Relevant bibliographies by topics / Missiles - Flight Control

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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 'Missiles - Flight Control'

Author: Grafiati
Published: 4 June 2021
Last updated: 7 September 2023

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Journal articles on the topic "Missiles - Flight Control"

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Li, Yang, Hao Zhou, and Wanchun Chen. "Three-Dimensional Impact Time and Angle Control Guidance Based on MPSP." International Journal of Aerospace Engineering 2019 (February 24, 2019): 1–16. http://dx.doi.org/10.1155/2019/5631723.

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A new nonlinear guidance law for air-to-ground missile cooperation attacks is proposed in this paper. This guidance law enables missiles with different initial conditions to attack targets simultaneously, and it can also precisely satisfy the terminal impact angle conditions in both flight-path angle and heading angle. The guidance law is devised using the model predictive static programming (MPSP) method, and the control saturation constraint is incorporated in the MPSP algorithm. The first-order-lag acceleration of the missile is taken as the state variable to realize the convergence of the terminal acceleration to zero. Moreover, a collision avoidance strategy for three-dimensional missile cooperative flight is proposed. The simulation results show that the guidance law can make the missiles hit the target accurately at the same time with the ideal impact angles and can realize the control saturation constraints of the missiles. This can increase the attack effects and is significant for collaborative attacks.
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Chubarov, Anton. "Constructing the models of programmed flight for path calculation in designing tactical and anti-aircraft guided missiles." Eastern-European Journal of Enterprise Technologies 1, no. 4 (109) (2021): 21–30. http://dx.doi.org/10.15587/1729-4061.2021.225594.

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Several models of programmed flight have been constructed to perform calculations on flight path optimization in designing tactical and anti-aircraft-guided missiles. The developed models are based on the determination of interrelated programmed values of altitude and the flight path angle depending on the range which have a differential relationship. The combination of flight altitude and flight-path angle programs allows the users to simulate the steady flight of a guided missile to the calculated endpoint using the methods of proportional control. Good correspondence of the developed models to the physics of flight was shown by assessing the quality of approximation of the developed models of flight paths of anti-aircraft guided missiles obtained using other known models. The obtained approximation error was less than 5 % which indicates a good correspondence of the developed models to the physics of flight. Compliance of the developed models of programmed flight with the intended purpose and the advantage over the most common known models were proved by optimizing the flight paths of the anti-aircraft-guided missile. In most of the considered calculation cases, the value of the objective function was improved to 2.9 %. The flight path was optimized using a genetic algorithm. The developed models have a simple algebraic form and a small number of control parameters are presented in a ready-to-use form and do not require refinement for a concrete task. This allows them to be implemented in design practice without spending much time to speed up the calculation of optimal design variables and optimal flight paths of tactical and anti-aircraft-guided missiles
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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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Huai, Zepeng, Hongbo Wang, Min Gong, Pengfei Ren, Zijian Xu, and Lingxiao Cheng. "A Specific Sliding Mode Control for Autopilot Design of Bank-to-Turn Missiles." MATEC Web of Conferences 179 (2018): 01015. http://dx.doi.org/10.1051/matecconf/201817901015.

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This paper studies the BTT missile's sliding mode flight controller. Firstly, the control model is established according to dynamic inverse method and the general dynamic equation of the missile flying in the atmosphere. Then, the sliding mode controller is designed and it adopts the time-varying sliding mode surface, the self-defined reaching law and the adaptive control parameters. Finally, three sets of simulation are carried out to prove the flight controller designed in this paper for BTT missile can follow the guidance instructions and meet operational needs.
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CICHOCKI, Maciej K., Dariusz SOKOŁOWSKI, and Zbigniew LEWANDOWSKI. "Influence of Mass Parameters Modification on Manoeuvrability of 9K33 „OSA” Set 9M33M3 Missile." Problems of Mechatronics Armament Aviation Safety Engineering 11, no. 3 (2020): 9–18. http://dx.doi.org/10.5604/01.3001.0014.3704.

