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Modern air-to-air missiles rely on data updated via a datalink about the position and velocity of a target until their own seeker can lock on to the target. The quality of the datalink target data depends on the errors of position and velocity updates, delay of these updates and lost updates. This paper introduces a simulation framework for analyzing the utilization of this data. The framework consists of models describing the target, the missile, and the generation of the datalink target updates. The versatile simulation experiments presented in the paper analyze the effects of the quality of the datalink data on the performance of different air-to-air missiles. The measure of performance is the probability of kill. The results of the simulations imply that the quality of the final updates before attempting the transition to using the missile's seeker have the largest effect on the performance. Unless a large percentage of the target updates are lost or the seeker's lock on to the target is delayed, the missile can typically get within a lethal miss distance of the target. The framework presented in this paper is suitable for evaluating the performance of all types of guided weapons. [ABSTRACT FROM AUTHOR]

In modern warfare, missiles play a pivotal role but typically spend the majority of their lifecycle in long-term storage or standby mode, making it difficult to detect failures. Preemptive detection of missiles that will fail is crucial to preventing severe consequences, including safety hazards and mission failures. This study proposes a contamination-based stacking ensemble model, employing the local outlier factor (LOF), to detect such missiles. The proposed model creates multiple base LOF models with different contamination values and combines their anomaly scores to achieve a robust anomaly detection. A comparative performance analysis was conducted between the proposed model and the traditional single LOF model, using production-related inspection data from missiles deployed in the military. The experimental results showed that, with the contamination parameter set to 0.1, the proposed model exhibited an increase of approximately 22 percentage points in accuracy and 71 percentage points in F1-score compared to the single LOF model. This approach enables the preemptive identification of potential failures, undetectable through traditional statistical quality control methods. Consequently, it contributes to lower missile failure rates in real battlefield scenarios, leading to significant time and cost savings in the military industry. [ABSTRACT FROM AUTHOR]

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Copyright of Computer Measurement & Control is the property of Magazine Agency of Computer Measurement & Control and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Rouya Turkiyyah is the property of Insight Turkey and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

In response to the problem that traditional anti-interference performance evaluation indices are concentrated at the level of missile guidance systems, which cannot meet the anti-interference performance evaluation of guidance systems, based on the analysis of the internal error transmission principle of guidance systems during the anti-interference process and the measurement error of guidance systems, this paper proposes a guidance system anti-interference performance evaluation index based on line of sight angular velocity accuracy, so as to evaluate its anti-interference performance timely in the development process of guidance systems.Due to the difficulty for measurement of the line-of-sight angular velocity accuracy in field experiments, in order to improve the testing efficiency, a simplified calculation method for line-of-sight angular velocity accuracy is proposed based on the principle of proportional guidance. Furthermore, for non proportional guidance scenarios, an equivalent testing method for line-of-sight angular velocity accuracy using recognition time is given. The results of field data testing indicate that the indices can reflect the anti-interference performance of missile in different scenarios, and this method has certain rationality.

Copyright of Journal of Ballistics / Dandao Xuebao is the property of Journal of Ballistics Editorial Department and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Aero Weaponry is the property of Aero Weaponry Editorial Office and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

In order to solve the severe challenge brought by the flight of ultra sonic missiles to the structure and thermal protection of missile bodies, and to improve the integrated load/thermal protection performance, an individual disturbance multi-strategy salp swarm algorithm for structural optimization design is proposed. Sobol sequence is introduced to homogenize the initial population for maintaining population diversity. The dynamic weight adjustment mechanism is used to improve algorithm speed. The variation factor and reverse solution strategy are fused to improve algorithm accuracy. The optimal Pareto solution can be obtained by using a temporary reserve. Finally, the improved algorithm is used to optimize the missile body structure and thermal protection system. Under the same environment, the optimal adaptive value and average convergence rate of improved algorithm are better than the standard salp swarm algorithm(SSA) and other optimization algorithms. Experimental data shows that the improved algorithm can solve the problem of mutual influence between thermal protection efficiency and structure quality. So the improved algorithm can not only improve algorithm speed and convergence accuracy, but also improve the load/thermal protection performance of the missile body structure.

