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In recent decades, missile guidance and control have advanced significantly, with methods like pure pursuit (PP), command to line-of-sight (CLOS), and proportional navigation (PN) enabling accurate target interception in uncertain environments through line-of-sight (LOS) tracking. In this work, we propose a novel 3D sliding pure pursuit guidance (3DSPP) law for controlling a surface-to-air missile against a maneuvering target. The algorithm is compared with established guidance laws such as zero-effort miss distance “ZEM-PN” and “3D-PP”, with performance metrics including the miss distance Md and time of closest approach tcap. The results demonstrate that the 3DSPP outperforms the conventional methods by achieving the lowest Md= 0.1497 m and the fastest tcap= 7.3853 s, ensuring more precise and rapid interception. The algorithm also exhibits superior robustness to noise and efficient energy management, making it a promising solution for real-world missile guidance systems.

In pursuit–evasion scenarios, the pursuer typically possesses a lethal zone. If the evader effectively utilizes perceptual information, they can narrowly escape the lethal zone while minimizing energy consumption, thereby avoiding excessive and unnecessary maneuvers. Based on optimal control theory, we propose a guidance law for achieving critical safe miss distance evasion under bounded control. First, we establish the zero-effort miss (ZEM) state equation for the evader, while approximating disturbances from the pursuer. Next, we formulate an optimal control problem with energy consumption as the objective function and the ZEM at the terminal time as the terminal constraint. Subsequently, we design an iterative algorithm that combines the homotopy method and Newton’s iteration to solve the optimal control problem, applying Pontryagin’s Maximum Principle. The simulation results indicate that the designed iterative method converges effectively; through online updates, the proposed guidance law can successfully achieve critical safe miss distance evasion. Compared to programmatic maneuvering and norm differential game guidance law, this approach not only stabilizes the evader’s evasion capabilities but also significantly reduces energy consumption.

The article presents the method of using a modified acoustic miss distance indicator applied together with the set of controlled aerial target imitators (ZSMCP) Jaskółka “Swallow” operated in the Polish Armed Forces. The described method enables the implementation of controlling and testing the new CZT imitators and inspect the technical condition of these, which are still operated.

In order to solve the problem of excessive miss distance and energy loss when tracking high maneuverable targets with fixed coefficient proportional navigation guidance (PNG) law, this paper proposes a value-policy decomposed twin delayed deep deterministic (VPD-TD3) policy gradient algorithm and designs a corresponding proportional guidance law with intelligent parameter adjustment. By designing an energy-based reward function, the problem of reward-strategy coupling in three-dimensional guidance is resolved, thereby optimizing the training process. This approach was used to design a navigation ratio and compared with traditional guidance law designs. Simulation results demonstrate that the VPD-TD3 guidance law, compared to traditional proportional guidance laws, can track targets with low miss margins while reducing energy consumption. It also exhibits good adaptability to untrained scenarios, robustness, and generalization capabilities.

This paper considers a conflict situation on the plane as follows. A fast evader E has to break out the encirclement of slow pursuers Pj1,...,jn = Pj1,..., Pjn , n ≥ 3, with a miss distance not smaller than r ≥ 0. First, we estimate the minimum guaranteed miss distance from E to a pursuer Pa, a ∈ j1,..., jn, when the former moves along a given straight line. Then the obtained results are used to calculate the guaranteed estimates to a group of two pursuers Pb,c = Pb, Pc, b, c ∈ j1,..., jn, b ≠ c, when E maneuvers by crossing the rectilinear segment PbPc, and the state passes to the domain of the game space where E applies a strategy under which the miss distance to any of the pursuers is not decreased. In addition, we describe an approach to the games with a group of pursuers Pj1,...jn, n ≥ 3, in which E seeks to break out the encirclement by passing between two pursuers Pb and Pc, entering the domain of the game space where E can increase the miss distance to all pursuers by straight motion. By comparing the guaranteed miss distances with r for all alternatives b, c ∈ j1,..., jn, b ≠ c, and a ∉ b, c, it is possible to choose the best alternative and also to extract the histories of the game in which the designed evasion strategies guarantee a safe break out from the encirclement.

