In traditional chined waverider design, the adjustment of design profile parameters is complex and the design intuitiveness is insufficient. To address these issues, this paper proposes a chined upper surface design method based on B-spline curves. The design flexibility and convenience are improved by directly adjusting the design profile through control points. The base profile is constructed by means of Bezier curves, the leading edge and lower surface base profile are determined using the osculating cone theory, and the upper surface profile is designed using cubic and quadratic B-spline curves. The reliability of the proposed method is verified by computational fluid dynamics (CFD) methods, and the aerodynamic performance of the chined waverider is analyzed. The results demonstrate that, as the angle of attack gradually increases, the influence of the chined upper surface on aerodynamic characteristics weakens gradually, and the maximum lift-to-drag ratio appears at the angle of attack ranging from 4° to 6°. The proposed method provides a more intuitive profile optimization means for waverider design, which has reference value for engineering design.

Loitering munitions integrate multiple functions such as reconnaissance, attack, and assessment. They have low usage costs, flexible combat deployment, and are difficult to detect and intercept. They have significantly enhanced the strike accuracy and ability against targets and have become important weapons in the Russia-Ukraine conflict, attracting great attention from major military powers. This paper summarizes the characteristics of loitering munitions, introduces the development status of major loitering munitions at home and abroad, including the “Switchblade” series and “BattleHawk” series of the United States, the “KUB” series and “Lancet” series of Russia, and the “Hero” series and “Harpy” series of Israel, which have practical applications. It comparatively analyzes the performance parameters of relevant loitering munitions, combs the key technologies in the development of loitering munitions, including power technology, anti-interference technology, modular technology, and intelligent cooperative combat technology, summarizes the development trends of loitering munitions, and on this basis, analyzes the combat applications of loitering munitions and the defense means against them.

To improve the resistance of B₄C/Al composite targets against explosively-formed projectile (EFP) penetration, the surface morphology of ceramic strike face is modified. Seven types of B₄C/Al composite targets featuring different protrusion-array structures on the strike face are examined. The processes of EFPs penetrating into the composite targets at 1.5, 1.7, and 1.9 km/s are simulated using LS-DYNA. The evolutions of the projectile's mass, velocity and kinetic energy during penetration are analyzed. The results indicate that B₄C/Al composite targets with protruded strike-face structures exhibit superior penetration resistance and deceleration capability compared with B₄C/Al flat-faced targets. Among them, the composite target with a pyramidal protrusion array provides the best deceleration performance for the simulated EFP.The R3 semi-cylindrical target demonstrates the best protective performance under normal impact. The penetration direction significantly affects the penetration resistance of anisotropic protrusion-array targets and the sinusoidal-structured target has the optimal protection performance under oblique impact.

The mechanical properties of high-entropy alloys (HEAs) are studied. For this purpose, a simple and precise testing system is established for determining the equation-of-state parameters of HEAs. Based on the principle of wave impedance matching, a test setup is designed using the pressure comparison method to obtain the shock adiabat data of HEA materials. The acquired experimental data is then optimized through adaptive clustering detection. After optimization, the confidence intervals for the slope and intercept of the experimentally determined shock adiabat are narrowed from [1.66293, 2.03332] and [4.01158, 4.38089] to [1.6461, 1.92734] and [4.15248, 4.27542], respectively, and the coefficient of determination (R²) is improved from 0.9687 to 0.9849. The Hugoniot equation-of-state parameters for the HEA are determined as C₂=4.214km/s and λ₂=1.787.The Hugoniot equation of state established in this study is applicable within a pressure range of approximately 5.86-32.77 GPa, and its extrapolation to higher pressure regimes necessitates further experimental validation to guarantee reliability. The results demonstrate that the proposed system achieves high-precision measurement of equation-of-state parameters for high-entropy alloys hrough the combination of data optimization algorithms with experimental design. This work provides critical technical support for the performance assessment and practical application of such materials under dynamic mechanical conditions.

In order to investigate the blast resistance of a 316L stainless steel honeycomb sandwich structure, a honeycomb sandwich structure was designed and fabricated using 316L stainless steel powder by selective laser melting (SLM). Concurrently, solid panels of equivalent surface density were produced by this method and constituted the control group. The mechanical behavior of the structure under near-field static explosion load is obtained through static explosion experiments and LS-DYNA simulation experiments, and the propagation mode of the stress wave within it is investigated in order to elucidate the underlying anti-explosion principle. Moreover, optistruct is utilized to optimize the topology and structure of the structure, with the objective of enhancing its blast resistance. The findings indicate that the backplate deflection of the porous sandwich structure is diminished by 13.2% in comparison to that of the plate with isoplanar density, thereby enhancing blast resistance. The established numerical model of fluid-solid coupling is capable of describing the three phases of the static explosion experiment, namely the shock wave propagation phase, the fluid-solid coupling phase, and the inertia phase. The explosion experiment yielded definitive results at the center of the target plate, thereby demonstrating that the "川" crack is caused by residual core layer extrusion. Moreover, the core layer deformation failure mechanism for the honeycomb panel was observed to manifest as in-plane stretching and tearing. The optistruct optimization results demonstrate the formation of a triangular skeleton and circular holes, alternating with corrugated plates. The structure, optimized for a corrugated core target plate, displays enhanced resilience in comparison to the optimization of a traditional honeycomb sandwich panel. The explosion load backboard deflection exhibited a 25.4% reduction, the peak pressure behind the plate demonstrated a 17.6% reduction, and the blast resistance was significantly enhanced. In comparison to honeycomb panels, the circular hole structure has been demonstrated to reduce the backplane deflection by 38.1%, while the triangular hole structure has been shown to reduce the peak pressure behind the plate by 22.4%.

