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The probability of actuator lock, control surface damage, and thermal insulation failure on supersonic aircraft due to high speed and temperature is significant. Additionally, foldable fins are often used in missiles to increase the number of missiles that can be loaded onto a launcher and facilitate transportation, but this design presents the potential for malfunction and failure to open during flight. This study focuses on scenarios where control surfaces do not open or are partially damaged, leading to asymmetries and changes in the vehicle’s dynamics and aerodynamic model. The aim is to detect such failures and design a control system that can withstand these issues. To achieve this, the paper proposes an equivalent aerodynamic model representing the vehicle’s dynamics. The health of each fin is monitored using a nonlinear filter to estimate a parameter. Using separation theory, the dynamic system is divided into fast and slow subsystems, and a control signal for the faulty dynamics is designed based on back-stepping theory principles. Furthermore, the control allocation method is modified to accommodate the condition of the fins and generate the desired control moment. The proposed technique can quickly detect and isolate fin failures within seconds, while the designed controller effectively compensates for these failures.

This paper presents a performance analysis of missile control systems considering nonlinear pursuit dynamics and proportional navigation guidance (PNG) laws. In order to analyze the system stability, missile dynamics are simplified as a linearized model which is often considered in missile autopilot design and the well-known H ∞ approach is employed. A sufficient condition guaranteeing miss distance and the closed loop stability is proposed. The provided condition of missile system stability can be numerically easily verified by a linear matrix inequality (LMI).

This paper compares the operational mechanism of artillery to laser weapon, microwave weapon and guided missile, and summarizes the advantage and inherent shortcoming of traditional gun. By carrying out the simulation of different scenarios, the hot probability of artillery to target with different characteristics at different distance is obtained. For giving full play to the advantage of artillery and improving the operational, this paper cording the development direction of artillery technology and proposes the concept of cluster artillery, provides a new idea for the leapfrog discovery of artillery technology.

In long-range air defense multi-missile cooperative interception missions, due to the low accuracy of indication information and the lack of ground radar support, significant errors exist in estimating the true position of the target. This makes it difficult for the interception regions of multiple missiles to cooperatively cover the target error region. To address this issue, a multi-missile cooperative coverage guidance strategy based on an improved snake optimization (ISO) algorithm is proposed. First, a missile cooperative coverage model is established, with the interception regions treated as nodes in the coverage optimization problem, and the highest regional interception probability used as the optimization criterion. Next, the snake optimization (SO) algorithm is improved by enhancing its initialization, exploration, and exploitation phases, resulting in the ISO algorithm. Based on this, a multi-missile cooperative coverage guidance strategy is proposed, where the interception regions of each missile are optimally allocated within the target error region, expanding the overall interception region and improving the cooperative interception probability across the coverage area. Finally, the effectiveness of the proposed strategy is validated through numerical simulations.

To explore the feasibility of collaborative guidance for small tactical air-to-ground missiles and enhance their ability to cope with future complex battlefield systems, this article first elaborated on the principle of multi missile collaborative guidance. Then, based on the operational mission of air-to-ground missiles, several collaborative guidance combat modes were proposed. For specific combat modes, time and angle collaborative guidance laws suitable for air-to-ground missiles were designed and developed. Overcoming the problems of short flight time, fast speed and inability to adjust of air-to-ground missiles, and completing mathematical simulation calculations, the results show that this method can effectively solve the problem of coordinated guidance of air-to-ground missiles, achieve simultaneous attack, rapid attack, and multi target attack, and improve the penetration ability, battlefield survival ability, and strike ability of air-to-ground missiles against targets.

To address the operational requirements of engaging important surface vessels with multiple anti-ship missiles, this paper proposes an attack time cooperative guidance law based on distributed event-triggered mechanism. This law enables multiple missiles to simultaneously engage the target with minimal communication. First, design a two-stage guidance law that includes a cooperative guidance stage and an independent guidance stage. In the cooperative guidance stage, the time-to-go estimates of each missile are synchronized through inter-missile communication to achieve consistency. In the independent guidance stage, the missiles can independently guide themselves towards the target without the need for further communication. The key to the implementation of this strategy is the time-to-go estimates can represent the real time-to-go after achieving consensus. Furthermore, an event-triggered mechanism is introduced during the cooperative stage to effectively reduce the frequency of communication required during the cluster coordination process. Finally, the stability of the proposed cooperative guidance law is proven using Lyapunov theory, ensuring the absence of Zeno behavior. Numerical simulation results validate the effectiveness of the algorithm and confirm the correctness of the stability analysis.

This study introduces an innovative guidance law that allows for controlled impact time while meeting the missile’s field-of-view angle constraints. The equation that shows the missile-target relative movement is first established. A non-singular sliding mode guidance law is designed, leveraging sliding mode control theory. Under the field-of-view constraints, the impact time reaches the desired value, as proven according to the Lyapunov stability theory. The analyses derived from the numerical simulation support that the missile’s field-of-view angle remains within constraints throughout the attack process, and the control commands are smooth without singularities. The research findings hold significant value as a reference for designing multi-missile coordinated attack strategies.