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This paper discusses analytical method for realization of preliminary missile stability design calculations. Action has been taken to estimate influence of replacing massive blocks of analogue electronics with compact solutions of digital electronics in missiles remaining in operation. On an example of a short-range 9M33M3 missile from 9K33 „OSA” set and its previously analysed aerodynamic characteristics, the analysis of the centre of gravity location impact was carried out to determine maximum loads occurring in the two most interesting phases of flight: after booster engine burnout and directly after cruise engine burnout. The suggestion for modification suggestion of flight parameters’ optimization is presented which defines stability and its critical impact of these parameters on aeronautical engineering. For the tested missile, the methodology suggestions for the modification is discussed with the comparison of serially produced copies to define the ability of improving the flight parameters. The paper includes visualizations and quantity analysis of: maximal loads on the fuselage, minimal turn radius, and control wing inclination angle as missile’s angle of attack function.
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CERNAT, Romică. "Impactul tehnologiilor emergente și disruptive asupra domeniului militar." Gândirea Militară Românească 2021, no. 4 (2021): 230–45. http://dx.doi.org/10.55535/gmr.2021.4.13.

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Hypersonic missiles are a new category of weapons that have sparked intense debate among security experts. The hypersonic weapons, this combination of speed, accuracy, surprise, and maneuverability makes the defense against them more difficult than against standard ballistic or cruise missiles and therefore makes them more destabilizing. Capable of traveling over five times the speed of sound (Mach 5), and of performing evasive maneuvers mid-flight, they are considered practically impossible to intercept using conventional missile defense systems. Innovative nuclear and conventional weapon delivery systems are impressive and developing. These are grouped into three categories: intercontinental ballistic missiles, hypersonic delivery systems and new advanced strategic weapon delivery capabilities. These and other technological advances being made simultaneously may also impact arms control and strategic stability. Other characteristics of hypersonic systems, however, are potentially advantageous compared with ballistic missiles. Of particular interest are the ability to fly at low altitude, making detection by earth-based sensors difficult; the ability to maneuver during flight to avoid detection and interception; and the unpredictability of targets, since hypersonic vehicles do not follow a ballistic trajectory.
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CERNAT, Romică. "The Potential of Hypersonic Weapons and the Great Military Powers Strategy regarding their Production. Case Study." Romanian Military Thinking 2021, no. 4 (2021): 230–45. http://dx.doi.org/10.55535/rmt.2021.4.13.

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Hypersonic missiles are a new category of weapons that have sparked intense debate among security experts. The hypersonic weapons, this combination of speed, accuracy, surprise, and maneuverability makes the defense against them more difficult than against standard ballistic or cruise missiles and therefore makes them more destabilizing. Capable of traveling over five times the speed of sound (Mach 5), and of performing evasive maneuvers mid-flight, they are considered practically impossible to intercept using conventional missile defense systems. Innovative nuclear and conventional weapon delivery systems are impressive and developing. These are grouped into three categories: intercontinental ballistic missiles, hypersonic delivery systems and new advanced strategic weapon delivery capabilities. These and other technological advances being made simultaneously may also impact arms control and strategic stability. Other characteristics of hypersonic systems, however, are potentially advantageous compared with ballistic missiles. Of particular interest are the ability to fly at low altitude, making detection by earth-based sensors difficult; the ability to maneuver during flight to avoid detection and interception; and the unpredictability of targets, since hypersonic vehicles do not follow a ballistic trajectory.
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Chen, Chao Bo, Bing Liu, Ning He, Song Gao, and Quan Pan. "PID Control Based Missile Sub-Channel Simulation." Advanced Materials Research 433-440 (January 2012): 7011–16. http://dx.doi.org/10.4028/www.scientific.net/amr.433-440.7011.

