公开(公告)号：US20190233079A1

公开(公告)日：2019-08-01

申请号：US15886655

申请日：2018-02-01

Applicant: Bell Helicopter Textron Inc.

Inventor： Michael Reaugh Smith

IPC: B64C1/32 ,  B64C1/14

Abstract: An emergency escape window for a rotorcraft includes a window frame, a window pane set inside the window frame, a plurality of pins connecting the window frame to the fuselage of the rotorcraft, and a release mechanism having at least one actuator connected to a respective pin and constructed to retract the pin from the window frame. The escape window can then be pivoted away and/or completely detached from the fuselage in the event of an emergency to allow occupants to safely exit the rotorcraft. The disclosure also relate to a method of operating an emergency escape window for a rotorcraft and to a rotorcraft having an emergency escape window.

公开(公告)号：US20180329430A1

公开(公告)日：2018-11-15

申请号：US15594393

申请日：2017-05-12

Applicant: Bell Helicopter Textron Inc.

Inventor： Christopher Mike Bothwell ,  Jillian Samantha Alfred ,  Sung Kyun Kim ,  Marko Vuga ,  Matthew Hendricks ,  Mark Wasikowski ,  Thomas Parham ,  Michael Reaugh Smith

IPC: G05D1/08 ,  B64C27/82 ,  B64C27/04 ,  B64C27/57

CPC classification number: G05D1/0858 ,  B64C27/001 ,  B64C27/04 ,  B64C27/57 ,  B64C27/82 ,  G05D1/0825

Abstract: 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

公开(公告)号：US20180265186A1

公开(公告)日：2018-09-20

申请号：US15459781

申请日：2017-03-15

Applicant: Bell Helicopter Textron Inc.

Inventor： Christopher Edward Foskey ,  Frank Bradley Stamps ,  Michael Reaugh Smith

IPC: B64C27/00 ,  B64C27/10 ,  B64C27/82 ,  B64C27/22

CPC classification number: B64C27/001 ,  B64C27/10 ,  B64C27/22 ,  B64C27/82 ,  B64C2027/002 ,  B64C2027/8236 ,  B64C2027/8281

Abstract: A vibration isolation system for an advancing blade concept rotorcraft having a pylon assembly and an airframe. The vibration isolation system includes one or more pylon links each having first and second ends with the first end coupled to the pylon assembly and the second end coupled to the airframe. Each pylon link includes a vibration isolator, such as a Liquid Inertia Vibration Eliminator unit, that is interposed between the pylon assembly and the airframe. The vibration isolator system is operable to reduce or eliminate transmission of the pylon assembly vibration to the airframe.

公开(公告)号：US20190185179A1

公开(公告)日：2019-06-20

申请号：US15846783

申请日：2017-12-19

Applicant: Bell Helicopter Textron Inc.

Inventor： Cheng-Ho Tho ,  Michael Reaugh Smith

IPC: B64D45/00 ,  B64C1/14 ,  B64C1/34

CPC classification number: B64D45/00 ,  B64C1/1484 ,  B64C1/1492 ,  B64C1/34 ,  B64D2045/0095

Abstract: An in-flight impact protection system for aircraft. An aircraft having a panel, with a sensor disposed on the aircraft and adapted to transmit a signal and receive a reflection of the signal. A controller coupled to the sensor and adapted to receive the reflection from the sensor to determine whether an object is near the aircraft's panel. An inflation device, which includes a tube member, is coupled to the controller and positioned inside the aircraft, proximate the panel. After determining that the object is near the panel, the controller can activate the inflation device so that the tube member inflates, thereby buttressing at least a portion of the panel. The panel can be a windshield, fuselage member, or other suitable component.