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Relevant bibliographies by topics / Missile flight control; Autopilot

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Academic literature on the topic 'Missile flight control; Autopilot'

Author: Grafiati

Published: 4 June 2021

Last updated: 16 February 2022

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Journal articles on the topic "Missile flight control; Autopilot"

1

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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Wang, Jiang, De Fu Lin, and Jun Fang Fan. "Control Limitations on Static Unstable Airframe Using Two-Loop Acceleration Autopilot." Advanced Materials Research 383-390 (November 2011): 4385–90. http://dx.doi.org/10.4028/www.scientific.net/amr.383-390.4385.

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An analysis for controlling a static-unstable tactical missile using two-loop acceleration autopilot was detailed. The rate feedback loop was firstly presented. The equivalent actuator dynamics was introduced and examined. Thus an overall stabilization condition combined with both low and high frequency cases was proposed. The lever effect led by inertial measurement unit was of benefit to a great controllable range. The results show that the autopilot control capacity is dominated by actuator bandwidth, and a compromise should be determined between the flight performance and the actuator requirement for a static unstable tactical missile.

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3

Wang, Jin, and Min Zhang. "Backstepping-Based Adaptive Fuzzy Sliding Mode Control for Autopilot Design." Applied Mechanics and Materials 365-366 (August 2013): 853–58. http://dx.doi.org/10.4028/www.scientific.net/amm.365-366.853.

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A backstepping approach, combined with adaptive fuzzy sliding mode control, is used to design a missile autopilot in this paper. The proposed scheme separated the plant into two subsystems, such that single controllers can be designed and therefore the stability of entire system is reached automatically. The single control laws are designed using sliding mode control based on the Lyapunov stability theorem, and the adaptive law is derived to adapt the value of the lumped uncertainty in real-time. Moreover, with the universal approximation ability, an adaptive fuzzy system is used to approximate strong coupling nonlinear dynamics of the missile during large angle-of-attack flight and provide robustness to parametric uncertainties in the missile aerodynamics.

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Bruyere, L., A. Tsourdos, and B. A. White. "Robust augmented lateral acceleration flight control design for a quasi-linear parameter-varying missile." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 219, no. 2 (2005): 171–81. http://dx.doi.org/10.1243/095441005x9076.

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An augmented lateral acceleration autopilot is designed for a model of a tactical missile and robust stability of the closed-loop system investigated. The tail-controlled missile in the cruciform fin configuration is modelled as a second-order quasi-linear parameter-varying system. This non-linear model is obtained from the Taylor linearized model of the horizontal motion by including explicit dependence of the aerodynamic derivatives on a state (side-slip velocity) and external parameters (longitudinal velocity and roll angle). The autopilot design is based on input-output pseudolinearization, which is a restriction of input-output feedback linearization to the set of equilibria of the non-linear model. The design makes Taylor linearization of the closed-loop system independent of the choice of equilibria. Thus, if the operating points are in the vicinity of the equilibria, then only one linear model will describe closed-loop dynamics, regardless of the rate of change in the operating points. Simulations for constant lateral acceleration demands show good tracking with fast response time. Robust autopilot design taking into account parametric stability margins for uncertainty aerodynamic derivatives is implemented using convex optimization and linear matrix inequalities.

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Wicks, Frank. "A Model Mission." Mechanical Engineering 126, no. 12 (2004): 44–46. http://dx.doi.org/10.1115/1.2004-dec-5.

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This article illustrates details of Maynard Hill, an experimenter, who sent a man in the air on a 600-pound flying machine. He continued to build models throughout high school, during his World War II Navy aviation service, and during his years at Penn State, where he received degrees in metallurgy in 1950 and 1951. Vacuum tube radio made flight control complicated. Hill said he struggled for two years before he achieved a marginally successful flight with a descending glider by means of stepping the rudder position. Hill's plan was to begin the flight under manual radio control, transfer to autopilot for the ocean portion, and then back to radio control for landing by another team waiting in Ireland. The autopilot weighed only a few ounces. It was developed by team member Joe Foster. A challenge was performing a smooth transition from manual to autonomous control and then back to manual for landing. The first attempted flight started successfully on radio control, but failed to stabilize when Joe Foster sent the radio signal to transfer control to autonomous flight. They suspected that the airplane was too far out of trim for the transition. He expertly transferred the airplane to his radio control, cut the engine, and guided it to a dead-stick landing near the monument that marks the 1919 landing spot of John Alcock and Arthur Brown.

