Modern Defense Technology

Modern Aerospace Defense Systems Constructed by En-Intelligence

Mingnan TANG, Chenglong ZHANG, Ran WEI, Bohan WANG

2023, 51(5): 1-7. doi:10.3969/j.issn.1009-086x.2023.05.001

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Currently， the strategic competition among major powers is intensifying. Various operational concepts such as joint all domain concept （JADC）， mosaic warfare， and distributed defense， have brought new threats to the existing aerospace defense system. Against the background of strategic competition among major powers， the characteristics of modern aerospace defense systems are analyzed， such as completeness of operation elements， openness of architecture， antagonism of systems， and convergence of capabilities. The challenges of intelligent development in the aerospace defense system are studied， and the key points of intelligent development of aerospace defense systems are given. In addition， a development vision for an intelligent aerospace defense system featuring agile operation， robust antagonism， and efficient management and control is presented， which provides a new idea for the modernization construction of aerospace defense systems.

Analysis of Threat Control Zone of US Ground-based Midcourse Defense

Yuyan TANG

2023, 51(5): 8-14. doi:10.3969/j.issn.1009-086x.2023.05.002

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Based on the public intelligence information and performance parameters of US ground-based midcourse defense system， a method of threat control zone of ballistic missile defense is proposed. An analysis model of threat control zone of US ground-based midcourse defense is constructed. The threat control zone of US ground-based midcourse defense in the two cases of GBI in flight keeping line-of-sight communication with base and supported by multiple IFICS data terminals （IDT） is simulated， which will contribute to understand the capabilities of US ground-based midcourse defense more thoroughly and accurately.

Deployment Method of Ground-Based Tactical Laser System for UAV Swarm Defense Based on PSO Algorithm

Changhong QU, Yu SONG, Kun WANG, Qingyong CUI, Jiangyang CHEN

2023, 51(5): 15-24. doi:10.3969/j.issn.1009-086x.2023.05.003

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In modern wars， it is difficult for traditional air defense systems to effectively and economically counter unmanned aerial vehicle （UAV） swarm， and ground-based laser systems have become an important means of UAV swarm defense under the key area defense scenarios. Research on the deployment of laser systems will help give full play to their combat capability. Based on the power density concept， the damage model of ground-based laser systems to the UAV target flying at a uniform speed in a straight line is derived. A fitness function is designed to evaluate the advantages and disadvantages of the deployment scheme. Additionally， the particle swarm optimization （PSO） algorithm is adopted to provide the optimal deployment scheme under different specifications and quantities of deployable laser systems， and under different possible attack directions， heights， and speeds of UAVs. Comparison with the scheme of deploying all the laser systems in the center of the key area and of deploying these systems randomly verifies the correctness of the proposed scheme.

Development of US Hypersonic Defense System

Zhong ZHONG

2023, 51(5): 25-30. doi:10.3969/j.issn.1009-086x.2023.05.004

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Under the strategy of competition among major powers， the US military continues to promote the development and construction of hypersonic defense systems from three aspects of sensor layer， command and control， and interception weapons. Finally， this can offset the equipment advantages of hypersonic weapons and crack the anti-intervention/regional denial capabilities of opponents in “competition among major powers”. Since the US Department of Defense decided to adopt a layered defense strategy for hypersonic defense， the US military has fully relied on the existing ballistic missile defense systems. By exploring emerging technologies， developing various interception methods， and cooperating with allies， the US military builds a multi-platform early warning and detection system based on space and supplemented by ground and sea sensors. Meanwhile， a networked command and control system with real-time transmission and sky-to-earth connectivity is established. An interception system that mainly involves gliding interception and terminal interception with multiple interception methods coexisting is planned to build the theater-level hypersonic defense capability by 2034.

Development Trend Analysis of Small Caliber Anti-aircraft Gun Ammunition

Wenmin LUO, Shenghui QI, An PENG, Tao TAO

2023, 51(5): 31-38. doi:10.3969/j.issn.1009-086x.2023.05.005

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This paper analyzes the evolution of air attack targets and combat modes， the characteristics of new air attack targets， and the research status of similar ammunition in China and abroad. On this basis， it proposes that the small-caliber anti-aircraft gun ammunition will develop towards high-efficiency composite damage of armor piercing ammunition， great penetration capability， ammunition “proximity” attack capability， high-efficiency damage capability of fragment warhead， precision hit capability， high security， electromagnetic gun ammunition， and new concept ammunition of countersunk ammunition. Meanwhile， some key technical points in the development are analyzed， which provides references for the demonstration and research on small-caliber anti-aircraft gun ammunition， helps build an efficient small-caliber anti-aircraft ammunition system under the information warfare environment， and improves the operational efficiency of anti-aircraft guns.

