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

Author: Grafiati

Published: 4 June 2021

Last updated: 16 February 2022

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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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2

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 requ

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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 approximat

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4

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

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5

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 a

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6

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.

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7

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 thre

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8

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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9

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 contr

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10

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

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11

Stevenson, Jonathan D., Siu O'Young, and Luc Rolland. "Assessment of alternative manual control methods for small unmanned aerial vehicles." Journal of Unmanned Vehicle Systems 3, no. 3 (2015): 73–94. http://dx.doi.org/10.1139/juvs-2015-0007.

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This paper is a summary of experiments to assess alternative methods to control a small (<25 kg; under Transport Canada rules, small UAV are classified as under 25 kg; Transport Canada. 2014. TP15263 – Knowledge requirements for pilots of unmanned air vehicle systems (UAV) 25 kg or less, operating within visual line of sight. Transport Canada. August. Available from http://www.tc.gc.ca/eng/civilaviation/publications/page-6557.html [accessed 17 August 2015]) unmanned aerial vehicle (UAV) in manual mode. While it is true that the majority of a typical UAV mission will be in automatic mode (i.

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12

Kehoe, J. J., R. S. Causey, M. Abdulrahim, and R. Lind. "Waypoint navigation for a micro air vehicle using vision-based attitude estimation." Aeronautical Journal 110, no. 1114 (2006): 821–29. http://dx.doi.org/10.1017/s000192400000169x.

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Missions envisioned for micro air vehicles may require a high degree of autonomy to operate in unknown environments. As such, vision is a critical technology for mission capability. This paper discusses an autopilot that uses vision coupled with GPS and altitude sensors for waypoint navigation. The vision processing analyses a horizon to estimate roll and pitch information. The GPS and altitude sensors then command values to roll and pitch for navigation between waypoints. A flight test of a MAV using this autopilot demonstrates the resulting closed-loop system is able to autonomously reach se

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13

Liu, Ri, Xiuxia Sun, Wenhan Dong, Dong Wang, and Yungang Chang. "Dynamics Modeling andL1Adaptive Control of a Transport Aircraft for Heavyweight Airdrop." Mathematical Problems in Engineering 2015 (2015): 1–15. http://dx.doi.org/10.1155/2015/365130.

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The longitudinal nonlinear aircraft model with cargo extraction is derived using theoretical mechanics and flight mechanics. Furthermore, the nonlinear model is approximated by a semilinear time-varying system with the cargo disturbances viewed as unknown nonlinearities, both matched and unmatched types. On this basis, a novel autopilot inner-loop based on the LQR andL1adaptive theory is developed to reject the unknown nonlinear disturbances caused by the cargo and also to accommodate uncertainties. Analysis shows that the controller can guarantee robustness in the presence of fast adaptation,

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14

Mykhatskyi, Oleksii. "INFORMATIVE SAFETY OF UNMANNED AVIATION SYSTEMS RADIO COMMUNICATION CHANNELS." Cybersecurity: Education, Science, Technique, no. 1 (2018): 56–62. http://dx.doi.org/10.28925/2663-4023.2018.1.5662.

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An analysis of navigation and command-telemetric radio channels is used for exploitation of unmanned aviation systems are proceeds. The classification of radio channels vulnerability is tied to the modes of unmanned aerial vehicles control and their safe exploitation key terms. The criteria of flight mission feasibility and applicability of the different control modes are set in the conditions of violation at the radio channels data communication. The signs of successful flight task processing are the aircraft returning and landing to the set point, absence of distortions or rejections of pres

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15

Zardashti, R., and M. Bagherian. "A new model for optimal TF/TA flight path design problem." Aeronautical Journal 113, no. 1143 (2009): 301–8. http://dx.doi.org/10.1017/s0001924000002979.

