GB760431A - Improvements in or relating to centering device - Google Patents

Abstract

760,431. Aircraft controls. NORTHORP AIRCRAFT, Inc. May 26, 1954, No. 15527/54. Class 4. [Also in Group XXIV] In a mechanism wherein an axially-loaded "centering link " is employed to return to its neutral position a member such as an aircraft control column 4, Fig. 1, the centering link comprises a rod 18 having a widened end portion formed with a heart-shaped aperture 24, Fig. 5, coacting with two rollers 26, 27 on the column 4, so that the rod 18 pivots on one or other of the two rollers and, at or near the neutral position, ensures a positive centering moment about the pivot 5 of the control column. The column 4 actuates control surfaces through a link 7. The axial loading of rod 18 is provided by a device 3 which produces a force dependent on the aircraft speed to induce synthetic " feel " of airloads, said device comprising a diaphragm 13- separating two compartments which are respectively subjected to ram air and atmospheric air, the diaphragm being fixed to a slidable rod 10 pivoted to the rod 18. The distance between the axes of the rollers 26, 27 may be equal to or slightly less than the distance between the axes of the bearing surfaces in the aperture 24, the latter alternative eliminating any sharp bottoming effect. The rollers are mounted between a pair of discs 34, Fig. 4, housed in circular apertures in spaced plates 31 secured to a plane on the control column 4. Two clamping plates 35 of tear-drop shape are provided and in assembly the discs 34 and plates 35 are rotatively adjusted to locate the rollers correctly in the aperture 24, and subsequently the plates 35 and 31 are drilled to receive a locking bolt 39.