Experimental investigation of the stability, control, and induced rolling moments of a canard missile airframe at a Mach number of 1.7

This report presents the results of an investigation of the stability, control, and induced rolling moments of a canard missile having cruciform wings of rectangular plan form at a Mach number of 1.7.A l l data including the measured hinge moments of the canard control surfaces, the axial forces on the complete missile, and the forces and moments on the various combinations of the missile components are presented in tabular form.Data concerned with the longitudinal stability and the rolling moments of the complete missile are presented graphically.with the wings interdigitated 4 5 O with respect to the forward fins the missile exhibits nearly linear normal-force and pitching-moment characteristics for most flight conditions and is statically stable in roll.However, interdigitation of the wings was not effective in reducing the rolling moments induced by the vertical canard controls such as would occur during lateral-acceleration maneuvers.is necessary in order to reduce the roll rate to acceptable values.These data show that 'Some method of roll control