Log in

Relevant bibliographies by topics / Guided missiles Guidance systems / Journal articles

To see the other types of publications on this topic, follow the link: Guided missiles Guidance systems.

Journal articles on the topic 'Guided missiles Guidance systems'

Author: Grafiati

Published: 4 June 2021

Last updated: 4 March 2023

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the top 50 journal articles for your research on the topic 'Guided missiles Guidance systems.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Browse journal articles on a wide variety of disciplines and organise your bibliography correctly.

1

Moskalets, S., V. Zhyrnyi, O. Mokrinskyi, and A. Rudyk. "EFFECTIVE APPLICATION AND PROSPECTS OF IMPROVEMENT OF ANTI-TANK ROCKET COMPLEX MANAGEMENT SYSTEMS." Наукові праці Державного науково-дослідного інституту випробувань і сертифікації озброєння та військової техніки, no. 5 (December 22, 2020): 56–63. http://dx.doi.org/10.37701/dndivsovt.5.2020.07.

Full text

Abstract:

Tanks are one of the main means of implementing aggressive plans to capture land territory. To combat tanks and other armored vehicles the projectiles with different types of warheads and anti-tank guided missiles are used. The best means of defeating tanks are anti-tank missile systems (ATMS), which are classified by aiming methods. The purpose of this work is to review the prospects for development and use of existing ATMS by analyzing the trends of new national and foreign weapons control systems. Anti-tank missile systems of most advanced world‟s armed forces are, predominantly, second-generation systems with a semi-automatic infrared or laser beam guided systems. Missiles of these systems have a high probability of hitting the target (and penetration of armor) when firing under good visibility conditions. The retrofit of the second- generation systems is being done by increasing the protection against jamming caused to aiming systems due to creating combined infrared and thermal coordinators, improving signal processing methods, and increasing the flight speed of missiles and the reliability of command transmission. The tank engine is a powerful contrasting source of thermal energy. The main weak links of systems with semi-automatic guidance systems in terms of jamming counteraction are the operator who tracks the target along the missile's flight, and the coordinator of the missile's command aiming that can be “blinded”. Large-scale works on the creation of next generation anti-tank missile systems based on the latest scientific and technological achievements have been considered. The system‟s operator is one of the weakest links. Careful attitude to the life of every Ukrainian warrior should be a priority, as it is in the modern militaries of the world. This attitude can be ensured by using a reliable missile weapons both natioanl and foreign that would be capable of hitting enemy tanks from a safe distance with a remote control using “fire-and- forget”principle.

APA, Harvard, Vancouver, ISO, and other styles

2

Rusnak, Ilan. "Bounds on the Miss of Radar-Guided Missiles with Discrete Guidance." Journal of Guidance, Control, and Dynamics 43, no. 4 (April 2020): 825–30. http://dx.doi.org/10.2514/1.g004811.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Kucherenko, Oleg K. "DETERMINATION OF THE ACOUSTO-OPTICAL DEFLECTOR PARAMETERS FOR A LASER-RADIATION ROCKET GUIDANCE SYSTEM." Bulletin of Kyiv Polytechnic Institute. Series Instrument Making, no. 62(2) (December 24, 2021): 17–22. http://dx.doi.org/10.20535/1970.62(2).2021.249110.

Full text

Abstract:

The work is devoted to the development of an acousto-optic deflector for a laser-beam guidance system (LLSN) of missiles. LLSN is used in semiautomatic portable missile systems to destroy hostile targets of various types. An analysis of the methods for constructing such systems has shown that the most promising devices with pulse-code modulation using semiconductor pulsed lasers. The article provides a diagram and describes the principle of operation of the LLSN with pulse-code modulation. A problematic issue in the implementation of such a system is the development of a device for deflecting a laser beam, through which the missile is guided to a target. Scanning mechanical devices that are currently in use have a complex design, significant dimensions and weight, and limited performance. The article proposes to use an acousto-optic deflector to deflect the laser beam within the information field of the guidance system, which is devoid of these disadvantages, since it replaces the mechanical scanning device with an electronic one. The purpose of the article is to determine the main parameters of the acousto-optical deflector. The article discusses the principle of operation of an acousto-optic deflector. It is noted that glasses based on germanium chalcogenides, in particular, glass with the composition Ge2.17As39.13S58.70, have especially low values of acoustic losses (α <1 dB / cm). The largest deflection angle of the laser beam will be observed with Bragg diffraction. Relationships are given that can be used to determine the main characteristics of the deflector: the angle of deflection of the laser beam, the modulation frequency of the acoustic wave, resolution, speed, and others. When using the above ratios for the typical parameters of the existing guidance system, the values of the indicated characteristics are calculated.