To address the issue of small penetration aperture in traditional shaped charge warheads against underwater single-layer targets,a novel W-shaped shaped charge structure design method based on the inner cone angle α and outer cone angle β is proposed.The influence of liner structure on jet formation and damage effectiveness is studied.The ratio μ of the lengths of the inner and outer sides of the liner is defined a-s a characterization parameter affecting the underwater formation and damage performance of the W-shaped liner.The influence of the ratio μ on the formation and initiation points on the formation and penetration of annular jet are analyzed through numerical simulations.The results indicate that,the annular jet converges excessively toward the axis when μ is 0.22,forming an explosively formed projectile (EFP).When 0<μ<1,the outward expansion trend of the annular jet gradually intensifies,the head-to-tail velocity difference decreases,and the jet stability improves with the increase in μ.When μ>1,the slug at the jet tail is reduced,the jet head expands,the head-to-tail velocity difference increases,and the jet stability significantly decreases under the influence of the external water medium with the increase in μ.Additionally,the increase in the number of initiation points induces necking at the head of the annular jet,which has little impact on penetration and aperture formation under the condition of small standoff distance.The large-area damage of annular jet to the target plate can be achieved by optimizing the combination of the inner and outer cone angles of the liner to adjust the value of μ and the number of initiation points.

The penetration tests on three sets of geometrically similar projectiles with scaling ratios of 1/1, 1/2 and 1/3 are carried out to investigate the size effect of penetration depth of projectile into concrete media. A calculation method for penetration depth with the projectile diameter coefficient as a variable is proposed, and a conversion coefficient model that takes into account the scaling ratio is established for penetration depth. The dynamic strain rate of material in the projectile-target contact zone during the penetration processare quantitatively analyzed through numerical simulation, and the values of penetration depth conversion coefficients under different scaling ratios are ultimately determined. The results show that the size effect exists in the dimensionless penetration depth between the prototype projectile and the model projectile, which arises from the difference in the average strain rates of target in the tests with different scaling ratios. The strain rate increases with the increase of penetration velocity and the decrease of projectile diameter, and does not conform to the geometric similarity scaling relationship. The established penetration depth conversion coefficient is correlated with the target strain rate and the scaling ratio. This conversion coefficient not only quantifies the influence of the material strain rate on the size effect, but also clarifies the mechanism of the size effect of penetration depth in concrete media from a mechanistic perspective.

In order to investigate the influence of liner structure parameters on the formation of jet penetration charge (JPC) as well as the penetration ability and post-effect action of the formed JPC on ceramic composite target plates, this study adopts orthogonal experimental optimization to design the structure parameters of an equal-wall-thickness conical liner. The LS-DYNA software is utilized to conduct research on how warhead structure parameters (cone angle, thickness, length-to-diameter ratio) affect the characteristic parameters of JPC damage elements. Through range analysis, the combination of structure parameters that results in better JPC formation performance is obtained. Based on the optimized structure, the damage situation of JPC damage elements on composite targets is studied. The results showed that when the liner cone angle is 90°, the wall thickness is 2.5 mm, and the charge length-to-diameter ratio is 0.9, the penetration effect is better. At this time, the funnel pit diameter increased by 8.93%, the funnel pit depth increased by 3.7%, the average diameter of the hole increased by 8.29%, and the total penetration thickness increased by 9.88% after removing the target plate spacing. This research can provide a theoretical and technical basis for the design of rod-shaped jet liner structure parameters and for studying the penetration ability on ceramic composite target plates.

In order to improve the detection ability of infrared small targets in complex backgrounds, a small infrared target detection algorithm based on joint gradient discrimination and adaptive matching was proposed. The suspected target area is screened out for the first time in the image through multi-directional gradient features, and the adaptive model is generated by using the grayscale information in the region for re-judgment. Quantitative evaluation was established for gradient judgment and adaptive model matching, and confidence functions were introduced to evaluate different suspected target areas and screen out suspected targets. In order to enable the algorithm to be applied in dynamic platforms such as UAVs, an embedded system was built to realize the detection of small targets in real scenes by the detection system through infrared camera framing. By testing different public datasets and comparing with WSLCM (weighted strengthened local contrast measure) and TLLCM (tri-layer local contrast measure) algorithms in different complex scenarios, the proposed algorithm has good adaptability, and the recognition rate under different samples is more than 92%. The algorithm is processed by hardware acceleration through the customization of the IP core of the embedded platform and the co-design of software and hardware, and the real-time video frame rate is greater than 30 frame/s, which verifies its effectiveness.