Based on the military net evaluation report published by Rand Corporation, this paper independently explores the combat effectiveness evaluation theory driven by the analytical model of the US military, and studies in detail the analysis and evaluation method of precision guided weapons attacking the airbase in the joint integrated contingency model (JICM), also carries out the deduction and calculation. The results show that the air force aircraft sorties ability is greatly affected by the damage of the airbase, which plays a vital role in the fight for air control. This paper has positive theoretical significance for the in-depth understanding and application of modern combat simulation deduction and evaluation.

Based on the flow field characteristics of the missile body, an integrated design method for missile and inlet with two side layout is proposed under asymmetric inflow. The result of numerical simulation shows that shock waves hit on cowl lip on the symmetry plane at the design condition, which verifies the method of integrated design. And the flow characteristics of inlet under the influence of the missile body are analyzed. Under the influence of asymmetric incoming flow and missile body, the first shock wave surface of the two-dimensional inlet presents the characteristics of a three-dimensional concave surface, and there is a pair of asymmetric vortex structures in the inner flow path. Finally, a bleed cavity of self-adaptively adjusting bleeding by vortex is proposed to improve the performance of inlet and broaden the inlet start and attack angle boundary. The minimum Mach number of the inlet start is reduced from 2.8 to 2.3 at ɑ = 6° and the maximum attack angle of inlet start is widened from ɑ = −1° to ɑ = 3° at Ma = 2.1. [ABSTRACT FROM AUTHOR]

To address the trajectory tracking problem of missiles, an optimal disturbance rejection guidance law (ODRGL) in three dimensions is proposed under the premise of uncontrollable speed. Error models of the actual and the reference trajectory are built in channels of pitch and yaw, respectively. In the yaw channel, a modeling error is introduced as the model cannot be built directly. According to the separation theorem, the controller and the observer are designed respectively. A fixed-gain disturbance observer (FGDO) is proposed to estimate the disturbance such as wind disturbances and modeling errors, and the disturbance is compensated for feed-forward. The nominal error models of pitch and yaw channels are linearized by the differential geometric linearization theory, and then linear quadratic regulator (LQR) controllers are designed for the linearized models. The simulation results show that in the presence of wind disturbances and modeling errors, the optimal guidance law proposed in this paper can stabilize the original nonlinear system and ensure energy optimization. • A three-dimensional trajectory tracking optimal guidance law is proposed under the premise of uncontrollable speed. • A fixed-gain disturbance observer, which has a high estimation accuracy and a fast convergence rate of estimation error, is proposed. • Linearizing the error model using the differential geometry linearization theory is more accurate than that of the existing guidance laws. [ABSTRACT FROM AUTHOR]

Copyright of Aero Weaponry is the property of Aero Weaponry Editorial Office and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

From the beginning of World War II, dual-axis tracking radars have played an important role in the tracking of missiles in test ranges. These radars operate mostly in S- or C-band of frequencies. However, these Radars have associated problems with the costly maintenance budget, various errors that creep into the data, and inter-radar bias correction. The modern-day global navigation satellite system (GNSS) together with space-based augmentation systems (SBAS) have provided scope to obtain internally generated and telemetered trajectory data from the missile under test (MUT) from the onboard GNSS receiver with SBAS capabilities within comparable or better accuracies. This research presents a comparison of the precession parameters of the MUT's position solutions between data from several tracking radars and those from the enhanced GNSS data. Also, experiments have been conducted using various satellite navigation constellations including NavIC and SBAS augmentation to demonstrate the improvement in accuracy and precession parameters applicable to the Indian scenario. To compete with the outcomes of contemporary satellite-based navigation system together with the augmentation systems for trajectory generation of cooperative missile targets, radar manufacturers must reconsider their design philosophies for usage on missile test ranges. [ABSTRACT FROM AUTHOR]

