Pub Date : 2019-07-30DOI: 10.1504/IJSPACESE.2019.10022791
Yu Shi, Hao Peng, Yue Wang, Shijie Xu
The trajectory for a global exploration of an asteroid is designed to make a comprehensive investigation of different areas. The areas to be visited are considered as target points scattered on the asteroid's surface and all the target points are supposed to be visited by the spacecraft propelled by impulsive thrusts. The trajectory of the spacecraft is optimised for fuel saving in two parts: the transfer orbit optimisation and the exploration sequence optimisation. Firstly, transfer orbits between any two target points via two impulses are optimised for fuel saving by solving a nonlinear programming problem. The solution of the Lambert problem in the gravitational field of a point mass is used as initial guesses in the optimisation. Then, with all the optimal transfer orbits determined, the exploration sequence is processed as a travelling salesman problem (TSP). Branch and bound method and greedy algorithm for solving this problem are compared. Finally, the trajectory for a global exploration of the asteroid 433 Eros is designed for a demonstration purpose.
{"title":"Optimal trajectory design for global exploration of an asteroid via bi-impulsive transfers","authors":"Yu Shi, Hao Peng, Yue Wang, Shijie Xu","doi":"10.1504/IJSPACESE.2019.10022791","DOIUrl":"https://doi.org/10.1504/IJSPACESE.2019.10022791","url":null,"abstract":"The trajectory for a global exploration of an asteroid is designed to make a comprehensive investigation of different areas. The areas to be visited are considered as target points scattered on the asteroid's surface and all the target points are supposed to be visited by the spacecraft propelled by impulsive thrusts. The trajectory of the spacecraft is optimised for fuel saving in two parts: the transfer orbit optimisation and the exploration sequence optimisation. Firstly, transfer orbits between any two target points via two impulses are optimised for fuel saving by solving a nonlinear programming problem. The solution of the Lambert problem in the gravitational field of a point mass is used as initial guesses in the optimisation. Then, with all the optimal transfer orbits determined, the exploration sequence is processed as a travelling salesman problem (TSP). Branch and bound method and greedy algorithm for solving this problem are compared. Finally, the trajectory for a global exploration of the asteroid 433 Eros is designed for a demonstration purpose.","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":null,"pages":null},"PeriodicalIF":0.2,"publicationDate":"2019-07-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45581237","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 : 2019-07-30DOI: 10.1504/IJSPACESE.2019.10022799
Kui Lin, X. Zhan, Jihong Huang
In recent years, Global Navigation Satellite System (GNSS) showed a remarkable capability to serve for medium and high earth orbit spacecraft, called space service volume (SSV). However, SSV users face a critical problem of insufficient GNSS signal visibility. In previous studies, the ionospheric signals are usually discarded, which results in a large discrepancy in mission design and system optimisation. In this paper, a three-dimensional ray-tracing method is adopted to analyse signal propagation through the ionosphere. Taking GPS constellation and a GEO user as an example, the principles are validated with a careful simulation. The results show an interesting phenomenon that the bending angle of the signal path and the ionospheric attenuation are very small, and the ionospheric delay is large but eliminable. If the ionospheric signals are considered, the signal visibility and availability will significantly increase, which leads to a shortened maximum outage time for SSV users.
