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This paper concentrates on developing a missile terminal guidance law against a highly maneuvering target whose maneuvering acceleration is very close to that of the missile or even exceeds the missile normal acceleration in a finite period of time. A new saturated super-twisting algorithm is proposed and applied to the design of missile guidance law. The proposed algorithm has the advantages of simple structure, easy parameter tuning rules and a full utilization of the limit control input. The designed saturated super-twisting sliding mode guidance law is then employed in a missile guidance system. Simulation and its superior performance against strong maneuvering targets is demonstrated.

The missile-target assignment (MTA) is a typical weapon-target assignment problem in Command and Control of modern warfare. Despite the significance of the problem, traditional algorithms still lack efficiency, solution quality, and practicability in the adversarial environment. In this article, we propose a data-driven policy optimization with deep reinforcement learning (PODRL) for the adversarial MTA. We design a comprehensive reward function to motivate the optimization of assignment policy. As such, the learned policy can implicitly model the penetration of missiles under an adversarial environment in a data-driven way. We also present a fair sample strategy to improve the sample efficiency and accelerate the policy optimization. Experimental results show that PODRL can adaptively generate satisfactory solutions in both small-scale and large-scale instances. Furthermore, we evaluate the effectiveness of PODRL in a multiobjective scenario. The result demonstrates that a well-optimized policy can achieve high-quality allocation and demand forecast of the missile resources simultaneously.

In this paper, an integrated guidance and control approach is presented to improve the performance of the missile interception. The approach includes damping augmented system with attitude rate feedback to decrease the oscillation during the homing phase for missiles with low damping. In addition, physical constraints, which can affect the performance of the missile interception, such as acceleration limit, seeker’s look angle, and look angle rate constraints are considered. The integrated guidance and control problem is formulated as a convex quadratic optimization problem with equality and inequality constraints, and the solution is obtained by a primal–dual interior point method. The performance of the proposed method is verified through several numerical examples.

The task of substantiating operational and strategic requirements for an anti-aircraft missile system is considered. The essence of this task is to determine the totality of the most important quantitative and qualitative indicators characterizing the functional characteristics of the system, in which the tasks assigned to the system are ensured under the predicted conditions for conducting an air defense operation. The defi nition of an anti-aircraft missile system as a technical system is given, which consists of functionally interacting subsystems of fi re weapons, reconnaissance, command and control equipment. The content of operational and strategic requirements for an anti-aircraft missile system is disclosed, which is understood as information that refl ects the purpose, principles of construction and application of the system, tasks assigned to the system, and the necessary levels of their solution, composition, condition and development prospects of air attack systems, required values of the functional properties of the system. These indicators include the purpose and spatio-temporal characteristics of the system, quantitative and qualitative requirements for fi repower, mobility, survival, applicability, resistance to enemy opposition, the conditions for using the system in the preparation and conduct of an air defense operation. It is shown that the substantiation of the requirements for the anti-aircraft missile system should be based on a system-conceptual approach in the process of operational research of confl ictinformation confrontation between the anti-aircraft missile system and the air attack system using static and dynamic simulation methods. The features of the development and use of simulation and mathematical models that describe the functioning of the system as part of the operational-strategic grouping of anti-aircraft missile forces when performing tasks to cover important state facilities in the predicted conditions for conducting an air defense operation are considered. It is shown that application off ered approach will allow to create the system of zenithal rocket armament, rational on a criterion «effi ciency - cost» and able to decide operational-strategic tasks in relation to the protection of objects and troops in the diff erent forms of conduct of antiaircraft operation.

Jamming resources allocation (JRA) is an essential task in clustered combat environments. Especially in cases with multiple threats, efficient JRA is imperative for protecting key assets. In this study, multiple distributed outboard jammers protecting multiple targets against a multi‐missile threat are considered, where the function of JRA includes jamming object selection and jammer power allocation. To address this problem, first, a scheme to evaluate the jamming effectiveness of the radar seeker under cooperative jamming from multiple jammers is proposed. Considering power allocation, a mixed‐integer programing model for the optimisation of JRA is further established. A two‐track simultaneous update binary particle swarm algorithm (TS‐BPSO) is then devised to obtain the solutions of the JRA. Finally, the effectiveness of the proposed method for multiple jammers in the multiple missiles scenario is evaluated through simulations. The simulation results suggest that the distributed cooperative jamming resource allocation is affected by the incoming orientation of the missile and the relative position of the jammers and the targets. The findings of the study enable evaluating the use of jammer formations and provide insights into developing effective jamming strategies.

This paper proposes a novel guidance law based on model predictive control for protecting an aircraft from a homing missile. Considering that in the target‐missile‐defender engagement the attacking missile is pursuing the target aircraft by employing a known linear guidance law, a non‐linear predictive model for the engagement is established. This predictive model allows converting the three‐body engagement to a one‐on‐one engagement. The time‐to‐go for the defender towards the future position of the incoming missile is analytically derived, indicating that the optimal time for the defender to intercept the incoming missile is a fixed‐point of a real‐valued function. As a result, the optimal interception duration can be obtained by a standard fixed‐point iteration method, and thus the interception point can be readily predicted via integrating the predictive model. The guidance command is generated by directly leading the defender to the predicted intercept point. Numerical simulations in different scenarios validate the algorithm to be computationally efficient, and demonstrate that the proposed strategy outperforms previous techniques in terms of miss distance, engagement duration, and the control effort.