APA, Harvard, Vancouver, ISO, and other styles

4

Polimera, Mugdha Sunil, and V. Kalaichelvi. "Stability and Robustness Analysis of a LASER Guided Missile System Using PID Controller." Applied Mechanics and Materials 666 (October 2014): 208–12. http://dx.doi.org/10.4028/www.scientific.net/amm.666.208.

Full text

Abstract:

A LASER Guided Missile System is used in most military operations for its known accuracy. But, a typical such system has a high order of non-linear characteristics and thus, a highly unstable performance. Such systems have a guidance and control system which acts as a flying servomechanism - an electromechanical device that positions an object according to a variable signal by reducing the error between two quantities. The guidance portion of the system develops the variable input signal. The input signal represents the desired course to the target. The missile control system operates to bring the missile onto the desired course. Thus, the output of the guidance and control system is the actual missile flight path. This paper dwells into the idea of using a PID Controller as part of the ‘control system’ in the missile, introducing stability in the system by reducing the error. The controller has been simulated using Simulink environment of MATLAB. The robustness of this PID controller, for different non-ideal environments, is tested post – tuning and is analysed based on performance criteria like overshoot, settling time etc.

APA, Harvard, Vancouver, ISO, and other styles

5

Han, Yingchao, Weixiao Meng, and Xiaodong Wang. "Design and Experimental Analyses of an Accuracy Verification System for Airborne Target Tracking via Radar Guidance Systems." Applied Sciences 12, no. 14 (July 6, 2022): 6838. http://dx.doi.org/10.3390/app12146838.

Full text

Abstract:

A radar guidance system is a core component of a radar-guided air-to-air missile, and its tracking accuracy of airborne targets determines the operational effectiveness of said missile. To verify the tracking accuracy of the radar guidance system against an airborne target under the real flight conditions of the missile, an experimental verification system was implemented in this study. The mechanical, electrical, and bus interfaces of the verification system were examined. A tracking accuracy evaluation model of the seeker was designed based on the data obtained from the experiments using the proposed test method, and the tracking accuracy of the seeker in the typical state was analyzed.

APA, Harvard, Vancouver, ISO, and other styles

6

Srinivas, Gopisetty, Harish Kumar Gowda, Harshitha C. Gowda, Jyothi S. T., Ravi Shankar D., and undefined undefined. "Survey on Laser Guided Missile Systems and Implementation by Developing a Laser Guidance System." Global Journal of Electronic and Communication Research 12, no. 1 (June 30, 2021): 1. http://dx.doi.org/10.37622/gjecr/12.1.2021.1-9.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Ouda, A. N., Gamal El Sheikh, Yehia Elhalwagy, and Mahmoud Ashry. "Nominal model selection and guidance computer design for antitank guided missile." International Journal of Automation and Control 13, no. 1 (2019): 34. http://dx.doi.org/10.1504/ijaac.2019.096418.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Ouda, A. N., Mahmoud Ashry, Yehia Elhalwagy, and Gamal El Sheikh. "Nominal model selection and guidance computer design for antitank guided missile." International Journal of Automation and Control 13, no. 1 (2019): 34. http://dx.doi.org/10.1504/ijaac.2019.10016560.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Gözde, Haluk, and Semih Ozden. "Adaptive True Proportional Navigation Guidance Based On Heuristic Optimization Algorithms." Defence Science Journal 71, no. 2 (March 10, 2021): 271–81. http://dx.doi.org/10.14429/dsj.71.16218.

Full text

Abstract:

The PN-guidance (Proportional Guidance) still continues to be improved, because it is the simplest, cheapest and most reliable algorithm. One of the most important techniques to improve PN-guidance is to adapt the navigation constant depending on time. In this study, first, the entire adaptation methods for PN-guidance are classified, then the adaptation process is online achieved by using heuristic optimization during guiding the missile. The novelty of this study is that the heuristic optimization approach is used at the first time to update the navigation constant of PN-guidance. It is considered that having short program code, fast convergence speed and just simple algebraic computations without derivative are vital advantages of heuristic algorithms using into missile systems. In this scope, an Adaptive True-PN (ATPN) guidance algorithm is designed by optimizing navigation constants varying according to the target behavior. The results show that while the acceleration gap of the pitch axis decreases 21.8%, the acceleration gap of yaw axis reduces 39.68%. These reductions mean that while the missile guided by ATPN is maneuvering, it is exposed to less acceleration and less strain.

