GB1108391A - Aircraft having a spin indicator system - Google Patents

Abstract

1,108,391. Aircraft spin indicators. ELLIOTT BROS. (LONDON) Ltd. 7 May, 1965 [7 May, 1964], No. 19103/64. Heading B7W. [Also in Division G1] Apparatus for indicating whether or not an aircraft is in a spin comprises two gyroscopes for measuring the rates and senses of rotation of the aircraft about its yaw and roll axes, the gyroscopes being connected to individual indicating instruments arranged in a cluster so as to be easily readable by the pilot. Each gyroscope comprises a single axis rate gyro with a potentiometer pick-off. In the described embodiment, a relay is connected in the yaw rate gyro pick-off circuit, the relay being arranged to block the indicating instrument connected to the roll rate gyro until a predetermined rate of rotation about the yaw axis exists. Alternatively the yaw rate indication, indicated by the lower pointer 22, may be blocked by a relay in the roll rate gyro pick-off circuit or the blocking may be dispensed with. A further potentiometer pick-off is provided to sense the positions of the ailerons, this being connected to the upper indicator 22 in the same cluster of instruments as provided for the gyroscope indicators 26. A fail-safe arrangement may be incorporated, whereby the instrument pointers disappear from view in the case of a power failure, and a safety height switch may be connected in the power supply to the instruments to interrupt the supply when the minimum height at which recovery from a spin cannot be guaranteed has been reached.