The selection of weapon systems involves a number of activities to choose the best system in relation to the predefined operational requirements and other vital criteria. In the case of surface to air missile systems competing for the NAREW program, attempts are being made to obtain an asset that will be capable of engaging a spectrum of air threats, under specified conditions, with a predefined high degree of probability. In order to make the right choice, it is necessary to analyze information on performance and combat capabilities. Thus, the aim of this article is to develop a preliminary method of evaluating the capabilities of surface to air missile systems offered under the NAREW program. The theoretical foundation of the empirical study was provided by the method of literature content analysis. Using the methods of comparison and generalization, the author obtained data on the combat capabilities of surface to air missile systems expressed through their tactical and technical parameters. Among the empirical methods, the author applied the algorithm of a multi-criteria analysis and an assessment of the capabilities of surface to air missile systems based on the use of matrix calculus. The diagnostic survey, conducted by means of the questionnaire technique, made it possible to prioritize the adopted evaluation criteria and, consequently, to conduct proper research. The formulation of the final conclusions and establishing the links between the theoretical and empirical part of the study was achieved by means of a synthesis. The results obtained in such a manner may constitute a valuable information database, showing the directions that should be considered when selecting a short-range surface to air missile (SAM) system for Poland. The evaluations and suggestions included in this study can be used for prospective solutions and research conducted in a similar area.

Purpose: This study aimed at developing a model that can improve the accuracy of reliability prediction through guided missile field big data analysis. Methods: All the relevant operational and field maintenance data was collected by cooperating with the maintenance organization within the military. A data purification method was adopted to analyze the collected data. Omissions and missing data were processed by using the results of a parallel review that was conducted by examining the results of the consultation session with the missile operation expert and the quality data of the missile producer. The actual data was analyzed at the level of military repair parts, and the correction factor was calculated. Results: Since the correction factor analyzed in this study was calculated at the component level, it can be applied to correct the predicted failure rate of components calculated when developing new weapon system projects in the future. It is possible to improve the accuracy of the analysis results in the field of element development, which requires the failure rate of the component unit. Conclusion: In this study, the reliability of a guided missile in the operations and maintenance phase was analyzed through field big data analysis of the missile. Based on the results, the reliability predicted during the R&D phase was corrected, and a methodology (correction factor) was applied to reduce the reliability gap.

An improved methodology to quantify the required level of combat capabilities of the Air Force of the Armed Forces of Ukraine is proposed, taking into account the dynamics of the quantitative and qualitative components of the enemy air force in the medium and long-term development of its weapons system. The methodology is intended for use in the system of long-term and medium-term defense planning based on the capabilities for substantiating programs and plans for the development of weapon system and military equipment of anti-aircraft missile troops and tactical aviation. Unlike the well-known methodological approaches, this methodology takes into account the impact on the change in the required level of сapability of the maximum possible rate of delivery of the advanced weapons and military equipment to the air enemy troops, which are limited not only by the factors of financing by the enemy air force of programs and plans for the development of their forces, but also by the maximum production and technological capabilities of the enemy industry in terms of the rate of mass production of the advanced high-technology samples. This makes it possible to more thoroughly and adequately determine the date of timely response by the state to the growth of military threat, determine priorities and rationally distribute expenses over time for defense needs. The methodological basis to quantify the possible rate of serial production of the advanced high-technology weapons and military equipment of enemy air force is the use of set of mathematical models based on the processing of world-class statistical scientific and technical information. These models constitute formalized relationship between the values of the maximum possible rate of mass production of multirole fighters on the generalized indicators of their combat properties, as well as the dependence of these indicators on a number of tactical and technical characteristics that determine the combat properties of the sample for solving combat missions as intended. It is proposed to determine the required level of capabilities based on the use of the method of combat potentials, by establishing the correspondence between the share of the combat potential of anti-aircraft missile troops and tactical aviation, which can be implemented in each specific scenario of the use of the air component of the joint forces for each operational (combat) mission, which is necessary for applying unacceptable damage to the enemy. The result of the practical use of the proposed methodology is the dependence of quantitative estimates of the level of required capabilities on time throughout the depth of long-term defense planning.

The article examines the role and place of modern technologies in the development of modern systems (complexes) of anti-aircraft missile weapons. It is shown that the development of anti-aircraft missile weapons is due to the dialectical confrontation with the means of air attack, the development of which in the developed countries of the world is given special attention. The purpose of the article is to determine the structure and main directions of development of the technological basis necessary for the creation of modern systems (complexes) of anti-aircraft missile weapons in Ukraine. The analysis of the problematic issues of the development of the technological basis in Ukraine is carried out on the example of the medium-range anti-aircraft missile system, as the most complex and science-intensive product of military equipment. It is shown that the creation of such a system in Ukraine is possible only with the transition to the priority creation of a scientific and technical reserve, which can be used as the basis for the creation of radar, fire and other combat assets of this system. Based on the analysis, a list of priority and critical technologies was substantiated. It is shown that the components of these technologies are technologies of active phased antenna arrays, including digital, transmitting and receiving devices, devices for indicating and displaying information, specialized computer technology, communications and other technologies necessary for the creation and use of composite parts of modern medium-range anti-aircraft missile systems. It is shown that the development of the technological basis should be carried out on the basis of the principles of universality and unification, which will allow to reduce costs throughout the entire life cycle of the product, both during its development and production, and during operation. The results obtained can be used to determine priorities in planning research on the creation of technologies necessary for the creation and production in Ukraine of systems (complexes) of anti-aircraft missile weapons, the effectiveness of which will not be inferior to the best world standards.

The article, based on the analysis of scientific works and experience of local wars and conflicts, indicators and criteria of the effectiveness of solving problems by the reconnaissance system of an air enemy, which are created by radio-technical troops, are selected, as a functional from the generalized indicators of the quality of solution the assigned tasks. Generalized indicators of the spatial combat capabilities of the grouping of radio engineering troops are proposed, namely, the coefficient of implementation of the required boundaries for issuing combat information for AAMT and fighter aircraft troops. As a complex indicator of spatial combat capabilities of the grouping air defence, which provides a comparative evaluation efficiency of options for building combat orders of groupings, suggested to use the cover factor of the object. The normalized value of the complex indicator - the coefficient of coverage of the object depends on the values ​​of the generalized indicators of the spatial combat capabilities of the grouping of radio engineering troops. The logical sum of the coefficients of coverage of the object by units of anti-aircraft missile forces and fighter aircraft makes it possible to evaluate the result of interaction between anti-aircraft missile forces and fighter aircraft when performing a common task of covering an important object. The use of the proposed generalized spatial indicators of the combat capabilities of radio engineering troops and a complex indicator of the effectiveness of an air defense grouping makes it possible to increase the objectivity and information content of the result of a comparative assessment of options for building a combat formation of a group of radio engineering forces. The use of the proposed indicators for the comparative assessment of effectiveness does not contradict existing scientific approaches and allows to formalize the methodology for selecting positions for units of radio technical troops.