APA, Harvard, Vancouver, ISO, and other styles

10

Zhang, Wei, He Zhang, Bin Liu, and Jing Xu. "Design of Small Laser Tracking System Based on Four-Quadrant Detector." Applied Mechanics and Materials 300-301 (February 2013): 393–99. http://dx.doi.org/10.4028/www.scientific.net/amm.300-301.393.

Full text

Abstract:

Returned laser detection is bottleneck in remote active laser detection. A practical small laser tracking system with simple structure based on four-quadrant detector (QD) is presented in this paper. For the volume restriction in weapon systems, design a small laser receiving optical system. An orientation calculation circuit based on the Sum and Difference circuit with Divisional normalization algorithm is designed to decrease the burden on processor. A simple MCU circuit based on high-speed chip C8051F020 is generated, accomplishing AD-conversion and further calculation. Through programming of the electric signals from the orientation calculation circuit with C8051F020, a control signal used by the missile guidance is formed. Laser signal receiving experiment is conducted by the circuit board as presented in this paper. It is possible to achieve the ideal requirements, and provide a good foundation for collaborative processing of other sensor signals to jointly get guided control commands.

APA, Harvard, Vancouver, ISO, and other styles

11

Antsiferov, Alexander A. "Ways to Improve the Effectiveness of Defeating Group Air Targets in Anti-Aircraft Combat." Journal of Siberian Federal University. Engineering & Technologies 14, no. 7 (November 2021): 763–75. http://dx.doi.org/10.17516/1999-494x-0355.

Full text

Abstract:

This article discusses ways to improve the efficiency of anti-aircraft guided missiles to intercept group air targets. An effective way to defeat the elements of group air targets using anti-aircraft guided missiles is the joint guidance of several missiles at several air targets from the group. The basic technical requirements for anti-aircraft guided missiles for the implementation of this principle are defined

APA, Harvard, Vancouver, ISO, and other styles

12

MOTYL, Krzysztof, and Ryszard WOŹNIAK. "CURRENT STATUS AND DEVELOPMENT TRENDS OF ANTITANK MISSILE SYSTEMS." Scientific Journal of the Military University of Land Forces 165, no. 3 (July 1, 2012): 272–88. http://dx.doi.org/10.5604/01.3001.0002.3498.

Full text

Abstract:

The article presents the current status in the field of antitank guided missiles in the Polish Armed Forces. It describes the modern solutions of this type of weapons in the leading armies in the world and presents development trends in antitank guided missiles, emphasizing the needs of the Polish Armed Forces.

APA, Harvard, Vancouver, ISO, and other styles

13

Ai, X. L., L. L. Wang, and Y. C. Shen. "Co-operative 3D salvo attack of multiple missiles under switching topologies subject to time-varying communication delays." Aeronautical Journal 123, no. 1262 (April 2019): 464–83. http://dx.doi.org/10.1017/aer.2019.7.

Full text

Abstract:

ABSTRACTThis study focuses on the co-operative salvo attack problem of multiple missiles against a stationary target under jointly connected switching topologies subject to time-varying communication delays. By carefully exploring certain features of the typical pure proportional navigation guidance law, a two-stage distributed guidance scheme is proposed without any information on time-to-go in this study to realise the simultaneous attack of multiple missiles. In the first guidance stage, a co-operative guidance law is proposed using local neighbouring communications only to achieve consensus on range-to-go and heading error to provide favourable initial conditions for the latter phase, in which switching topologies and time-varying communication delays are taken into account when obtaining sufficient conditions of consensus in terms of linear matrix inequalities. Then, missiles disconnect from each other and are guided individually by the typical pure proportional navigation guidance law with the same navigation gain to realise salvo attack in the second guidance phase. Finally, numerical simulations are carried out to clearly validate the theoretical results.

APA, Harvard, Vancouver, ISO, and other styles

14

Kim, Wonsop, Keehyun Ahn, and Minseok Lee. "Squib Ignition and Status Check Circuits Design for Compact Embedded Systems in Guided Missiles." Journal of the Korea Institute of Military Science and Technology 26, no. 1 (February 5, 2023): 64–71. http://dx.doi.org/10.9766/kimst.2023.26.1.064.

Full text

Abstract:

In the recent defence industries, it is required to develop the small and low cost embedded systems for guided missiles. According to the characteristics of guided missiles, the mission is conducted with multiple phases, which include a squib activation phase. By considering the unexpected squib activation, the squib system should be disabled after the launch of a guided missile. Therefore, the squib system needs to include the functions of the safe ignition and status check. This paper presents the squib ignition and status check circuits design for the compact embedded systems in guided missiles. Validation results show that for the functions of the squib ignition and status check, the presented circuits design performs well. The designed circuits also were implemented with various electronic devices and validated by the ground and flight tests.

