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Tiny GPS receiver for space application
Abstract
GPS receivers used in car navigation and other applications have been downsized to dozens of grams, with significant gains in power conservation. With the assistance of a vehicle GPS manufacturer, a vehicle GPS receiver has been modified and a space application GPS receiver with ultralow power consumption that generates pseudo-range data has been developed. We expanded the frequency search range for the GPS receiver, and we conducted on-orbit simulations using a GPS simulator and confirmed that the positioning accuracy performance of the receiver is less than 1 m. It has also been confirmed that the receiver has a 20-krad radiation tolerance and that it is latch-up-free with respect to 200-MeV protons. The GPS receiver will be deployed on the small scientific satellite INDEX which is under development by the Aerospace Science Research Department of the Japan Aerospace Exploration Agency. © 2006 Wiley Periodicals, Inc. Electron Comm Jpn Pt 1, 89(11): 56–67, 2006; Published online in Wiley InterScience (www.interscience.wiley.com). DOI 10.1002/ecja.20234
According to the application characteristics of low-earth-orbit satellite-borne global positioning system (GPS) receiver, the influence of GPS measurement data error on cycle-slip detection is analyzed. Then a modified TurboEdit preprocessing method is proposed. In the modified method, a weighted factor which closely relates to the GPS satellite elevation angle is introduced in the cycle-slip detection process. The weighted factor estimates the error of measurement data based on the variation of GPS elevation angle and establishes a relationship between the cycle-slip detection process and error of measurement data. Then the cycle-slip detection judgment is adjusted by the weighted factor. The modification algorithm not only reduces the fault rate of cycle-slip detection, but also promotes the autonomous ability of orbit determination by increasing the quantity of measurement data that will participate in low-earth-orbit-satellite orbit determination. Finally, the modified algorithm is verified by GPS measurement data of GRACE satellite formation.
The shape of the filter response can be controlled by a combination of ring resonators, such as series coupling, parallel
coupling, and cascade topology. In particular series coupling is effective to realize box-like spectrum responses, which are
required for wavelength filtering in WDM systems for photonic networks. In this chapter, the transfer function of series-coupled
ring resonators is derived using the matrix method, and the optimum conditions for coupling coefficients to realize the box-like
filter response are described. In addition, the free spectral range (FSR) extension method using the Vernier effect in series-coupled
ring resonators with dissimilar radii will be discussed. Last, the transfer function of parallel-coupled ring resonators is
derived and an application to interleaving is introduced.
Real-time spacecraft navigation based on spaceborne GPS receivers is becoming a common technique for low-earth orbits (LEO), but has not yet been demonstrated for geostationary orbits (GEO). The TOPSTAR 3000 spaceborne GPS receiver was designed for a wide range of missions, including high-altitude orbits. A flight model of this receiver has been obtained by the STENTOR GEO program, the purpose of which is to experiment with new techniques for the next generation of GEO telecommunications spacecraft. One of these experiments involves autonomous orbit control, for which the on-board GPS receiver acts as the main means for localization and time transfer. This paper describes the particular features of the GPS receiver in GEO, and introduces additional features required for autonomous orbit control. Results of tests performed with the TOPSTAR 3000 receiver in a GEO configuration are presented, including behavior during GEO station-keeping maneuvers using electric propulsion.
Intelligent agent technology is a rapidly developing area of research. However, in reality, there is a truly heterogeneous body of work being carried out under the agent banner. In this paper, software agent technology is introduced by briefly overviewing the various agent types currently under investigation by researchers.
This paper describes outline of the piggy-back satellite “INDEX” for demonstration of advanced satellite technologies as well as for observation of fine structure of aurora. Aurora observation will be carried out by three cameras(MAC) with a monochromatic UV filter. Electron and ion spectrum analyzer (ESA/ISA) will measure the particle phenomena together with the aurora imaging. INDEX satellite will be launched in 2002 by Japanese H2-A. The satellite is mainly controlled by the high-speed, fault-tolerant on-board RICS processor (three-voting system of SH-3). The attitude control is a compact system of three-axis stabilization. Although the size of INDEX is small (50Kg class), several newly-developed technologies are applied to the satellite system, including silicon-on-insulator devices, variable emittance radiator, solar-concentrated paddles, lithium-ion battery, and GPS receiver with all-sky antenna-coverage.
Car navigation SOC with a built-in GPS-IP
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