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The accuracy and real-time of modern missile flight control system of traditional aerodynamic can not be satisfied. In this paper a new method is presented to improve the accuracy and real-time of missiles under this condition. First of all, a missile sub-channel model of the dynamic equations and steering gear is established, then based on the established model, using PID controller to control steering gear and three channels of missile pitch, yaw, roll respectively which is called missile sub-channel PID control method, and finally making use of MATLAB/Simulink to complete the simulation. Simulation results show that compared with traditional aerodynamic control system, this method can reduce the response time of aerodynamic missile and enhance the stability of the control system obviously.
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Sang, D.-K., and M.-J. Tahk. "Guidance law switching logic considering the seeker's field-of-view limits." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 223, no. 8 (2009): 1049–58. http://dx.doi.org/10.1243/09544100jaero614.

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The impact time control guidance (ITCG) method, which has been proposed recently, can be applied successfully to a salvo attack of multiple missiles. Compared to the proportional navigation guidance law, this guidance method makes additional manoeuvres to synchronize the impact times. However, such manoeuvres do not consider the manoeuvrability and the seeker's field-of-view (FOV) of a missile and may cause the target to move out of the missile seeker's FOV; maintaining the seeker lock-on condition during the engagement is critical for missile guidance. To solve this problem, two methods are presented in this article: one is based on the calculation of minimum and maximum flight times considering the missile's manoeuvring limit and the seeker's FOV limit to check the available impact time. The other is based on guidance law switching logic that keeps the target look angle of the seeker constant. These methods can provide the boundary limit of the impact time of the salvo attack and prevent the lock-on failure because of the seeker's FOV limit of the missile during the homing phase when the ITCG is used. This method was applied to the case of a time critical salvo-attack of multiple missiles, which have manoeuvring limit and the seeker's FOV limit, and desired results were obtained.
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Lee, Kyoung Haing, and Hyeong Pil Seo. "Analysis of the flight trajectory characteristics of North Korea SLBM due to launching mode." International Journal of Modeling, Simulation, and Scientific Computing 07, no. 04 (2016): 1643005. http://dx.doi.org/10.1142/s1793962316430054.

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The current research aims to simulate the flight trajectory of the North Korean submarine–launched ballistic missile (SLBM) and analyze its flight characteristics based on its range control method. Recently, North Korea has completed the test flight of SLBM and it has become a significant threat to international security. North Korea obtained SLBM technologies from Russia while disbanding decommissioned Russian submarines, and it is suspected that North Korea will continue to experiment in related fields along with its continued attempts to miniaturize nuclear weapons. If North Korea completes the development of SLBM and deploys the missiles, it means the completion of the three asymmetric warfare elements (nuclear weapon, ballistic missile, and submarine) and they will be the most significant threats to northeast Asia. Therefore, it is imperative to scientifically analyze SLBM to adeptly respond to such threat. One characteristic of SLBM is capability of attacking its target in a variety of ways based on its range control method. Based on this fact, the current research derives the flight equation of North Korean SLBM and simulates its flight trajectory based on various range control methods. The flight trajectories that we derive can be used to establish an effective anti-ballistic missile defense system in northeast Asia.
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Dissertations / Theses on the topic "Missiles - Flight Control"

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Tanil, Cagatay. "Optimal External Configuration Design Of Missiles." Master's thesis, METU, 2009. http://etd.lib.metu.edu.tr/upload/12610873/index.pdf.