Conceptual Design and Trajectory Programming of an Intercept Missile for Hypersonic Gliding Target

Qixin ZHANG, Shuanghou DENG, Li ZHOU, Zhenhao ZHU, Guoxu FENG

2023, 51(5): 39-49. doi:10.3969/j.issn.1009-086x.2023.05.006

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In view of the intercept problem of a hypersonic gliding target， the intercept window， intercept mode， and damage mode are analyzed， and the conceptual design and trajectory programming requirements of the intercept missile are put forward. The conceptual design is conducted， and an intercept missile scheme with a two-stage booster is designed. Meanwhile， the basic parameters of the propulsion and maneuver systems are determined accordingly. The aerodynamic appearance design and centroid location of the intercept missile are completed. The analysis method and tool of intercept missile trajectory programming are constructed. Based on the design constraints， the intercept missile trajectory programming for the HTV-2 hypersonic gliding target is studied， and the trajectory is solved by particle swarm optimization （PSO）. The results show that the expected maximum intercept speed can be achieved， and the speed constraint index of intercept missile intercepting gliding weapon can be satisfied. In addition， the intercept probability evaluation of the intercept missile is carried out， and it is determined that the hypersonic gliding target can be intercepted from multiple intercept stations in sequence through layered defense.

Research on Resilience Reconstruction of Community Network of Unmanned Aerial Vehicle Swarm

Guodong YUAN, Ming HE, Wei HAN, Minggang YU, Mingyang CHENG

2023, 51(5): 50-58. doi:10.3969/j.issn.1009-086x.2023.05.007

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Unmanned aerial vehicle swarm （UAVS） operation is a new operation mode in the future war. The resilience reconstruction capability of the UAVS network is a key index to evaluate the combat effectiveness of the UAVS system. The resilience reconstruction mechanism of the UAVS network is analyzed. A community network model of UAVS is designed to improve network connectivity. Since the network performance of UAVS is sharply degraded under malicious attack， the minimum threshold of information network interaction capability is proposed， and the resilience evaluation method of swarm network performance at the failure stage is optimized. Finally， the average shortest path， information interaction capability， network clustering coefficient， and other parameters of the network under different scales are compared by simulation modeling. The swarm network is reconstructed under the condition of multi-type and multi-scale damage， and the impact on network resilience is evaluated. The experimental results show that the proposed model has higher resilience. The research results can improve the ability of UAVS to cope with complex disturbances and provide theoretical guidance for the multi-task planning of UAVS.

Theoretical Analysis of Navigation Attitude Error for Vehicle INS with Large Inclination Angle

Hui PENG, Shengyi YU, Sheng WANG, Xianmu LI, De MU

2023, 51(5): 59-66. doi:10.3969/j.issn.1009-086x.2023.05.008

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In order to analyze the navigation attitude error of the vehicle inertial navigation system （INS） with a large inclination angle， in this paper， it is proposed that the non-verticality of the turntable shaft is the error source of navigation attitude under a large inclination angle condition. The theoretical formula of navigation attitude error related to the attitude angle of the vehicle INS and the non-verticality of the turntable shaft when vehicle INS with a large inclination angle works is evolved， and the simulation and physical verification are implemented. Study results show that under the condition of a large inclination angle， the azimuth error of the INS with a large inclination angle is the tangent obtained by making the pitch angle multiply the non-verticality of the turntable shaft modulated by the azimuth angle. The roll error is the cosine obtained by making the non-verticality of the turntable shaft modulated by the azimuth angle divided by the pitch angle. The pitch angle error is the modulated non-verticality of the turntable shaft and has no relation with the pitch angle of INS. The navigation azimuth error and roll error increase obviously at a large pitch angle when the turntable shaft is non-vertical. The navigation attitude error of INS presents 360° periodic variation and is independent of the INS roll angle.