{"title":"GNSS signals ionospheric propagation characteristics in space service volume","authors":"Kui Lin, X. Zhan, Jihong Huang","doi":"10.1504/IJSPACESE.2019.10022799","DOIUrl":"https://doi.org/10.1504/IJSPACESE.2019.10022799","url":null,"abstract":"In recent years, Global Navigation Satellite System (GNSS) showed a remarkable capability to serve for medium and high earth orbit spacecraft, called space service volume (SSV). However, SSV users face a critical problem of insufficient GNSS signal visibility. In previous studies, the ionospheric signals are usually discarded, which results in a large discrepancy in mission design and system optimisation. In this paper, a three-dimensional ray-tracing method is adopted to analyse signal propagation through the ionosphere. Taking GPS constellation and a GEO user as an example, the principles are validated with a careful simulation. The results show an interesting phenomenon that the bending angle of the signal path and the ionospheric attenuation are very small, and the ionospheric delay is large but eliminable. If the ionospheric signals are considered, the signal visibility and availability will significantly increase, which leads to a shortened maximum outage time for SSV users.","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":null,"pages":null},"PeriodicalIF":0.2,"publicationDate":"2019-07-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41695460","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 : 2019-06-18DOI: 10.1504/IJSPACESE.2020.109745
R. Siddiqui, R. Jagpal, S. Abrarov, B. Quine
The description, imagery and interpretation of cloud scenes by remote sensing datasets from Earth-orbiting satellites have become a great debate for several decades. Presently, there are many models for cloud detection and its classifications have been reported. However, none of the existing models can efficiently detect the clouds within the small band of shortwave upwelling radiative wavelength flux (SWupRF) in the spectral range from 1100 to 1700 nm. Therefore, in order to detect the clouds more effectively, a method known as the radiance enhancement (RE) can be implemented (Siddiqui et al., 2015). This article proposes new approaches how with RE and SWupRF methods to distinguish cloud scenes by space orbiting Argus 1000 micro-spectrometer utilizing the GENSPECT line-by-line radiative transfer model (Quine and Drummond, 2002; Siddiqui, 2017). This RE approach can also be used within the selected wavelength band for the detection of combustion-originated aerosols due to seasonal forest fires.
几十年来，地球轨道卫星遥感数据集对云场景的描述、成像和解释一直是一个大争论。目前，云检测的模型和分类已经有了很多的报道。然而，现有的模式都不能有效地探测1100 ~ 1700 nm光谱范围内短波上升流辐射波长通量(SWupRF)小波段内的云。因此，为了更有效地探测云，可以实施一种称为辐射增强(RE)的方法(Siddiqui et al.， 2015)。本文提出了利用GENSPECT逐行辐射传输模型(Quine and Drummond, 2002;西迪基,2017)。这种RE方法也可以在选定的波长范围内用于检测由于季节性森林火灾而产生的燃烧气溶胶。
{"title":"Radiance enhancement and shortwave upwelling radiative flux methods for efficient detection of cloud scenes","authors":"R. Siddiqui, R. Jagpal, S. Abrarov, B. Quine","doi":"10.1504/IJSPACESE.2020.109745","DOIUrl":"https://doi.org/10.1504/IJSPACESE.2020.109745","url":null,"abstract":"The description, imagery and interpretation of cloud scenes by remote sensing datasets from Earth-orbiting satellites have become a great debate for several decades. Presently, there are many models for cloud detection and its classifications have been reported. However, none of the existing models can efficiently detect the clouds within the small band of shortwave upwelling radiative wavelength flux (SWupRF) in the spectral range from 1100 to 1700 nm. Therefore, in order to detect the clouds more effectively, a method known as the radiance enhancement (RE) can be implemented (Siddiqui et al., 2015). This article proposes new approaches how with RE and SWupRF methods to distinguish cloud scenes by space orbiting Argus 1000 micro-spectrometer utilizing the GENSPECT line-by-line radiative transfer model (Quine and Drummond, 2002; Siddiqui, 2017). This RE approach can also be used within the selected wavelength band for the detection of combustion-originated aerosols due to seasonal forest fires.","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":null,"pages":null},"PeriodicalIF":0.2,"publicationDate":"2019-06-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1504/IJSPACESE.2020.109745","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43192111","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 : 2019-01-23DOI: 10.1504/IJSPACESE.2019.10018509
G. Vukovich, Y. Kim
In the absence of disturbances, an Earth orbiting satellite will follow a Keplerian orbit, which is a regular ellipse with Earth at a focus. However, in reality, there are many additional factors such as gravity field irregularities, Earth magnetic field interactions with satellite magnetic residual and induced magnetic field, solar radiation pressure, the gravitational influence of other celestial bodies and atmospheric drag, which disturb satellite orbits and deflect them from the classic Kepler ellipse fixed in inertial space. Generally, these orbital disturbances are relatively minor over the short-term of a few orbits. However, for low Earth orbiting satellites, atmospheric drag is the dominant factor, causing a satellite to gradually lose altitude (orbital decay) and eventually enterer the dense lower layers of the Earth's atmosphere, where is burned up. Even for fairly high altitudes, this decay can be fairly rapid. This effect can also be used for planned destruction of defunct satellites so as not to add to the space debris problem. This study develops simple models and simulators for satellite atmospheric drag orbital decay prediction. The simulator can be used for satellite orbital decay assessment and studying its effects.