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LI, HAO, ZHONG-LIANG ZHAO, and ZHAO-LIN FAN. "SIMULATION METHOD FOR WIND TUNNEL BASED VIRTUAL FLIGHT TESTING." International Journal of Modern Physics: Conference Series 19 (January 2012): 381–89. http://dx.doi.org/10.1142/s2010194512008975.

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The Wind Tunnel Based Virtual Flight Testing (WTBVFT) could replicate the actual free flight and explore the aerodynamics/flight dynamics nonlinear coupling mechanism during the maneuver in the wind tunnel. The basic WTBVFT concept is to mount the test model on a specialized support system which allows for the model freely rotational motion, and the aerodynamic loading and motion parameters are measured simultaneously during the model motion. The simulations of the 3-DOF pitching motion of a typical missile in the vertical plane are performed with the openloop and closed-loop control methods. The objective is to analyze the effect of the main differences between the WTBVFT and the actual free flight, and study the simulation method for the WTBVFT. Preliminary simulation analyses have been conducted with positive results. These results indicate that the WTBVFT that uses closed-loop autopilot control method with the pitch angular rate feedback signal is able to replicate the actual free flight behavior within acceptable differences.

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Kopyt, Antoni, Sebastian Topczewski, Marcin Zugaj, and Przemyslaw Bibik. "An automatic system for a helicopter autopilot performance evaluation." Aircraft Engineering and Aerospace Technology 91, no. 6 (2019): 880–85. http://dx.doi.org/10.1108/aeat-07-2018-0190.

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Purpose The purpose of this paper is to elaborate and develop an automatic system for automatic flight control system (AFCS) performance evaluation. Consequently, the developed AFCS algorithm is implemented and tested in a virtual environment on one of the mission task elements (MTEs) described in Aeronautical Design Standard 33 (ADS-33) performance specification. Design/methodology/approach Control algorithm is based on the Linear Quadratic Regulator (LQR) which is adopted to work as a controller in this case. Developed controller allows for automatic flight of the helicopter via desired three-dimensional trajectory by calculating iteratively deviations between desired and actual helicopter position and multiplying it by gains obtained from the LQR methodology. For the AFCS algorithm validation, the objective data analysis is done based on specified task accomplishment requirements, reference trajectory and actual flight parameters. Findings In the paper, a description of an automatic flight control algorithm for small helicopter and its evaluation methodology is presented. Necessary information about helicopter dynamic model is included. The test and algorithm analysis are performed on a slalom maneuver, on which the handling qualities are calculated. Practical implications Developed automatic flight control algorithm can be adapted and used in autopilot for a small helicopter. Methodology of evaluation of an AFCS performance can be used in different applications and cases. Originality/value In the paper, an automatic flight control algorithm for small helicopter and solution for the validation of developed AFCS algorithms are presented.

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Buschek, Harald. "Design and flight test of a robust autopilot for the IRIS-T air-to-air missile." Control Engineering Practice 11, no. 5 (2003): 551–58. http://dx.doi.org/10.1016/s0967-0661(02)00063-1.

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Słowik, Maciej, Daniel Ołdziej, and Zdzisław Gosiewski. "Integration and In-Field Gains Selection of Flight and Navigation Controller for Remotely Piloted Aircraft System." Acta Mechanica et Automatica 11, no. 1 (2017): 33–37. http://dx.doi.org/10.1515/ama-2017-0005.