APA, Harvard, Vancouver, ISO, and other styles

15

Gao Ye, 高. 晔., 周. 军. Zhou Jun, 郭建国 Guo Jianguo, and 冀. 华. Ji Hua. "Study on distributed cooperative guidance law for infrared imaging guided missiles." Infrared and Laser Engineering 48, no. 9 (2019): 904007. http://dx.doi.org/10.3788/irla201948.0904007.

Full text

APA, Harvard, Vancouver, ISO, and other styles

16

Gurfil, Pini, Mario Jodorkovsky, and Moshe Guelman. "Neoclassical Guidance for Homing Missiles." Journal of Guidance, Control, and Dynamics 24, no. 3 (May 2001): 452–59. http://dx.doi.org/10.2514/2.4765.

Full text

APA, Harvard, Vancouver, ISO, and other styles

17

Innocenti, Mario. "Nonlinear guidance techniques for agile missiles." Control Engineering Practice 9, no. 10 (October 2001): 1131–44. http://dx.doi.org/10.1016/s0967-0661(01)00094-6.

Full text

APA, Harvard, Vancouver, ISO, and other styles

18

Pinchuk, A., M. Garbuz, P. Zeleny, D. Harnets, and D. Ivanov. "ANALYSIS OF EXPERIENCE IN THE APPLICATION OF MISSILE LAUNCH DETECTION SYSTEMS." Наукові праці Державного науково-дослідного інституту випробувань і сертифікації озброєння та військової техніки, no. 9 (December 3, 2021): 118–29. http://dx.doi.org/10.37701/dndivsovt.9.2021.14.

Full text

Abstract:

Analysis of combat losses of aircraft in local armed conflicts in recent decades shows that most cases of aircraft hits are related to the impact of guided surface-to-air and air-to-air missiles equipped with homing warheads. The use of modern guided missiles equipped with homing warheads is one of the main threats to aircraft of various types. This is due to the fact that modern guided missiles are characterized by high speed, maneuverability, accuracy of aiming and difficulty of detection. Solving the problem of protecting aircraft from guided missiles consists of several stages: detection of missile launch; confirmation that the detected missile is heading directly toward the protected object; missile identification and decision-making on the most effective countermeasure system employment. At present, there are no missile launch detection systems that guarantee a 100% probability of threat detection, but an analysis of aviation combat losses in local armed conflicts in recent decades convincingly shows that the number of combat losses of aircraft equipped with such systems is much lower than those in which missile launch detection is carried out visually. For example, most of the Soviet Union's losses during the war in Afghanistan and the United States‟ losses during Operation “Desert Storm” in Iraq were related to the use of portable anti-aircraft missile systems, which missiles were equipped with infrared homing warheads. Realizing the scale of the threat posed by such missiles, most of the world's leading countries have significantly increased the expenses on development new or improvement existing countermeasures. As a result, the aggregate losses of coalition forces in Iraq, Afghanistan and Syria since 2001 clearly suggest that these costs have paid off, with losses from the use of portable anti-aircraft missile systems significantly reduced, while the total number of combat sorties increased. Therefore, in the face of all the challenges and threats posed to Ukraine due to the aggressive actions of the Russian Federation, conducting research in the interests of aviation of the Armed Forces of Ukraine to improve the effectiveness of missile detection systems for ensuring timely detection of threats, warning of aircraft crew and activation in the automatic mode the means of countermeasures is as relevant as ever.

APA, Harvard, Vancouver, ISO, and other styles

19

Hull, D. G., J. L. Speyer, and C. Y. Tseng. "Maximum-information guidance for homing missiles." Journal of Guidance, Control, and Dynamics 8, no. 4 (July 1985): 494–97. http://dx.doi.org/10.2514/3.20010.

Full text

APA, Harvard, Vancouver, ISO, and other styles

20

Yunes Sh., ALQUDSI, and EL-BAYOUMI Gamal M. "Guidance Optimization for Tactical Homing Missiles and Air Defense Systems." INCAS BULLETIN 10, no. 1 (March 11, 2018): 193–205. http://dx.doi.org/10.13111/2066-8201.2018.10.1.17.

Full text

APA, Harvard, Vancouver, ISO, and other styles

21

Morgan, Robert Wes, Hal Tharp, and Thomas L. Vincent. "Minimum Energy Guidance for Aerodynamically Controlled Missiles." IEEE Transactions on Automatic Control 56, no. 9 (September 2011): 2026–37. http://dx.doi.org/10.1109/tac.2011.2108619.