Current geopolitical context presents a vast way for procedures regarding actions of disinformation and propaganda, as a base component of the hybrid warfare, especially in information warfare spectrum. This paper seeks to present the modes and ways of presenting the information regarding technical themes from the present Russian – Ukrainian war and their effects on the decision makers and population. [ABSTRACT FROM AUTHOR]

Copyright of Problems of Mechatronics. Armament, Aviation, Safety Engineering / Problemy Mechatroniki. Uzbrojenie, lotnictwo, Inżynieria Bezpieczeństwa is the property of Index Copernicus International and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Aero Weaponry is the property of Aero Weaponry Editorial Office and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Copyright of Computer Measurement & Control is the property of Magazine Agency of Computer Measurement & Control and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

There are different models and methods for technology acquisition, but making the right choice and optimal use of models and methods plays an important role in success technology acquisition. In this research different methods and models are both introduced and criticized. In addition, a three dimensional model resulting from the interaction of factors related to owner, receiver, and nature of technology was chosen to survey technology acquisition methods in Iran's missile industry. Based on this model, Iran used a combination of "Optimal methods" (such as Human Exchange and Hiring method, Joint research and development method, Education method and Reverse engineering)," Possible but not Optimal methods" (such as Turnkey method) and "Methods not conforming to the selected model" (such as training and internal R&D method) for acquiring different missile technologies. Based on this, Iran has used a wide range of technology acquisition methods simultaneously and in parallel to develop its missile capabilities.

Cooperative guidance is an important research direction in the field of missile guidance in recent years. Based on the classification criteria such as mission requirements, communication structure, constraints, etc., this paper classifies and summarizes the current multi-missile cooperative terminal guidance strategies, and combs the research status of time cooperative guidance law, spatial cooperative guidance law, and spatial-time cooperative guidance law. It analyzes the key issues for cooperative guidance at this stage, such as the estimation problem of remaining flight time, the cooperative interception problem of maneuvering targets, the information registration problem of closed-loop cooperative guidance, the communication problem of closed-loop cooperative missile, etc. Finally, this paper proposes four research directions of the future multi-missile cooperative terminal guidance technologies: cooperative interception technology for large maneuvering targets, robust cooperative guidance technology for real scenes, intelligent autonomous cooperative guidance technology, and parallel interactive design technology for cooperative operations.

Missile guidance, owing to highly complex and non-linear relative movement between the missile and its target, is a challenging problem. This is further aggravated in case of a maneuvering target which changes its own flight path while attempting to escape the incoming missile. In this study, to achieve computationally superior and accurate missile guidance, deep learning is employed to propose a self-tuning technique for a Fractional-Order Proportional Integral Derivative (FOPID) controller of a radar-guided missile chasing an intelligently maneuvering target. A multi-layer two-dimensional architecture is proposed for a deep neural network that combines the prediction feature of recurrent neural networks and estimation feature of feed-forward artificial neural networks. The proposed deep learning based missile guidance scheme is non-intrusive, data-based, and model-free wherein the parameters are optimized on-the-run while predicting the target’s maneuvering tactics to correct for processing time and loop delays of the system. Using deep learning for online optimisation with minimal computational burden is the core feature of the proposed technique. Dual-core parallel simulations of missile-target dynamics and the control system were performed to demonstrate superiority of the proposed scheme in feasibility, adaptability, and the ability to effectively minimize the miss-distance in comparison with traditional and neural offline-tuned PID and FOPID based techniques. Compared to state-of-the-art offline-tuned neural control, the miss-distance was reduced by 68.42 % for randomly maneuvering targets. Furthermore, a minimum miss-distance of 0.97 m was achieved for intelligently maneuvering targets for which the state-of-the-art method failed to hit the target. Overall, the proposed technique offers a novel approach for addressing the challenges of missile guidance in a computationally efficient and effective manner. [ABSTRACT FROM AUTHOR]