In this paper, a cooperative guidance law is proposed for missiles with thrust control to realize impact angle constrained salvo attack, where missile speed limit is also considered. Guidance of a ...

Several models of programmed flight have been constructed to perform calculations on flight path optimization in designing tactical and anti-aircraft-guided missiles. The developed models are based on the determination of interrelated programmed values of altitude and the flight path angle depending on the range which have a differential relationship. The combination of flight altitude and flight-path angle programs allows the users to simulate the steady flight of a guided missile to the calculated endpoint using the methods of proportional control. Good correspondence of the developed models to the physics of flight was shown by assessing the quality of approximation of the developed models of flight paths of anti-aircraft guided missiles obtained using other known models. The obtained approximation error was less than 5% which indicates a good correspondence of the developed models to the physics of flight. Compliance of the developed models of programmed flight with the intended purpose and the advantage over the most common known models were proved by optimizing the flight paths of the anti-aircraft-guided missile. In most of the considered calculation cases, the value of the objective function was improved to 2.9%. The flight path was optimized using a genetic algorithm. The developed models have a simple algebraic form and a small number of control parameters are presented in a ready-to-use form and do not require refinement for a concrete task. This allows them to be implemented in design practice without spending much time to speed up the calculation of optimal design variables and optimal flight paths of tactical and anti-aircraft-guided missiles

This paper aims to propose a new guidance algorithm for intercepting a high-speed maneuvering target, such as a tactical ballistic missile that flies in a quasi-ballistic trajectory. The motivation of this study lies in the fact that the classical proportional navigation guidance (PNG) undergoes the performance degradation under the above engagement scenario due to its intrinsic property. To deal with the issue, an accurate collision course that reflects the motion characteristics of the ballistic target and missile is first analyzed. The desired look angle that leads to achieving the accurate collision course is then determined with the help of a novel time-to-go calculation method. Finally, the proposed guidance law providing the desired look angle is obtained by leveraging the concept of the biased PNG. Since the proposed method is designed to achieve an accurate collision course, it does not lead to unnecessary maneuvering near the target under the engagement scenario. This property is desirable for reserving the operational margin of maneuverability for reacting to unexpected situations during the engagement. It could improve the capturability of the target. Finally, the performance of the proposed method is verified through numerical simulations in a way to compare with the existing methods such as PNG and the augmented PNG (APNG).

Beyond-visual-range (BVR) engagement becomes more and more popular in the modern air battlefield. The key and difficulty for pilots in the fight is maneuver planning, which reflects the tactical decision-making capacity of the both sides and determinates success or failure. In this paper, we propose an intelligent maneuver planning method for BVR combat with using an improved deep Q network (DQN). First, a basic combat environment builds, which mainly includes flight motion model, relative motion model and missile attack model. Then, we create a maneuver decision framework for agent interaction with the environment. Basic perceptive variables are constructed for agents to form continuous state space. Also, considering the threat of each side missile and the constraint of airfield, the reward function is designed for agents to training. Later, we introduce a training algorithm and propose perceptional situation layers and value fitting layers to replace policy network in DQN. Based on long short-term memory (LSTM) cell, the perceptional situation layer can convert basic state to high-dimensional perception situation. The fitting layer does well in mapping action. Finally, three combat scenarios are designed for agent training and testing. Simulation result shows the agent can avoid the threat of enemy and gather own advantages to threat the target. It also proves the models and methods of agents are valid and intelligent air combat can be realized.

Path planning is a global optimization problem aims to program the optimal flight path for Unmanned Aerial Vehicle (UAV) that has short length and suffers from low threat. In this paper, we present a Mixed-Strategy based Gravitational Search Algorithm (MSGSA) for the path planning. In MSGSA, an adaptive adjustment strategy for the gravitational constant attenuation factor alpha ( $\alpha$ ) is presented firstly, in which the value of $\alpha $ is adjusted based on the evolutionary state of the particles. This helps to adaptively balance the exploration and exploitation of the algorithm. In addition, to further alleviate the premature convergence problem, a Cauchy mutation strategy is developed for MSGSA. In this strategy, only when the global best particle cannot be further improved for several times the mutation is executed. In the MSGSA based path planning procedure, we construct an objective function using the flight length cost, threat area cost, and turning angle constraint to decrease the flight risk and obtain the smoother path. For performance evaluation, the MSGSA is applied to two typical simulated flight missions with complex flight environments, including user-defined forbidden flying areas, Radar, missile, artillery and anti-aircraft gun. The obtained flight paths are compared with that of the standard Gravitational Search Algorithm (GSA) and two improved variants of GSA, i.e. gbest -guided GSA (GGSA), and hybrid Particle Swarm Optimization and GSA (PSOGSA). The experimental results demonstrate the superiority of the MSGSA based method in terms of the solution quality, robustness, as well as the constraint-handling ability.

