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Spacecraft and Missions
Published in Julio Sanchez, Maria P. Canton, William Perrizo, Space Image Processing, 2018
Julio Sanchez, Maria P. Canton
The apogee is the point in the orbit in which the satellite is farthest away from the earth and the perigee the one in which the satellite is closest to the earth. The ascending node is the point where the satellite orbit crosses the equator when moving south to north, that is, on the ascending pass. The descending node is the point where the satellite orbit crosses the equator when moving north to south, on the descending pass. The points where the path crosses the equator are also called the equatorial crossing. The orbital inclination is the angle between the satellite track and the equator at the ascending node.
A survey on quantum positioning system
Published in International Journal of Modelling and Simulation, 2021
Shiqi Duan, Shuang Cong, Yuanyuan Song
In 2016, China launched the world first quantum satellite ‘Mozi’ (Figure 4) and achieved the quantum communication between satellite and ground station for the first time. It is a 640 kg sun-synchronous orbit experimental satellite with an orbital inclination of 97.37 degree, and was designed to have a 2-year operational life. At present, China has successfully carried out experiments on high-speed quantum key distribution between satellite and ground station, long-distance free-space quantum key distribution during the daytime, and intercontinental quantum network establishment in satellite relay. The successful development and launch of the ‘Mozi’ quantum satellite made China establish a leading position in the field of quantum communication. Meanwhile, it will promote the information security in communication technology. By 2020, intercontinental quantum key distribution between Asia and Europe will be realized, and the quantum communication network which connects Asia and Europe will be built.
Ground resource optimization for navigation constellation based on satellite link scheduling
Published in Engineering Optimization, 2019
Tianjiao Zhang, Jing Li, Yikang Yang, Hengnian Li, Jisheng Li, Zexi Li
This study employed MEO satellites as research objects in the CNSS networking background. The complete constellation satisfied the Walker24/3/2 satellite configuration with an orbital inclination of 55°, an orbital altitude of approximately 20,000 km, an intersection period of 12 h 53 min and a regression cycle of 13 laps/7 days. Two sets of instances were tested in both hybrid and fast-varying ISL working systems. The first one consisted of three instances in a partial network, which corresponded to the static topologies in the first 3 h of the regression cycle; the second set was in a complete navigation constellation. The simulation duration was set to the first 3 h of a regression cycle. The objective-function preference parameters were set as. Based on the preliminary test, the ACO parameters were set as follows: the maximum number of iterations was 100; the number of ants was set to 20, and was equal to 0.85. The GA was implemented using the characteristics and parameters available in Rao and Wang (2011).
Thermal vibration analysis of a composite sandwich plate in the space environment
Published in Mechanics of Advanced Materials and Structures, 2023
External heat fluxes of the solar panel are divided into heat fluxes applied to upper surface and lower surface of the solar panel. These two heat fluxes are involved in direct solar radiation, Earth-emitted radiation and Albedo radiation, the radiative heat fluxes are referred to orbit altitude and orbital inclination.