Copyright of Aero Weaponry is the property of Aero Weaponry Editorial Office and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

In order to solve the possible collision problem in the process of sub-interceptors intercepting UAV cluster, this paper proposes a collision avoidance pure proportional guidance law (CA-PPN) by combining the virtual repulsion force with the pure proportional guidance law. Firstly, it proposes an operational concept of submunition missile intercepting UAV cluster, and analyzes the guidance problem of sub-interceptors. Then, aiming at the possible collision problem in the guidance of sub-interceptors, it designs an artificial potential field for collision avoidance between sub-interceptors, and analyzes the characteristics of PPN. On this basis, combining PPN with the virtual repulsion force in the artificial potential field, and adding the field of view angle and overload constraints, the CA-PPN is proposed. The simulation results show that CA-PPN can effectively intercept the target and avoid the collision between sub-interceptors.

Aiming at the problem of low efficiency and high cost of missile modeling, this paper introduces longitudinal contour description function on the basis of 2D CST parameterization technology, extends the original 2D modeling to 3D modeling, and establishes an analytical function that can accurately describe the 3D shape characteristics of the missile. On this basis, the geometric model can be automatically generated, repaired and updated in CATIA through secondary development in VB environment. Geometric models can be derived and preserved as a basis for multidisciplinary design and analysis. The results show that the 3D CST modeling technology proposed in this paper can meet the requirements of complex geometric modeling, effectively simplify the missile parameterization process.

Modern missiles must deal with stringent performance requirements and ensure robustness across a wide range of operating conditions during flight time. Classic gain-scheduling designs have been successful in practice, but do not provide theoretically ensured bounds on both performance and robustness. Controllers are interpolated at intermediate operating conditions and switching them may cause instability. On the other hand, polytopic linear parameter-varying (LPV) controllers avert this switching and use real-time information about the plant, in order to smooth out the gain scheduling. We hereby propose a novel procedure to yield an output feedback LPV controller that ensures robust $\text{H}_{\infty} $ performance to a missile longitudinal autopilot. Our novel approach considers the four-block loop-shaping $\text{H}_{\infty} $ control theory with polytopic LPV weights that use polytopic coordinates of the LPV plant. One is capable of adjusting the singular values of the open-loop plant individually at the polytope vertices, and benefits from a trade-off between linear matrix inequalities (LMI) based optimization tools and the designer experience. This can be construed as a natural extension of the traditional $\text{H}_{\infty} $ loop-shaping method that uses linear time-invariant (LTI) weights. Assuming the scheduling variables are frozen, we also include LMI conditions for assigning closed-loop poles and hence circumvent controller order reduction. Nonlinear simulations assess the proposed autopilot, and results show an improved robust stability margin, in addition to an improved response to the acceleration command, concerning the LTI-based approach.

With the fourth generation stealth aircraft gradually becoming the main combat equipment of major military powers in the world, the improvement of missile anti stealth combat capability has become an inevitable requirement for the construction of weapons and equipment. In the evaluation of missile operational effectiveness, real shot shooting is an essential link. At present, there are a certain number of small stealth target aircraft that can be used to simulate the main target characteristics of the fourth generation stealth aircraft. However, their analysis of simulation fidelity and the accuracy of missile operational effectiveness evaluation is rarely seen in relevant literature. This paper makes a detailed comparison and analysis of the differences between the small stealth target and the real stealth aircraft in radar scattering characteristics, physical dimensions, vulnerability, electronic countermeasure characteristics, etc. Through the study of the impact of the differences in target characteristics on missile functions and effectiveness, it is believed that the small stealth target is difficult to be comprehensive to accurately evaluate the operational effectiveness of missiles due to its own shape and size inherent characteristics, it is necessary to attach importance to the development of large-scale stealth target aircraft, which is of positive significance for evaluating the operational effectiveness of missiles and correctly guiding the improvement of missile anti stealth capability.

