Textron Corporation

Floyd W Carlson

Wesley L Cresap

David A Popelka

Michael L Hester

Joseph Mashman

A horizontal stabilizer structure for improved stabilizer performance at positive and negative angles of attack is disclosed in which a leading edge slat/spoiler extending lengthwise along the stabilizer is disposed forward and below the leading edge of the stabilizer. The leading edge slat/spoiler directs airflow along the under surface of the stabilizer at negative attack angles and disrupts airflow over the upper surface at positive attack angles.

Fixed leading edge slat spoiler for a horizontal stabilizer

This invention relates to controls for helicopters and more particularly to an improved collective pitch lever system in which the pilot, lever and pivot orientation is such that the possibility of pilot-induced oscillations is greatly reduced. In a further aspect, a collective pitch lever is provided in which the operative elements are so located as to be logically related to the elements controlled thereby in their respective mountings on the airframe. Further, the collective lever is provided in which the pilot-input motion for given command is harmonious or compatible with corresponding pilot inputs in fixed-wing aircraft.

Helicopter collective lever

A helicopter fuselage is coupled to a pylon to permit fore/aft pivotal movement of the fuselage relative to the pylon with resilient means connected between the pylon and fuselage to oppose and limit such pivotal movement. Structure is then provided to decouple the rotor control linkages to permit limited fore/aft rotation of the fuselage relative to the pylon upon change of location of the center of gravity without introducing control motion in the control linkages. The control linkages include control tubes extending longitudinally of the fuselage from a pilot input location. Bell cranks are connected to the control tubes and are coupled as to control the pitch of rotor blades. Structure connecting the fuselage and each bell crank alters the pivot points of the bell cranks relative to the fuselage. The positions of the bell crank pivot points depend upon rotation of the fuselage relative to the pylon.

Growing community of inventors

Fort Worth, TX, United States of America

Floyd W Carlson