Full text

APA, Harvard, Vancouver, ISO, and other styles

22

Brighton, Caroline H., Adrian L. R. Thomas, and Graham K. Taylor. "Terminal attack trajectories of peregrine falcons are described by the proportional navigation guidance law of missiles." Proceedings of the National Academy of Sciences 114, no. 51 (December 4, 2017): 13495–500. http://dx.doi.org/10.1073/pnas.1714532114.

Full text

Abstract:

The ability to intercept uncooperative targets is key to many diverse flight behaviors, from courtship to predation. Previous research has looked for simple geometric rules describing the attack trajectories of animals, but the underlying feedback laws have remained obscure. Here, we use GPS loggers and onboard video cameras to study peregrine falcons, Falco peregrinus, attacking stationary targets, maneuvering targets, and live prey. We show that the terminal attack trajectories of peregrines are not described by any simple geometric rule as previously claimed, and instead use system identification techniques to fit a phenomenological model of the dynamical system generating the observed trajectories. We find that these trajectories are best—and exceedingly well—modeled by the proportional navigation (PN) guidance law used by most guided missiles. Under this guidance law, turning is commanded at a rate proportional to the angular rate of the line-of-sight between the attacker and its target, with a constant of proportionality (i.e., feedback gain) called the navigation constant (N). Whereas most guided missiles use navigation constants falling on the interval 3 ≤ N ≤ 5, peregrine attack trajectories are best fitted by lower navigation constants (median N < 3). This lower feedback gain is appropriate at the lower flight speed of a biological system, given its presumably higher error and longer delay. This same guidance law could find use in small visually guided drones designed to remove other drones from protected airspace.

APA, Harvard, Vancouver, ISO, and other styles

23

Huang, Lan, Jianmei Song, Minqiang Zhang, and Gaohua Cai. "Optical flow based guidance system design for semi-strapdown image homing guided missiles." Chinese Journal of Aeronautics 29, no. 5 (October 2016): 1345–54. http://dx.doi.org/10.1016/j.cja.2016.08.011.

Full text

APA, Harvard, Vancouver, ISO, and other styles

24

Hong, Seong-Min, Dong-Yeon Lee, and Min-Jea Tahk. "Stage Optimization of Anti-Air Missiles Considering Guidance Laws." IFAC-PapersOnLine 52, no. 12 (2019): 227–31. http://dx.doi.org/10.1016/j.ifacol.2019.11.247.

Full text

APA, Harvard, Vancouver, ISO, and other styles

25

Aggarwal, Romesh K., and Charles R. Moore. "Terminal Guidance Algorithm for Ramjet-Powered Missiles." Journal of Guidance, Control, and Dynamics 21, no. 6 (November 1998): 862–66. http://dx.doi.org/10.2514/2.4349.

Full text

APA, Harvard, Vancouver, ISO, and other styles

26

Kim, Y. S., H. S. Cho, and Z. Bien. "A new guidance law for homing missiles." Journal of Guidance, Control, and Dynamics 8, no. 3 (May 1985): 402–4. http://dx.doi.org/10.2514/3.19994.

Full text

APA, Harvard, Vancouver, ISO, and other styles

27

Shieh, C. S. "Tunable H∞ robust guidance law for homing missiles." IEE Proceedings - Control Theory and Applications 151, no. 1 (January 1, 2004): 103–7. http://dx.doi.org/10.1049/ip-cta:20040065.

Full text

APA, Harvard, Vancouver, ISO, and other styles

28

Horton, M. P. "Autopilots for Tactical Missiles: An Overview." Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 209, no. 2 (May 1995): 127–39. http://dx.doi.org/10.1243/pime_proc_1995_209_373_02.

Full text

Abstract:

In recent years, a number of technology and operational features have emerged which have had an impact on the design of control systems for tactical missiles. These have required the closer tuning of autopilots to both the guidance loop and the aerodynamic limits and, at the same time, new design and assessment methods have also been developed for control systems. It is the purpose of this paper to bring these developments together and show how the various aspects contribute to the overall design process which enables a missile autopilot to reach maturity.

APA, Harvard, Vancouver, ISO, and other styles

29

Markevich, V. E., and V. V. Legkostup. "Modified method of proportional navigation to intercept aeroballistic targets with a limited sector guidance of missile." «System analysis and applied information science», no. 4 (February 6, 2019): 28–50. http://dx.doi.org/10.21122/2309-4923-2018-4-28-50.

