Patent · US Active

Preventing helicopter loss of tail rotor effectiveness

US11801936B2 · kind B2 · utility

0Cited by

4References

18Claims

0Family size

Assignee

Textron Innovations Inc. · US

Inventors

Albert G. Brand · Fort Worth, US
Bradley Paul Regnier · Fort Worth, US
Matthew Hill · Keller, US

Key dates

Filing date	Jan 19, 2021
Grant date	Oct 31, 2023
Priority date	—
Expiry date	Nov 5, 2041

Classification

Technology area (CPC B)Performing Operations; Transporting
CPC primaryB64C2027/8209
WIPO fieldTransport
WIPO sectorMechanical engineering

Abstract

Embodiments are directed to a flight control system for a helicopter comprises a pilot interface configured to receive a control input, at least one electronically controlled actuator, and a computing device configured to translate the control input to an actuator command, wherein the computing device is further configured to apply yaw rate limits to the actuator command to avoid loss of tail rotor effectiveness. The yaw rate limits are associated with a vortex ring state (VRS) envelope for a tail rotor of the helicopter. The electronically controlled actuator comprises a tail rotor actuator. The control input is a pedal input.

Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.