In modern warfare, the damage efficacy of high-speed penetration weapons against high-strength targets such as underground bunkers and reinforced structures has become a focal point of research. This paper systematically reviews the research progress on the dynamic behavior of projectile materials, constitutive models, and structural responses under high-speed penetration. It analyzes the mechanisms of strain hardening, thermal softening, and adiabatic shear deformation under the coupled effects of high temperature and high strain rate, and compares the applicability of typical constitutive models such as the Johnson-Cook model. Key factors influencing mass erosion, critical instability velocity, and structural failure during high-speed penetration are emphasized, along with their underlying mechanisms. Additionally, technical approaches to enhance penetration capabilities through material optimization and structural design are explored, providing valuable references for researchers in related fields.

Dynamic explosion point localization constitutes a pivotal element in damage assessment. The explosive sound wave, originating from the attenuation of a shock wave, is characterized by supersonic velocity and a defined sphere of influence. Accordingly, the accuracy of explosion point acoustic localization is susceptible to the influence of the explosive shock wave. To explore the impact of the explosive shock wave segment on the acoustic localization outcomes during the explosion point localization process, a wave arrival time-distance model for the attenuation of the shock wave into a sound wave was constructed, predicated on the pressure attenuation law of the explosive shock wave. This model was subsequently integrated into the localization methodology based on the time difference of arrival (TDOA). Utilizing a prototypical arrangement as a case study, the preset explosion point and the acoustic sensor array's position were delineated, and the corresponding wave arrival times were computed. The TDOA-based localization approach was employed to retrodict the position of the explosion point relative to the acoustic sensor array, and the acoustic localization error of the explosion point was ascertained by juxtaposing the retrodicted position with the preset position. Furthermore, by modulating the preset explosion point position and the charge mass, the influence of the explosive shock wave on the acoustic localization error was scrutinized. The research findings suggest that the charge mass and the distance from the explosion center are the predominant factors influencing the localization error. As the scaled distance escalates, the localization error induced by the shock wave exhibits a diminishing trend. When the scaled distance surpasses 18.45, the relative distance error can be mitigated to below 1%. It is anticipated that these findings will serve as a reference for the systematic error correction of explosion point acoustic localization, thereby enhancing the computational precision of explosion point acoustic localization.

The influence of grooved structure on the penetration and damage performance of copper-aluminum/polytetrafluoroethylene (Cu-Al/PTFE) energetic composite liner is investigated.A energetic composite liner with large cone angle (140°) is numerically simulated and experimented,and the damage effect of a pre-grooved energetic composite liner on concrete target is examined.A comparison shows good agreement between the experimental and simulated results.The influences of groove structure parameters such as groove width,depth,and wall thickness ratio on the damage effect of jet are further analyzed.The results show that the groovee structure has an effect on the distribution of jet energy between radial expansion and axial penetration.The smaller widths,shallow depths and narrow spacing of grooves are conducive to the radial hole enlargement,whereas the larger widths,greater depths and wider spacing of grooves enhance energy concentration,thereby increasing the penetration depth.Additionally,the number of grooves and the wall thickness ratio significantly influence the stability of jet and the ability of reactive materials to follow up.In particular,a wall thickness ratio of 1∶1 between the copper and reactive material layers yields favourable jet formation and damage performance.

With the progressive complication of modern war scenarios, traditional loitering munition which is only suitable for a unitary combat environment is failed to meet the needs of the actual warfare. The trans-medium loitering munition swarm can lead to revolutionary changes of modern military field due to its excellent multi- scenario adaptability. A comprehensive analysis is given from three aspects: the basic design of loitering munition, the unique performance of trans-medium aircraft, and the intelligent management of swarm technology. The core theory and technology of trans-medium loitering munition swarm are studied. Based on the new characteristics of equipment, command, and personnel in modern wars, the future development trend of trans-medium loitering munition swarm is prospected.

Rapid development of UAV swarming technology will provide new operational mode for the future battlefield, this paper mainly introduces the status of the UAV swarming operation systems under development in the military powers such as the United States, Russia, Israel and Britain, including the Gremlins, Coyote and Lightning UAV swarm programs, and also introduces the loyal wingman programs such as Skyborg,Mosquito and S-70. In addition, the introduction of the Golden Horde ammunition swarm program based on UAV swarming technology is presented. On this basis, the future development trend of UAV swarming operation system is summarized and analyzed in the aspects of modular design, low-cost development, multi-platform application and cutting-edge technology exploration.