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Abstract In the paper the implementation process of commercial flight and navigational controller in own aircraft is shown. The process of autopilot integration were performed for the fixed-wing type of unmanned aerial vehicle designed in high-wing and pull configuration of the drive. The above equipment were integrated and proper software control algorithms were chosen. The correctness of chosen hardware and software solution were verified in ground tests and experimental flights. The PID controllers for longitude and latitude controller channels were selected. The proper deflections of control surfaces and stabilization of roll, pitch and yaw angles were tested. In the next stage operation of telecommunication link and flight stabilization were verified. In the last part of investigations the preliminary control gains and configuration parameters for roll angle control loop were chosen. This enable better behavior of UAV during turns. Also it affected other modes of flight such as loiter (circle around designated point) and auto mode where the plane executed a pre-programmed mission.

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Irmawan, Erwhin, and Erwan Eko Prasetiyo. "Kendali Adaptif Neuro Fuzzy PID untuk Kestabilan Terbang Fixed Wing UAV (Adaptive Control of Neuro Fuzzy PID for Fixed Wing UAV Flight Stability)." Jurnal Nasional Teknik Elektro dan Teknologi Informasi 9, no. 1 (2020): 73–78. http://dx.doi.org/10.22146/jnteti.v9i1.142.

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Unmanned Aerial Vehicle (UAV), especially fixed wing, are widely used to carry out various missions, namely civil and military missions. To support the implementation of this mission, it is necessary to develop an intelligent automatic control system (autopilot). In this paper, an autopilot system with adaptive neuro fuzzy PID control is developed to control lateral (pitch) and longitudinal (roll) motion, by taking advantage of PID, fuzzy, and neural network control. Therefore, robust controls which can handle non-linear conditions can be formed. This paper aims to determine the performance of adaptive control of neuro fuzzy PID controllers for longitudinal and lateral motion on UAV. The result shows that adaptive control of neuro fuzzy PID are able to control the lateral and longitudinal motion of the aircraft and able to compensate for interferences from environmental disturbances in flying condition, such as changes in direction and wind speed that causes changes in aircraft attitude. The control characteristics of neuro fuzzy PID adaptive control in lateral and longitudinal motion are relatively similar. Adaptive control of neuro fuzzy PID has better performance than fuzzy PID control, i.e., faster settling time and lower percentage of maximum overshoot.

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Dissertations / Theses on the topic "Missile flight control; Autopilot"

1

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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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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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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Doruk, Resat Ozgur. "Missile Autopilot Design By Projective Control Theory." Master's thesis, METU, 2003. http://etd.lib.metu.edu.tr/upload/4/1089929/index.pdf.

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In this thesis, autopilots are developed for missiles with moderate dynamics and stationary targets. The aim is to use the designs in real applications. Since the real missile model is nonlinear, a linearization process is required to get use of systematic linear controller design techniques. In the scope of this thesis, the linear quadratic full state feedback approach is applied for developing missile autopilots. However, the limitations of measurement systems on the missiles restrict the availability of all the states required for feedback. Because of this fact, the linear quadratic design will be approximated by the use of projective control theory. This method enables the designer to use preferably static feedback or if necessary a controller plus a low order compensator combination to approximate the full state feedback reference. Autopilots are checked for the validity of linearization, robust stability against aerodynamic, mechanical and measurement uncertainties.

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Bibel, John Eugene. "Missile autopilot design using Mu-Synthesis." Thesis, This resource online, 1998. http://scholar.lib.vt.edu/theses/available/etd-08252008-161841/.

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Counsell, John Mark. "Optimum and safe control algorithim (OSCA) for modern missile autopilot design." Thesis, Lancaster University, 1992. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.332382.

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White, David Paul. "Missile autopilot design using a gain scheduling technique." Ohio : Ohio University, 1994. http://www.ohiolink.edu/etd/view.cgi?ohiou1179860306.

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Ozkan, Bulent. "Dynamic Modeling, Guidance, And Control Of Homing Missiles." Phd thesis, METU, 2005. http://etd.lib.metu.edu.tr/upload/12606533/index.pdf.