A Fuzzy Variable Coefficient Variable Structure Guidance Law with Terminal Line-of-Sight Angle Constraint

Xiaobiao DUN, Xinbo ZHANG, Tong YIN, Jingzhu CAI, Hongyu LI, Chenglong YU, Jingya XIU

2023, 51(5): 67-76. doi:10.3969/j.issn.1009-086x.2023.05.009

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A fuzzy variable coefficient variable structure guidance law is designed for intercepting high-speed maneuvering targets with terminal line-of-sight angle constraints. Firstly， an adaptive variable structure guidance law is proposed to adaptively adjust the velocity approaching the sliding mode surface according to the distance of the missile target. Then， the chattering is eliminated by replacing the switch term in guidance law with the saturation function. Simulation results show that the proposed guidance law can meet the requirements of line-of-sight angle constraint and miss distance for intercepting high-speed non-maneuvering and maneuvering targets， but it requires a large overload. To this end， a fuzzy control method is introduced and a fuzzy controller is designed to optimize the guidance coefficient in the variable structure guidance law. Finally， a fuzzy variable structure guidance law with a variable coefficient is obtained to satisfy the line-of-sight angle constraint and restrain the required system overload.

Multi-ballistic Trajectory Planning and Simulation Based on Multi-objective Optimization Algorithm

Yaohua ZHANG, Yaning XU, Shaojie GAO, Peng ZHANG, Renti LIU, Xiaolong SHI, Xi YANG

2023, 51(5): 77-85. doi:10.3969/j.issn.1009-086x.2023.05.010

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Multi-missile coordination is a hot research direction of missile weapons with high research value， and how to plan the flight trajectory of multiple missiles is an important research content. In this paper， a multi-ballistic trajectory simulation method based on a multi-objective evolutionary algorithm based on decomposition （MOEA/D） algorithm is proposed， which takes the glide phase of boost glide missile as the research object and aims at planning multiple high-quality trajectories. The maximum range and the maximum final velocity are selected as the objective functions to realize the trajectory planning of the glide phase. Meanwhile， in order to reduce the impact of the initial population on the multi-objective optimization problem， the pseudo-spectral method is used to provide high-quality initial populations for the multi-objective optimization algorithm. The simulation results show that the method can obtain multi-ballistic trajectories with optimal range and final velocity.

High-Precision Simultaneous Pulsed Polarization Measuring Method Based on Oblique Projection Filtering

Xinyang GU, Daoming ZHANG, Yong ZHANG, Jian YANG

2023, 51(5): 86-92. doi:10.3969/j.issn.1009-086x.2023.05.011

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The high-precision radar target & simultaneous pulsed polarization measuring method requires high orthogonality of transmitting waveform. However， in practical applications， it is often difficult to transmit precise pulsed polarization measuring waveforms that meet the requirements of time width， bandwidth， and high orthogonality at the same time. A high-precision simultaneous pulsed polarization measuring method based on oblique projection filtering is proposed. Due to the nature of no orthogonality of the linear subspaces by oblique projection filtering algorithm， this method can obtain high-precision pulsed polarization measuring results with non-ideal orthogonal waveforms. Simulation results show that compared with the conventional simultaneous pulsed polarization measuring methods based on matched filtering， this method can reduce the amplitude and phase measurement errors of target polarization parameters and greatly improve the precision of simultaneous pulsed polarization measurement.

Performance Evaluation of Intelligent Radar Information Processing Based on Improved AHM-TOPSIS

Duanyang SHI, Qiang LIN, Bing HU, Jiajun CHEN

2023, 51(5): 93-103. doi:10.3969/j.issn.1009-086x.2023.05.012

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According to the needs of performance evaluation of intelligent radar information processing， the performance evaluation index system of intelligent radar information processing was constructed from three technologies including target detection， target recognition， and residual clutter suppression. The attribute hierarchy model was improved by replacing the proportion scale with the score scale， and the index system was weighted by the improved attribute hierarchy model. In the evaluation model， the grey correlation analysis method was introduced， and the grey correlation coefficient was used to replace the Euclidean distance. The improved technique for order preference by similarity to the ideal solution method was used to rank the performance of different intelligent radar schemes， and the optimal intelligent radar technology scheme was screened out. The effectiveness of this method was verified by the working data of intelligent radars.

Integrated Support Design Method of Weapons Based on Health Management

Yanjun QI, Yufeng WANG, Rui LI

2023, 51(5): 104-109. doi:10.3969/j.issn.1009-086x.2023.05.013

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Guided by precise support， this paper proposes the concept of integrated support design of weapons based on health management and analyzes the relationship between precise support and health management of weapons. The traditional design process of integrated support is summarized according to the current design steps of integrated support of weapons， and its shortcomings in the context of demand for precise support are proposed. Finally， this paper proposes the design method and process of integrated support based on health management， and the traditional design process is compared with the design process based on health management， which provides support for the subsequent integrated support design of weapons.