The direction-finding performance of guidance and direction-finding system is limited with a small-aperture array and the array configuration optimization is a key step to improve system performance due to platform resource constraints such as weight,volume,and deployment space.In this paper,the Cramér-Rao bounds (CRBs) for wideband two-dimensional direction-of-arrival (DOA) estimation of both scalar arrays and polarization-sensitive arrays are derived,and a CRB-based performance evaluation and configuration optimization method for small-aperture arrays is proposed.Firstly,the development of wideband DOA estimation and the typical two-dimensional array structures are reviewed,and the wideband signal models based on subband decomposition are established for both scalar arrays and polarization-sensitive arrays.For scalar arrays,a closed-form expression for the CRB of wideband two-dimensional DOA estimation is provided.Subsequently,a general framework and closed-form expression for the CRB of wideband two-dimensional DOA estimation of polarization-sensitive arrays are derived,and a performance evaluation criterion for two-dimensional direction finding with such arrays is established.Finally,A two-dimensional array configuration optimization method based on the derived CRB is proposed by considering the constraints ofguidance system platform on the number of array elements and array aperture.The quantitative optimization of array layout can be achieved by constructing an array configuration optimization set and conducting theoretical performance evaluation.The research results provide theoretical support and technical guidance for the array configuration design and performance evaluation of small-aperture guidance direction-finding systems.

In order to improve the penetration ability of multiple explosive formed projectile (MEFP) to armored targets, based on the design of end face MEFP, a combined end face ring double layer MEFP charging structure was constructed, which could form one main EFP and 24 auxiliary EFP in the circumferential direction, and could achieve multi-point damage to armored targets. ANSYS/LS-DYNA software was used to study the influence of the structural parameters of the cartridge cover on the molding effect and penetration performance of the MEFP warhead. The results show that when the wall thickness of the auxiliary cover increases, the projectile velocity of the auxiliary cover gradually decreases, the projectile dispersion angle of the middle auxiliary cover gradually decreases, and the projectile dispersion angle of the outer auxiliary cover gradually increases. When the radius of curvature of the auxiliary hood increases, the projectile velocity of the auxiliary hood gradually decreases, the angle of departure of the intermediate auxiliary hood gradually increases, and the angle of departure of the outer auxiliary hood gradually decreases. When the span of the auxiliary hood increases, the projectile velocity of the auxiliary hood gradually increases, the angle of dispersion of the intermediate auxiliary hood projectile decreases, and the angle of dispersion of the peripheral auxiliary hood projectile increases. The MEFP can penetrate 15 mm thick 45# steel target, thus effectively increasing the number of damage elements and damage area. The annular double layer MEFP structure of the end face combined charge structure has important reference significance for the warhead design of the terminal sensitive bomb.

In response to the application requirements of inertial navigation systems for quartz flexible accelerometers with a large range and high dynamic flight accuracy, a new structure for the pendulum assembly of quartz flexible accelerometer is proposed to enhance the range and second-order coefficient of accelerometer. A mathematical model of the designed pendulum assembly is established to derive the scale factor of the designed accelerometer. The design range of accelerometer is theoretically calculated based on the load capacity of servo circuit. The optimization method for the second-order coefficient of the accelerometer is analyzed, and an optimization scheme for the second-order coefficient is provided. Through numerical simulations, it is verified that the deflection and stress of the designed pendulum assembly under full-scale conditions meet the design requirements. Experimental results show that the quartz flexible accelerometer achieves a range of 110g and a second-order coefficient better than 5 μg/g², thereby improving the dynamic application capability of quartz flexible accelerometers in inertial navigation systems.

In order to improve the survivability of underground protection engineering, it is necessary to accurately consider the damage to the structure caused by the continuous action of penetration and explosion. Through the SPH-FEM coupled numerical simulation method, the simulation of the entire process of penetration and explosion of underground structures is realized, which solves the simulation problem of high intensity and large deformation in the vicinity of the invasion and explosion by the traditional finite element method. According to the empirical formula, the validity of the model is verified. The results show that the penetration projectile has a sealing effect on the rock mass, which enhances the damage effect. SPH algorithm compensates for the penetration hole unloading defect of the erosion algorithm for the penetration explosion process, and more accurately simulates the joint effect of penetration explosion; pouring separately from the straight wall can reduce structural damage; In addition to arch feet, the vault and spandrel are the weak parts of the straight wall arch structure under the action of penetration explosion. The research results can provide a basis for the design of underground protective structures.

According to the current development trend of air-to-air missile, the tactical characteristics of the fifth generation air-to-air missile based on ramjet are analyzed, and the air-to-air missile mission (air-to-air combat and ground attack) is given. With reference to “meteor” air-to-air missile, considering the basic characteristics of small size, long-range and high-speed of future embedded long-range air-to-air missile, the calculation model of ramjet is established with two-dimensional three wave system inlet, side intake cavity combustor and axisymmetric Laval nozzle. The three-dimensional three wave ramjet (small size, diameter 167 mm) at high Mach number (3.0~5.0) is completed. The feasibility of the ramjet as an embedded long-range high-speed air-to-air missile in the future is preliminarily verified by dimensional numerical calculation and analysis.