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DYNAMIC MODELING, GUIDANCE, AND CONTROL OF HOMING MISSILES &Ouml<br>ZKAN, B&uuml<br>lent Ph. D., Department of Mechanical Engineering Supervisor: Prof. Dr. M. Kemal &Ouml<br>ZG&Ouml<br>REN Co-Supervisor: Dr. G&ouml<br>kmen MAHMUTYAZICIOgLU September 2005, 236 pages In this study, the dynamic modeling, guidance, and control of a missile with two relatively rotating parts are dealt with. The two parts of the missile are connected to each other by means of a roller bearing. In the first part of the study, the governing differential equations of motion of the mentioned missile are derived. Then, regarding the relative rotation between the bodies, the aerodynamic model of the missile is constructed by means of the Missile Datcom software available in T&Uuml<br>BiTAK-SAGE. After obtaining the required aerodynamic stability derivatives using the generated aerodynamic data, the necessary transfer functions are determined based on the equations of motion of the missile. Next, the guidance laws that are considered in this study are formulated. Here, the Linear Homing Guidance and the Parabolic Homing Guidance laws are introduced as alternatives to the Proportional Navigation Guidance law. On this occasion, the spatial derivation of the Proportional Navigation Guidance law is also done. Afterwards, the roll, pitch and yaw autopilots are designed using the determined transfer functions. As the roll autopilot is constructed to regulate the roll angle of the front body of the missile which is the controlled part, the pitch and yaw autopilots are designed to realize the command signals generated by the guidance laws. The guidance commands are in the form of either the lateral acceleration components or the flight path angles of the missile. Then, the target kinematics is modeled for a typical surface target. As a complementary part of the work, the design of a target state estimator is made as a first order fading memory filter. Finally, the entire guidance and control system is built by integrating all the models mentioned above. Using the entire system model, the computer simulations are carried out using the Matlab-Simulink software and the proposed guidance laws are compared with the Proportional Navigation Guidance law. The comparison is repeated for a selected single-body missile as well. Consequently, the simulation results are discussed and the study is evaluated.

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Sefastsson, Ulf. "Evaluation of Missile Guidance and Autopilot through a 6 DOF Simulation Model." Thesis, KTH, Optimeringslära och systemteori, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-188897.

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Missile guidance and autopilot have been active fields of research since the second world war. There are lots of literature on the subjects, but the bulk of which are confined to overly simplified models, and therefore the publications of the methods applied to more realistic models are scarce. In this report a nonlinear 6 DOF simulation model of a tail-controlled air-to-air missile is considered. Through several assumptions and simplifications a linearized approximation of the plant is obtained, which then is used in the implementation of 5 guidance laws and 2 autopilots. The guidance laws are all based on a linearized collision geometry, and the autopilots are based on model predictive control (MPC). Both autopilots use linear quadratic MPC (LQMPC), and one is more robust to modelling errors than the conventional LQMPC. The guidance laws and autopilots are then evaluated with respect to performance in terms of miss distance in 4 interception scenarios with a moving target. The results show that the in this model the autopilots perform equally well, and that the guidance laws with more information about the target generally exhibit smaller miss distances, but at the cost of a considerably larger flight time for some scenarios. The conclusions are that the simplifying assumptions in the modelling are legitimate and that the challenges of missile control probably does not lie in the guidance or autopilot, but rather in the target tracking. Therefore it is suggested that future work include measurement noise and process disturbances in the model.<br>Det har forskats kring styrlagarna och styrautomaterna för robotar sedan an-dra världskrigets. Det finns mycket litteratur på områdena, men merparten av de publicerade resultaten behandlar enbart grovt förenklade modeller, och därför är tillgången på publikationer där metoderna applicerats i en mer realistisk modell begränsat. I denna rapport behandlas en olinjär simuleringsmodell av en jaktrobot som styrs med stjärtfenor och har sex frihetsgrader. Genom en rad antaganden och förenklingar erhålls en linjäriserad modell av missilen, vilket sedan används för implementering av fem styrlagar och två styrautomater. Styr-lagarna är alla baserade på en linjäriserad kollisionsgeometri och styrautomaterna är baserade på modellprediktiv styrning (MPC). Båda styrautomaterna använder linjärkvadratisk MPC, där den ena påstås vara mer robust gentemot modellfel. Styrlagarna och -automaterna utvärderas ur ett prestandaperspektiv med fokus på bomavstånd i fyra realistiska genskjutningsscenarier med ett rörligt mål. Resultaten visar att båda styrautomaterna presterar lika bra, och att de styrlagar med mer information om målets position/hastighet/acceleration generellt presterar bättre, men att de för vissa skjutfall får en väsentligt längre flygtid. Slutsatserna är att förenklingarna och antagandena i linjäriseringen är välgrundade, och att utmaningarna i missilstyrning inte ligger i utformning av styrlag/-automat, utan förmodligen i målsökningen. Därför föreslås det slutligen att framtida arbete bl. a. inkluderar mätbrus och störningar.