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Abstract This paper focuses on the three dimensional flight path planning for a UAV on a low altitude terrain following/terrain avoidance mission. Using an approximate grid-based discretisation scheme, we transform the continuous optimisation problem into a search problem over a finite network, and apply a variant of the shortest-path algorithm to this problem. In other words using the three dimensional terrain information, three dimensional flight path from a starting point to an end point, minimising a cost function and regarding the kinematics constraints of the UAV is calculated. A network

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16

Kauhanen, H., P. Rönnholm, M. Vaaja, and H. Hyyppä. "DESIGNING AND BUILDING A COST-EFFICIENT SURVEY DRONE." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLIII-B1-2020 (August 6, 2020): 165–72. http://dx.doi.org/10.5194/isprs-archives-xliii-b1-2020-165-2020.

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Abstract. In this paper, we present a workflow how to design and implement a low-cost survey drone that meets the quality requirements of a much higher cost drone system. The technical specifications of available components and our design boundaries were applied in eCalc RC – xcopterCalc calculator in which the optimal setup was found by simulation. The main boundaries of design were derived from safety, operation time and payload capacity. Pixhawk 2 FCU, which is based on ArduPilot open source platform, was selected to handle autopilot and control functionalities. In addition, the system incl

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17

Yousefimanesh, Amir, Alireza Khosravi, and Pouria Sarhadi. "Composite adaptive posicast controller for the wing rock phenomenon in a delta-wing aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 15 (2019): 5579–91. http://dx.doi.org/10.1177/0954410019856836.

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The nonlinear dynamic phenomenon like wing rock is one of the important issues in the high performance aircraft autopilot design. This phenomenon occurs in the form of constant amplitude oscillations in the roll dynamics, during the flight at high angles of attack (AOAs) and endangers carrying out the mission of an aircraft. In this paper, a composite adaptive posicast controller is designed for the wing rock phenomenon in a delta-wing aircraft with known input delay. The existence of the input delay besides the parametric uncertainties of the system dynamics adds to the complexity of the prob

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18

Kopecki, Grzegorz, Andrzej Tomczyk, and Paweł Rzucidło. "Algorithms of Measurement System for a Micro UAV." Solid State Phenomena 198 (March 2013): 165–70. http://dx.doi.org/10.4028/www.scientific.net/ssp.198.165.

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The article presents a measurement system for a micro UAV designed at the Department of Avionics and Control Systems of Rzeszów University of Technology. Since the project is based on earlier projects, e.g.[[[[1[[[1, the introduction begins with their short presentation [they are mentioned in the introduction firs. Then, the current project is discussed. The major objective of the project is to create a miniature autopilot cooperating with navigation units, data transmission units and measurement units. The system is based on Polish technological solutions. The autopilot is designed as a singl

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19

Ada, Celâl, and Ayhan Kural. "Three-axes predictive control of autopilot for missile." Aircraft Engineering and Aerospace Technology 89, no. 1 (2017): 1–10. http://dx.doi.org/10.1108/aeat-06-2014-0090.

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Purpose The purpose of this paper is to present the autopilot design for the missile under various disturbances. Design/methodology/approach In this study, model predictive control (MPC) method has been used for autopilot design for each axis. The aim of autopilot is that to keep the roll angle value around the zero degree and to track pitch/yaw acceleration commands. This three-axes control methodology also takes into consideration the interaction between pitch, yaw and roll motions. Findings The purpose of using MPC method for three-axes of the autopilot is to decrease the control effort and

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20

Tang, Wei-Qiang, and Yuan-Li Cai. "Predictive Functional Control-Based Missile Autopilot Design." Journal of Guidance, Control, and Dynamics 35, no. 5 (2012): 1450–55. http://dx.doi.org/10.2514/1.56329.

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21

Abo-Elela, Magdy, Ayman El-Shabrawy, and Ibrahim Hassan. "On-line Control Technique for Missile Autopilot." International Conference on Electrical Engineering 7, no. 7 (2010): 1–8. http://dx.doi.org/10.21608/iceeng.2010.32994.

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22

Pang, Mei Sa, Deng Hua Li, Jun Fang Fan, and Xue Fei Li. "Double Loop Autopilot Design Based on Frequency Domain." Advanced Materials Research 301-303 (July 2011): 1724–29. http://dx.doi.org/10.4028/www.scientific.net/amr.301-303.1724.