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The main area of emphasis in this study is to investigate the methods and technology for aerodynamic configuration sizing of missiles and to develop a software platform in MATLAB&reg<br>environment as a design tool which has an ability of optimizing the external configuration of missiles for a set of flight requirements specified by the user through a graphical user interface. A genetic algorithm based optimization tool is prepared by MATLAB is expected to help the designer to find out the best external geometry candidates in the conceptual design stage. Missile DATCOM software package is employed to predict the aerodynamic coefficients needed in finding the performance merits of a missile for each external geometry candidate by integrating its dynamic equations of motion. Numerous external geometry candidates are rapidly eliminated according to objectives and constraints specified by designers, which provide necessary information in preliminary design. In this elimination, the external geometry candidates are graded according to their flight performances in order to discover an optimum solution. In the conceptual design, the most important performance objectives related to the external geometry of a missile are range, speed, maneuverability, and control effectiveness. These objectives are directly related to the equations of motion of the missile, concluding that the speed and flight range are related to the total mass and the drag-to-lift ratio acting on missile. Also, maneuverability depends on the normal force acting on missile body and mass whereas the control effectiveness is affected by pitching moment and mass moment of inertia of missile. All of the flight performance data are obtained by running a two degree-of-freedom simulation. In order to solve the resulting multi-objective optimization problem with a set of constraint of linear and nonlinear nature and in equality and inequality forms, genetic-algorithm-based methods are applied. Hybrid encoding methods in which the integer configuration variables (i.e., nose shape and control type) and real-valued geometrical dimension (i.e., diameter, length) parameters are encoded in the same individual chromosome. An external configuration design tool (EXCON) is developed as a synthesis and external sizing tool for the subsonic cruise missiles. A graphical user interface (GUI), a flight simulator and optimization modules are embedded into the tool. A numerical example, the re-configuration problem of an anti-ship cruise missile Harpoon, is presented to demonstrate the accuracy and feasibility of the conceptual design tool. The optimum external geometries found for different penalty weights of penalty terms in the cost function are compared according to their constraint violations and launch mass values. By means of using EXCON, the launch mass original baseline Harpoon is reduced by approximately 30% without deteriorating the other flight performance characteristics of the original Harpoon.
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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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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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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.<br>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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Lai, Haoyu. "On the design of nonlinear gain scheduled control systems." Ohio : Ohio University, 1998. http://www.ohiolink.edu/etd/view.cgi?ohiou1176486900.

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Jones, Campbell Llyr. "Neural control of a sea skimming missile." Thesis, University of Southampton, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.387900.

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Aydin, Gunes. "Aerodynamic Parameter Estimation Of A Missile In Closed Loop Control And Validation With Flight Data." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12615044/index.pdf.

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Aerodynamic parameter estimation from closed loop data has been developed as another research area since control and stability augmentation systems have been mandatory for aircrafts. This thesis focuses on aerodynamic parameter estimation of an air to ground missile from closed loop data using separate surface excitations. A design procedure is proposed for designing separate surface excitations. The effect of excitations signals to the system is also analyzed by examining autopilot disturbance rejection performance. Aerodynamic parameters are estimated using two different estimation techniques which are ordinary least squares and complex linear regression. The results are compared with each other and with the aerodynamic database. An application of the studied techniques to a real system is also given to validate that they are directly applicable to real life.
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Ng, Chuk Man. "On the digital re-design of an analogue missile flight control system using PIM method." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1999. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape4/PQDD_0030/MQ64239.pdf.

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Ng, Chuk Man 1974. "On the digital re-design of an analogue missile flight control system using PIM method." Thesis, McGill University, 1999. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=30263.

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This research examines some of the ways to design a digital control system with particular reference to the control of yaw plane dynamics of an air-to-air missile model. Specific attention is paid to compare two methods of global digital re-design of validated analogue closed loop control system. These two methods are the multi-input multi-output (MIMO) Plant Input Mapping (PIM) method and multi-loop PIM method. The thesis will first show how a specific class of closed loop MIMO feedback systems with a single-input multi-output (SIMO) plant can be re-structured as multi-loop control systems, which includes the closed loop missile control system. Some special characteristics pertaining to SIMO systems for control system design are explored. The aforementioned two methods of PIM global digital re-design are then applied to the MIMO analogue missile control system and its re-structured multi-loop counterpart. A comparison of the two methods is made on its design procedure, implementation structure and results from computer simulation.<br>This thesis also touches upon the topic of controller order reduction, particularly in consideration of the PIM digital re-design of analogue feedback systems. (Abstract shortened by UMI.)
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DeBoy, Christopher C., Paul D. Schwartz, and Richard K. Huebschman. "Midcourse Space Experiment Spacecraft and Ground Segment Telemetry Design and Implementation." International Foundation for Telemetering, 1996. http://hdl.handle.net/10150/608390.

