GB813184A - Improvements in and relating to the control of model aircraft - Google Patents

Abstract

813,184. Model aircraft. ZAIC, F. June 1, 1956 [July 21, 1955], No. 16987/56. Class 4. A model aircraft is provided with automatic control mechanism which, during the relatively high speed of launching, moves the elevator to a no-lift position and then moves it upwardly when the aircraft speed decreases to ensure a correct landing approach. The aircraft comprises, at the tail end of the fuselage 11, a fin 12 and a tail plane 14 having an elevator 15 pivoted thereto at 16. A control vane 21 is pivoted at 22 to fin 12 and urged outwardly therefrom by an elastic element 24, the trailing edge of the vane being connected by a flexible link 28 to the trailing edge of the elevator 15. Pivotal movement of elevator 15 is limited by the lower edge of fin 12 and a notched extension 18. During the relatively high speed of launching airflow acting on vane 21 forces it against fin 12 thereby slackening link 28 and allowing the elevator to take up a no-lift position. After the launching force has been dissipated and the. speed of the aircraft reduced the tension in element 24 will pull the vane 21 outwardly from the fin and this movement will be transmitted through link 28 to elevator 15 causing it to move upwardly and trim the aircraft to a high angle of attack suitable for landing. The aircraft will be caused to circle during landing by the offset deflection of vane 21. The vane 21 may be mounted on tailplane 12 in spaced relation to fin 12 or it may be mounted on the fin so that its lower rear edge may cooperate with one or two cam surfaces secured to the elevator, the elastic element being connected between the elevator and the tail plane. In a further embodiment, the elevator or pitchcontrolling member may be mounted on the trailing edge of the wing of a tail-less all-wing aircraft.