To address the angular constraint requirements during air-to-air missile attack trajectories, this study employs model predictive planning technology to establish state-space equations, The control quantities and terminal angular constraints are determined through systematic derivation of partial derivatives for state variables, control parameters, and terminal constraints, ultimately forming an angular constraint guidance algorithm based model predictive and correction. A three-degree-of-freedom digital simulation model was developed to validate the performance of this adaptive guidance algorithm. Comparative simulations with conventional angular guidance laws demonstrated that the proposed algorithm not only achieves precise terminal angular constraints but also outperforms traditional approaches in both angular implementation accuracy and ballistic robustness.