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The static stability of missile pitching movement is one of the important performances in guidance and control systems. In this paper, a method which consists of the single and double loop longitudinal autopilot using frequency domain approach is proposed to solve the problem efficiently. Single-loop autopilot is used to simplify the system design when the missile is highly static stable; the double-loop autopilot is employed to stabilize the system and improve frequency performance when the missile is static stable or static unstable. Control gain of the system is determined by aerodynamic pa

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23

Kamel, Mohamed M., Karim M. Ali, Mohammed A. H. Abozied, and Yehia Z. Elhalwagy. "Simulation and modelling of flight missile dynamics and autopilot analysis." IOP Conference Series: Materials Science and Engineering 610 (October 11, 2019): 012033. http://dx.doi.org/10.1088/1757-899x/610/1/012033.

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24

Bai, Chengchao, Fei Lu, and Xibao Xu. "Hybrid BTT/STT missile autopilot design." Aircraft Engineering and Aerospace Technology 89, no. 6 (2017): 809–14. http://dx.doi.org/10.1108/aeat-05-2015-0134.

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Purpose Traditional skid-to-turn (STT) missile control mode is adopted mostly, but with the improvement of requirements for mobility and the emergence of new aerodynamic layout, a bank-to-turn (BTT) control mode gradually shows a greater advantage. However, the BTT missile also has certain defects, for example, when attacking against a maneuvering target and at the last section of guidance, the maximum lifting surface position of the missile needs to be adjusted frequently, thereby increasing the difficulty of control as well as introducing high-frequency noise. Design/methodology/approach Bas

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25

Shima, Tal, Moshe Idan, and Oded M. Golan. "Sliding-Mode Control for Integrated Missile Autopilot Guidance." Journal of Guidance, Control, and Dynamics 29, no. 2 (2006): 250–60. http://dx.doi.org/10.2514/1.14951.

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26

Wise, K. A., and J. L. Sedwick. "Missile Autopilot Design Using Nonlinear H ∞ Optimal Control." IFAC Proceedings Volumes 27, no. 13 (1994): 133–39. http://dx.doi.org/10.1016/s1474-6670(17)45789-2.

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27

WAEL, Mohsen Ahmed, and Quan QUAN. "Robust Hybrid Control for Ballistic Missile Longitudinal Autopilot." Chinese Journal of Aeronautics 24, no. 6 (2011): 777–88. http://dx.doi.org/10.1016/s1000-9361(11)60092-7.

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28

Guo, Jianguo, Guoqing Wang, Zongyi Guo, and Jun Zhou. "Augmented predictive functional control for missile autopilot design." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 10 (2016): 1794–803. http://dx.doi.org/10.1177/0954410016675892.

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In this paper, an augmented predictive functional control approach is investigated to design a missile autopilot system, which can be expressed as a linear model with state-dependent coefficient matrices. A novel performance index depending on the reference trajectory, the output prediction and the set-point is proposed to improve the closed-loop dynamic performance. An augmented predictive functional control strategy is designed based on the proposed index and the stability is proven by using the Z-transform. In order to demonstrate the performance of the proposed approach, numerical simulati

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29

Zugaj, M., and J. Narkiewicz. "Autopilot for Reconfigurable Flight Control System." Journal of Aerospace Engineering 22, no. 1 (2009): 78–84. http://dx.doi.org/10.1061/(asce)0893-1321(2009)22:1(78).

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30

Li, Mei Hong, Jian Yin, Xue Yang Sun, Jin Xiang Xu, and Mei Mei Zhang. "Design of Missile Longitudinal Control System Based on Backstepping Control." Applied Mechanics and Materials 496-500 (January 2014): 1401–6. http://dx.doi.org/10.4028/www.scientific.net/amm.496-500.1401.

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Missile control system is not block strict feedback system which is suitable to use backstepping method. So in this paper, a backstepping control method is proposed to design a missile longitudinal autopilot and is proved to be asymptotically stable by Lyapunov stability theory. The simulation results show that the designed system can still track commands quickly and accurately and is robust with aerodynamic perturbation and control input saturation.