Full text

Abstract:

The improved version of the algorithm realizing a method of proportional navigation for guidance of anti-aircraft guided missiles in the limited sector of the angular tracking connected with the line of sight of the aero ballistic target and the anticipations providing sustainable missile guidance with the maximum the angles of pre-emption, which aren’t exceeding maximum permissible is considered. The analytical expressions describing the algorithm of calculation of guidance command and signals of correction, adaptive to parameters of the movement and realizing steady tracking and control of a guided anti-aircraft missile in the wide the ranges of the radial distance, heights and speeds of the movement of aerodynamic target are given. Results of mathematical simulation of a problem of spatial interception of the aero-ballistic targets and also the comparative analysis and preliminary estimate of accuracy of guidance of the existing classical and modified versions of a method of proportional navigation are presented.

APA, Harvard, Vancouver, ISO, and other styles

30

Alpert, Joel. "Miss distance analysis for command guided missiles." Journal of Guidance, Control, and Dynamics 11, no. 6 (November 1988): 481–87. http://dx.doi.org/10.2514/3.20343.

Full text

APA, Harvard, Vancouver, ISO, and other styles

31

Shima, T., and O. M. Golan. "Bounded differential games guidance law for dual-controlled missiles." IEEE Transactions on Control Systems Technology 14, no. 4 (July 2006): 719–24. http://dx.doi.org/10.1109/tcst.2006.876642.

Full text

APA, Harvard, Vancouver, ISO, and other styles

32

Jianguo, Guo, Wang Xinming, and Zhou Jun. "Efficient information-based cooperative guidance law of multi-missiles." Transactions of the Institute of Measurement and Control 41, no. 9 (October 25, 2018): 2651–65. http://dx.doi.org/10.1177/0142331218806961.

Full text

Abstract:

This paper investigates a novel cooperative guidance law for the task of salvo attack based on efficient information. The concept of efficient information is first introduced as the basis of a multi-missile cooperative structure in a nominal engagement situation. The effective time of the efficient information, which can be regarded as an important parameter to indicate the ability of a missile to attack a given stationary target, is estimated by modifying the current time-to-go estimation method in the presence of a lateral acceleration constraint. Utilizing the effective time, a novel cooperative guidance law with better adaptiveness and robustness is proposed for multi-missile systems to realize the simultaneous attack. Finally, the effectiveness of the proposed cooperative guidance law is demonstrated via simulations.

APA, Harvard, Vancouver, ISO, and other styles

33

Yang, Ciann-Dong, and Hsin-Yuan Chen. "Nonlinear H Robust Guidance Law for Homing Missiles." Journal of Guidance, Control, and Dynamics 21, no. 6 (November 1998): 882–90. http://dx.doi.org/10.2514/2.4321.

Full text

APA, Harvard, Vancouver, ISO, and other styles

34

Cheng, V. H. L., and N. K. Gupta. "Advanced midcourse guidance for air-to-air missiles." Journal of Guidance, Control, and Dynamics 9, no. 2 (March 1986): 135–42. http://dx.doi.org/10.2514/3.20081.

Full text

APA, Harvard, Vancouver, ISO, and other styles

35

Thong, Do Quang. "Synthesis of High-Precision Missile Homing System Using Proportional Guidance Method." Mekhatronika, Avtomatizatsiya, Upravlenie 21, no. 4 (April 11, 2020): 242–48. http://dx.doi.org/10.17587/mau.21.242-248.

Full text

Abstract:

Modern air targets are characterized by low visibility, high maneuverability and high survivability. In addition, for some specific targets, for instance ballistic missiles, in order to defeat them the missile need tobe guided and carried out direct hit, i.e. "hit to kill". Therefore, in this paper, we present a high-precision missile homing system (MHS) using the proportional guidance method for firing at the highly maneuverable targets. Specifically, we propose a parametric optimization method for choosing a set of optimal parameters of the missile homing system for each dynamic parameter set of the missile. In addition, the paper gives the recommendations of choosing the initial conditions for the synthesis of missile homing system. In our experience, we should choose the small initial condition for synthesizing the missile homing system. Finally, the article also investigates the influence of systematic error in determining the speed, normal acceleration of missiles and the angular velocity of the line of sight of the missile and target on the accuracy of the missile homing system. We implement the proposed missile homing system and the parametric optimization method in Matlab. The experimental results illustrate that, using proposed system and the parametric optimization method, the missile can defeat the modern air targets with low visibility, high maneuverability and high survivability.

APA, Harvard, Vancouver, ISO, and other styles

36

Özkan, Bülent, M. Kemal Özgören, and Gökmen Mahmutyazıcıoğlu. "Modeling of dynamics, guidance, and control systems of air-to-surface missiles." Journal of Defense Modeling and Simulation: Applications, Methodology, Technology 9, no. 2 (May 18, 2011): 101–12. http://dx.doi.org/10.1177/1548512911407647.

