Relevant bibliographies by topics / Guided missiles Guidance systems

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Guided missiles Guidance systems'

Author: Grafiati
Published: 4 June 2021
Last updated: 4 March 2023

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Journal articles on the topic "Guided missiles Guidance systems"

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.

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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.
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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.

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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.

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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.
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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.

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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.
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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.

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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.
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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.

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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.

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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.

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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.

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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.
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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.

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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.
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Dissertations / Theses on the topic "Guided missiles Guidance systems"

1

Vural, Ozgur Ahmet. "Fuzzy Logic Guidance System Design For Guided Missiles." Master's thesis, METU, 2003. http://etd.lib.metu.edu.tr/upload/1026715/index.pdf.

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This thesis involves modeling, guidance, control, and flight simulations of a canard controlled guided missile. The autopilot is designed by a pole placement technique. Designed autopilot is used with the guidance systems considered in the thesis. Five different guidance methods are applied in the thesis, one of which is the famous proportional navigation guidance. The other four guidance methods are different fuzzy logic guidance systems designed considering different types of guidance inputs. Simulations are done against five different target types and the performances of the five guidance methods are compared and discussed.
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2

Lukacs, John A. "Hit-to-kill guidance algorithm for the interception of ballistic missiles during the boost phase." Thesis, Monterey California. Naval Postgraduate School, 2006. http://hdl.handle.net/10945/2829.

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A near-optimal guidance law has been developed using the direct method of calculus of variations that maximizes the kinetic energy transfer from a surface-launched missile upon interception to a ballistic missile target during the boost phase of flight. Mathematical models of a North Korean Taep'o-dong II (TD-2) medium-range ballistic missile and a Raytheon Standard Missile 6 (SM-6) interceptor are used to demonstrate the guidance lawâ s performance. This law will utilize the SM-6â s onboard computer and active radar sensors to independently predict an intercept point, solve the two-point boundary value problem, and determine a near-optimal flight path to that point. Determining a truly optimal flight path would require significant computing power and time, while a near-optimal flight path can be calculated onboard the interceptor and updated in real time without significant changes to the interceptorâ s hardware. That near-optimal guidance path is then converted into a set of command functions and fed back into the control computer of the interceptor. By modifying the second and third derivatives of the two-point boundary value problem, the intercept conditions can be varied to study their effects upon the optimal flight path regarding the maximization of kinetic energy upon impact.
US Navy (USN) author.
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3

Corban, J. Eric. "Real-time guidance and propulsion control for single-stage-to-orbit airbreathing vehicles." Diss., Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/12889.

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Leung, Martin S. K. "A real-time near-optimal guidance approach for launch vehicles." Diss., Georgia Institute of Technology, 1992. http://hdl.handle.net/1853/12022.

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Rogers, Jonathan. "Applications of internal translating mass technologies to smart weapons systems." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/31813.

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Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2010.
Committee Chair: Mark Costello; Committee Member: Eric Johnson; Committee Member: Frank Fresconi; Committee Member: Olivier Bauchau; Committee Member: Peter Plostins. Part of the SMARTech Electronic Thesis and Dissertation Collection.
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Katzir, Shevach. "Optimal and on-board near-optimal midcourse guidance." Diss., Virginia Polytechnic Institute and State University, 1988. http://hdl.handle.net/10919/53546.

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Optimal midcourse guidance is examined for an air-to-air missile featuring boost-coast-sustain propulsion. A vertical plane, point-mass model is studied with load factor as a control variable. Time-range-energy optimal trajectories are computed, open-loop, via the usual necessary conditions and a multiple-shooting algorithm. A requirement on terminal velocity magnitude is examined for its effect on firing range. Next, a study of the optimal midcourse guidance problem with reduced-order models is presented. The models under study, in addition to the point-mass model, are: - Singularly perturbed model with y as fast variable; - Point mass model with approximation of the induced-drag; - Energy model. One of the major results in this study is that the reduced-order models are not accurate enough to approximate the optimal trajectories and so are of limited use as reference trajectories in an on-board scheme. Thus, optimal trajectories, computed by using the point-mass model, are selected as the reference trajectories for a closed-loop guidance scheme. Finally, an approach to on-board real-time calculations for an optimal guidance approximation is derived. Extremal fields and neighboring extremal theory ideas are used together with pre-calculated Euler solutions to construct a closed-loop guidance algorithm. The method is applied to the midcourse guidance of an air-to-air missile and was found to perform quite well.
Ph. D.
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7

Kumar, Renjith R. "Optimal and near-optimal medium range air-to-air missile guidance against maneuvering targets." Diss., Virginia Polytechnic Institute and State University, 1989. http://hdl.handle.net/10919/54224.

