Structural lightweight is a critical technology to improve endurance time and maneuvering performance for the anti-aircraft missile, which is of great significance for the future development of defense equipment. The structure and service environment of the anti-aircraft missile were analyzed in this study. Then, the progress of theory and application of structural optimization methods including size optimization, shape optimization and topology optimization were also studied. The applications of high performance lightweight materials such as metallic material, polymer matrix composites, ceramic matrix composites and metal matrix composites in missiles were reviewed. Finally, advanced manufacturing technologies including near net shape forming technology, additive manufacturing technology, and composite material molding technology were introduced. This paper presents the current challenges faced by the lightweight technology of anti-aircraft missiles, and the trends of research in the future are explained.

The aircraft control surfaces, which generate the necessary control forces to maintain controlled flight, are highly susceptible to damage in combat situations. Conducting damage assessment of aircraft control surfaces is critical for accurate damage evaluation of aircraft targets, reducing the vulnerability of the entire aircraft, and enhancing the aircraft’s battlefield survivability. This paper has reviewed the basic aspects of aircraft control surface damage assessment and summarized the research framework from four aspects: damage assessment targets, damage mode analysis, low-vulnerability design, and stability augmentation control algorithms. Then six key technologies used in control surface damage assessment were analyzed. Based on the above findings, considering the demands for high survivability design of future aircraft and the need for rapid and accurate damage assessment technology, combined with advanced technological development trends, this paper revealed the issues that require attention and urgent solutions from the perspective of functional damage.

The battlefield among great power wars drives the direction of high dynamic and high intensity. A single weapon system or its kill chain is difficult to adapt to future wars. As a new operational concept with high dynamics and high flexibility, the kill web has high self-adaptability, high organization and toughness. Through the extremely fast response speed, the commander can complete the combat groupings and the command control, which significantly enhances the decision-making efficiency. Firstly, this paper conducted research aiming at the combat concept of the kill web. Then, it discussed and analyzed the background of the kill chain, the transition from chain to web, basic concepts, typical cases and key technologies. Finally, utilizing intelligent technology, the paper summarized the concept of a future intelligent kill web.

According to the offensive and defensive operations of UAVs （Unmanned Aerial Vehicles） in the conflict between Russia and Ukraine, the methods of countering new air threats represented by UAVs in the future were studied. By reviewing the overall situation of the UAVs employed by Russia and Ukraine, the methods of using various UAVs to build an integrated reconnaissance and offensive system on both sides were summarized. From the perspective of responding to the UAV threat, this paper elaborated on the overall overview of the anti-UAV equipment employed by both sides and summarized the methods of building an integrated anti-UAV system using various soft and hard killing methods. According to the practical experience of warfare, considering the development of strong hostile UAVs and anti-UAV equipment such as the US military, enlightenment and suggestions for the future development of anti-UAV equipment were proposed.

The traditional cruise missiles have been typically used to carry out ground and sea combat missions. In recent years, under the continuous promotion of military requirements and technology, the application of cruise missiles in air defense operations has developed rapidly. Since the United States dominates the military power, it has launched a series of demonstration and verification projects using cruise air defense weapons, and a few of them have achieved operational combat capabilities, which could become an important part of the future air defense equipment system and profoundly change the future combat style. This paper has comprehensively analyzed the current development status of foreign cruise air defense weapons and sorted out the key technologies that need to be resolved. It then proposed the future development directions for patrol air defense weapons.

An improved statistical narrow band (I-SNB) model was proposed in this study to calculate the infrared radiation characteristics of the rocket engine plumes. This model can discretize the spectral lines within a narrow band in a non-uniform mode, thus the discretized spectral lines perform similar behaviour when temperature and concentration change simultaneously to adapt to the highly non-uniform plume flow field. The modelling accuracy of the I-SNB model has been evaluated using FTIR reference measurement spectral data and line-by-line (LBL) benchmark solutions, and the results show that the accuracy is significantly better than that from the traditional statistical narrow-band ( SNB) model. Based on the American Atlas 5 launch vehicle configuration and combining the rocket flight ballistic parameters in the boost stage, the infrared spectral radiation characteristics of rocket engine plumes in the boost stage were studied. The calculated band range was respectively from 2.0 to 5.0 μm and 8.0 to 12.0 μm. The calculated spectral radiation characteristics included spectral radiation intensity, characteristic band radiation image and integrated radiation intensity. This study provides the oretical support for space-based infrared early warning system for booster phase interception.

To improve the combustion performance of solid rocket scramjet and understand the effect of combustor design parameters on combustion mode and performance, this study has analyzed the impact of the minimum geometric throat of combustor and the distance between the front edge of cavity and fuel injector port on the flow and gas-solid two-phase combustion characteristics in the combustor using numerical simulation. The results show that the minimum geometric throat of the combustor affects the position of the thermal throat by changing the degree of obstruction in the combustor. With the increasing distance between the front edge of the cavity and the fuel injector port, the resulting low-speed zone presents a stronger blocking effect on the air flow, thus increasing the retention time of the particulate phase fuel and improving the combustion efficiency. The combustion efficiency of particulate phase fuel is the key factor that dominates the overall combustion efficiency, and affects the improvement of the combustor performance and the modification of combustion mode.

To resolve the problem of low terminal velocity of high and long-range ballistic missiles, combiningthe application of a double-pulse solid rocket motor in air defense missiles, this study analyzed the influence of thrust of the solid rocket motor and ignition interval of the two-stage engine on the terminal velocity of a high and long-range ballistic missile. Focusing on maximizing the terminal velocity of air defense missiles on highand long-rangetrajectories, the thrust and ignition interval of the double-pulse solid rocket motor were optimized using the improved Classified Chemical Reaction Optimization (CCRO) algorithms established in this study. Finally, the optimal energy distribution scheme for the motorenhancing the missile’s terminal velocity was achieved.