Full text

APA, Harvard, Vancouver, ISO, and other styles

37

Vovik, G. V., M. S. Sergeev, and Yu M. Shabatura. "ALGORITHMS OF DIMENSIONAL MODELING OF FOLLOWING MEASURING SYSTEMS OF SELF-WATER SYSTEMS." Vestnik komp'iuternykh i informatsionnykh tekhnologii, no. 185 (November 2019): 21–28. http://dx.doi.org/10.14489/vkit.2019.11.pp.021-028.

Full text

Abstract:

Algorithms for seminatural stochastic (statistical) modeling of tracking gauges of homing systems are intended for use in models of guided missiles of information about angular errors of homing heads recorded in real conditions of use. Such information is obtained by processing the data of field experiments. Algorithms provide reproduction of signals at the output of angular measurements, which are closest to the signals observed in field experiments. To achieve the coincidence of the reproduced angular errors with errors recorded in the actual conditions of the use of guided missiles, data on the phase coordinates of the homing heads, such as expectation and dispersion of angular errors, are used. Information on angular errors is placed in a specialized two-dimensional database of angular errors. The target coordinates of the database and the angular velocity of the line of sight of the target, which are the components of the vector of signs of the phase coordinates, are used as the address coordinates of the database. An example of a comparative evaluation of three possible stochastic modeling algorithms is given. The assessment was performed using the information quality indicator in the form of a percentage of the decrease in relative conditional entropy. For the considered example, it is shown that the algorithm using the quadratic prediction of changes in the signs of phase coordinates has advantages over the algorithm for linear prediction and the algorithm for selecting the “closest” value of the signs of phase coordinates.

APA, Harvard, Vancouver, ISO, and other styles

38

Menon, P. K. A., and M. M. Briggs. "Near-optimal midcourse guidance for air-to-air missiles." Journal of Guidance, Control, and Dynamics 13, no. 4 (July 1990): 596–602. http://dx.doi.org/10.2514/3.25375.

Full text

APA, Harvard, Vancouver, ISO, and other styles

39

He, Shaoming, and Defu Lin. "Three-Dimensional Optimal Impact Time Guidance for Antiship Missiles." Journal of Guidance, Control, and Dynamics 42, no. 4 (April 2019): 941–48. http://dx.doi.org/10.2514/1.g003971.

Full text

APA, Harvard, Vancouver, ISO, and other styles

40

Hexner, G., and A. W. Pila. "Practical Stochastic Optimal Guidance Law for Bounded Acceleration Missiles." Journal of Guidance, Control, and Dynamics 34, no. 2 (March 2011): 437–45. http://dx.doi.org/10.2514/1.51543.

Full text

APA, Harvard, Vancouver, ISO, and other styles

41

Green, A., J. Shinar, and M. Guelman. "Game optimal guidance law synthesis for short range missiles." Journal of Guidance, Control, and Dynamics 15, no. 1 (January 1992): 191–97. http://dx.doi.org/10.2514/3.20818.

Full text

APA, Harvard, Vancouver, ISO, and other styles

42

Hong, Seong-Min, Min-Jea Tahk, and Chang-Hun Lee. "Stage Optimization of Anti-air Missiles Using Practical Guidance Laws." International Journal of Aeronautical and Space Sciences 21, no. 2 (November 21, 2019): 394–403. http://dx.doi.org/10.1007/s42405-019-00224-y.

Full text

APA, Harvard, Vancouver, ISO, and other styles

43

Kamel, Ahmed M., Valerie Renaudin, John Nielsen, and Gérard Lachapelle. "INS Assisted Fuzzy Tracking Loop for GPS-Guided Missiles and Vehicular Applications." International Journal of Navigation and Observation 2013 (February 27, 2013): 1–17. http://dx.doi.org/10.1155/2013/750385.

Full text

Abstract:

Autonomous Navigation Systems used in missiles and other high dynamic platforms are mostly dependent on the Global Positioning System (GPS). GPS users face limitations in terms of missile high dynamics and signal interference. Receiver’s tracking loops bandwidth requirements to avoid these problems are conflicting. The paper presents a novel signal frequency and phase tracking algorithm for very high dynamic conditions, which mitigates the conflicting choice of bandwidths and reduces tracking loop measurement noise. It exploits the flexibility of fuzzy control systems for directly generating the required Numerically Controlled Oscillator (NCO) tuning frequency using phase and frequency discriminators information and is labeled Fuzzy Frequency Phase Lock Loop (FFPLL). Because Fuzzy Systems can be computationally demanding and an Inertial Navigation System (INS) is often onboard the vehicle, an assisted INS Doppler version has been designed and is also proposed. Assessment of the new GPS tracking method is performed with both simulated and experimental data under jamming conditions. The main enhancements of the proposed system consist in reduced processing time, improved tracking continuity and faster reacquisition time.

