Analytical design and performance analysis of LEO mega chain satellite constellation
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With the development of microsatellite technology and the growth of ground reconnaissance demand, the rapid design of a LEO constellation with minimum satellite number, low revisit time (within 10 minutes), and permanent inter-satellite links has become a hotspot and difficulty in constellation design. Aiming at the problem to use the minimum satellite number to achieve low revisit time coverage, a LEO (low earth orbit) Walker-chain constellation and its design method is proposed. The difference between the chain constellation and the classical Walker constellation is that it has one or more closed chain configurations. According to the coverage requirements and sensor field of view angle, the analytical design method is derived. A LEO chain constellation containing 132 satellites is designed for the ground reconnaissance mission. Comparing with the classical Walker-δ constellation and repeat ground track constellation, the chain constellation has fewer satellites, lower revisit time and the permanent inter-satellite links.Keywords:
Satellite constellation
The low earth orbit satellite constellation is used for the discussed object in this paper. Regarding coverage performance as an important consideration, it states the general idea and method of the optimal design with the requirement of partial coverage for small satellite constellation in details. Based on the analysis of the key factors effect on the constellation performance, the optimal model is given by choosing the appropriate parameters with some constraints. For the design of different satellite planes, the potential and characteristic of constellation optimization are stated through the comparison between two orbit surface and three orbit surface constellation with some a specific task. Whereafter simulation and analysis is done. The result shows that the optimal model provided herein is of theoretical meaning and practical application.
Satellite constellation
Orbit (dynamics)
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Satellite constellation
Link (geometry)
Routing algorithm
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In this paper, a constellation of four low earth orbit nanosatellites for disaster monitoring is presented; their small size, low cost, and short time development give them the opportunity to be widely selected. The space segment is based on existing subsystems that are assembled on the bottom part of a developed structure and present acceptable performance for the mission. The payload is a multispectral camera which fulfills the mission's requirements (remote sensing). The ground segment is based on an existing modular ground station, used for the ALSAT-1 DMC, which will be adapted to fit with the specifications of the mission.
Payload (computing)
Satellite constellation
Ground segment
Orbit (dynamics)
Ground station
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This paper reviews some basic equations of motion and coverage of satellites in earth orbit as well as examining satellite constellation design techniques. Specific orbit properties are highlighted and their applicability to constellation design and earth coverage are then investigated. A PCN oriented satellite constellation is then proposed with some unique properties. The proposed constellation scheme allows for a reduction in overall system cost in two ways. Firstly, simplification in satellite design result in satellite development costs being reduced and secondly, because each satellite will be designed for a particular orbit, constellation lifetime can be significantly extended.
Satellite constellation
Medium Earth orbit
Satellite broadcasting
Orbit (dynamics)
Communications satellite
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In order to improve service performance of navigation constellation,many experts consider the mixed constellation configuration of GEO satellite,IGSO satellite and MEO satellite.In the design of the new constellation configuration or the research of the existing constellation performance,the inter-satellite link(ISL) is needed to established,and the connectivity and robustness of the ISL are needed to analyze.The characteristics of the mixed constellation configuration are analyzed,and the characteristics of ISL establishment and the service performance of GEO satellite,IGSO satellite and Walker-δ constellation are discussed firstly.Then,the method to determine ISL connectivity in the mixed constellation by the adjacency matrix is put forward,and the standards of the ISL robustness are given using the number of ways between any two satellites,cutting point,cutting edge,k-connectivity degree and k-edge connectivity degree of graph theory.The minimum required number of ISLs of a k-connectivity′s constellation and the construction method of k-connectivity′s constellation are given for the first time.Finally,the 3GEO+3IGSO+24MEO constellation configuration is simulated.The criteria for ISL establishment,the connectivity and robustness of this mixed constellation configuration are studied,and many important conclusions are obtained.
Satellite constellation
Robustness
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Spaceborne netted radars are of benefit for low-earth-orbit (LEO) object detection. Methods of constellation design are presented in detail by mean of the analysis on satellite orbital parameters, types of constellation coverage and other parameters related to constellation design. Simu-lations on LEO objects detection using spaceborne netted radars are implemented under the constraint of rational operating parameters of space-based radars. Walker con-stellation and non-Walker constellation with different pa-rameter configuration are compared in terms of observation time gap for one satellite as an example, followed by the statistical results of observation time intervals for more than one hundred objects. The simulation results show that the observation time intervals for LEO objects can be shortened effectively by means of spaceborne netted radars, resulting in higher coverage ratio of observation.
Satellite constellation
Orbit (dynamics)
Earth observation
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This paper mainly discusses how to design a regional constellation by MEO satellites. Firstly, it addresses that the LEO satellite constellation is not good enough for designing partial coverage satellite system. Then the method of designing regional constellations with an MEO satellite chain is introduced, including how to compute and optimize constellation parameter. Two regional constellations are given with their coverage capability. At last, partial coverage constellation is compared with Rosette constellation. The regional constellations are suitable to China.
Satellite constellation
Communications satellite
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Satellite constellation
Orbit (dynamics)
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Constellation configuration design is a prerequisite and critical step in the construction of a mega-constellation system in low Earth orbit. However, the huge number of satellites and the intricate changes in relative positions among them make the configuration design the most challenging part. In this paper, we propose a configuration design scheme for mega-constellations considering collision-avoidance constraints with the objective of uniform global coverage. In this design scheme, the constellation is made up of multiple Walker constellations with the same orbital altitude and different orbital inclination. Moreover, the analytical expression for the minimum distance between any two satellites in the same orbital altitude is derived, and the constellation internal collision-avoidance constraint is established accordingly. Finally, a permanent inter-satellite link design scheme without dynamic reconstruction is presented based on the mega-constellation configuration. Simulation results show that the mega-constellation design scheme introduced in this paper can achieve relatively uniform global coverage (its N Asset Coverage ranges from 18 to 25). The mixed Walker constellation is capable of providing a greater number of N Asset Coverage for most of the world than the Walker constellation of the same satellite order of magnitude. In addition, the inter-satellite link scheme designed in this paper can ensure continuous and stable communication between any satellite nodes.
Satellite constellation
Circular orbit
Medium Earth orbit
Orbit (dynamics)
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In this paper LEO-polar constellation for full earth coverage is investigated. Some important features of a constellation are introduced such as number of satellites and orbits needed for continues coverage, handover, intersatellite links and seam. Also the effects of satellite altitude on minimum elevation angle are analyzed and in the end some numeric results are gained.
Satellite constellation
Polar orbit
Orbit (dynamics)
Medium Earth orbit
Geocentric orbit
Elevation (ballistics)
Sun-synchronous orbit
Earth's orbit
Satellite broadcasting
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