The results of the analysis of the participation of missile troops and artillery in the enemy’s fire defeat during the operation in the occupied area of Donbass show that the process of enemy fire defeat has a number of problems that have significantly reduced its effectiveness. Among them: lack of intelligence information or its excess, rapid aging of intelligence information in the face of transient hostilities, lack of appropriate mechanism for prioritizing targets, inconsistency of intelligence means of destruction, lack (imperfection) of automated control systems, which led to processing only 20 % of intelligence information. These problems were investigated only on some issues, such as: saturation of troops (forces) with new, sometimes upgraded models of weapons and military equipment, both reconnaissance and destruction to increase their capabilities; increasing the implementation of reconnaissance and destruction capabilities as components of the process of enemy fire damage by developing, implementing or improving automated control systems for enemy fire damage; improving the reconnaissance system to realize the potential capabilities of missile troops and artillery to fire at the enemy and create reconnaissance and fire system, increase the level of efficiency of intelligence. The purpose of the article is to carry out a system analysis of the process of engaging the enemy with fire in order to determine its components, the interrelationships between them and their influence on the process. The study of the process of fire defeat of the enemy was carried out by the «tree of aims» method, which allowed dividing it into components, taking into account their equivalent contribution to the goal, identify the links between them and their impact on the process. To evaluate each component of this process, efficiency indicators are proposed, which can be used to determine the contribution of each component in achieving the goal of firing enemy defeat, which will balance them for the effective implementation of the tasks of this process. Both existing and new models and methods for evaluating the effectiveness of firing enemy defeat can be used to calculate efficiency indicators.

As a maritime country with a large area, besides the need to defend itself with the military, it also needs to protect itself with aerospace technology that can be controlled automatically. This research aims to develop an air defense system that can control guided missiles automatically with high accuracy. The right method can provide a high level of accuracy in controlling missiles to the targeted object. With the backpropagation neural network method for optimal control output feedback, it can process information data from the radar to control missile’s movement with a high degree of accuracy. The controller uses optimal control output feedback, which is equipped with a lock system and utilizes an accelerometer that can detect the slope of the missile and a gyroscope that can detect the slope between the target direction of the missile to follow the target, control the position, and direction of the missile. The target speed of movement can be easily identified and followed by the missile through the lock system. Sampling data comes from signals generated by radars located in defense areas and from missiles. Each part’s data processing speed is calculated using a fast algorithm that is reliable and has a level of accuracy and fast processing. Data processing impacts on the accuracy of missile movements on any change in the position and motion of targets and target speed. Improved maneuvering accuracy in the first training system can detect 1000 files with a load of 273, while in the last training, the system can detect 1000 files without a load period. So the missile can be guided to hit the target without obstacles when maneuvering.

The main issues of the use of unmanned aerial vehicles (UAVs) in the Armenian-Azerbaijani military conflict and possible ways to combat them with the use of various anti-aircraft missile (artillery) systems to solve certain problems are considered. In addition, the possibilities of using air defense units (AIR) and electronic warfare (EW), the use of various means of reconnaissance, passive location to effectively detect UAVs, combat them and identify the main advantages and disadvantages of UAVs, which depend on the capabilities effective actions of air defense, EW, intelligence. The criterion of efficiency is also defined and the offers on increase of efficiency of management of division of air defense and EW in fight in various conditions of a situation are developed. The complex of existing problems and issues that determine the state of air defense units and their capabilities in the fight against UAVs, necessitated the development of a scientific apparatus that will assess the effectiveness of combat air defense units and identify ways to improve it. In other words, such a device should be used to develop scientifically sound practical recommendations based on objective laws using the latest scientific advances. The main thing is to reveal and reasonably use the mechanisms of manifestation of the laws of air defense units, to develop and creatively apply scientifically based principles of combat organization, management issues and methods of work of commanders and staffs of JI air defense troops using modern technical means. The main requirement in solving air defense tasks is to maintain the combat readiness of air defense units to the extent that it will avoid a sudden strike by enemy air attack means (AML), including UAVs, which are effectively used in various military conflicts and their number is steadily increasing. In such conditions, the timely and effective functioning of air defense means becomes a decisive factor that ensures success in the fight against the aggressor.

This study aims to solve the problem of multi-missile simultaneous attacks on maneuvering target. The challenges include multi-missile cooperative control and target’s trajectory prediction. A controller based on nonlinear distributed model predictive control (NDMPC) is designed for multiple missiles against a maneuvering target, and a trajectory prediction method based on particle swarm optimization (PSO) algorithm is proposed. This study has mainly completed the following three aspects of work. Firstly, the cost function of the controller is constructed to optimize the accuracy and synchronization of the multi-missile system with consideration of collision avoidance. Secondly, the velocity control of the leading missile is designed by using the range-to-go information in real time to ensure the attack efficiency and the control of the terminal velocity difference. Finally, a kinematic model of the target is estimated by using short-term real-time data with the PSO algorithm. The established model is employed to predict the target trajectory in the interval between radar scans. Numerical simulation results of two different scenarios demonstrate the effectiveness of the proposed cooperative guidance approach.

The recent research is focused on the development of an advanced interceptor missile that has hit-to-kill accuracy against ballistic targets performing evasive maneuvers. In this paper, a guidance law that achieves hit-to-kill accuracy against ballistic target executing worst-case maneuvers is developed using second-order sliding mode control and optimal control. The guidance law thus developed is continuous and has minimum time convergence for worst-case target maneuvers. The performance of the continuous guidance law with minimum time convergence is evaluated through numerical simulations against ballistic targets executing step maneuvers with changing polarity and weaving maneuvers.