Copyright of Journal of Ordnance Equipment Engineering is the property of Chongqing University of Technology and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Aiming at the problem of impact angle constrained guidance, an arbitrary time convergent impact angle constrained guidance (ATC-IACG) law against the stationary target is designed based on the pure proportion navigation (PPN) guidance law and the arbitrary time convergence control method. Firstly, the dynamic equation of impact angle error based on the PPN guidance law is derived. Then, the arbitrary time convergence control method is employed, and the ATC-IACG is designed, which could make the impact angle error converge to zero in a predefined convergent time. Finally, the guidance performance of the ATC-IACG law is demonstrated through numerical simulation results, and compared with that of the impact angle control guidance law based on optimal error dynamics. The simulation results show that the larger the expected impact angle, the smoother the change of the missile's guidance acceleration, also the less the missile's energy consumption. Under the guidance law, the missile can achieve the attack mission constrained by the expected convergence time and the terminal impact angle.

In order to solve the problem of selecting missile health state evaluation indexes and the mapping relationship between the selected indexes and missile health state, a missile health state prediction method based on CA-RBF neural network is proposed. Firstly, the influencing factors of missile health state are analyzed through missile life profile, and the quantitative method is given. Then, the corresponding analysis (CA) method is used to screen the influencing factors of missile health state. Taking the selected factors and the evaluation results of missile health state as the input and output of neural network, the training samples of RBF neural network are established to predict the missile health state. Finally, an example is given to illustrate the practicability and effectiveness of the proposed method. This method can provide a new idea for the selection of missile health state indexes and missile health state prediction, and provide a basis for missile preventive maintenance decision-making.

Proportional navigation guidance law (PNG) is widely used for passive homing missiles. But PNG often suffers from inaccurate tracking of target or even failure when the target is maneuvering quickly or releasing artificial decoys. In order to solve this problem, the angular acceleration compensation guidance law (AACG) is constructed by using line of sight (LOS) angular velocity and LOS angular acceleration. The stability analysis with Lyapunov stability theory shows that AACG system is asymptotically stable on a large scale under certain stability constraint conditions. AACG command is designed to be perpendicular to the LOS and optimized by gravity compensation. AACG is neither dependent on target acceleration nor the distance between the missile and the target. The numerical simulation results indicate that AACG has good guidance performance on air-to-air missiles when the target maneuvers violently or releases artificial decoys in the endgame term.

This paper discusses the intelligent classification and characteristics of missile weaponry, and defines the concept and connotation of intelligent missile. Based on the principle of algorithm design and the development characteristics of missile weaponry, the intelligent level of missile is divided into four levels, that are the initial level, the medium level, the high level and the super level, and the internal meaning of each level is expounded. This paper focuses on the intelligent characteristics of missile weaponry, and describes the capability performance of four levels of intelligent missiles, also discusses the key development technologies of intelligent missile, and introduces the research focus of various key technologies at the current stage based on the current technical status.

Copyright of Journal of Ballistics / Dandao Xuebao is the property of Journal of Ballistics Editorial Department and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)

