The Experimental Satellite on Electromagnetism Monitoring(ESEM) was proposed in 2003 and proved in 2013 after 10-years' scientific demonstration. The ESEM mission was proposed to be the first satellite of space-ba...The Experimental Satellite on Electromagnetism Monitoring(ESEM) was proposed in 2003 and proved in 2013 after 10-years' scientific demonstration. The ESEM mission was proposed to be the first satellite of space-based geophysical fields observation system in China with a lot of application prospects in earthquake science, geophysics, space sciences and so on. And coincide with the mission objectives, the satellite decides to use the Circular Sun Synchronous Orbit with an altitude of 507 km and descending node time at 14:00 LT. The payload assemble includes 8 instruments,Search-Coil Magnetometer, Electric Field Detector, High precision Magnetometer, GNSS occupation Receiver, Plasma Analyzer, Langmuir Probe, Energetic Particle Detector, and Three-frequency Transmitter. According to the planned schedule, the satellite is due to be launched in 2016–2017 and will be onboard operated for 5 years.展开更多
This paper is based on the second problem of the 8th China Space Trajectory Design Competition(CTOC8).The background is LEO constellation design strategy for monitoring discrete multi-targets with small stellite under...This paper is based on the second problem of the 8th China Space Trajectory Design Competition(CTOC8).The background is LEO constellation design strategy for monitoring discrete multi-targets with small stellite under J model.The difculty is that the small satellite is equipped with low-cost cameras with limited coverage ability and the targets are distributed separately in a key area,which result in long revisit time or large pumber of satelites based on traditional design method.In this paper,a speciflc LEO consellation design method is proposed to cope with the problems.First,grid search and numerical method are performed to construct a database consisting of repeating ground track orbits.Then several orbits are carefully selected by pruning method to visit each target.Finally,repeating ground track costellation is constructed to meet the maximun revisit time constraint.The present method provides a systematic constellation design methodology of remote sensing observation with limited coverage ability,and demonstrates the resulting constellation can obtain rapid revisit frequency over discrete multi-targets with the least number of satellites.展开更多
文摘The Experimental Satellite on Electromagnetism Monitoring(ESEM) was proposed in 2003 and proved in 2013 after 10-years' scientific demonstration. The ESEM mission was proposed to be the first satellite of space-based geophysical fields observation system in China with a lot of application prospects in earthquake science, geophysics, space sciences and so on. And coincide with the mission objectives, the satellite decides to use the Circular Sun Synchronous Orbit with an altitude of 507 km and descending node time at 14:00 LT. The payload assemble includes 8 instruments,Search-Coil Magnetometer, Electric Field Detector, High precision Magnetometer, GNSS occupation Receiver, Plasma Analyzer, Langmuir Probe, Energetic Particle Detector, and Three-frequency Transmitter. According to the planned schedule, the satellite is due to be launched in 2016–2017 and will be onboard operated for 5 years.
基金This work was supported by the National Natural Science Foundation of China(Grant No.91438206).
文摘This paper is based on the second problem of the 8th China Space Trajectory Design Competition(CTOC8).The background is LEO constellation design strategy for monitoring discrete multi-targets with small stellite under J model.The difculty is that the small satellite is equipped with low-cost cameras with limited coverage ability and the targets are distributed separately in a key area,which result in long revisit time or large pumber of satelites based on traditional design method.In this paper,a speciflc LEO consellation design method is proposed to cope with the problems.First,grid search and numerical method are performed to construct a database consisting of repeating ground track orbits.Then several orbits are carefully selected by pruning method to visit each target.Finally,repeating ground track costellation is constructed to meet the maximun revisit time constraint.The present method provides a systematic constellation design methodology of remote sensing observation with limited coverage ability,and demonstrates the resulting constellation can obtain rapid revisit frequency over discrete multi-targets with the least number of satellites.