The results of the research published in the article will be useful for logistic support specialists who are involved in the creation (modernization) of the samples of weapons and military equipment. A methodical approach to substantiating the firepower requirements of a promising anti-aircraft missile system (system) is presented, which provides for the assessment of the components of firepower – search capabilities, firepower and fire resource, taking into account the intensity of the air attack, range and conditions of use of the complex (systems) for each type of goal. A list of indicators of firepower is given, namely, the average time of detection and recognition, the intensity of reconnaissance of targets, the density of the flow of missile launches (rate of fire), the preparation time of the first launch, the probability of hitting a target, and the average consumption of missiles per target. It is shown that the firepower indicators of a promising anti-aircraft missile system (system) at a given level of protection should be determined provided that it is necessary to defeat a selected group of air targets with a probability of not lower than a given level. The requirements for the firepower of a promising anti-aircraft missile system (system) can be substantiated using a complex of mathematical models that provide the opportunity to study scenarios of conflict-information interaction of a promising anti-aircraft missile system (system) and air targets in the form of a simulation machine experiment. It is shown that, based on the simulation results, the indicators of search capabilities, fire performance and fire resource of a promising anti-aircraft missile complex (system), as well as the mathematical expectation of the number of people hit by the whole when the ammunition load of anti-aircraft guided missiles installed on launchers are used, should be determined.

This paper proposes a robust three-dimensional cooperative guidance law (RTCGL) against a maneuvering target. When some missiles are intercepted during the engagement, this RTCGL integrated with a local filtering algorithm can ensure that the rest missiles hit the maneuvering target simultaneously. The pitch acceleration command is designed based on an augmented proportional navigation guidance law and can make the missile’s trajectory fall into its yaw plane. Then the three-dimensional cooperative problem is converted into a planar one. The yaw acceleration command consists of a guidance component for homing and a coordination component for simultaneous arrival. Numerical simulation results are presented to verify the effectiveness of the cooperative guidance law.

This study proposes an algorithm to calculate fast the predicted intercept point (PIP) of the anti-ballistic missile system. A neural network system is trained to learn the motion of the ballistic target to predict the future target position. Then a prediction algorithm iteratively calculates PIP and the launch time of the interceptor. PIP calculation enables the missile to effectively approach to the ballistic target. Computer simulations using simple interceptor models are conducted, demonstrating the usefulness of the proposed PIP determination algorithm. The proposed algorithm significantly reduces the computation time required for target trajectory prediction in real-time.

The results of the research published in the article will be useful for logistic support specialists who are involved in the organization of the operation and renewal of weapons and military equipment. The article discusses the methodical approach to solving the question of ensuring the choice of a rational option for maintaining the efficiency of the anti-aircraft missile system, taking into account the impact of moral aging of the third kind. The publications in the scientific and technical literature on the issues of predicting the durability of weapons and military equipment based on logical-probabilistic models, which take into account both changes in the properties of components of anti-aircraft missile systems, as well as the possibility of its logistics support system, analyzed the task of choosing a rational option for maintaining the technical condition of anti-aircraft missile systems, taking into account the above factors, they were not considered, which allowed to determine the unsolved scientific problem, which consists in the further development of the scientific and methodological approach of choosing a rational variant of maintaining the technical condition of the anti-aircraft missile systems, taking into account the change of the properties of the elements of the equipment and the capabilities of the logistics system to restore its technical resource. A mathematical model of choosing a rational option for maintaining the technical condition of an anti-aircraft missile system is described taking into account changes in the properties of equipment elements and the capabilities of a system for restoring its technical resource. It is shown that the choice of one or another variant of maintaining the operability of an anti-aircraft missile system should be based on assessments of the technical and economic efficiency of compensating for the degradation of resource fail-safety. It is shown that to compensate for the degradation of resource fail-safety of the air defense system’s operability, methods of modernizing electronic equipment and methods to increase the availability of operational processes can be used. Based on the mathematical apparatus of the trees of the limiting state, analytical expressions are obtained for calculating the estimates of the indicators of technical and economic efficiency of the application of various methods of compensating for resource fail-safety. An approach is proposed to justify the choice of the most rational option for maintaining the health of air defense systems by the criterion of maximum technical and economic efficiency based on the results of ranking estimates of technical and economic efficiency indicators.

The choice of the most appropriate methods and tactics of overcoming the enemy’s modern air defense while striking at their ground targets is an urgent task during the combat use of aviation in modern conditions. In the article, one of the ways to solve this problem is the automation of calculation and selection of the most profitable route for overcoming the enemy’s air defense. This will allow taking into account many factors affecting the effectiveness of overcoming the enemy’s air defense, in a short time to find such an option for the flight of an aircraft along a route in which opposition of the ground anti-aircraft missile systems of the enemy will be minimal. It is noted that the goal of solving this problem is to find the optimal flight criterion according to the criterion of the minimum of successful launches (striking shots) in the conditions of a well-known grouping of enemy air defense equipment. The essence of the solution of the problem lies in the fact that, based on the initial information, the electronic computing device searches for a route represented by straight sections by successively switching from the reference (initial) trajectory to the optimal one in a finite number of steps. In this case, the minimum total number of successful launches (striking shots) is the criterion. The end result is the optimal coordinates of the turning points of the route and the flight altitude on the route sections from the point of view of effectively overcoming the enemy air defense. The proposed models and an algorithm for solving the problem will contribute, at the stage of planning combat operations by combatants of tactical aviation units (subunits), to significantly improve the quality of decision-making, reduce the time for preparation for military operations in the conditions of time pressure, and increase the efficiency of combat missions in combat military operations. Using this technique will allow you to develop the best option for a combat flight to the target and vice versa, as well as automate the decision-making process in preparation for combat operations.

In recent days, our Indian nation moves towards “Make in India” and “Digital India” concepts. To make those concepts go live, the proposal aims at the development of an indigenous embedded system for the real time acquisition of the missile position when it is ready to be launched. The system to be developed will also communicate from the Missile Launch vehicle to the control center. It displays the position of the missile in addition to its video stream displayed on the operator’s console in control center. An extensive algorithm to calculate the angular position of the missile using the video streams captured from three different cameras will be formulated. The possibilities of real-time implementation will be explored and an extensive effort on developing a framework to implement using Field programmable Gate Arrays (FPGAs) will be carried out. The final outcome of this work will be the system on programmable chip (SoPC) implementation using FPGA for video streams, angular position display of the missile and Wireless communication between Missile launch vehicle and operator’s console in the Control center. This entire module will ensure the reliability of the angular position at which the missile has to be launched and also compactness can be achieved since the conventional computing systems will be replaced by FPGAs.