　　航天发射技术是研究运载火箭、各类飞行器等的发射原理、发射方式和发射设施设计、制造、试验和使用的工程科学技术，是航天技术的一个分支和重要组成部分，是一门综合性、系统性极强的学科方向。航天发射技术的发展水平决定了一个国家航天活动和国防保障区域的范围，反映了一个国家工程科学和基础工业的综合水平。
　　近年来，为适应航天运载工具的快速发展，全球航天发射技术正朝着规模化、复杂化、自动化与国际化的方向迈进。我国航天发射技术也获得了长足的进步，取得了丰硕的成果，如海南发射场的建成有力保障了我国未来各类航天任务的开展；以“长征-11”运载火箭为代表的机动航天发射技术的出现为我国应急航天发射任务提供了多元化发射手段。这些进展不仅彰显了我国航天技术的创新实力，也为未来深空探测、商业发射和国防需求奠定了坚实基础。
　　当前，各航天大国均把发展先进的发射和运载技术作为保持其在航天领域领先地位的战略部署之一。无论是空间应用、科学探测、载人航天、国际商业发射与国际合作，还是国防建设，都对发射技术提出了新的要求，亟待发展规模更大、成本更低、兼容性更强、可靠性更高、发射周期更短、更加智能的大型航天发射场；随着航天发射任务的大幅增加和各类应急发射需求的大量涌现，提出了发展快速机动的低成本航天发射方式；面向低碳、绿色、高效、低成本发射的需求，提出了地面超高速发射一级直接入轨等新型发射概念；此外，深空探测任务的推进，使得地外天体发射技术成为前沿研究热点。
　　在此背景下，《弹箭与制导学报》编辑部联合北京理工大学姜毅教授团队，策划推出本期“火箭导弹发射技术”专刊，旨在汇聚领域内最新研究成果，推动学术交流与技术突破。本期专刊特邀姜毅教授(北京理工大学)、姚建勇教授(南京理工大学)担任编审，共收录18篇高质量论文，内容涵盖发射技术理论创新、工程实践及未来发展趋势，以期为国家航天事业发展提供有益参考。
　　我们谨向所有参与本专刊撰写的专家学者致以诚挚谢意，也期待本期专刊能为航天发射技术的进步注入新动力，助力我国迈向航天强国的宏伟目标。

The launch of the Mars ascent vehicle(MAV) is the first step for ascent from the Martian surface to orbit around Mars, a critical step in the Mars sample return mission. In the MAV's inclined hot launch process, the force-thermal impacts are significant and gas flow structure is complex, so when designing its launch system, it is necessary to consider the complex force-thermal effect in launching process. This study employs computational fluid dynamics to conduct a numerical simulation of the force-thermal impacts of the MAV's inclined thermal launch on the Martian surface, with comparisons to similar launch conditions on earth. The findings reveal that during the inclined hot launch from Mars, the MAV's maximum surface temperature reaches 2 868 K, while the launch platform attains a peak temperature of 2 908 K. Furthermore, during ejection, the platform's pitch-up moment progressively increases, the launch apparatus may topple under Mars' low-gravity conditions. Notable differences are observed between inclined hot launch processes on Mars and Earth; the MAV launch on Mars exhibits greater stability yet endures more severe force-thermal impacts on both the platform and the MAV.

Aiming at the path planning problem of UAVs in complex scenes,this paper proposes a coupling algorithm that uses the improved A-star algorithm and the improved dynamic window method for path planning,so that the UAV has the ability to avoid static and dynamic obstacles.In terms of global planning,by improving the evaluation function of the A^* algorithm,a path planning algorithm that does not rely on the obstacle expansion map is proposed,so that the UAV can plan a safe path against a priori static obstacles.In terms of local planning,an evaluation function for handling dynamic obstacles is added,so that the UAV has good obstacle avoidance capabilities when facing high-speed dynamic obstacles.Aiming at the problem of too many inflection points on the path resulting in frequent acceleration and deceleration after improving the global planning algorithm,a redundant inflection point deletion strategy was proposed.The simulation results show that compared with the traditional algorithm,the improved algorithm has better obstacle avoidance ability and shorter driving trajectory,which verifies the practicability of the algorithm.

Because of low cost and flexible operation mode, more and more loitering munitions have been used in local conflicts worldwide in recent years, which has attracted wide attention. This paper introduces the development status of main foreign loitering munitions in the world, involving products of the United States, Israel and other military powers which include the Switchblade series, Coyote series, KUB-BLA series, Lancet series, Harop and Hero series of loitering munitions. Based on the introduction, the paper provides analysis of the development status of foreign loitering munitions, and puts forward the future development trend in the aspects of low cost, serialization, multi-platform delivery, stealth development and swarming operation.

To ensure that the UAV (unmanned aerial vehicle) can accurately locate the reconnaissance target, image matching plays a critical role in the localization process, and its performance directly affects the localization accuracy of the targets. However, UAVs often encounter challenges when performing reconnaissance tasks in complex environments, especially when background information is similar, which hinders the effective elimination of a large number of outliers. This paper proposes an improved RANSAC (random sample consensus) algorithm. First, an initial dataset is constructed using triplet relationships. Based on these relationships, an improved strategy for selecting initial data is proposed, which reduces computational costs and improves matching accuracy through neighborhood-based geometric consistency and triangulation. Second, a data subset refinement strategy is introduced to further enhance the algorithm's sampling performance. Finally, the proposed algorithm is compared with other advanced algorithms on UAV reconnaissance image datasets featuring complex environments and similar background information. Experimental results demonstrate that the proposed algorithm achieves higher computational efficiency and correct matching rates, thus improving both the computational speed and localization accuracy, providing a novel method for UAV reconnaissance target localization.