Introduction: The Russian army is developing some reconnaissance and interceptor vehicles such as the S.300 systems to defend strategic areas belonging to some of its allied countries. Another defensive shield system was also produced on a regional scale, such as the S-400 which is more capable than the S-300 system. During this process, the Russian military began production of the S-500 defense system. Production sites of S-300 and S-400 missile systems were established in some vital regions of Russia (in Kaliningrad and Crimea) and the territory of some allied countries. However, the Russian defense shield is technically weaker and more limited compared to the Western countries defense shield, but without a doubt, this plan will not remain at these levels. The development of Russia's defense shield means that Russian leaders intend to defend their country against the threat of Western ballistic missiles. Of course, these equipments increase the offensive power of Western countries, especially by carrying tools and increasing missile defense systems. One of the main tools of Russia's defense shield is the S-300 missile system. The PMU S-300 model is capable of countering an attack missile with a speed of Mach 2-8 and a range of 1000 km. This system was established in Armenia, Tajikistan, Kyrgyzstan, Kazakhstan and Belarus. The S-400 system is also capable of shooting down stealth aircraft, ballistic missiles, hypersonic missiles and drones with a range of 400 km. But two tools only work on atmosphere. The S-500 system is also in the final stage of production with a range of 600 km and a speed of Mach 7, which is capable of shooting down hypersonic missiles and spy satellites. It is expected to be fulfilled by 2025. In addition, the Russian military has developed some ground-based early warning radars called Voronezh. The Voronezh MD model has an inspection area of 6000 km and has the capacity to detect 500 targets. Of course, this radar is only an early warning system and is not compatible with any interceptor device. Reconnaissance satellite technology has also been used for defense. Currently, several Cosmos class satellites are in service and will be deployed in outer space for this purpose. The Russian military plans to upgrade this technology and surveillance. The plan to deploy Russian missile defense systems appears not as a tactical plan, but as a strategic plan. This plan is simultaneously qualitative and quantitative in the development of detection and interception systems as well as early warning systems. Research Question: "Why is Russia thinking of creating a missile defense shield? Research Hypothesis: The hypothesis of the article is that "the concern of Russian leaders about the Western plan to create a missile defense shield has led to the development of their own missile defense tools." Methodology (and theoretical framework if there are): This is a historical and descriptive method with an emphasis on monitoring Russia's anti-ballistic systems, as well as examining the country's official doctrine in the field of security and foreign policy. This research also deals with the situation of the Russian authorities. Results and Discussion: The research results show that the US and NATO defense shield was the main motivation of the Russian authorities to create missile defense systems. The US and NATO missile defense shields consists of SM3 interceptors, Aegis radars and early warning satellites. However, each part is separated but they are connected by all. They will be deployed in four stages in the mentioned areas, which can defend the American forces and its allies. Those regions are American homeland, Alaska, Greenland, South Persian Gulf and South Korea. They are also carried by destroyers in the Mediterranean and the Pacific. In parallel, NATO is building its own defense shields in some places in the center and east of the continent, which are: The radar station in Turkey, the Aegis radar system in Poland and the THAAD system in Romania and the command section in Germany. The four Aegis radar systems installed on the ships they command are in the port of Rota (Spain). Some say that the third and fourth parts of the defense shield are capable of targeting Russian intercontinental ballistic missiles. The defensive shield also protects Western countries that have developed their offensive capacity in conjunction with defensive tools. Due to the withdrawal from the INF Treaty, there are no restrictions against the West. Putin's opposition to Trump's extension of the New Start Treaty without any conditions and Trump's insistence on concluding a comprehensive agreement annoyed Russian authorities. In addition, Russian authorities are not happy about the establishment of a Western defensive shield near the country's western borders. These actions cause Russia to react in the same way. Conclusion: Russia's action in the development of defense systems is one of the main factors of change in the military doctrine of this country. Previously, the Russian military organized its strategic tools around the doctrine of nuclear deterrence and parity. But Russia is trying in the same direction in response to the deployment of Western missile defense elements in some strategic parts of the continent. As a result, Russia's new doctrine is based on an offensive and defensive strategy. Nevertheless, the current interactions between the West and Russia have created a new round of arms competition, especially in strategic defense tools. Russian defense systems are not at the level of their Western counterparts either in terms of content or technical quality. But these are accompanied by offensive tools that have been developed in strategic areas to pose the same threats against the West. According to this emerging trend, the Russian missile defense zone will also cover more strategic areas in the future. [ABSTRACT FROM AUTHOR]

Copyright of Aero Weaponry is the property of Aero Weaponry Editorial Office and its content may not be copied or emailed to multiple sites or posted to a listserv without the copyright holder's express written permission. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.)