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31

Yang, Chong, Ke Zhang, and Mei Bai Lu. "Design of Missile Autopilot with Aerodynamic Lift and Reaction Jets Based on Auto Disturbance Rejection Controller." Advanced Materials Research 472-475 (February 2012): 1036–39. http://dx.doi.org/10.4028/www.scientific.net/amr.472-475.1036.

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First a new autopilot design model is presented for the interceptor missile with the blended aerodynamic lift and reaction jet. The reaction jet can improve the response speed, but the structure of control system becomes more complex. Therefore how to design control strategy properly is an urgent problem. Second, considering the discrete property of the lateral pulse jet thrusters and the continuous property of the aerodynamic fins, a kind of ADRC (active disturbance rejection control) autopilot system was designed for the aerodynamic lift/reaction jet missile. Finally, through a testing in th

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32

Qutbodin, Khaleel. "Merging Autopilot/Flight Control and Navigation-Flight Management Systems." American Journal of Engineering and Applied Sciences 3, no. 4 (2010): 629–30. http://dx.doi.org/10.3844/ajeassp.2010.629.630.

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33

Yuan, Chengzhi, Yang Liu, Fen Wu, and Chang Duan. "Hybrid Switched Gain-Scheduling Control for Missile Autopilot Design." Journal of Guidance, Control, and Dynamics 39, no. 10 (2016): 2352–63. http://dx.doi.org/10.2514/1.g001791.

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34

He, Shaoming, Defu Lin, and Jiang Wang. "Compound Control Methodology for a Robust Missile Autopilot Design." Journal of Aerospace Engineering 28, no. 6 (2015): 04014145. http://dx.doi.org/10.1061/(asce)as.1943-5525.0000484.

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35

Abdallah, M., A. Kamel, Y. EL Halwagy, and G. EL Nashar. "Short Range Missile Autopilot Design using Fuzzy Control Technique." International Conference on Aerospace Sciences and Aviation Technology 16, AEROSPACE SCIENCES (2018): 1–14. http://dx.doi.org/10.21608/asat.2018.22935.

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36

Wu, Fen, Andy Packard, and Gary Balas. "Systematic Gain-Scheduling Control Design: A Missile Autopilot Example." Asian Journal of Control 4, no. 3 (2008): 341–47. http://dx.doi.org/10.1111/j.1934-6093.2002.tb00362.x.

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37

Ouda, A. N. "A robust adaptive control approach to missile autopilot design." International Journal of Dynamics and Control 6, no. 3 (2017): 1239–71. http://dx.doi.org/10.1007/s40435-017-0352-4.

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38

Li, Zongxing, and Rui Zhang. "Two-Timescale Missile Autopilot Design Based on Suboptimal Control." Journal of Physics: Conference Series 1828, no. 1 (2021): 012147. http://dx.doi.org/10.1088/1742-6596/1828/1/012147.

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Cahyaningtias, Sari, and Subchan Subchan. "Application of Pontryagin’s Minimum Principle in Optimum Time of Missile Manoeuvring." CAUCHY 4, no. 3 (2016): 107. http://dx.doi.org/10.18860/ca.v4i3.3534.

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Missile is a guided weapon and designed to protect outermost island from a thread of other country. It, commonly, is used as self defense. This research presented surface-to-surface missile in final dive manoeuvre for fixed target. Furthermore, it was proposed manoeuvring based on unmanned aerial vehicle (UAV), autopilot system, which needs accuration and minimum both time and thrust of missile while attacking object. This paper introduced pontryagin’s Minimum Principle, which is useable to solve the problem. The numerical solution showed that trajectory of the missile is split it up in three

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40

Wang, Shuo, Ziyang Zhen, Ju Jiang, and Xinhua Wang. "Flight Tests of Autopilot Integrated with Fault-Tolerant Control of a Small Fixed-Wing UAV." Mathematical Problems in Engineering 2016 (2016): 1–7. http://dx.doi.org/10.1155/2016/2141482.