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International Telemetering Conference Proceedings / October 28-31, 1996 / Town and Country Hotel and Convention Center, San Diego, California<br>This paper reviews the performance requirements that provided the baseline for development of the onboard data system, RF transmission system, and ground segment receiving system of the Midcourse Space Experiment (MSX) spacecraft. The onboard Command and Data Handling (C&DH) System was designed to support the high data outputs of the three imaging sensor systems onboard the spacecraft and the requirement for large volumes of data storage. Because of the high data rates, it was necessary to construct a dedicated X-band ground receiver system at The Johns Hopkins University Applied Physics Laboratory (APL) and implement a tape recorder system for recording and downlinking sensor and spacecraft data. The system uses two onboard tape recorders to provide redundancy and backup capabilities. The storage capability of each tape recorder is 54 gigabits. The MSX C&DH System can record data at 25 Mbps or 5 Mbps. To meet the redundancy requirements of the high-priority experiments, the data can also be recorded in parallel on both tape recorders. To provide longer onboard recording, the data can also be recorded serially on the two recorders. The reproduce (playback) mode is at 25 Mbps. A unique requirement of the C&DH System is to multiplex and commutate the different output rates of the sensors and housekeeping signals into a common data stream for recording. The system also supports 1-Mbps real-time sensor data and 16-kbps real-time housekeeping data transmission to the dedicated ground site and through the U.S. Air Force Satellite Control Network ground stations. The primary ground receiving site for the telemetry is the MSX Tracking System (MTS) at APL. A dedicated 10-m X-band antenna is used to track the satellite during overhead passes and acquire the 25-Mbps telemetry downlinks, along with the 1-Mbps and 16-kbps real-time transmissions. This paper discusses some of the key technology trade-offs that were made in the design of the system to meet requirements for reliability, performance, and development schedule. It also presents some of the lessons learned during development and the impact these lessons will have on development of future systems.
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Books on the topic "Missiles - Flight Control"

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Lin, Ching-Fang. Modern navigation, guidance, and control processing. Prentice Hall, 1991.

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Kadam, N. V. Practical design of flight control systems for launch vehicles and missiles. Allied Publishers, 2009.

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Lihua, Xue, ed. Xian dai dao dan zhi dao: Modern Missile Guidance. Guo fang gong ye chu ban she, 2013.

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Ben-Asher, Joseph Z. Optimal control theory with aerospace applications. American Institute of Aeronautics and Astronautics, 2010.

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Kailiwai, George. The electronic combat challenge of the 1990s: Flight testing fire control systems against low observables. Rand, 1990.

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Kailiwai, George. The electronic combat challenge of the 1990's: Flight testing fire control systems against low observables. Rand Corp., 1991.

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Optimal control theory with aerospace applications. American Institute of Aeronautics and Astronautics, 2010.

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Cloud, Dave. Designing cost-effective space missions: An integrated, systems engineering approach. Teaching Science and Technology, Inc., 1999.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Artificial neural network approaches in guidance and control. AGARD, 1991.

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United States. National Aeronautics and Space Administration., ed. STS-71 Shuttle/Mir mission report. National Aeronautics and Space Administration, 1995.

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Book chapters on the topic "Missiles - Flight Control"

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Wu, Sentang. "Member Flight Control System (MFCS)." In Cooperative Guidance & Control of Missiles Autonomous Formation. Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-0953-3_6.

