Nonlinear Rolling Motion Analysis of a Canard-Controlled Missile Configuration at Angles of Attack from 0to 30deg in Incompressible Flow.

摘要

Dynamic subsonic wind tunnel test data are presented for four canard-controlled missile configurations at angles of attack from 0 to 30 deg. The configurations included three body build-up configurations (canard plus body, body plus tail, and canard plus body plus tail) with zero fin deflections. A canard plus body plus tail configuration with a 15 deg canard pitch control deflection was also tested. Nonlinear static and dynamic roll moment coefficients were extracted from the test data by fitting a differential equation of rolling motion to the test data using a global nonlinear least-squares procedure. The results indicated that the equation of motion was adequate to describe the canard-controlled configurations' rolling motion. Extracted linear roll damping coefficients showed that the roll damping moment is a nonlinear function of angle of attack for all the configurations. Roll damping was also found to vary with the missiles' roll angle at angles of attack above 20 deg. The results for the body build-up configurations show that there is a significant canard/tail interference present on the canard plus body plus tail configuration. The canard contribution to the induced roll moment is small. The results for the canard plus body plus tail configuration with the 15 deg pitch control deflection on the canards show that the canard deflection generally increases the roll damping moment. (Author)