Formation satellite finite-time configuration containment control method
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A control method and time-limited technology, applied in the field of formation satellite configuration including control, can solve problems such as poor robustness and inability to fully meet the actual application environment
Active Publication Date: 2015-09-09
HARBIN INST OF TECH
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[0008] The present invention solves the problem of poor robustness of the existing multi-satellite system formation control method and the pro
Method used
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specific Embodiment approach 1
[0048] 1. The finite-time configuration of formation satellites includes control methods,
[0049] Based on the following assumptions:
[0050] (1) The time-varying form of control input τ for all pilot stars oi =[τ oix τ oiy τ oiz ] T is unknown to all following stars, but its upper bound information can be obtained by the adjacent follower star of the pilot star, namely
[0051] (2) Generalized interference τ doi is time-varying and unknown, satisfying in is an unknown, bounded constant, defined τ ‾ do = max ( τ ‾ do 1 , . . . , τ ‾ doN ) ;
[0052] (3) There is a positive con...
specific Embodiment approach 2
[0073] Step 3 of the present embodiment provides the specific implementation process of the weighted adjacency matrix A and the Laplacian matrix in the directed graph graph theory of the satellite formation system as follows:
[0074] ν F ={1,…,N} is the set of following stars, ν L ={N+1,…,N+m} is the set of pilot stars, and the set of satellite formation system is ν=ν L ∪ν F ;
[0075] The communication topology between formation satellites is represented by a directed graph G=(ν,ε), where ν is the set of all nodes, is the set of all edges; for formation satellites i and j, edge (ν i ,ν j )∈ε means that formation satellite j can receive information from formation satellite i, but the opposite is not necessarily true; node ν i The neighbors of are defined as satisfying (ν j ,ν i ) ∈ ε relation of all formation satellites j set, denoted as N i ={ν j :(ν j ,ν i )∈ε};
[0076] The weighted adjacency matrix A of the directed graph G=[a ij ], if (v j ,v i ) ∈ ε the...
specific Embodiment approach 3
[0086] The specific implementation process of step 4 of this embodiment is as follows:
[0087] First define the following error function
[0088] e i 1 x = Σ j 1 ∈ v F a i 1 j 1 ( p i 1 - p j 1 ) + Σ j 2 ∈ v L a i ...
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Abstract
The invention relates to a formation satellite configuration containment control method, in particular, a formation satellite finite-time configuration containment control method. The objective of the invention is to solve the problem of low robustness of an existing multiple-satellite system formation control method and the problem of incapability of completely adapting to a practical application environment which is caused by a situation that inter-satellite communication topology is an undirected graph in the existing multiple-satellite system formation control method. The formation satellite finite-time configuration containment control method includes the following steps that: a relative orbit dynamic model of formation satellites i of a satellite formation system and relative reference points is established according to an established relative motion dynamic equation of reference satellites and accompanying satellites, and is simplified as an expression described in the descriptions; a weighted adjacent matrix A and a Laplacian matrix in the graph theory of a directed graph in the satellite formation system are provided according to the formation types of the formation satellites i; and a distributed finite-time configuration containment control laws of the multi-dynamic-pilot-satellite satellite formation system are designed, and therefore, each following satellite can achieve at a configuration convex hull formed by pilot satellites in finite time, and formation satellite finite-time configuration containment control can be realized. The formation satellite finite-time configuration containment control method of the invention is applicable to the control field of formation satellite configuration.
Description
technical field [0001] The invention relates to a control method for formation satellite configuration inclusion. Background technique [0002] Since the Soviet Union launched the first artificial earth satellite in 1957, making the dream of human beings into space a reality, after more than 50 years of development, aerospace technology has become one of the most influential high-level technologies in modern science and technology. The political, economic, military and all aspects of human life have had a wide and far-reaching impact. These satellites are used in all aspects of human life, such as communication satellites, weather satellites, military reconnaissance satellites, deep space exploration, etc. However, with the continuous development of aerospace technology, space missions are becoming more and more diverse, making a single satellite larger in size and more complex in structure to adapt to changing environments. Moreover, once a certain structure of the satell...
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