The article develops an approach to building a universal automated control and testing station using expert systems. An analysis of the airborne equipment of anti-aircraft guided missiles of methods and means of their control showed that the most difficult task to determine a reliable technical condition is to conduct, using test stations, the control and measurement operations of electronic anti-aircraft guided missiles. The prospects of using expert systems in the field of technical control is shown, which allows to increase the effectiveness of monitoring the technical condition of airborne equipment of anti-aircraft guided missiles by taking into account the knowledge of experts, accumulating knowledge, taking into account the experience of experts and implementing self-training of an expert control system. The formation of information-control models of the current technical condition of anti-aircraft guided missiles (the set of all values of controlled parameters and their change in time, the "passport" of anti-aircraft guided missiles) is proposed, which makes it possible to make the forecast of the technical condition of anti-aircraft guided missiles more reliable by taking into account trends in changes in control parameters . This allows us to draw an extended conclusion on the results of the expert monitoring system: the anti-aircraft guided missile is operational (malfunctioning) or operational (inoperative), the parameters are outside the normal range and the following intercontrol interval is recommended. The proposed structure of the control and testing station implements the control tasks in a comprehensive manner: according to the control program it provides stimulating signals, analyzes output reactions, replenishes the base of reference values of the measured signal parameters and forms information-control models of the current technical condition of the anti-aircraft guided missile, which are then compared using an algorithm with information -controlled models of the reference state of the anti-aircraft guided missile, which is controlled. The proposed approach to the construction of a universal automated control and test station using expert systems will ensure the construction of a universal unified automated control and test station with a variable configuration, which will allow automated control of several samples of anti-aircraft guided missiles with a high degree of reliability and recommend an intercontrol interval for it.

In the context of the Joint Forces operation in eastern Ukraine and the new challenges of the hybrid war on the part of the Russian Federation, there is an urgent need for finding possible ways of building an effective control system for a spatially distributed network-centered air defense missile cover system. The article presents a conceptual approach to the design of the structure that would be effective for controlling such a system, which is based on both the classical construction principles of control systems and the novel network-centric approach to design of control systems. The conceptual approach takes into account the peculiarities of building a spatially distributed tier of air defense missile cover.

The paper presents the features of the computer application developed in the RAD Studio XE4-10.1 Berlin programming environment for the simulation of guided flight of the GROM type missile. The application uses an integrated algorithm to solve a system of differential equations, as well as a dynamics model for the missile, target and atmosphere. Further to this, simulation tests have also been conducted.

Maneuver decision-making directly determines the success or failure of air combat. To improve the dogfight ability of unmanned combat aerial vehicles and avoid the deficiencies of traditional methods, such as poor flexibility and a weak decision-making ability, a maneuver method using deep learning is proposed. A total of 72 different maneuvers are constructed, and 544320 states are designed. Flight simulations are conducted under these different states to obtain corresponding future azimuth angles. A deep neural network is trained with these offline data, and thus, the network possesses state prediction capability. A situation assessment function and a decision objective function based on azimuth angles are constructed. During air combat, the optimal maneuver is selected from the maneuver library according to the predicted state and the decision objective function. The results of air combat simulations indicate that the unmanned combat aerial vehicle (UCAV) can win the air combat game by the proposed method in a balanced situation and can meet missile launching conditions in an adverse situation. The operational time of this method has been reduced by 0.01 s compared with the comparison method.

This paper studies the cooperative guidance and control problems with formation-containment tracking requirement under directed topologies for multiple tactical missiles. The states of the formation-leaders can not only keep a parallel triangle formation but also make tracks for the state trajectory generated by the tracking-leader, while the states of followers converge to the convex hull formed by those of the formation-leaders. Firstly, an integrated cooperative guidance and control framework is proposed, and combat missions are distinguished in line with tactical missiles rewarded different functions in practical applications. Then, a terminal slide mode guidance law with impact angle is presented in three-dimensional space, which ensures attack missile to attack the target in finite time. Sufficient conditions for multiple tactical missiles to achieve formation-containment tracking are derived. On the basis of Lyapunov theory, it is shown that the expected formation-containment tracking can be realized by reconnaissance and decoy missiles in the presence of the tracking-leaders' unknown control input. In addition, in the case of unknown drag force, the six degrees of freedom missile controller is designed by combining genetic algorithm and disturbance observer to dynamically adjust the rudder deflection and thrust, ensuring stable tracking of overload command during cooperative attack. Finally, numerical simulations validate the feasibility and effectiveness of the proposed results.

This paper proposes a new reinforcement learning approach for executing combat unmanned aerial vehicle (CUAV) missions. We consider missions with the following goals: guided missile avoidance, shortest-path flight and formation flight. For reinforcement learning, the representation of the current agent state is important. We propose a novel method of using the coordinates and angle of a CUAV to effectively represent its state. Furthermore, we develop a reinforcement learning algorithm with enhanced exploration through amplification of the imitation effect (AIE). This algorithm consists of self-imitation learning and random network distillation algorithms. We assert that these two algorithms complement each other and that combining them amplifies the imitation effect for exploration. Empirical results show that the proposed AIE approach is highly effective at finding a CUAV’s shortest-flight path while avoiding enemy missiles. Test results confirm that with our method, a single CUAV reaches its target from its starting point 95% of the time and a squadron of four simultaneously operating CUAVs reaches the target 70% of the time.

