Showing papers by "Mingming Wang published in 2009"
18 Sep 2009
TL;DR: A distributed integrated simulator for spacecraft autonomous navigation, with the characteristics of modularization and universalisation, was developed with computers and data bus and has been applied successfully to provide usefu1 advice for designers.
Abstract: Before developing an integrated navigation system, it is an efficient method to build an integrated navigation simulator to reduce cost and shorten period of development. Building a distributed simulator with multiple computers will be more close to the actual system. A distributed integrated simulator for spacecraft autonomous navigation, with the characteristics of modularization and universalisation, was developed with computers and data bus. Based on the previously research, autonomous navigation sensors consists of Strap-down Inertial Navigation System (SINS), Global Positioning System (GPS) and Star Sensor (SS). To realize integrated navigation function, the configuration of the distributed simulator was designed to include Trajectory Generator subsystem, Inertial Measurement Unit subsystem, SINS subsystem, GPS subsystem, SS subsystem and Integrated Navigation subsystem. Hardware design and software development of the simulator are discussed. The federated/centralized Kalman filters are used as simulator information fusion algorithm. The distributed simulator has been applied successfully to provide usefu1 advice for designers.
3 citations
02 Oct 2009
TL;DR: Simulations show that GPS/INS could still supplies better navigation parameters for STV in orbit transferring just with 3 GPS navigation satellites.
Abstract: Facing the probable situation of less four navigation satellites of Global Positioning System (GPS) during the orbit transferring of Space Transfer Vehicle (STV), the integrated navigation plan from three satellites pesudorange information is supposed and the performance of GPS/Strapdown Inertial Navigation System (SINS) based three GPS satellites is discussed. We construct the SINS space navigation model, derive the navigation errors model of SINS and chose the errors as the states of Kalman Filter. The corresponding Kalman Filter with three pesudorange information is designed. Simulations show that GPS/INS could still supplies better navigation parameters for STV in orbit transferring just with 3 GPS navigation satellites.
3 citations
30 Oct 2009
TL;DR: The simulations show that the filter precision of relative position and velocity descend when attitude error is big, and the precision is improved when attitude equivalent error is introduced to filter.
Abstract: The absolute attitude error of chaser vehicle is always neglected in observation equation of space relative navigation filter when chaser satellite on-board radar using as the measurement sensor. But the attitude error could affect relative navigation filter precision in fact. The new observation equation, which contains the absolute attitude error of chaser vehicle, is constructed. And the plan, using equivalent measurement error as attitude error, is put forward. The simulations show that the filter precision of relative position and velocity descend when attitude error is big, and the precision is improved when attitude equivalent error is introduced to filter. The plan of attitude equivalent error is proved to be feasible.
2 citations