{"title":"Satellite orbit decay due to atmospheric drag","authors":"G. Vukovich, Y. Kim","doi":"10.1504/IJSPACESE.2019.10018509","DOIUrl":"https://doi.org/10.1504/IJSPACESE.2019.10018509","url":null,"abstract":"In the absence of disturbances, an Earth orbiting satellite will follow a Keplerian orbit, which is a regular ellipse with Earth at a focus. However, in reality, there are many additional factors such as gravity field irregularities, Earth magnetic field interactions with satellite magnetic residual and induced magnetic field, solar radiation pressure, the gravitational influence of other celestial bodies and atmospheric drag, which disturb satellite orbits and deflect them from the classic Kepler ellipse fixed in inertial space. Generally, these orbital disturbances are relatively minor over the short-term of a few orbits. However, for low Earth orbiting satellites, atmospheric drag is the dominant factor, causing a satellite to gradually lose altitude (orbital decay) and eventually enterer the dense lower layers of the Earth's atmosphere, where is burned up. Even for fairly high altitudes, this decay can be fairly rapid. This effect can also be used for planned destruction of defunct satellites so as not to add to the space debris problem. This study develops simple models and simulators for satellite atmospheric drag orbital decay prediction. The simulator can be used for satellite orbital decay assessment and studying its effects.","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":null,"pages":null},"PeriodicalIF":0.2,"publicationDate":"2019-01-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44660563","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 : 2019-01-23DOI: 10.1504/IJSPACESE.2019.10018514
J. Moores, H. Podmore
This paper is intended to provoke a discussion within the space community of how a starchip architecture could benefit the exploration of the solar system and the part that Canada might play in advancing and using this technology. We find that the amount of required development is greatly reduced with a viable pathway to implementing this technology by the mid 2020s. Canada's expertise in optics, spacecraft development and geographical position offers unique advantages over other spacefaring nations in taking advantage of this opportunity. A 1-100 MW facility located above the Arctic Circle would allow for the exploration of much of the solar system through planetary fly-bys. Furthermore, as starchips make excellent entry vehicles and may make effective solar sails, such architecture would enable network science near planets in the inner solar system and on the surfaces of those with substantial atmospheres, such as Mars, Venus, Titan and the Giant Planets.
{"title":"Starchips in solar system planetary exploration: an opportunity for Canada","authors":"J. Moores, H. Podmore","doi":"10.1504/IJSPACESE.2019.10018514","DOIUrl":"https://doi.org/10.1504/IJSPACESE.2019.10018514","url":null,"abstract":"This paper is intended to provoke a discussion within the space community of how a starchip architecture could benefit the exploration of the solar system and the part that Canada might play in advancing and using this technology. We find that the amount of required development is greatly reduced with a viable pathway to implementing this technology by the mid 2020s. Canada's expertise in optics, spacecraft development and geographical position offers unique advantages over other spacefaring nations in taking advantage of this opportunity. A 1-100 MW facility located above the Arctic Circle would allow for the exploration of much of the solar system through planetary fly-bys. Furthermore, as starchips make excellent entry vehicles and may make effective solar sails, such architecture would enable network science near planets in the inner solar system and on the surfaces of those with substantial atmospheres, such as Mars, Venus, Titan and the Giant Planets.","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":null,"pages":null},"PeriodicalIF":0.2,"publicationDate":"2019-01-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44854973","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 : 2019-01-23DOI: 10.1504/IJSPACESE.2019.10018486
Ja’Mar A. Watson
This research benchmarks the Mars DRA 5.0 by quantifying its mission utility in satisfying mission objectives derived from human exploration of Mars community consensus. Acolytion's Progspexion is utilised for modelling and simulation of the DRA in determination of potential mission outcomes and computation of crewed mission to Mars metrics. While establishing a baseline performance, the research determines the DRA's mission utility is limited due to a lack of its consideration during design. In addition, the research indicates the DRA simultaneously contains an overwhelming number of single points of failure with high criticality and lacks an adequate hierarchy of contingency and abort strategies to preclude loss of mission and crew fatality.