In this paper, a trajectory optimization method of hypersonic glide missile is put forward by using penalty function method to hand non full course flying height and angle of attack constraints, which is based on Gauss Pseudo-spectral Method and takes into account multi phases, multi complex constraints and penetration mission-oriented requirements and so on. Its simulation results show that all constraint indexes are effectively controlled, and the penalty function method has more advantages in handling mission segmented constraints compared to conventional segmented constraint methods, which verified the effective coverage ability of the method under different ranges, launch heights and target heights.

Artificial intelligence technology is widely used in the military field, which significantly improves combat efficiency and promotes the development of military technology. The US military is in a leading position in the research and application of artificial intelligence technology in the military field, which was discussed in detail. The application of artificial intelligence technology in intelligence, surveillance and reconnaissance, logistics support, cyber operations, command and control, semi-autonomous and autonomous vehicles and autonomous weapons and other fields are deeply analyzed, and the future development trend of artificial intelligence technology in the military field is predicted. Finally, it points out the guiding and referential role for the domestic military field to carry out artificial intelligence technology research.

As unmanned combat systems have increasingly emerged as a critical asymmetric warfare approach in naval operations, small unmanned surface vehicles (USVs) have become focal points of international military competition.While leading military powers are actively developing and equipping USVs while advancing countermeasure technologies, significant challenges remain. This study adopts the offensive-defensive dynamics of USVs as its analytical framework, examines the evolving nature of naval warfare in contemporary conflicts, and systematically analyzes the technical specifications, operational tactics, and defensive countermeasures associated with advanced small USVs deployed internationally.Building upon the concept of the USV closed-loop kill chain, we proposes an integrated anti-USV defense architecture that synergistically combines radar surveillance, electronic warfare (reconnaissance/jamming), infrared/electro-optical detection, multi-domain interception systems (air-to-surface/underwater), and asymmetric countermeasures. The findings establish a theoretical foundation for advancing USV-related technologies while providing actionable insights for the development and tactical deployment of next-generation counter-USV systems.

Aiming at the problems of uncontrollable drop point and insufficient strike accuracy of the traditional terminal sensitive projectile, this paper proposes a parafoil based terminal sensitive projectile drop point control technology, which adopts parafoil instead of traditional parachute to achieve accurate control of its drop point. Based on the proposed parafoil-missile system, this paper designs an accurate parafoil-missile yaw angle controller based on active disturbance rejection control technology, which can offset the interference caused by the external wind field and compensate for the initial position error of the non-sensitive missile, so as to achieve accurate autonomous control of the system. Based on the above research content, the parafoil- missile system is built in this paper, and the actual airdrop experiment is carried out. In the experiment of airdrop, the error of the final landing point of the parachute-projectile system is less than 30 meters, and the minimum error of the air level is less than 4 meters, which proves the effectiveness of the proposed algorithm and provides a new idea for the design of smart ammunition in China.

The active sidestick is a crucial control device that can adjust the flight attitude of an aircraft. In the automatic flight mode, the active sidestick follow-up function tracks the control commands from the flight controller in real-time to enhance the pilot's perception of the aircraft's flight status, thereby effectively improving flight safety. However, unknown disturbance torques in the system can degrade the tracking accuracy of the active sidestick. To address this challenge, a control method based on composite nonlinear feedback and adaptive integral sliding mode is proposed for the follow-up control of the active sidestick. This method integrates an integral sliding mode control algorithm and the composite nonlinear feedback control algorithm, where the composite nonlinear feedback control effectively improves the steady-state performance of the active sidestick system, and the adaptive integral sliding mode control effectively restrains unknown system disturbances. Extensive experimental results show that the proposed improved active sidestick follow-up control algorithm can reduce the adjustment time by approximately 41% and the steady-state error by about 93.6% compared to the previous composite nonlinear feedback control algorithm. Furthermore, under disturbance conditions, the improved follow-up control algorithm can reduce the adjustment time by about 79% compared to the traditional PID algorithm. This demonstrates that the designed improved active sidestick follow-up control algorithm can significantly enhance the system's control accuracy and response performance, and possess excellent disturbance rejection capabilities.

To investigate the damage effectiveness of low, slow and small Unmanned Aerial Vehicles(UAVs) under fragmentation strikes, an evaluation model is established to comprehensively assess the damage effectiveness of fragments against UAVs. Numerical simulations are conducted to analyze the damage probability of a single fragment impacting various UAV compartments under different initial velocities, diameters, and material conditions, followed by extensive shooting simulations using the Monte Carlo method, with thousands of iterations to ensure statistical robustness. The results indicate that the initial velocity, diameter, and material of the fragment significantly influence the damage probability. An increase in initial velocity and diameter notably enhances the damage probability; however, the effectiveness tends to saturate within the velocity range of 900~1 500 m/s and diameter range of 4~8 mm, showing diminishing returns beyond these thresholds. The use of multiple fragments significantly increases the damage probability, suggesting that an increase in the number of fragments leads to a substantial improvement in damage effectiveness, making the quantity of fragments a crucial factor in determining the overall damage outcomes. Based on these findings, selecting fragment diameters between 2 mm and 4 mm, initial velocities between 600 m/s and 900 m/s, and appropriate materials can optimize the design of fragmentation warheads, thereby significantly enhancing their damage effectiveness against UAVs. This study provides a scientific basis for the precise evaluation of UAV damage effectiveness, offering valuable insights for the development of more effective countermeasures and supporting informed decision-making in combat scenarios to ensure enhanced operational effectiveness and strategic advantages.