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Sharma, Manu. "A neuro-adaptive autopilot design for guided munitions." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12470.

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Books on the topic "Missile flight control; Autopilot"

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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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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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Office, General Accounting. [Impoundment control--deferrals of budget authority in GSA]. The Office, 1993.

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Office, General Accounting. [ Impoundment control--President's fifth special message for FY 1995]. The Office, 1995.

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Office, General Accounting. [Impoundment control--President's second special message for FY 1994]. The Office, 1994.

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Office, General Accounting. [Impoundment control--President's fourth special message for FY 1992]. The Office, 1992.

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Office, General Accounting. [Impoundment control--President's sixth special message for FY 1991]. The Office, 1991.

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Office, General Accounting. [Impoundment control--President's second special message for FY 1994]. The Office, 1994.

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Office, General Accounting. [Impoundment control--President's fifth special message for FY 1991]. The Office, 1991.

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Office, General Accounting. [Impoundment control--President's sixth special message for FY 1991]. The Office, 1991.

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Book chapters on the topic "Missile flight control; Autopilot"

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Duda, Holger, Gerhard Bouwer, J. Michael Bauschat, and Klaus-Uwe Hahn. "Autopilot design based on the Model Following Control approach." In Robust Flight Control. Springer Berlin Heidelberg, 1997. http://dx.doi.org/10.1007/bfb0113868.

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Looye, Gertjan. "Helical Flight Path Trajectories for Autopilot Evaluation." In Advances in Aerospace Guidance, Navigation and Control. Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-19817-5_7.

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Petersen, Ian R., Valery A. Ugrinovskii, and Andrey V. Savkin. "Missile autopilot design via minimax optimal control of stochastic uncertain systems." In Communications and Control Engineering. Springer London, 2000. http://dx.doi.org/10.1007/978-1-4471-0447-6_10.

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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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Liu, Gang, Wen-da Zheng, Jie Yang, Hong-qing Hou, and Ming-hao Wang. "Adaptive Fuzzy Wavelet Neural Networks Control for Nonlinear MIMO Missile Autopilot." In Lecture Notes in Electrical Engineering. Springer London, 2012. http://dx.doi.org/10.1007/978-1-4471-2386-6_39.

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Krings, Matthias, Karsten Henning, and Frank Thielecke. "Flight Test Oriented Autopilot Design for Improved Aerodynamic Parameter Identification." In Advances in Aerospace Guidance, Navigation and Control. Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-38253-6_17.

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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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Misgeld, Berno J. E., Marco Darcis, and Thomas Kuhn. "Robust Linear-Parameter Varying Autopilot Design for a Tail/Thrust Vector Controlled Missile." In Advances in Aerospace Guidance, Navigation and Control. Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-19817-5_23.

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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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Conference papers on the topic "Missile flight control; Autopilot"

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Buschek, Harald, and Raimund Dold. "Flight test of a scheduled mu-synthesis autopilot for an air-to-air missile." In AIAA Guidance, Navigation, and Control Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-4215.