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Optimal intercept trajectories for a boost-sustain-coast medium-range air-to-air missile are synthesized using optimal control theory. Optimality in time/range/energy at intercept of a target is the main objective. Attainable sets and their boundaries are obtained and used to generate optimal intercept points in a three-dimensional scenario. A three-phase closed-loop guidance scheme is used to generate an efficient guidance law against a maneuvering target. In the present study, target maneuvers are restricted to the horizontal plane. An initial boost-phase with near-optimal guidance in the presence of active control constraints and thrust switches is simulated. Target maneuvers are neglected during this phase. A new method of gain evaluation is detailed. A midcourse guidance scheme with neighboring guidance, transversal comparisons, and chasing center-of-attainability of target to augment performance is studied. Modifications in terminal guidance using proportional navigation, such as chasing the center-of-attainability of target, altitude shaping, and drag-resolution schemes are used to attempt better performance at intercept. A composite guidance strategy using a combination of neighboring guidance and proportional navigation for the midcourse guidance is introduced. The excellent performance of this guidance strategy and the improvement in storage requirements for on-board use make it a very special scheme.
Ph. D.
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Kilic, Kayhan Caglar. "Autopilot And Guidance Algorithms For Infrared Guided Missiles." Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/2/12607930/index.pdf.

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Guided missiles are among the most effective threats against air platforms. Aircraft and helicopter losses in the last decades were mostly due to guided missiles, 70% of which were infrared guided missiles. Today, there are as many as 500,000 shoulder-fired missiles in military arsenals around the world, whose guidance algorithms enable them to track the desired trajectories very precisely. In this thesis, main focus is on defining infrared missile guidance and control algorithms in order to study on various target-missile scenarios for the effectiveness of these algorithms. First, a mathematical model of a generic missile is given. Then the flight control system of the missile is created by using LQR and PID controllers. Different kinds of PNG algorithms applied to an infrared missile are presented. The seeker part of the infrared missile is also discussed. The effectiveness of guidance algorithms are studied based on different target &ndash
missile scenarios and the responses of them to IR countermeasures are also observed. This study shows that different guidance algorithms can be used for different scenarios. If suitable algorithms are combined and suitable constants are applied, the guided missile can track the target very precisely. In addition, the seeker part has to be improved with tracking algorithms in order to recognize IR-countermeasures and not to follow them.
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Ozcan, Ali Erdem. "Autopilot And Guidance For Anti-tank Imaging Infrared Guided Missiles." Master's thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/12610111/index.pdf.

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An anti-tank guided missile is a weapon system primarily designed to hit and destroy armored tanks and other armored vehicles. Developed first-generation command-guided and second-generation semi-automatic command guided missiles had many disadvantages and lower hit rates. For that reason, third generation imaging infrared fire-and-forget missile concept is very popular nowadays. In this thesis, mainly, a mathematical model for a fire-and-forget anti-tank missile is developed and a flight control autopilot design is presented using PID and LQR techniques. For target tracking purposes, &ldquo
correlation&rdquo
, &ldquo
centroid&rdquo
and &ldquo
active contour&rdquo
algorithms are studied and these algorithms are tested over some scenarios for maximizing hit rate. Different target scenarios and countermeasures are discussed in an artificially created virtual environment.
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Riddle, David Baker Hartfield Roy J. "Design tool development for liquid propellant missile systems." Auburn, Ala, 2007. http://repo.lib.auburn.edu/2006%20Fall/Theses/RIDDLE_DAVID_20.pdf.

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Books on the topic "Guided missiles Guidance systems"

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Jiang, Jiahe. Guidance principle of missiles. Beijing: Beijing hang kong hang tian da xue chu ban she, 2012.

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2

Zarchan, Paul. Tactical and strategic missile guidance. 3rd ed. Reston, Va: American Institute of Aeronautics and Astronautics, 1997.

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American Institute of Aeronautics and Astronautics, ed. Tactical and strategic missile guidance. 6th ed. Reston, VA: American Institute of Aeronautics and Astronautics, 2012.

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Tactical and strategic missile guidance. 4th ed. Reston, Va: American Institute of Aeronautics and Astronautics, 2002.

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Ben-Asher, Joseph Z. Advances in missile guidance theory. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

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Radar homing guidance for tactical missiles. New York: Wiley, 1986.

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Radar homing guidance for tactical missiles. Basingstoke: Macmillan, 1986.

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Zarchan, Paul. Tactical and strategic missile guidance. Washington, DC: American Institute of Aeronautics and Astronautics, 1990.

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Shneydor, N. A. Missile guidance and pursuit: Kinematics, dynamics and control. Chichester, UK: Horwood, 2008.

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Lin, Ching-Fang. Modern navigation, guidance, and control processing. Englewood Cliffs, N.J: Prentice Hall, 1991.

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Book chapters on the topic "Guided missiles Guidance systems"

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Yanushevsky, Rafael T. "Analysis of PN Guided Missile Systems in the Time Domain." In Modern Missile Guidance, 23–30. Second edition. | Boca Raton, FL : Taylor & Francis/CRC Press, [2019]: CRC Press, 2018. http://dx.doi.org/10.1201/9781351202954-3.