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A fault-tolerant control scheme for the autopilot of the small fixed-wing UAV is designed and tested by the actual flight experiments. The small fixed-wing UAV called Xiang Fei is developed independently by Nanjing University of Aeronautics and Astronautics. The flight control system is designed based on an open-source autopilot (Pixhawk). Real-time kinematic (RTK) GPS is introduced due to its high accuracy. Some modifications on the longitudinal and lateral guidance laws are achieved to improve the flight control performance. Moreover, a data fusion based fault-tolerant control scheme is inte

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41

Panchal, Bhavnesh, and S. E. Talole. "Generalized ESO and Predictive Control Based Robust Autopilot Design." Journal of Control Science and Engineering 2016 (2016): 1–12. http://dx.doi.org/10.1155/2016/5741603.

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A novel continuous time predictive control and generalized extended state observer (GESO) based acceleration tracking pitch autopilot design is proposed for a tail controlled, skid-to-turn tactical missile. As the dynamics of missile are significantly uncertain with mismatched uncertainty, GESO is employed to estimate the state and uncertainty in an integrated manner. The estimates are used to meet the requirement of state and to robustify the output tracking predictive controller designed for nominal system. Closed loop stability for the controller-observer structure is established. An import

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42

Lee, K. W., and S. N. Singh. "Immersion- and invariance-based adaptive missile control using filtered signals." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 226, no. 6 (2012): 646–63. http://dx.doi.org/10.1177/0954410011414993.

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The article presents a new non-certainty-equivalent adaptive (NCEA) longitudinal autopilot for the control of a missile based on the immersion and invariance theory. The interest here is to control the angle of attack of the missile in the presence of large parametric uncertainties. For the derivation of the control law, a backstepping design procedure is used. At each step of the design, certain filtered signals are generated for the synthesis of a stabilizing control signal and a parameter estimator. Using Lyapunov stability analysis, it is shown that in the closed-loop system, trajectory co

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43

Buschek, Harald. "Full Envelope Missile Autopilot Design Using Gain Scheduled Robust Control." Journal of Guidance, Control, and Dynamics 22, no. 1 (1999): 115–22. http://dx.doi.org/10.2514/2.4357.

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44

Kim, Seung-Hwan, and Chanho Song. "A Robust Adaptive Nonlinear Control Approach to Missile Autopilot Design." IFAC Proceedings Volumes 31, no. 21 (1998): 49–52. http://dx.doi.org/10.1016/s1474-6670(17)41057-3.

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45

Font, S., H. Siguerdidjane, and E. Devaud. "Some Control Strategies of High Angle of Attack Missile Autopilot." IFAC Proceedings Volumes 31, no. 21 (1998): 53–58. http://dx.doi.org/10.1016/s1474-6670(17)41058-5.

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46

Kim, Seung-Hwan, Yoon-Sik Kim, and Chanho Song. "A robust adaptive nonlinear control approach to missile autopilot design." Control Engineering Practice 12, no. 2 (2004): 149–54. http://dx.doi.org/10.1016/s0967-0661(03)00016-9.

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Lee, Ho Chul, Yong Seok Choi, and Jae Weon Choi. "Autopilot Design for Agile Missile Using Time-Varying Control Technique." IFAC Proceedings Volumes 37, no. 6 (2004): 665–70. http://dx.doi.org/10.1016/s1474-6670(17)32252-8.

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Ryu, Sun-Mee, Dae-Yeon Won, Chang-Hun Lee, and Min-Jea Tahk. "Missile Autopilot Design for Agile Turn Control During Boost-Phase." International Journal of Aeronautical and Space Sciences 12, no. 4 (2011): 365–70. http://dx.doi.org/10.5139/ijass.2011.12.4.365.

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Tian, Jiayi, Shifeng Zhang, and Huabo Yang. "Enhanced extended state observer based control for missile acceleration autopilot." ISA Transactions 96 (January 2020): 143–54. http://dx.doi.org/10.1016/j.isatra.2019.06.009.

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Hou, Ming-Zhe, and Guang-Ren Duan. "Adaptive dynamic surface control for integrated missile guidance and autopilot." International Journal of Automation and Computing 8, no. 1 (2011): 122–27. http://dx.doi.org/10.1007/s11633-010-0563-z.

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