Abstract

A tilt testing device simultaneously measures the angle of tilt of a plurty of nozzles of a multi-nozzle rocket motor and the direction in which each nozzle is tilted. A programable calculator computes the composite effect that such nozzle tilt would have on spin, pitch and yaw of a missile in flight. The calculator displays the numerical value of the composite effect, indicates the acceptance or rejection of the inspected work piece, and, when desired, prints a record of the resultant calculations. The tilt tester utilizes an electromechanical-pneumatic combination to lower a plurality of alignment determining probes into the nozzles while the work piece is clamped against a reference surface. An indexing rotating sensor assembly scans each probe for its angle of tilt and sends signals to the calculator for interpretation and display.