With the evolution of modern warfare, the role of missile defense systems in air defense operations has become increasingly important. This paper proposes a novel launch strategy aimed at addressing the active defense problem in air-to-air combat scenarios, where the defending aircraft proactively launches defensive missiles to intercept incoming threats. On this basis, the paper performs online optimization, using the miss distance, impact angle, and maximum overload as performance metrics. For defensive missiles guided by proportional guidance, the optimization problem is transformed into equivalent parameter optimization, and the optimal launch timing is determined through multi-objective optimization. The results show that the algorithm significantly improves interception success rates and provides effective decision support for air defense operations.

The maximum attack zone of an air-to-air missile is significant for enhancing the effectiveness of beyond-visual-range combat. Firstly, the target aircraft and missile models are established, as well as the missile-target relative motion model. Then, two sets of mid-course composite guidance strategies and a miss-distance-relaxation simulation strategies are proposed. The impact of miss distance is introduced into the traditional golden section search optimization, and the optimization results of the traditional golden section search are improved by relaxing the restraints on miss distance. Finally, the effects of the improved composite guidance strategy and the miss-distance-relaxation simulation strategies are verified through the simulation results of the maximum attack zone. The results show that the proposed simulation and guidance strategies can achieve a larger missile attack range.

Aiming at the problems of high-frequency oscillation of line-of-sight (LOS) angular rate and overload saturation in the terminal guidance phase when the Proportional Navigation (PN) law intercepts high-speed and high-maneuvering targets, this paper proposes an improved augmented proportional navigation law for the terminal guidance phase. First, the two-dimensional relative motion relationship between the aircraft and the target is analyzed, and the shortcomings of the classical Proportional Navigation law and Augmented Proportional Navigation (APN) law are clarified. Then, a prediction term for the target’s LOS angular rate is introduced, and an improved guidance model is constructed by combining the remaining interception time and LOS angular acceleration, which optimizes the guidance trajectory by predicting the encounter point. Simulation results show that the improved guidance law can significantly reduce the peak normal overload and terminal fluctuation in the terminal guidance phase, and further reduce the miss distance, laying a foundation for the effective interception of high-speed and high-maneuvering targets.

To effectively intercept enemy ballistic missiles during the boost phase, the interceptor must possess high velocity and acceleration capabilities, necessitating a guidance mechanism capable of maneuvering precisely with the target. This paper analyzes the characteristics of booster phase interceptor missiles based on relevant research and establishes a trajectory simulation model. Considering the required guidance performance throughout the missile’s flight process, we design guidance laws for the initial, mid-course, and final stages to conduct trajectory simulations. The results demonstrate that the guidance law proposed in this paper outperforms the conventional guidance mechanism regarding miss distance, ballistic angle, and required overload. Moreover, it satisfies the interception accuracy requirements during the boost phase interception.

To address the challenges of large navigation errors and the demand for onboard autonomy and real-time performance in the orbital rendezvous phasing of a Mars sample return mission, this paper proposes a multi-impulse real-time planning method. By incorporating the updated navigation data before each maneuver, the method reconstructs the subsequent maneuver sequence in real time, enabling rapid determination of maneuver parameters to reduce the effects of errors. A Monte Carlo simulation process is established based on the high-precision Mars orbital dynamic model to evaluate the impact of navigation errors and real-time planning on the terminal miss distance, as well as the performance of different real-time planning schemes. Simulation results demonstrate that the proposed multi-impulse real-time planning approach can stably reduce the terminal miss distance to values within 1 km, achieving an 80% improvement in the accuracy compared with the open-loop planning method. This satisfies the stringent requirements on the phasing terminal state of Mars orbital rendezvous missions. The method significantly enhances the reliability of autonomous rendezvous under complex perturbations around Mars and provides a valuable reference for future Mars sample return missions.