For loitering munition patrol flight trajectory path planning algorithm design and combat mission scenarios, combined with a space based on 2D and 3D digital terrain model, based on the nature of ants foraging path planning algorithm of the shortest path theory, implement cruise missile threat to the established operational area designated objectives cruise flight path planning of obstacle avoidance. The correctness and effectiveness of the ant colony algorithm are verified by the flight simulation and analysis of the patrolling missile in the established environment.

This paper investigates the guidance of missiles striking the maneuvering targets in three-dimensional (3D) space in the presence of model uncertainties, unknown target maneuvers and terminal impact angle constraints. An impact angle control guidance law based on nonsingular fixed-time sliding mode control (NFTSMC) and fuzzy logic is proposed. First, a 3D missile-target relative motion model is established, and the terminal impact angle constraint control is reformulated as a line-of-sight (LOS) angle tracking problem. To overcome the singularity commonly encountered in conventional terminal sliding mode control, a nonsingular fixed-time sliding mode surface (NFTSMS) is constructed, and an auxiliary function is introduced to guarantee singularity-free controller design. In addition, a fuzzy logic system (FLS) is incorporated to online approximate the lumped disturbances induced by target maneuvers and model uncertainties. The fixed-time stability of all signals from the closed-loop system is strictly proved based on Lyapunov stability theory. The simulated results show that the proposed guidance law can achieve the accurate interception of maneuvering targets under different initial conditions. Compared with the existing fixed-time sliding mode guidance strategy, it has significant advantages in suppressing the control command chattering and improving the line-of-sight angle tracking accuracy.

Aiming at the problem that the assembled fuze in active duty can not meet the test requirements during the underwater explosion damage test of a depth bomb, an safe fuze for detonation experiment is designed based on the original assembled fuze. The structure is composed of sealing arming device, limit water pressure arming device and auxiliary arming device etc. By using the nonlinear finite element software AUTODYN for numerical simulation analysis and underwater arming test verification, the process of the electric detonator exploding through the water inlet of the sealing structure in the sealing arming device is used to simulate and test, the results of experiment and numerical simulation are basically consistent. The fuze has been verified by drop, transportation and underwater explosion tests, it shows that the improved fuze can meet the requirements of fuze safety for handing of fuze, it can better solve the problems of safe operation and reliable operation in the underwater explosion test of deep-water mine bomb, and it has certain engineering application value and can be applied to other similar underwater explosion tests.

Micro Optic Gyroscope is a new type of miniature and integrated angular velocity sensor based on waveguide rings and Sagnac effect. Because of their potential advantages in comprehensive performance, MOGs will be widely used in smart ammunition,unmanned air and underwater vehicles and other small platforms. This paper briefly describes the basic principles of three types MOGs. The progress made by domestic and foreign research institutions in technical schemes of three type MOGs, the schemes of key components such as various optical waveguides and integrated optical devices and their manufacturing technology are introduced in detail. The development prospect of MOG is prospected.

It is an important direction for the future development of UAV military field to coordinated attack of multi-UAV to accomplish specific strike tasks. Aiming at the problem of coordinated attack of multi-UAV, a typical confrontation scenario is constructed. The unmanned aerial vehicle cooperative attack problem is modeled as a decentralized partially observable Markov decision process (Dec-POMDP), and a unique reward function is designed. The multi-agent deep deterministic policy gradient (MADDPG) algorithm is used to train the attack strategy. Monte Carlo method is used to analyze the simulation experiment, and the results show that after the training of the multi-agent reinforcement learning algorithm, the completion rate of the UAV cooperative attack task reaches 82.9% in specific confrontation scenarios.

The dynamic behavior of hemispherical resonator comprises the physical basis of hemispherical resonator gyros (HRG). This paper concerns the common problems that exists in the domestic researches of dynamic modeling of HRG to date, such as the lack of specific sources of reference, plenty of ambiguous deductions (some are even incorrect), hence the derivation process of dynamic modeling of resonator is carefully presented in detail. The paper summarizes the general background knowledge of relevant disciplines, and teases out two main types of modeling thoughts, in the sake of providing a theoretical support for the subsequent researches and engineering applications. Firstly, the elastic shell theory used as a general basis in dynamic modeling of hemispherical resonator is introduced, including the elastic geometric equations that describe the relationship between strain and displacement and the Hooke’s law that relates strain to stress; then the modeling method based on the d’Alembert principle commonly used in early theoretical researches is presented, and the second-order motion equations of resonator is obtained by establishing equilibrium equations and load analysis; finally, the modeling method based on Lagrangian mechanics which is inspired from aboard research is introduced, and the second-order motion equations are derived by calculating the kinetic and strain energy of the overall resonator with substitution of the Lagrangian equations. The latter method is increasingly popular by domestic researchers in recent years.

