Wing maneuvering load control method of high maneuvering aircraft

For high-maneuverability aircraft, maneuver loads constitute the primary design constraint for airframe structural strength, significantly impacting structural mass and fatigue damage accumulation. To address the requirements for lighter airframes and extended service life, a wing maneuver load control methodology was developed utilizing normal acceleration load factor as the feedback parameter and implementing active control surface deflection. Focusing on typical extreme maneuvers of conventional-configuration high-maneuverability aircraft, an optimal load control strategy was derived through systematic evaluation of wing control surface deflection effects, thereby establishing deflection parameters for subsequent simulations. Comparative analyses of wing maneuver load control effectiveness were conducted for multiple threshold-initiated strategies. Results demonstrate that initiating control at 75% of the maximum normal load factor and applying a 5° deflection command reduces peak wing bending moment by 10%. This approach shows significant potential in reducing structural load-bearing requirements and mitigating fatigue damage in high-maneuverability aircraft, supporting structural integrity enhancement.