Uses the entire flying process, starting from ground launching of orbital transfer vehicle (OTV) to injecting payload into earth synchronous orbit, as an example for real-world engineering practices

Organized in a coherent style making it easy to understand

Divides the vary-trajectory control of space vehicles into the guidance realized by the sustainer motor and the midcourse correction fulfilled by the small engine, pertinent to the actual OTV flight features

Autorentext
Dr. Xuefeng Li is currently Professor, Ph.D. advisor at Beijing Aerospace Automatic Control Institute. He graduated from Northwestern Polytechnical University with master's and doctor's degree of aircraft control, guidance and simulation in 1993 and 1996, repectively. At present, he holds the position of chief designer of national key project - "large launch vehicle control system", and chief designer of the upper stage model control system of the Expedition series, deputy director of the state key laboratory of astronautics intelligent control technology, academic leaders of China Aerospace Science and Technology Corporation, chief expert of China Academy of Launch Vehicle Technology (CALT). For years, he had been engaging in aircraft control, guidance and integrated design. His research field mainly involved navigation and guidance, attitude control, integrated circuit of control system and ground launching system. He presided over completion of projects including Research on Intelligent Potential Analysis Technology of Aerospace Control System and Demonstration of Development Program of Civil Aerospace Pre-research Advanced Upper Stage Control System sponsored by China National Natural Science Foundation. Prof. Li has published nearly 20 academic papers on domestic key academic journals, obtained 30 national defense patents, and a number of awards including Ministerial and Provincial-level Science and Technology Progress, and Military Science and Technology Progress Award. In 2004, he was awarded with Young & Middle-aged Experts of Outstanding Contribution in National Defense Industry. In 2005, he received State Council Special Allowance by the Chinese Government and in 2008 received China Space Foundation Award. Mr. Chaobing Li is senior engineer of Beijing Aerospace Automatic Control Institute. He received his MS degree from Peking University in 2007. At present, he holds the position of chief designer ofupper s tage gu idance system of national project model Expedition series. For years, he has been engaging in theoretical research and project development of guidance system of space aircraft. His main research field involves integrated navigation, optimal control orbit planning and design, fault diagnosis and redundant design of inertial system, etc. Mr. Li has published 6 academic papers on key academic journals, obtained 15 national defense patents. He has received Outstanding Individual of Key Technology Technical Breakthrough and project development of the Third Lunar Exploration Program of State Administration of Science, Technology and Industry for National Defense, and many awards including Military Science and Technology Progress, prizes of CASC Science and Technology Progress, China Academy of Launch Vehicle Technology Science and Technology Progress and the Prize of Stage Achievement, and Model Innovation Award.

Inhalt

Introduction.- Modeling and Hardware Components of Control System of Orbital Transfer Vehicle.- Orbit Prediction Technology.- Inertial Navigation and Initial Alignment Technology.- INS/GNSS Integrated Navigation Technology.- INS/CNS Integrated Navigation Technology.- Redundant Fault Tolerance and Failure Reconfiguration Technology of Inertial Sensor.- Guidance and Midcourse Correction Technology.- Orbit Control Strategy.