Dogfight is often a continuous and multi-round process with missile attacks. If the fighter only considers the security when evading the incoming missile, it will easily lose the superiority in subsequent air combat. Therefore, it is necessary to maintain as much tactical superiority as possible while ensuring a successful evasion. The amalgamative tactical requirements of achieving multiple evasive objectives in a dogfight are taken into account in this paper. A method of generating a nondominated maneuver strategy set for evading missiles with tactical requirements is proposed. The tactical requirements include higher miss distance, less energy consumption, and higher terminal superiority. Then the evasion problem is defined and reformulated into a multi-objective optimization problem, which is solved by a redesigned multi-objective evolutionary algorithm based on decomposition (MOEA/D). Simulations are used to demonstrate the feasibility and effectiveness of the approach. A set of approximate Pareto-optimal solutions satisfying the tactical requirements are obtained. These solutions can not only guide the fighter to avoid being hit but also achieve the goal of relatively reducing energy consumption and improving terminal superiority.

This study deals with the autonomous evasive maneuver strategy of unmanned combat air vehicle (UCAV), which is threatened by a high-performance beyond-visual-range (BVR) air-to-air missile (AAM). Considering tactical demands of achieving self-conflicting evasive objectives in actual air combat, including higher miss distance, less energy consumption and longer guidance support time, the evasive maneuver problem in BVR air combat is defined and reformulated into a multi-objective optimization problem. Effective maneuvers of UCAV used in different evasion phases are modeled in three-dimensional space. Then the three-level decision space structure is established according to qualitative evasive tactical planning. A hierarchical multi-objective evolutionary algorithm (HMOEA) is designed to find the approximate Pareto-optimal solutions of the problem. The approach combines qualitative tactical experience and quantitative maneuver decision optimization method effectively. Simulations are used to demonstrate the feasibility and effectiveness of the approach. The results show that the obtained set of decision variables constitutes nondominated solutions, which can meet different evasive tactical requirements of UCAV while ensuring successful evasion.

Based on adaptive sliding mode control method, this paper considers the interception problem to deal with both impact time and angle constraints. The stability and convergence characteristic of proposed guidance law are analyzed. The requirements of the terminal constraints and minimum miss distance can be satisfied. An adaptive law is put forward to adjust the guidance gain. The simulation results indicate that the missile with proposed guidance law can intercept the target successfully with not only desired impact time but also expected impact angle. The interception task can be fulfilled in a satisfactory manner.

This article describes a project to tackle the task of re-equipment of anti-aircraft missiles, anti-aircraft missile complex S-75M missile target based on research of world experience in creation of rocket targets relevant to modern requirements, by maximizing the potential capabilities of antiaircraft guided missiles anti-aircraft missile system, with the elaboration and implementation of new ideas and solutions for the application of component parts of missiles AAMS for a new purpose, implementing the criteria for "maximum results at minimum costs".

Privacy concerns on smartphones have been raised by the public as more and more personal data are now stored on them. In this paper, we show that location information can be compromised through mobile inertial sensors which are considered insensitive and accessible by any mobile application in both iOS and Android without special privilege. We present MISSILE, an automatic system that can infer users’ indoor location using labeled sensor data as prior knowledge. The key idea is that when a user reaches a particular indoor location, it is very likely that he/she has passed through some unique interior structures of a building, such as winding corridors, fire stop doors or elevators. These structures exhibit repeatable motion and environment patterns in mobile sensors that can be recognized by supervised learning. In our MISSILE system, the location labels of training data are automatically attained by Bluetooth beacons deployed in sensitive locations. With effective feature extraction procedure robust modeling, MISSILE shows good success rate for inference attack. For example, in a university campus with 15 sensitive locations, MISSILE achieves up to 73% correct prediction score whereas a random guess can only achieve 1/(15 + 1) = 6.25%. Further improvements on system performance and countermeasures are also discussed.

On the basis of analysis of world progress of technologies trends the structure of technological base, necessary for creation and production in Ukraine of the modern anti-aircraft missile systems (complexes) is substantiated. It is shown that basis of this technological base is made by the aggregate of food and productive technologies, describing the look of component parts (battle and technical facilities) of anti-aircraft rocket weapons, has a difficult structure and is based on achievements of scientific and technical progress in the different areas of knowledge. Principles over of development of technological base are brought and critical technologies, development of which will allow to create scientifically-technological reserves which can be fixed in basis of development and production in Ukraine of perspective systems (complexes) of the next generation anti-aircraft rocket weapon are presented.

This paper introduces a novel and efficient algorithm for online estimation of zero-effort-miss and time-to-go based on data driven method. Only missile-target separations are utilized to construct the estimation models, and a practical Fisher fusion algorithm is derived to acquire the estimates with high accuracy and computational efficiency. Further, the two parameters can be online estimated at a particular time. Meanwhile, the kinematics equations of the missile-target engagement are independent, and assumptions of the missile guidance system dynamics and behaviors of the missile and target are completely out of consideration. Moreover, the effectiveness and applicability are explicitly verified through various simulation scenarios. Keywords: Data driven, Missile-target separations, Online estimation, Time-to-go, Zero-effort-miss

The article describes the experience of creating automated control systems by foreign countries. Experience in controlling fire weapons and reconnaissance assets. The analysis of their interaction. Considered in detail the automated control system of field artillery of the United States of America Advanced Field Artillery Tactical Data System (AFTDS). This is an experience of creating a system of foreign countries. Experience in controlling fire weapons and reconnaissance assets. The analysis of their interaction. Considered in detail is the United States of America Advanced Field Artillery Tactical Data System (AFTDS). This is a multipurpose tactical information system of field artillery using mobile technology. It provides automated decision making for the functional subsystem, support for the ground forces and marines, as well as integrated operational units and united types of troops. The article describes the entire sector of the capabilities of this automated combat control system. The article also discusses ADLER (Artillerie Daten Lage and Einsatz Rechnerverbund) Germany’s automated field artillery control system. This automated field artillery control system provides all the field artillery control capabilities from the division to the gun (mortar, MLRS, reconnaissance equipment). The unified information network unites target detection facilities, combat (fire) and fire weapons control centers (points). it makes it possible not only to process the data, but also to control the detection mode and hit targets, including the evaluation of intermediate results. Integrated systems of reconnaissance, surveillance, target definitions and their destruction are considered by military experts of the leading, militarily, countries of the world as a critical element for achieving information superiority over the enemy. Analysis of the interaction of artillery reconnaissance forces and weapons and armaments of the leading military countries of the world provides an opportunity to study the development of weapons and military equipment to ensure the creation of an intelligence-information subsystem of artillery.