To study the unstable combustion performance of solid rocket motors, this paper utilized both experimental testing and numerical simulation to explore the influence of the side pipe's position and length on the chamber's acoustic mode. The differences in the acoustic mode under different experimental boundaries were compared, and the influence of airflow velocity and temperature on the acoustic mode characteristics of the combustion chamber was analyzed. Results show that when the side branch pipeline collapses inward and the length of the side branch pipeline decreases, the modal frequency value gradually increases; when the opening area increases, the acoustic modal frequency value increases. The acoustic modal results of the pipeline-connected state are close to those of the single-end open state; When the flow velocity increases, the modal values of each order of the sound cavity gradually decrease; when the temperature increases, the modal values of each order of the cavity gradually increase.

In recent years, the rapid development of China's aerospace industry has driven higher requirements for the temperature and distribution test of engine turbines, combustion chambers and other high temperature components, attracting widespread attention to thermo chromic paints. To address the temperature measurement challenges of high-temperature components such as aero-engine, it is necessary to further improve the upper limit of color change temperature and color display performance of temperature indicator paint. In this study, TEOS hybrid methylphenyl silicone resin (SR) was prepared by TEOS, diphenyl dimethoxy silane (DMDPS) and trimethylxy silane (TMPS). The flexibility of the resin was increased by adjusting the ratio of TEOS to DMDPS. A hybrid silicone resin with both toughness and high temperature resistance was produced by modifying the toughened SR with heptaisobutyl trisilane hydroxyl POSS that can cure at room temperature, retaining 82% of its weight at 500 ℃ . Pigments such as new carmine, tungsten trioxide, chromium trioxide, iron oxide, aluminum silicate were selected, along with zirconium powder and boron trioxide as high temperature fillers, and anhydrous ethanol as solvent. These were mixed and ground with the prepared high-temperature resistant silicone resin to produce a high temperature indicating paint. The effect and mechanism of color display at 400, 500, 800, 900, 1 000, 1 150 and 1 300 ℃ were analyzed. The results show that the paint achieves excellent properties in technology, high temperature resistance and color display performance, and can be used to measure the temperature of high temperature parts.

Taking cluster-to-sea combat as the application background, this article focuses on the spatiotemporal configuration and target allocation decision-making problems of multi-missile and multi-spatial dispersion. It established a missile active perception collaborative detection model in typical collaborative scenarios of multiple missiles and designed models and corresponding algorithms for missile cooperative detection and collaborative attacks. Initially, a three-degree-freedom model for missiles and a two-degree-freedom model for ships, an evaluation model for missile flight capability, an evaluation model for missile penetration probability, and a missile threat evaluation model were established, thus allowing the accurate measurements of changes in missile detection and strike capabilities. Then, this study designed an active perception collaborative detection model and collaborative attack model for missiles under incomplete information conditions, maximizing the benefits of missile collaborative operations and maximizing the destruction of enemy forces. After that, to address the problems of target allocation and missile formation configuration in missile coordinated strike, a particle swarm optimization algorithm incorporating a genetic algorithms (GAPSO) was introduced and compared with the traditional particle swarm optimization (PSO) algorithms, which allows a multi- dimensional consideration of battlefield situation information and integrated detection and attack of enemy targets. Finally, this article simulated the established combat model and obtained algorithm simulation graphs and statistical data from multiple simulations of the algorithm. Compared with other algorithms, this algorithm has obvious advantages, thus significantly improving the intelligent confrontation level and penetration strike ability of missiles.

The existing recurrent neural networks are subject to training overfitting, low prediction accuracy, poor generalization ability, and weak adaptability in solving target trajectory prediction. A target trajectory prediction method using an improved attention mechanism and Gated Recurrent Unit (GRU) was proposed, which could automatically terminate the network training process through an early stopping method to prevent overfitting during training. It saved the optimal network parameters during network training through the model checkpoint function. By introducing an attention mechanism into the GRU network and assigning different weights to trajectory features to focus on key trajectory information, the predictive performance of the network was optimized Finally, simulation experiments results show that the proposed method effectively improves the prediction accuracy, generalization, and adaptability of recurrent neural networks.

This study delves into the design methodology for typical maneuvering trajectories to enhance the maneuver penetration capability of hypersonic glide vehicles. Firstly, a high-precision altitude-velocity analytical solution was derived and used as the foundation for longitudinal trajectory designing. Secondly, based on the altitude and crossrange analytical solutions, longitudinal and lateral maneuver modes were devised to execute longitudinal skip and lateral weaving maneuvers. The effects of these modes on the vehicle's overload were analyzed, providing a basis for the choice of maneuver mode in the practical penetration. By meticulously designing the amplitude, frequency, and phase of trajectories in both longitudinal and lateral maneuver modes, spatial spiral and pendulum maneuvers were acquired. Finally, the effectiveness of the maneuver trajectory design method was simulated and verified, presenting high accuracy and meeting penetration requirements.

The hybrid advancing mechanism mixes logical and real-time advancing mechanisms. Logical advancing mechanisms can increase simulation efficiency, and real-time advancing mechanisms can increase simulation fidelity. The hybrid advancing mechanism combines the benefits of both the logical and real-time advancing mechanisms. In this study, the layered design pattern was employed to evaluate and deduct maritime anti-air weapon system-of-system. Emulating the integration of LVC, the architecture of the combat deduction system of maritime air and missile defense was designed. The function design and the interaction design of the system were completed. Real weapons and simulators were applied to expand the capability of the combat deduction system. The results show that the proposed system can veritably reflect the influence on the war of operational personnel quality and key weapons and improve combat deduction of high confidence coefficient.