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Wu, Sentang. "Flight Control System of MAF (FCSM)." In Cooperative Guidance & Control of Missiles Autonomous Formation. Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-0953-3_5.

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Xia, Yuanqing, and Mengyin Fu. "Cooperative Attack of Multiple Missiles Based on Optimal Guidance Law." In Compound Control Methodology for Flight Vehicles. Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-36841-7_12.

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Xia, Yuanqing, and Mengyin Fu. "Missile Guidance Law Based on ESO Techniques." In Compound Control Methodology for Flight Vehicles. Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-36841-7_10.

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Xia, Yuanqing, and Mengyin Fu. "Missile Guidance Laws Based on SMC and FTC Techniques." In Compound Control Methodology for Flight Vehicles. Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-36841-7_11.

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Xia, Yuanqing, and Mengyin Fu. "SMC for Missile Systems Based on Back-Stepping and ESO Techniques." In Compound Control Methodology for Flight Vehicles. Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-36841-7_5.

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Tekin, Raziye, Ozgur Atesoglu, and Kemal Leblebicioglu. "Flight Control Algorithms for a Vertical Launch Air Defense Missile." In Advances in Aerospace Guidance, Navigation and Control. Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-38253-6_6.

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Fumenti, Federico, and Stephan Theil. "Comparison of Multiple Spacecraft Configuration Designs for Coordinated Flight Missions." In Advances in Aerospace Guidance, Navigation and Control. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-65283-2_32.

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"Affordable Flight Control for Aircraft and Missiles." In Perspectives in Control Engineering Technologies, Applications, and New Directions. IEEE, 2009. http://dx.doi.org/10.1109/9780470545485.ch11.

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Barrett, Ronald. "Adaptive Fight Control Actuators and Mechanisms for Missiles, Munitions and Uninhabited Aerial Vehicles (UAVs)." In Advances in Flight Control Systems. InTech, 2011. http://dx.doi.org/10.5772/13796.

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Conference papers on the topic "Missiles - Flight Control"

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Seigler, T. Michael, Jae-Sung Bae, and Daniel J. Inman. "Flight Control of a Variable Span Cruise Missile." In ASME 2004 International Mechanical Engineering Congress and Exposition. ASMEDC, 2004. http://dx.doi.org/10.1115/imece2004-61961.

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In this work the benefits of variable span morphing are considered, specifically with regards to the increased maneuverability of bank-to-turn cruise missiles. Along with an increase in range associated with variable span aircraft-in the case where both wings are equally extended-there is also the possibility of an additional advantage of higher control authority over both pitch and roll motions. In the case of roll control, one wing is extended while the other is contracted thus producing a moment about the longitudinal axis of the missile. Compared to conventional tail surface control, this moment can be substantial depending on the flight conditions. There is, however, some complexity involved in flight control of variable span aircraft; namely the shift of the missile’s center of mass and the dependence of the roll producing moment on the angle of attack. The following work attempts to address these complexities through nonlinear control. First, a full nonlinear model of the missile is presented that includes aerodynamic effects and changes in weight distribution. Nonlinear methods are then used to control the trajectory of the missile via the roll angle, angle of attack, and sideslip angle. The results show that, in comparison with conventional missile configurations, the addition of variable span morphing has the capability of increasing overall flight performance.
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Mandic, Slobodan D., Milos Pavic, Bojan Pavkovic, and Milan Ignjatovic. "Efficiency of Aerodynamic Interceptors for Subsonic Missiles Roll Attitude Control." In 2018 Atmospheric Flight Mechanics Conference. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-3159.

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Theodoulis, Spilios, and Michael Proff. "Robust Flight Control Tuning for Highly Agile Missiles." In AIAA Scitech 2021 Forum. American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-1568.

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Mandic, Slobodan D., Milos Pavic, Bojan Pavkovic, and Milan Ignjatovic. "Withdrawal: Efficiency of Aerodynamic Interceptors for Subsonic Missiles Roll Attitude Control." In 2018 Atmospheric Flight Mechanics Conference. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-3159.c1.

