Limitations of autopilot design for controlling a statically unstable flexible interceptor |
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| Authors: | Ram B Sankar Pawan Kishore Tiwari Bijnan Bandyopadhyay Hemendra Arya |
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| Institution: | 1. Defence Research and Development Laboratory, Hyderabad, India;2. Indian Institute of Technology Bombay, Mumbai, India;1. Department of Information and Communication Engineering, DGIST, Daegu 42988, Republic of Korea;2. Department of Electrical and Biomedical Engineering, University of Vermont, Burlington, VT, USA;1. School of Electrical Engineering and Automation, Qilu University of Technology (Shandong Academy of Sciences), Jinan 250353, China;2. College of Information Science and Technology, Donghua University, Shanghai 201620, China;1. School of Automation and Information Engineering, Xi’an University of Technology, China;2. Autonomous Systems and Intelligent Control International Joint Research Center, Xi’an Technological University, China;3. State Key Laboratory of Astronautic Dynamics, China;1. School of Automation, Beijing Institute of Technology, Beijing 100081, China;2. Key Lab of Intelligent Control and Decision of Complex Systems, Beijing 100081, China;3. Beijing Institute of Technology Chongqing Innovation Center, Chongqing 401120, China;1. School of Automation, Nanjing University of Science and Technology, Nanjing 210094, PR China;2. School of Electrical and Automation Engineering, Nanjing Normal University, Nanjing 210023, PR China;3. School of Science, Huzhou Teachers College, Zhejiang, Huzhou 313000, PR China |
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| Abstract: | The Mach number, angle of attack and altitude of operation for an interceptor vary widely during the course of its trajectory. As a result, the interceptor Center of Pressure (CP) locations move significantly around a given Center of Gravity (CG) location at these operating conditions. This results in an inevitable variation in aerodynamic static stability leading to stable and unstable operating regions. In order to ensure good speed of response during the interceptor homing phase, lesser static stability is desirable. Hence the requirement to handle aerodynamic instability at some other operating conditions in the interceptor envelope become inevitable. Since flexibility has a strong bearing on autopilot design, it becomes necessary to control unstable operating points in the presence of flexibility modes. Despite the static stability variation, aerodynamic design can control the level of maximum instability of the configuration. Hence the maximum static instability the autopilot can handle has to be specified for aerodynamic configuration design. This paper brings out the limitations of autopilot design in controlling an unstable interceptor with low bending mode frequencies in terms of maximum instability the autopilot design can handle, which serves as an important input for aerodynamic design. |
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