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Yanushevsky, Rafael T. "Analysis of PN Guided Missile Systems in the Frequency Domain." In Modern Missile Guidance, 31–55. Second edition. | Boca Raton, FL : Taylor & Francis/CRC Press, [2019]: CRC Press, 2018. http://dx.doi.org/10.1201/9781351202954-4.

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James, D. A. "Seeker Antenna Systems." In Radar Homing Guidance for Tactical Missiles, 38–55. London: Macmillan Education UK, 1986. http://dx.doi.org/10.1007/978-1-349-08602-3_4.

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Padilla, Laura, and Dorin A. Todor. "Image Guidance Systems for Brachytherapy." In Handbook of Image-Guided Brachytherapy, 69–98. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-44827-5_4.

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Banathy, Bela H. "The Design of Evolutionary Guidance Systems." In Guided Evolution of Society, 325–54. Boston, MA: Springer US, 2000. http://dx.doi.org/10.1007/978-1-4757-3139-2_11.

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Tao, Xizi, Wei Dong, Chunyan Wang, and Jianan Wang. "Cooperative Guidance Law with Guaranteed Convergence for Multiple Missiles." In Proceedings of 2021 International Conference on Autonomous Unmanned Systems (ICAUS 2021), 1625–34. Singapore: Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-9492-9_160.

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Wan, Jiaqing, Jian Wang, Qiang Guo, and Xinguo Li. "Design of Multi-constraints Missiles Cooperative Terminal Guidance Algorithm." In Proceedings of 2021 International Conference on Autonomous Unmanned Systems (ICAUS 2021), 30–44. Singapore: Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-9492-9_4.

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Besant, C. B. "Guidance and navigation techniques for guided and autonomous vehicles." In Material Flow Systems in Manufacturing, 368–87. Boston, MA: Springer US, 1994. http://dx.doi.org/10.1007/978-1-4615-2498-4_13.

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Schoellnast, Helmut, and Stephen B. Solomon. "Imaging of Interventional Therapies in Oncology: Image Guidance, Robotics, and Fusion Systems." In Image-Guided Cancer Therapy, 277–91. New York, NY: Springer New York, 2013. http://dx.doi.org/10.1007/978-1-4419-0751-6_19.

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Liu, Juntong, Siyang Chen, and Kai Liu. "Research on Improved Cooperative Terminal Guidance Law of Multi-hypersonic Cruise Missiles." In Proceedings of 2021 International Conference on Autonomous Unmanned Systems (ICAUS 2021), 541–50. Singapore: Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-9492-9_54.

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Conference papers on the topic "Guided missiles Guidance systems"

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Benson, Dewey, Bill Ryan, Ted Drzewiecki, Dewey Benson, Bill Ryan, and Ted Drzewiecki. "An optofluidic control system for tactical missiles and guided munitions." In Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3834.

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Ohlmeyer, Ernest, Thomas Pepitone, B. Miller, D. Malyevac, John Bibel, Alan Evans, Ernest Ohlmeyer, et al. "GPS-aided navigation system requirements for smart munitions and guided missiles." In Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3683.

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ALPERT, JOEL. "Miss distance analysis for command guided missiles." In Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2582.

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Zhou, Zhiming, and Zhen Liu. "Stability of Spinning Missiles Guided by Trajectory Tracking Guidance Law." In 2022 34th Chinese Control and Decision Conference (CCDC). IEEE, 2022. http://dx.doi.org/10.1109/ccdc55256.2022.10034286.

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RITLAND, JOHN. "Survey of aided-inertial navigation systems for missiles." In Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-3497.

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Abdel-Rahim, M., M. El-Geneidy, and M. Rizk. "Robust Design of Stochastic Controller for a Guidance System of Command Guided Missile." In 1993 American Control Conference. IEEE, 1993. http://dx.doi.org/10.23919/acc.1993.4792902.

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Rajesh Kumar, B., and V. R. Jisha. "Hybrid Guidance Law for Cooperative Attack of Missiles." In 2018 Second International Conference on Intelligent Computing and Control Systems (ICICCS). IEEE, 2018. http://dx.doi.org/10.1109/iccons.2018.8663174.

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Poznyak, Alexander. "Non-smooth missiles guidance: Interceptor-defender scenario with uncertainties." In 2014 13th International Workshop on Variable Structure Systems (VSS). IEEE, 2014. http://dx.doi.org/10.1109/vss.2014.6881125.

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Ick-Ho Whang and Won-Sang Ra. "Time-to-go estimator for missiles guided by BPNG." In 2008 International Conference on Control, Automation and Systems (ICCAS). IEEE, 2008. http://dx.doi.org/10.1109/iccas.2008.4694685.

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Shima, Tal, and Oded Golan. "Linear Quadratic Guidance Laws for Missiles Having Dual Control Systems." In AIAA Guidance, Navigation, and Control Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-4841.

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Reports on the topic "Guided missiles Guidance systems"

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Menon, P. K., and Ernest J. Ohlmeyer. Integrated Guidance-Control Systems for Fixed-Aim Warhead Missiles. Fort Belvoir, VA: Defense Technical Information Center, November 2000. http://dx.doi.org/10.21236/ada389283.

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