{"title":"Benchmarking the human exploration of Mars Design Reference Architecture","authors":"Ja’Mar A. Watson","doi":"10.1504/IJSPACESE.2019.10018486","DOIUrl":"https://doi.org/10.1504/IJSPACESE.2019.10018486","url":null,"abstract":"This research benchmarks the Mars DRA 5.0 by quantifying its mission utility in satisfying mission objectives derived from human exploration of Mars community consensus. Acolytion's Progspexion is utilised for modelling and simulation of the DRA in determination of potential mission outcomes and computation of crewed mission to Mars metrics. While establishing a baseline performance, the research determines the DRA's mission utility is limited due to a lack of its consideration during design. In addition, the research indicates the DRA simultaneously contains an overwhelming number of single points of failure with high criticality and lacks an adequate hierarchy of contingency and abort strategies to preclude loss of mission and crew fatality.","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":null,"pages":null},"PeriodicalIF":0.2,"publicationDate":"2019-01-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46526276","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 : 2019-01-23DOI: 10.1504/IJSPACESE.2019.10018483
Anirudh Agarwal, G. Vukovich
A design methodology for certain third order systems is demonstrated using the root locus method, and extended and applied to a simple SISO model of a single axis of a flexible spacecraft with sensor and actuator dynamics included. The controller, including derivative and acceleration feedback, is tuned for the flexible spacecraft system to improve its steady state and transient performance. A numerical example then demonstrates the features of the controller.
{"title":"Proportional-derivative-acceleration controller design for spacecraft with flexible appendages","authors":"Anirudh Agarwal, G. Vukovich","doi":"10.1504/IJSPACESE.2019.10018483","DOIUrl":"https://doi.org/10.1504/IJSPACESE.2019.10018483","url":null,"abstract":"A design methodology for certain third order systems is demonstrated using the root locus method, and extended and applied to a simple SISO model of a single axis of a flexible spacecraft with sensor and actuator dynamics included. The controller, including derivative and acceleration feedback, is tuned for the flexible spacecraft system to improve its steady state and transient performance. A numerical example then demonstrates the features of the controller.","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":null,"pages":null},"PeriodicalIF":0.2,"publicationDate":"2019-01-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41789321","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.2019.10026795
A. J. Tang, Xiaofeng Wu
Formation flying involves multiple spacecraft flying with pre-defined relation to each other. This allows a number of individual, smaller satellites to work together and accomplish tasks extraneous to single satellite systems. However, the required precision of orbital positioning and control makes the maintenance of such formations quite challenging. This is particularly true for space systems without propulsive controls; even for systems equipped with active control, propellant consumption can be quite high. To facilitate orbital control, this study investigates formation flying in low earth orbit (LEO), focusing primarily on propulsion-free methods of control for micro and nano-class satellites such as aerodynamic differential drag. A fuzzy logic control algorithm was developed to control the satellites' position by manipulating the drag configuration of each satellite in the formation. The outcome of this study shows that successful formation control can be achieved using drag forces alone. The time taken for each formation control and by-products, including altitude loss are evaluated. The orbital modelling presented here can be used as the baseline for a control algorithm developed for station keeping of satellites in low earth orbit.