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Bhowmick, Parijat, Atanu Panda, Arijit Ganguly, Sanjay Bhadra, Soham Kanti Bishnu, and Malay Ganguly. "An optimal type-1 servo control mechanism for flight-path-rate-demand lateral missile autopilot." In 2021 IEEE International IOT, Electronics and Mechatronics Conference (IEMTRONICS). IEEE, 2021. http://dx.doi.org/10.1109/iemtronics52119.2021.9422590.

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Mahmood, Muhammad M., Md S. Chowdhury, Rizwan Ihsan, Umar M. Yousaf, Mohamed W. Afifi, and Imtiaz M. Chuwdhury. "UAV Autopilot Design for the AUVSI, UAS International Competition." In ASME 2009 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2009. http://dx.doi.org/10.1115/detc2009-86412.

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This paper provides an overview of the first participation of the design developed by the undergraduate students of American University of Sharjah to meet the requirements laid forth in the 2008 Association for Unmanned Vehicle Systems International (AUVSI) Student UAS competition. The overall objective of the competition is to fly autonomously over a GPS waypoint defined route and also to identify and locate ground based targets within a confined area. To meet the objectives an unmanned aircraft is equipped with autonomous functionality and aerial imaging system. A ground station and supportive software to keep track of the aircraft routine and log the raw data gained from the flight is also designed. Achieving complete success depends upon mission elements which include autonomous take-off and landing, autonomous control and waypoint navigation. The onboard equipment used was a flight control computer network, IMU, GPS, an air data system and a camera. Additionally, safety features such as manual override was also installed. Presented in this report are aircraft design and testing, the processes involved in accomplishing the goal, and the results and achievements.

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Brugarolas, P. B., V. Fromion, and M. G. Safonov. "Robust switching missile autopilot." In Proceedings of the 1998 American Control Conference (ACC). IEEE, 1998. http://dx.doi.org/10.1109/acc.1998.703297.

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Lv, DING, QIAN Long-jun, SUN Rui-sheng, and YU Ting. "Autopilot Design for Elastic Missile Systems." In 2019 Chinese Control Conference (CCC). IEEE, 2019. http://dx.doi.org/10.23919/chicc.2019.8865914.

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Tsourdos, A. "Autopilot design of a non-linear missile." In UKACC International Conference on Control (CONTROL '98). IEE, 1998. http://dx.doi.org/10.1049/cp:19980346.

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Xiaoxi, Cui, Lou Yingming, Wu Tao, Zhang Dongxiang, Wang Linping, and Zhang Nan. "Command optimization for missile roll autopilot." In 2013 25th Chinese Control and Decision Conference (CCDC). IEEE, 2013. http://dx.doi.org/10.1109/ccdc.2013.6561555.

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ARNOLD, III, W., N. GATES, and ARLYNN WILSON. "Multivariable stability margins for missile autopilot coupling." In Navigation and Control Conference. American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-2615.

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Buschek, Harald, and Harald Buschek. "Robust autopilot design for future missile systems." In Guidance, Navigation, and Control Conference. American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3763.

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Theodoulis, Spilios, and Gilles Duc. "Gain-scheduling techniques for missile autopilot synthesis." In European Control Conference 2007 (ECC). IEEE, 2007. http://dx.doi.org/10.23919/ecc.2007.7068374.

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Reports on the topic "Missile flight control; Autopilot"

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Bullock, T. E., and S. L. Fields. Application of Robust Control and Gain Scheduling to Missile Autopilot Design. Defense Technical Information Center, 1998. http://dx.doi.org/10.21236/ada357847.

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2

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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3

Napolitano, Marcello R. YF22 Model With On-Board On-Line Learning Microprocessors-Based Neural Algorithms for Autopilot and Fault-Tolerant Flight Control Systems. Defense Technical Information Center, 2002. http://dx.doi.org/10.21236/ada400639.

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