APA, Harvard, Vancouver, ISO, and other styles

44

Ma, Xiang, Keren Dai, Man Li, Hang Yu, Weichen Shang, Libo Ding, He Zhang, and Xiaofeng Wang. "Optimal-Damage-Effectiveness Cooperative-Control Strategy for the Pursuit–Evasion Problem with Multiple Guided Missiles." Sensors 22, no. 23 (November 30, 2022): 9342. http://dx.doi.org/10.3390/s22239342.

Full text

Abstract:

In this paper, an optimal-damage-effectiveness cooperative-control strategy based on a damage-efficiency model and a virtual-force method is proposed to solve the pursuit–evasion problem with multiple guided missiles. Firstly, different from the overly ideal assumption in the traditional pursuit–evasion problem, an optimization problem that maximizes the damage efficiency is established and solved, making the optimal-damage-effectiveness strategy more meaningful for practical applications. Secondly, a modified virtual-force method is proposed to obtain this optimal-damage-effectiveness control strategy, which solves the numerical solution challenges brought by the high-complexity damage function. Thirdly, adaptive gain is designed in this strategy based on guidance-integrated fuze technology to achieve robust maximum damage efficiency in unpredictable interception conditions. Finally, the effectiveness and robustness of the proposed strategy are verified by numerical simulations.

APA, Harvard, Vancouver, ISO, and other styles

45

Imado, Fumiaki, Takeshi Kuroda, and Susumu Miwa. "Optimal midcourse guidance for medium-range air-to-air missiles." Journal of Guidance, Control, and Dynamics 13, no. 4 (July 1990): 603–8. http://dx.doi.org/10.2514/3.25376.

Full text

APA, Harvard, Vancouver, ISO, and other styles

46

Durieux, J. L. "Comparison of angular and metric guidance laws for tactical missiles." Journal of Guidance, Control, and Dynamics 9, no. 4 (July 1986): 505–7. http://dx.doi.org/10.2514/3.20139.

Full text

APA, Harvard, Vancouver, ISO, and other styles

47

Hull, D. G., J. L. Speyer, and D. B. Burris. "Linear-quadratic guidance law for dual control of homing missiles." Journal of Guidance, Control, and Dynamics 13, no. 1 (January 1990): 137–44. http://dx.doi.org/10.2514/3.20527.

Full text

APA, Harvard, Vancouver, ISO, and other styles

48

Liu, Xiao, Shengjing Tang, Jie Guo, Yuhang Yun, and Zhe Chen. "Midcourse Guidance Law Based on High Target Acquisition Probability Considering Angular Constraint and Line-of-Sight Angle Rate Control." International Journal of Aerospace Engineering 2016 (2016): 1–20. http://dx.doi.org/10.1155/2016/7634847.

Full text

Abstract:

Random disturbance factors would lead to the variation of target acquisition point during the long distance flight. To acquire a high target acquisition probability and improve the impact precision, missiles should be guided to an appropriate target acquisition position with certain attitude angles and line-of-sight (LOS) angle rate. This paper has presented a new midcourse guidance law considering the influences of random disturbances, detection distance restraint, and target acquisition probability with Monte Carlo simulation. Detailed analyses of the impact points on the ground and the random distribution of the target acquisition position in the 3D space are given to get the appropriate attitude angles and the end position for the midcourse guidance. Then, a new formulation biased proportional navigation (BPN) guidance law with angular constraint and LOS angle rate control has been derived to ensure the tracking ability when attacking the maneuvering target. Numerical simulations demonstrates that, compared with the proportional navigation guidance (PNG) law and the near-optimal spatial midcourse guidance (NSMG) law, BPN guidance law demonstrates satisfactory performances and can meet both the midcourse terminal angular constraint and the LOS angle rate requirement.

APA, Harvard, Vancouver, ISO, and other styles

49

Kim, Yoon-Hwan, Chang-Kyung Ryoo, and Min-Jea Tahk. "Guidance Synthesis for Evasive Maneuver of Anti-Ship Missiles Against Close-In Weapon Systems." IEEE Transactions on Aerospace and Electronic Systems 46, no. 3 (July 2010): 1376–88. http://dx.doi.org/10.1109/taes.2010.5545195.

Full text

APA, Harvard, Vancouver, ISO, and other styles

50

Rinat, Keren, and Joseph Z. Ben-Asher. "Worst-Case Distributions for Performance Evaluation of Proportionally Guided Missiles." Journal of Guidance, Control, and Dynamics 23, no. 5 (September 2000): 895–98. http://dx.doi.org/10.2514/2.4623.

Full text

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!