{"title":"LEO satellite formation flying via differential atmospheric drag","authors":"A. J. Tang, Xiaofeng Wu","doi":"10.1504/ijspacese.2019.10026795","DOIUrl":"https://doi.org/10.1504/ijspacese.2019.10026795","url":null,"abstract":"Formation flying involves multiple spacecraft flying with pre-defined relation to each other. This allows a number of individual, smaller satellites to work together and accomplish tasks extraneous to single satellite systems. However, the required precision of orbital positioning and control makes the maintenance of such formations quite challenging. This is particularly true for space systems without propulsive controls; even for systems equipped with active control, propellant consumption can be quite high. To facilitate orbital control, this study investigates formation flying in low earth orbit (LEO), focusing primarily on propulsion-free methods of control for micro and nano-class satellites such as aerodynamic differential drag. A fuzzy logic control algorithm was developed to control the satellites' position by manipulating the drag configuration of each satellite in the formation. The outcome of this study shows that successful formation control can be achieved using drag forces alone. The time taken for each formation control and by-products, including altitude loss are evaluated. The orbital modelling presented here can be used as the baseline for a control algorithm developed for station keeping of satellites in low earth orbit.","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":null,"pages":null},"PeriodicalIF":0.2,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"66761885","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.2019.10026799
Min Luo, Qiong Wu, Wenbo Luo, Wentao Yang
{"title":"Design of passive launch and on-orbit vibration isolation system for control moment gyroscopes","authors":"Min Luo, Qiong Wu, Wenbo Luo, Wentao Yang","doi":"10.1504/ijspacese.2019.10026799","DOIUrl":"https://doi.org/10.1504/ijspacese.2019.10026799","url":null,"abstract":"","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":null,"pages":null},"PeriodicalIF":0.2,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"66761955","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.2018.10013617
A. Vincent
The photogravitational restricted five-body problem is employed to describe the motion of an infinitesimal test particle in the special case where two of the primaries are radiation sources. The four primaries mi, i = 0, , 3 three of which have equal masses (m1 = m2 = m3 = m) are located at the vertices of an equilateral triangle, while the fourth one with a different mass m0 is located at the centre of this configuration (Ollongren's configuration). The fifth body of negligible mass moves in the resultant force field of the primaries and does not affect the motion of the four bodies (primaries). We consider that the central primary body m0 and one of the peripheral bodies m1 are radiation sources. The equilibrium points lying out of the orbital plane of the primaries as well as the allowed regions of motion as determined by the zero velocity curves are studied numerically. Finally, the stability of these points is also examined.
用光引力限制五体问题描述了在两个原色粒子为辐射源的特殊情况下，一个无限小测试粒子的运动。四个质点mi, i = 0,3其中三个质点相等(m1 = m2 = m3 = m)位于等边三角形的顶点，而质量不同的第四个质点m0位于等边三角形的中心(Ollongren的质点)。第5个质量可忽略不计的物体在初级物体的合力场中运动，不影响四个物体(初级物体)的运动。我们认为主要的中心物体m0和一个外围物体m1是辐射源。用数值方法研究了初等星轨道平面外的平衡点和由零速度曲线确定的允许运动区域。最后，对这些点的稳定性进行了检验。
{"title":"Out-of-plane equilibria in the restricted five-body problem with radiation pressure","authors":"A. Vincent","doi":"10.1504/IJSPACESE.2018.10013617","DOIUrl":"https://doi.org/10.1504/IJSPACESE.2018.10013617","url":null,"abstract":"The photogravitational restricted five-body problem is employed to describe the motion of an infinitesimal test particle in the special case where two of the primaries are radiation sources. The four primaries mi, i = 0, , 3 three of which have equal masses (m1 = m2 = m3 = m) are located at the vertices of an equilateral triangle, while the fourth one with a different mass m0 is located at the centre of this configuration (Ollongren's configuration). The fifth body of negligible mass moves in the resultant force field of the primaries and does not affect the motion of the four bodies (primaries). We consider that the central primary body m0 and one of the peripheral bodies m1 are radiation sources. The equilibrium points lying out of the orbital plane of the primaries as well as the allowed regions of motion as determined by the zero velocity curves are studied numerically. Finally, the stability of these points is also examined.","PeriodicalId":41578,"journal":{"name":"International Journal of Space Science and Engineering","volume":null,"pages":null},"PeriodicalIF":0.2,"publicationDate":"2019-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"66761817","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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