The optimization study on the mitigation strategy of hinge moment of aircraft with multi-control surfaces

Abstract

For the unique aircraft configuration, control surface efficiency and control characters of irregular aerodynamic configuration aircraft, a mitigation strategy of maneuver load of aircraft with multi-control surfaces has been put forward in this paper. Through comprehensive analysis of the contribution to the aerodynamic characteristics of the whole aircraft and the effect on hinge moment of control surface, take the advantage that the control surfaces are at the trailing edge of the airfoil, a optimization strategy, combined deflection of control surfaces of same function but non-equal angle, is adapted. Based on the optimization strategy, several control surface combination deflection schemes are proposed and comprehensively analyzed to make a reasonable control surface configuration, so as to reduce the hinge moment, improve the aerodynamic characteristics of the high angle of attack, improve the maneuverability and expand the maneuver envelope, thus the purpose of optimizing the aerodynamic characteristics of the whole aircraft and reduction of the hinge moment of the control surface is achieved.