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2018 | Buch

Introduction Kapitel lesen Erstes Kapitel lesen

Navigation and Guidance of Orbital Transfer Vehicle

verfasst von: Prof. Xuefeng Li, Chaobing Li

Verlag: Springer Singapore

Buchreihe : Navigation: Science and Technology

Enthalten in: Springer Professional "Wirtschaft+Technik" , Springer Professional "Technik"

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Über dieses Buch

This book uses the entire flying process, starting from ground launching of the orbital transfer vehicle (OTV) to injecting payload into earth synchronous orbit, as an example for real-world engineering practices. It discusses in detail the analysis design and integrated OTV navigation and guidance system technologies in combination with the engineering experiences of the authors in analysis, design and integrated OTV navigation and guidance system applications, and the research on navigation and guidance theories. It focuses on establishing motion of air vehicle equations, control system hardware components, orbit prediction technology, inertial navigation and initial alignment technologies, INS/GNSS integrated navigation technologies, INS/CNS integrated navigation technologies, redundant fault tolerance and failure reconfiguration technology of inertial sensors, guidance and midcourse correction technologies and orbit control strategies.

The book is a valuable reference book for the engineers, technicians and researchers who are engaged in analysis, design and integrated application of OTV navigation and guidance control systems. It can also be used as teaching material for postgraduates and senior undergraduates majoring in OTV navigation and guidance systems and other related subjects.

Inhaltsverzeichnis

Frontmatter
Chapter 1. Introduction
Abstract
The Orbital Transfer Vehicle (OTV) is one type of autonomous and independent flight vehicle that sends payloads into the scheduled track through multi-orbital transfers after being launched into the Earth orbit by the base launch vehicle.
Xuefeng Li, Chaobing Li
Chapter 2. Modeling and Hardware Components of Control System of the OTV
Abstract
The design of navigation and guidance system of the OTV is carried out on the basis of the kinetic equations and dynamic equations of the control object.
Xuefeng Li, Chaobing Li
Chapter 3. Orbit Prediction Technology
Abstract
The OTV fulfills orbital maneuver by selecting appropriate transfer points to save fuels. Usually, before the orbital maneuver, it shall carry out non-powered free sliding in large elliptic orbit for a long time. During such process, due to the longer sliding period, the error of inertial navigation will be accumulated as time elapses. Meanwhile, when the orbit arrives at a certain height, the availability of satellite navigation signals becomes poor, the flight vehicle could not obtain accurate position and velocity with the INS/GNSS-integrated navigation in real time.
Xuefeng Li, Chaobing Li
Chapter 4. Inertial Navigation and Initial Alignment Technology
Abstract
Navigation is the technology to provide navigation parameters for the motional carrier to arrive at the destination accurately from the starting point. During the flight process of the OTV, the basic navigation parameters needed are the orbital and attitude parameters. Among which, the orbital parameters refer to the position and velocity of the flight vehicle in navigation coordinate system (the selected reference coordinate system, for example, geocentric inertial coordinate system, launching inertial coordinate system and launching coordinate system). Attitude parameters refer to the position relations of carrier coordinate system of flight vehicle corresponding to the navigation coordinate system, usually described by three Eulerian angles of pitch, yaw, and rolling.
Xuefeng Li, Chaobing Li
Chapter 5. INS/GNSS Integrated Navigation Technology
Abstract
As one type of autonomous navigation system, the inertial navigation does not need to receive any external information. Relying on the data measured by gyroscope and accelerometer, it could solve the motional parameters of position, velocity, and attitude via navigation computer, which is the most important navigation system for the OTV.
Xuefeng Li, Chaobing Li
Chapter 6. INS/CNS-Integrated Navigation Technology
Abstract
When the OTV is at medium high orbit, the navigation satellite signal received by the receiver is relatively weak, even unavailable at certain period. At this moment, the INS/GNSS-integrated navigation technology described in the previous chapter could not be used for improving the accuracy of inertial navigation.
Xuefeng Li, Chaobing Li
Chapter 7. Redundant Fault Tolerance and Failure Reconfiguration Technology of Inertial Devices
Abstract
As precision instrument and equipment, the Inertial Navigation System (INS) not only shall has high accuracy index, but also possess high working reliability. Commonly, there are two methods to improve reliability of the INS, one is to increase the reliability of single device and reduce the rate of occurrence of failures (ROCOF). The second is to adopt the concept of tolerance design, by adding additional hardware resources and algorithm in the system. If in case one component in the system fails, it could be tested and the fault can be reconfigured through redundant components and algorithms, and reach the purpose of absorbing or isolating fault. Restricted by manufacturing technology, there is limited space to guarantee the reliability of INS by improving the reliability of single component. Many studies show that redundant technique has apparent effects for improving reliability of system.
Xuefeng Li, Chaobing Li
Chapter 8. Guidance and Midcourse Correction Technology
Abstract
The orbit of Orbital Transfer Vehicle (OTV) commonly consists of the active flight section and free flight section. Among which, the active flight section refers to the motional process of the flight vehicle under the ignition of orbit maneuver motor. The free flight section is the motional process of the flight vehicle under the actions of gravitation and various types of perturbation effects after the shutdown of orbit maneuver motor.
Xuefeng Li, Chaobing Li
Chapter 9. Orbital Control Strategy
Abstract
The previous chapters have discussed the orbital prediction technology, inertial navigation and initial alignment technologies, inertial/satellite integrated navigation technology, inertial/starlight integrated navigation technology, inertial device redundant fault tolerance and fault reconfiguration technology, and guidance and midcourse correction technology of the OTV. During the whole process of flight mission of OTV, the technologies described in these chapters will be involved. Thus, the chapter takes the example of OTV sending the payloads into Earth synchronous orbit to make one integrated description of the technical applications in the chapters.
Xuefeng Li, Chaobing Li
Erratum to: Introduction
Xuefeng Li, Chaobing Li
Metadaten
Titel
Navigation and Guidance of Orbital Transfer Vehicle
verfasst von
Prof. Xuefeng Li
Chaobing Li
Copyright-Jahr
2018
Verlag
Springer Singapore
Electronic ISBN
978-981-10-6334-3
Print ISBN
978-981-10-6333-6
DOI
https://doi.org/10.1007/978-981-10-6334-3

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