagonistic vertical oscillations at each vibration isolator. A pylon structure extends between a pair of vibration isolators thereby allowing the vibration isolators to be spaced a away from a vibrating body to provide increased control.

Rotorcraft vibration suppression system in a four corner pylon mount configuration

A mount system for supporting a transmission in an aircraft can include a first link coupled between a structure of the aircraft and the transmission, the first link having a first axis; a second link coupled between the structure of the aircraft and the transmission, the second link having second axis; a third link coupled between the structure of the aircraft and the transmission, the third link having a third axis; and a fourth link coupled between the structure of the aircraft and the transmission, the fourth link having fourth axis. A forward focal point of the first axis and the second axis has a different waterline component compared to an aft focal point of the third axis and the fourth axis.

Helicopter transmission mount system

A restraint system for a transmission in an aircraft can include a first strut having a first fluid chamber, a first piston resiliently coupled to a first housing with a first elastomeric member. The restraint system can include a second strut having second fluid chamber, a second piston resiliently coupled to a second housing with a second elastomeric member. The restraint system can include a fluid line between the first fluid chamber and the second fluid chamber. The first strut and the second strut collectively provide not only torque restraint, but also torque measurement and fore/aft vibration isolation.

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Grand Prairie, TX, United States of America

Matthew Wade Hendricks