Purpose A laser seeker is an important element in missile guidance and control systems, responsible for target detection and tracking. Its control is, however, a challenging problem due to complex dynamics and various acting disturbances. Hence, the purpose of this study is to propose a systematic design, tuning, analysis and performance verification of a nonlinear active disturbance rejection control (ADRC) algorithm for the specific case of the laser seeker system. Design/methodology/approach The proposed systematic approach of nonlinear ADRC application to the laser seeker system consists of the following steps. The complex laser seeker control problem is first expressed as a regulation problem. Then, a nonlinear extended state observer (ESO) with varying gains is used to improve the performance of a conventionally used linear ESO (LESO), which enables better control quality in both transient and steady-state periods. In the next step, a systematic observer tuning, based on a detailed analysis of the system disturbances, is proposed. The stability of the overall control system is then verified using a describing function method. Next, the implementation of the NESO-based ADRC solution is realized in a fixed-point format using MATLAB/Simulink and Xilinx System Generator. Finally, the considered laser seeker control system is implemented in discrete form and comprehensively tested through hardware-in-the-loop (HIL) co-simulation. Findings Through the conducted comparative study of LESO-based and NESO-based ADRC algorithms for the laser seeker system, the advantages of the proposed nonlinear scheme are shown. It is concluded that the NESO-based ADRC scheme for the laser seeker system (with appropriate parameters tuning methodology) provides better control performance in both transient and steady-state periods. The conducted multicriteria study validates the efficacy of the proposed systematic approach of applying nonlinear ADRC to laser seeker systems. Practical implications In practice, the obtained results imply that the laser seeker system, governed by the studied nonlinear version of the ADRC algorithm, could potentially detect and track targets faster and more accurately than the system based on the common linear ADRC algorithm. In addition, the article presents the step-by-step procedure for the design, field programmable gate array (FPGA) implementation and HIL-based co-simulation of the proposed nonlinear controller, which can be used by control practitioners as one of the last validation stages before experimental tests on a real guidance system. Originality/value The main contribution of this work is the systematic procedure of applying the ADRC scheme with NESO for the specific case of the laser seeker system. It includes its design, tuning, analysis and performance verification (with simulation and FPGA hardware). The novelty of the work is also the combination and practical realization of known theoretical elements (NESO structure, NESO parameter tuning, ADRC closed-loop stability analysis) in the specific case of the laser seeker system. The results of the conducted applied research increase the current state of the art related to robust control of laser seeker systems working in disturbed and uncertain conditions.

The deployment of weapon systems prior to the engagement of anti-cruise missiles constitutes the primary research challenge in surface-to-air missile operations. Initially, it is essential to analyze operational requirements and scientifically delineate the guided radar detection area, kill zone, and interception zone based on physical realities. A model should be established to ascertain the fundamental conditions for site deployment, taking into account factors such as position height, shielding angle, and geographic coordinates. In relation to low-altitude approaches by adversarial forces, key considerations include the depth and breadth of firepower from the weapon system in the attack direction, firepower density in that direction, and lethality probability. An Operational Effectiveness model should be developed based on coverage area of firepower, effective interceptions per unit time, and lethality probabilities of weapon systems to evaluate each location’s effectiveness. Finally, leveraging land selection principles and external information coordination mechanisms will facilitate establishing a genetic algorithm-based strategy for deploying surface-to-air missile systems. The validity of this algorithm has been demonstrated through practical examples.

The modal parameters of long-range cruise weapon systems are typically obtained through finite element analysis and ground vibration testing. However, due to the inability to simulate the system’s time-varying characteristics under flight conditions, it is customary to conduct finite element modelling or ground vibration testing based on several representative operating scenarios. Subsequently, the flight modal frequency of the system is derived through numerical interpolation. This repetitive modelling, analysis, and ground testing process is both time-consuming and resource-intensive. This paper delves into the data-driven output-only identification approach, developing a recursive identification method solely based on the output, which incorporates a time-varying auto-regressive moving average (TARMA) model. By introducing a forgetting factor, the method effectively tracks the system’s time-varying characteristics, enabling rapid and accurate acquisition of the time-varying mode of long-range guided missiles even under unknown excitation conditions. Focusing specifically on the time-varying modal identification challenge posed by a long-range cruise missile, this study performs a frequency spectrum analysis of flight telemetry data. By comparing this analysis with ground vibration experimental data, the disparities between the in-flight and ground modes are elucidated. Leveraging the recursive identification method, the time-varying modal parameters of the flight telemetry data are successfully identified. The alignment between the identified results and the spectral analysis outcomes validates the effectiveness of the proposed online identification technique for time-varying modal parameters, thereby serving the engineering requirements for finite element model refinement and attitude control system design in long-range cruise missiles.