The traditional damage assessment methods can not assess the overall functional damage of light armored vehicles. Based on the requirement of “Serious Damage to Light Armored Vehicles”, through the evaluation and analysis of the dynamic damage probability of blast-fragmentation warheads from the aspects of structural damage, fragmentation damage, biological damage, impact and overpressure, the comprehensive damage assessment system of light armored vehicles are constructed. The criterion can comprehensively judge the damage grade of light armored vehicles from a single damage mode. According to the protection characteristics of light armored vehicles, the infantry vehicle is selected as a typical target to carry out target vulnerability analysis.And the equivalent target is designed and fired with projectile which carrying blast-fragmentation warheads. The damage conditions of its structure, biology, fragmentation, overpressure and overload are tested, which verifies that the comprehensive damage assessment criteria can accurately evaluate the damage grade of light armored vehicles. It has certain guiding significance to the damage assessment and analysis of light armored vehicles.

In recent years, the development of large-scale low-earth-orbit (LEO) satellite constellations has been progressing at an unprecedented pace, and their potential applications in the military domain have become increasingly prominent. These constellations possess unique technical characteristics that enable them to restructure the traditional kill chain, effectively addressing core challenges such as reconnaissance delays and insufficient cross-domain coordination in precision strikes. This paper provides a comprehensive introduction to the development of large-scale LEO satellite constellations and delves into their application directions in the military field. By examining typical combat scenarios from the perspectives of the kill chain and kill web, this paper analyzes how large-scale LEO satellite constellations can enhance the construction of the kill web and facilitate the closure of the kill chain in the field of precision strike. The findings of this study offer valuable insights and references for the construction of a global and systematic kill web based on a large-scale low-Earth-orbit constellation. Moreover, this research holds significant reference value for the development of China’s anti-access/area denial (A2/AD) strategic system architecture. As related projects in our country continue to advance steadily, the exploration of the potential of large-scale LEO satellite constellations in enhancing military capabilities becomes even more crucial.

To address the low decision-making efficiency and poor practicality of weapon-target assignment (WTA) in modern air-defense operations,a multi-objective WTA model that comprehensively considers four performance metrics including ammunition consumption,operational cost,total engagement time,and interception benefit is constructed.Practical constraints such as weapon-ammunition compatibility,ammunition inventory,and damage thresholds,etc,are also taken into account to enhance the battlefield applicability of the model.Secondly,a hybrid heuristic algorithm—hybrid ahaotic quantum particle swarm optimization-variable neighborhood search (HCQPSO-VNS) is proposed to solve the proposed WTA model.In the proposed algorithm,a logistic chaotic mapping is employed to improve the quality of the initial population,the quantum particle swarm optimization (QPSO) is utilized for global search; and the variable neighborhood search (VNS) with multiple neighborhood structures is integrated for local optimization to avoid premature convergence.Simulated results demonstrate that the proposed algorithm converges to a high-quality feasible solution within very few iterations.The obtained assignment schemes satisfy the expected lower bounds for damage,weapon-ammunition compatibility,and other constraints,while achieving an effective balance among four performance metrics.Comparative analysis shows that the overall performance of the proposed algorithm outperforms several mainstream algorithms,and can effectively improve the efficiency and scientific rigor of air-defense firepower allocation decisions.Meanwhile,as the problem complexity increases,the proposed algorithm retains high optimization efficiency and acceptable computational load,demonstrating favorable scalability.

In order to study the penetration power of ogive-nose projectile under the condition of wide velocity range, the ANSYS/LS-DYNA finite element analysis software is used to simulate the penetration of the ogive-nose projectile into concrete target plate without considering the impact response characteristics of its range. The effects of projectile material, caliber radius head, length-diameter ratio and mass on the penetration performance are studied under the impact velocity of 2.0Ma~6.0Ma. The results show that with the increase of the target velocity, the dimensionless penetration depth of the projectile increases first and then decreases. At the same time, compared with 93 tungsten alloy and TA7 titanium alloy, the penetration performance of G50 alloy steel is better. The caliber radius head has a significant effect on the dimensionless penetration depth during low-speed penetration, and the degree of influence is reduced during ultra-high-speed penetrating. The optimal caliber radius head ratio of the projectile is 3~4. The length-diameter ratio is positively correlated with the penetration depth at low speed penetration and negatively correlated with the penetration depth at ultra-high speed penetrating. The dimensionless penetration depth decreases with the increase of the length-diameter ratio, and the optimal length-diameter ratio of the projectile is 4~5. The mass has a significant effect on the depth of penetration, and has little effect on the dimensionless depth of penetration and the critical transformation rate. The critical transformation rate appears at 3.5Ma~4Ma.