Weapon Launcher Creep During Long-Term Storage

Yebo REN, Lina YANG, Song YAN

2023, 51(5): 110-117. doi:10.3969/j.issn.1009-086x.2023.05.014

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During the long-term storage of weapon launchers， creep will occur over time. The long-term storage of weapons and their launch process are simulated based on the finite element method to study the influence of creep on weapon launch. Meanwhile， the effects of launch angle and storage time on the creep in the launcher and the weapon launch process after storage are analyzed. The results show that the launcher ends the transient creep stage after about one year during storage and enters the steady-state creep stage. The weapon is deflected by the creep of the bottom carrying device， and the deflection is positively correlated with the launch angle and storage time. The weapon launched after long-term storage deviates from the initial launch axis， and the influence of creep on the launcher structure and the launch process of the weapon during storage cannot be ignored.

Influencing Factors of Backflow Current During Thermal Battery Activation

Dewei SHENG, Zhen WANG, Longqi WANG, Xiaodong MA

2023, 51(5): 118-125. doi:10.3969/j.issn.1009-086x.2023.05.015

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Thermal batteries are widely employed in various tactical weapons due to their high energy density， wide temperature range， strong instantaneous pulse resistance， short activation time， and long storage life. The output end of the thermal battery is the electrical interface for docking with the missile， and its backflow current during activation directly affects the reliability of the electronic equipment on the missile. Meanwhile， the influencing factors are studied to grasp the variation law of backflow current during thermal battery activation. The research shows that the backflow current is related to the number of parallel battery stack connections， the burning rate of the pilot strip， the burning rate of the heating plate， the stage plate area， the melting rate of the electrolyte， the number of single cells in series of the battery stack， the activation mode of the ignition head， line resistance， and the load power on the missile. This conclusion provides favorable support for designing a safe and reliable power supply circuit for the missile electrical system.

Design and Numerical Simulation of Gas Generator Based on Annular Combustor Structure

Fang ZHAO, Yu SHI, Haifeng WANG, Zebin REN, Xianfeng LI, Zhifeng LUO

2023, 51(5): 126-133. doi:10.3969/j.issn.1009-086x.2023.05.016

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A scheme of employing high-temperature gas source instead of normal-temperature air as the ejection gas source is proposed， and an air/alcohol gas generator based on aeroengine annular combustor structure is designed to meet the miniaturization and maneuverability of a high-energy chemical laser pressure recovery system. Meanwhile， CFD software is adopted to simulate the flow field of gas generator， and obtain the velocity， pressure， and temperature fields of gas generator in cold and combustion conditions. Some simulation results are compared with theoretical calculation and experimental values. The research shows that the design of the gas generator is reasonable， and there is no air flow separation at the diffuser and the junction of the two-channel cavity， without overflow at the cap. The recirculating zone of the main combustion zone is obvious with moderate scale， which is conducive to combustion organization and guides the location layout of high-energy electric fire devices. The air flow ratio is reasonable， and the jet depth of the main combustion hole and mixing hole meets the combustion and mixing requirements. The total pressure recovery coefficient of the combustion combustor reaches 96.7% with the combustion efficiency of 98.4%， which realizes efficient combustion. Additionally， the theoretical calculated values and experimental results in the same working conditions verify the rationality and feasibility of the numerical simulation method.

Simulation Analysis of G45 Steel Fragments Penetrating Medium and Large Caliber Projectile Body

Guoliang LIU, Yongfu SHEN, Jie HU, Peng CAO

2023, 51(5): 134-141. doi:10.3969/j.issn.1009-086x.2023.05.017

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The shell model of fragment penetration is built by finite element analysis software ANSYS/LS-DYNA to study the penetration effect of G45 steel fragments with different qualities on medium and large caliber ammunition shells. The ammunition shell is changed into a Q235 steel plate by the equivalent formula， and numerical simulations of the penetration of the equivalent target plate Q235 steel by G45 steel fragments with different qualities at different speeds are carried out. The simulation results show that under the same mass， the penetration depth and diameter of G45 steel fragments impinging on the target plate increase with the rising velocity. The small mass G45 steel fragments of 4.7 g and 9.8 g cannot penetrate the equivalent target of medium and large caliber projectiles in the velocity range of 800–1800 m/s. The limit penetration velocity of 19.5 g G45 steel fragment penetrating the equivalent target of 20 mm medium and large caliber projectiles is between 1 200 and 1 400 m/s.

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