Patent ID: 11897635
Assignee: SPACE ENGINEERING UNIVERSITY
Field: Transport (Mechanical engineering)
Classification: CPC B  G | IPC B  G

Claim 3:
4. The method for maintaining Walker constellation formation according to claim 2, wherein the step of determining the first drift amount of each satellite at each simulation moment according to the parameters of the Walker constellation further comprises:
determining the first relative drift amount of each satellite at each simulation moment according to a first formula, which is written as:, {
  
   
    
     
      
       
        ΔΩ
        i
       
       =
       
        
         (
         
          
           Ω
           i
          
          -
          
           Ω
           i
           *
          
         
         )
        
        -
        
         
          
           ∑
           
            i
            =
            1
           
           N
          
          
           (
           
            
             Ω
             i
            
            -
            
             Ω
             i
             *
            
           
           )
          
         
         N
        
       
      
     
    
    
     
      
       
        Δ
        ⁢
        
         λ
         i
        
       
       =
       
        
         (
         
          
           λ
           i
          
          -
          
           λ
           i
           *
          
         
         )
        
        -
        
         
          
           ∑
           
            i
            =
            1
           
           
            N
            /
            P
           
          
          
           (
           
            
             λ
             i
            
            -
            
             λ
             i
             *
            
           
           )
          
         
         
          (
          
           N
           /
           P
          
          )
         
        
       
      
     
    
   
   ,
  
 

where ΔΩi is a relative drift amount of a right ascension of ascending node of an ith satellite, Δλj is a relative drift amount of an along-track angle of the ith satellite, Ωi is a right ascension of ascending node of the ith satellite under a perturbative force, λi is an along-track angle of the ith satellite under a perturbative force, Ωi* is a right ascension of ascending node of a nominal orbit of the ith satellite, λi* is an along-track angle of the nominal orbit of the ith satellite, N is the total number of satellites, and P is the number of orbit planes.