In this paper, we present an observer-based partial integrated guidance and control (PIGC) scheme for missiles to achieve hit-to-kill attack at a given impact angle. This is particularly useful as the lethality of a missile can be maximized if collision occurs at a certain angle. A novel sliding mode observer is proposed to estimate all states of the system in finite time, from which the PIGC is designed to make all states converge to zero and achieve the objective. The observer parameters are automatically updated by adaptive laws, which removes the requirement of knowing the bound of disturbances and hence making the scheme more applicable to real missile systems.

Air-to-air missile is the main source of air confrontation, which plays an important role in air confrontation. The attack ability of air-to-air missile is one of the key factors of air combat. Establishing the models of motion and seeker tracking and introducing the greedy algorithm to improve the tracking ability, while regarding the third flight as attack target and establishing the model of motion and radiation. Simulating the infrared radiation characteristic of the target, calculating the attack region of missile and the optimization performance of algorithm It’s concluded that attack region of the simulation matches the reality and the greedy algorithm can usefully improve the recognition efficiency of seeker.

According to the research experience of air-to-air missile testing, the occurences of some product faults are of low frequency and sporadic, and the fault features usually hide in the details of testing signals. However, the conventional rule-based fault detection methods are difficult to issue early warning against these product faults. In order to solve the problems of miss-detection faced by the conventional missile fault detection methods, this paper started from studying the data feature extraction, feature space construction, and automatic data mining, and carried out the research on engineering application of the data-driven fault detection technology. In view of the complexity of missile test data, the feature extraction of missile test data was achieved with the applications of mathematical statistics, clustering, artificial intelligence, image feature extraction, defining a method of missile fault detection based on the \(3\sigma\) criterion, and a data-mining based fault diagnosis system was developed with the ability to evaluate product quality on the foundation of historical missile test data.

Based on the characteristics of spare parts configuration and maintenance strategies of the new type of anti- missile Radar system, the evaluation index system of the spare parts configuration and maintenance strategy of the new type anti -missile radar is constructed. The GRG method is integrated into the AHP method to calculate the weight of each index in the index system. Based on the theory of cloud gravity center, the performance evaluation cloud model of spare parts configuration and maintenance strategy for new anti-missile radar is constructed. The evaluation of spare parts configuration and maintenance strategy by the cloud model is finished, the feasibility of the method is verified by an example.

In view of the missile discharging, emergency repair, obstacle clearing and transportation tasks in the airport runway after the attack. This article analyzes the complexity of the bomb ejection and repair task under the set conditions, and uses the principle of optimal timeliness to quickly complete the airport runway. For bomb discharge and emergency repair tasks, an ant colony algorithm-based equipment joint scheduling method for airport bomb discharge and emergency repair is proposed. This method divides airport equipment scheduling into task scheduling and path planning, and establishes a mathematical model for task scheduling. Ant colony algorithm for task scheduling path planning, and finally performs real-time simulation verification. Experiments show that the method is highly feasible after the airport is attacked, and it can meet the needs of rapid blasting and repairing of the airport in wartime.

Self-reliance in satellite-based navigation is of immense importance to modern-day strategic missile defense programs. Indian Space Research Organization (ISRO) has designed, developed and deployed an indigenous regional satellite-based navigation system, Navigation using Indian Constellation (NavIC). This paper reviews the present status of multi-constellation GNSS over the Indian region and its applications in the Indian Missile Program, and the advantages of using NavIC in such strategic programs. The present configuration of NavIC and the roadmap ahead gives a promising scope of self-reliance in these critical strategic programs of Indian Defence. In the future, NavIC will turn out to be a game-changer in the Indian missile program both during peacetime and war scenarios.

High speed kinetic energy antitank missile is an important development direction of antitank weapons in the future. Aiming at the high-speed kinetic energy antitank missile system with pulse correction engine as actuator and three-point guidance scheme, a trajectory optimization method in the lead-in phase is designed, which can be applied in engineering. Firstly, the principle and mathematical model of the pulse correction high-speed kinetic energy antitank missile system are described in detail. Then, the trajectory optimization scheme of the pulse correction high-speed kinetic energy missile in the lead-in phase is described, and the trajectory optimization model is established. Then, taking a certain type of high-speed kinetic energy missile as an example, the trajectory optimization scheme of the lead-in phase is verified and analyzed by mathematical simulation. The real results show that the designed trajectory optimization algorithm can effectively reduce the pulse energy consumption in the lead-in phase.

This paper proposes an attitude control method for variable-wing missiles. First, the aerodynamic parameters of the missiles are generated using the Missile DATCOM, and then they are fitted into the polynomial functions for controller design. Due to the morphing structure and strong nonlinearity of variable-wing missiles, working-point-based model linearization will lose model accuracy and consequently degrades the control performance. In this paper, an attitude controller for morphing missiles is proposed by combing the disturbance observer and the feedback linearization (FL) method. Theoretical research and numerical simulations show that the designed control system is suitable for morphing missiles, and has strong robustness to system parameter perturbations and external disturbances.

In order to comprehensively carry out the construction of missile health state cognition and management capability, so as to enhance its survivability and combat effectiveness in the complex battlefield environment, the design of a multi-layer health management system for missile equipment based on PHM is proposed, including hardware and software modules, which realize the functions of missile index system construction, performance evaluation, assessment overview, structure evaluation, and fault prediction, etc., and comprehensively consider the bullet control system and ground control system working characteristics, basically can meet the missile failure prediction and health management requirements.