飞翼布局战斗机独特的优势使其成为未来先进战斗机发展方向之一。面对具有新型舵面配置的飞翼布局飞机在着舰控制过程中存在的非线性、控制量冗余且耦合、舰尾流干扰等问题，建立了多操纵面无尾布局飞机六自由度非线性数学模型，提出了一种基于增量非线性动态逆（INDI）控制框架的直接力着舰控制律：非线性增量动态逆方法设计直接力航迹控制律、姿态角控制律和速度保持控制律，并设计了固定时间干扰观测器（FTDO）用于估计和补偿直接力控制回路和姿态控制回路之间的耦合，实现2个回路之间的动态解耦。考虑各种舵面特性和推力矢量的执行能力，设计了气动舵面与推力矢量一体化直接力控制方法，使用气动系数雅可比矩阵将非线性控制分配问题转化成增量线性控制分配问题，在线快速解算实际舵面偏转增量。仿真验证表明：在飞翼布局舰载机着舰控制律中引入基于增量非线性动态逆的直接力控制，可以提高该种布局形式舰载机在舰尾流干扰情况下快速修正航迹、抑制舰尾流干扰的能力，最终显著提高该类飞机着舰的精度，为飞翼布局舰载机上舰提供一种思路。

The unique advantages of the flying-wing aircraft make it one of the future directions for advanced fighter development. However， in the landing control process， flying-wing aircraft with novel rudder configurations faces such challenges as the nonlinearity， redundancy and coupling of control surfaces， and interference from ship wakes of. To address these issues， this paper establishes a six-degree-of-freedom nonlinear mathematical model of tailless aircraft with multiple control surfaces and proposes a direct force control law based on the Incremental Nonlinear Dynamic Inversion （INDI） control framework. This proposed method designs a direct force trajectory control law， an attitude angle control law， and a speed maintenance control law using the nonlinear incremental dynamic inversion approach. Additionally， a Fixed-Time Disturbance Observer （FTDO） is designed to estimate and compensate for the coupling between the direct force control loop and the attitude control loop， achieving dynamic decoupling between the two loops. Considering various control surface characteristics and the execution capability of thrust vectoring， an integrated direct force control method combining aerodynamic control surfaces and thrust vectoring is designed. The nonlinear control allocation problem is transformed into an incremental linear control allocation problem using the aerodynamic coefficient Jacobian matrix， allowing for rapid online calculation of actual control surface deflection increments. Simulation verification shows that introducing direct force control based on incremental nonlinear dynamic inversion into the landing control law of flying-wing carrier-based aircraft can enhance the ability of such aircraft to quickly correct trajectories and suppress airwake， which ultimately， significantly improves the precision of aircraft landing and provides a solution for the deployment of flying-wing carrier-based aircraft.