Pub Date : 2019-01-01DOI: 10.1504/ijspacese.2019.10026797
Xue Wang, Zhenghong Zhu, Xiaochun Lu, Sen Wang
Global Navigation Satellite System (GNSS) is used to achieve low Earth orbiting (LEOs) satellites orbit determination and time synchronisation. The high accuracy time synchronisation and orbit determination between satellites are completely dependent on time and phase measurement accuracy of GNSS receiver. In this paper, the distortions of new BDS signal and the performance of spaceborne receivers are mainly analysed. The satellite orbit data are used to calculate the dynamics of radial distance, velocity, and acceleration between the LEO satellite and the BDS satellites, such as geostationary (GEO) and medium Earth orbit (MEO). In acquisition processing, the effects of signal correlation performance and carriers Doppler are analysed, such as the correlation loss, the drift of correlation curve and the bit inversion. In tracking processing, the carrier-to-noise ratio, tracking accuracy of code and carrier are simulated in the case of dynamic, especially the BDS signal is simulated.
{"title":"Analysis on BDS signal ranging performance onboard LEO satellite","authors":"Xue Wang, Zhenghong Zhu, Xiaochun Lu, Sen Wang","doi":"10.1504/ijspacese.2019.10026797","DOIUrl":"https://doi.org/10.1504/ijspacese.2019.10026797","url":null,"abstract":"Global Navigation Satellite System (GNSS) is used to achieve low Earth orbiting (LEOs) satellites orbit determination and time synchronisation. The high accuracy time synchronisation and orbit determination between satellites are completely dependent on time and phase measurement accuracy of GNSS receiver. In this paper, the distortions of new BDS signal and the performance of spaceborne receivers are mainly analysed. The satellite orbit data are used to calculate the dynamics of radial distance, velocity, and acceleration between the LEO satellite and the BDS satellites, such as geostationary (GEO) and medium Earth orbit (MEO). In acquisition processing, the effects of signal correlation performance and carriers Doppler are analysed, such as the correlation loss, the drift of correlation curve and the bit inversion. In tracking processing, the carrier-to-noise ratio, tracking accuracy of code and carrier are simulated in the case of dynamic, especially the BDS signal is simulated.","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":"1 1","pages":""},"PeriodicalIF":0.2,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"66761939","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2019-01-01DOI: 10.1504/ijspacese.2019.10026800
M. Ovchinnikov, D. Roldugin
Dual spin satellite motion in the attitude acquisition phase is considered. Starting from the arbitrary rotation state, the satellite should end up with its angular momentum aligned with the orbit normal. The satellite is equipped with magnetorquers that provide the angular velocity damping. Two control strategies are compared, that is the simple exponential damping and 'weighted' damping arising from the classical sliding control implementation. The time response of the control system depending on the satellite inertia moments is analysed. Simple damping is proven to provide better results for the low control authority even for the significantly elongated satellite. This result is proved with the analytical solution for the characteristic exponents approximations. Weighted damping is shown to provide better results for significant control authority through numerical simulation.
{"title":"Comparison of two magnetic damping laws for the attitude acquisition of a dual spin satellite","authors":"M. Ovchinnikov, D. Roldugin","doi":"10.1504/ijspacese.2019.10026800","DOIUrl":"https://doi.org/10.1504/ijspacese.2019.10026800","url":null,"abstract":"Dual spin satellite motion in the attitude acquisition phase is considered. Starting from the arbitrary rotation state, the satellite should end up with its angular momentum aligned with the orbit normal. The satellite is equipped with magnetorquers that provide the angular velocity damping. Two control strategies are compared, that is the simple exponential damping and 'weighted' damping arising from the classical sliding control implementation. The time response of the control system depending on the satellite inertia moments is analysed. Simple damping is proven to provide better results for the low control authority even for the significantly elongated satellite. This result is proved with the analytical solution for the characteristic exponents approximations. Weighted damping is shown to provide better results for significant control authority through numerical simulation.","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":"1 1","pages":""},"PeriodicalIF":0.2,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"66761991","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2019-01-01DOI: 10.1504/ijspacese.2019.10022073
Aguda Ekele Vincent
{"title":"Motion around the out-of-plane equilibrium points in the photogravitational Copenhagen elliptic restricted three-body problem with oblateness","authors":"Aguda Ekele Vincent","doi":"10.1504/ijspacese.2019.10022073","DOIUrl":"https://doi.org/10.1504/ijspacese.2019.10022073","url":null,"abstract":"","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":"1 1","pages":""},"PeriodicalIF":0.2,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"66761829","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2019-01-01DOI: 10.1504/ijspacese.2019.10026796
S. K. Choudhary, K. Raj, V. Muthukumar
This article studies the optimal control solution of the Moon-Lander problem. The main purpose of this article is to investigate the optimal strategy for trajectory design to ensure the soft landing of the lander from the Lunar parking orbit to the lunar surface with minimum consumption of fuel. The trajectory design of lunar lander is studied via two cases by formulating the optimal control problems, where specific requirements of this soft landing problem are all incorporated in the problem formulation. To analyse the proposed optimal strategies for a soft landing the paper briefly illustrates the numerical simulation results and it shows that the required velocity for the soft landing is achieved with minimum fuel consumption. The investigated computational methods for the optimal solutions of the Moon-Lander problem in both two cases are conceptually simple and efficient.
{"title":"Optimal trajectory design and analysis for soft landing on the moon from lunar parking orbits","authors":"S. K. Choudhary, K. Raj, V. Muthukumar","doi":"10.1504/ijspacese.2019.10026796","DOIUrl":"https://doi.org/10.1504/ijspacese.2019.10026796","url":null,"abstract":"This article studies the optimal control solution of the Moon-Lander problem. The main purpose of this article is to investigate the optimal strategy for trajectory design to ensure the soft landing of the lander from the Lunar parking orbit to the lunar surface with minimum consumption of fuel. The trajectory design of lunar lander is studied via two cases by formulating the optimal control problems, where specific requirements of this soft landing problem are all incorporated in the problem formulation. To analyse the proposed optimal strategies for a soft landing the paper briefly illustrates the numerical simulation results and it shows that the required velocity for the soft landing is achieved with minimum fuel consumption. The investigated computational methods for the optimal solutions of the Moon-Lander problem in both two cases are conceptually simple and efficient.","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":"1 1","pages":""},"PeriodicalIF":0.2,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"66761926","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 1900-01-01DOI: 10.1504/ijspacese.2022.10050729
M. Kalarus, Adrian Parzybut, T. Zawistowski, T. Noga
{"title":"Feasibility assessment of a small Earth observation satellite mission propelled with hydrogen peroxide system on a very low Earth orbit","authors":"M. Kalarus, Adrian Parzybut, T. Zawistowski, T. Noga","doi":"10.1504/ijspacese.2022.10050729","DOIUrl":"https://doi.org/10.1504/ijspacese.2022.10050729","url":null,"abstract":"","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":"1 1","pages":""},"PeriodicalIF":0.2,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"66762325","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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