In the digital docking system for large aircraft components, a redundant actuated parallel mechanism composed of multiple numerical control positioners are typically employed as actuators to adjust the spatial posture of aircraft components. Traditional posture control methods may lead to excessive local loads on positioners and reduced posture adjustment efficiency. To address these issues, this study investigates a coordinated optimization method for adjustment driving forces and trajectories. First, a rational combination of position control axes is derived based on screw theory. Aiming at the out-of-control error of distant measurement points caused by traditional position control axis assignment methods, the position axis combination is optimized in real time with the error sensitivity index of measurement points as the evaluation indicator. Simulation results demonstrate that this method can effectively reduce positioning error of large aircraft components, and the accuracy improvement for distant measurement points is particularly significant. Secondly, a load-balancing driving force optimization method is proposed, and the balanced distribution of driving force is realized via the penalty function method, so as to avoid excessive local load of positioners and large internal force during pose adjustment. Finally, considering the anisotropy of motion characteristics of different dimensions of the aircraft components, a trajectory planning method with differentiated time parameters is proposed, and the trajectory parameters are optimized by combining the particle swarm optimization and the dichotomy, which overcomes the problem of reduced pose adjustment efficiency caused by traditional homogeneous time parameters. To validate the effectiveness of the proposed method, an aircraft wing-fuselage alignment experimental platform is built, and multiple groups of comparative experiments are carried out. The experimental results demonstrate that the posture adjustment control method proposed reduces the average positioning error of measurement points to 0.27 mm, decreases the average internal force for aircraft components to 14.5 N, and shortens the average adjustment time by 23.1%. The research findings can effectively improve the accuracy, smoothness, and efficiency of aircraft component adjustment, providing technical support for precise and compliant assembly of aircraft components.