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Morote, Jesus. "Control of Roll Lock-In and Catastrophic Yaw for Cruciform Finned Missiles." In AIAA Atmospheric Flight Mechanics Conference. American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-5717.

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Pepitone, Thomas, Ernest Ohlmeyer, and David Hanger. "In-flight alignment techniques for Navy theater wide missiles." In AIAA Guidance, Navigation, and Control Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-4401.

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Feng, Gang, Zhiyong Yang, and Yongjin Liu. "EKF-based fault detection for guided missiles flight control system." In 11TH ASIAN CONFERENCE ON CHEMICAL SENSORS: (ACCS2015). Author(s), 2017. http://dx.doi.org/10.1063/1.4977327.

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Lin, I.-Fan, Chin-I. Huang, and Li-Chen Fu. "Flight Controller Design for Intercepting Missiles with Multiple TVC Systems and DCS." In 2007 American Control Conference. IEEE, 2007. http://dx.doi.org/10.1109/acc.2007.4282536.

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Lesieutre, Daniel, John Love, and Marnix Dillenius. "Prediction of the Nonlinear Aerodynamic Characteristics of Tandem-Control and Rolling-Tail Missiles." In AIAA Atmospheric Flight Mechanics Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-4511.

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Yuchun, Zhang, and Zhang Yongqiang. "The Research on Optimal Control Method of Missiles' Flight Based on Variable Calculus." In 2010 3rd International Conference on Intelligent Networks and Intelligent Systems (ICINIS). IEEE, 2010. http://dx.doi.org/10.1109/icinis.2010.128.

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Reports on the topic "Missiles - Flight Control"

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Noone, Emily, and Lydia Harriss. Hypersonic missiles. Parliamentary Office of Science and Technology, 2023. http://dx.doi.org/10.58248/pn696.

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Abstract:
This POSTnote looks at hypersonic missile technologies, efforts to develop them, potential applications, and the possible challenges they may present for missile defence and global stability. Key Points: • Hypersonic missiles combine speeds of over five times the speed of sound with significant manoeuvrability during flight. • Their manoeuvrability enables them to change trajectory during flight, making their flight-path and target difficult to predict. • They fly at lower altitudes than ballistic missiles, which means that they may be harder to track at long distances with some surface-based sensors, such as certain radar. • There are two main types of hypersonic missile: hypersonic glide vehicles (HGVs) and hypersonic cruise missiles (HCMs). • HGVs are mounted onto rocket boosters for launch and may be accelerated to speeds of Mach 20 or more. The glider then separates from the booster and flies unpowered in the Earth’s upper atmosphere at altitudes of 30-80 km, before diving towards the target. • HCMs typically have a ramjet or scramjet engine that enables them to reach hypersonic speeds at altitudes of 20-40 km. • China and Russia have reportedly deployed hypersonic missiles that could deliver conventional or nuclear weapons. The US is testing multiple hypersonic technologies. • The AUKUS agreement between the UK, US and Australia includes developing hyper-sonic and counter-hypersonic technologies. • Developing hypersonic missiles requires significant research and development challenges to be overcome, contributing to their high development and manufacturing costs. • The speed, manoeuvrability and altitude of hypersonic missiles may challenge existing missile defences, although their uses and effectiveness are still being assessed. • Defence analysts disagree about the potential implications of hypersonic missiles for global peace and stability. Some suggest they could increase the risk of conflict escalation, while others say that they will not alter the strategic balance between nuclear powers. • Arms control, export controls and other measures may help limit potential harm to peace and stability, but these approaches face challenges.
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Giurgiutiu, Victor, and Radu Pomirleanu. Smart-Material Actuated Missile Flight Control Surfaces Feasibility Study. Defense Technical Information Center, 2000. http://dx.doi.org/10.21236/ada384331.

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