Linearization methods for optimizing the low thrust spacecraft trajectory: Theoretical aspects

The theoretical aspects of the modified linearization method, which makes it possible to solve a wide class of nonlinear problems on optimizing low-thrust spacecraft trajectories (V. V. Efanov et al., 2009; V. V. Khartov et al., 2010) are examined. The main modifications of the linearization method are connected with its refinement for optimizing the main dynamic systems and design parameters of the spacecraft.     

Linearization Methods for Problems of Optimizing Low-Thrust Spacecraft Trajectories: Test Problem Solutions

Several test problems are solved with the modified linearization method (MLM) demonstrating its features and possibilities.     

Linearization Methods for Problems of Optimizing Low-Thrust Spacecraft Trajectories: Verification Procedure

Several well-studied problems for optimizing low-thrust spacecraft trajectories are solved using the modified linearization method (MLM). The results are compared with the results obtained by other authors. On this basis, conclusions are drawn on the possible use of the modified linearization method for optimizing low-thrust spacecraft trajectories.     

Linearization Method for Optimizing Noncoplanar Flights with Low Thrust

Solar System Research - Problems on optimizing the noncoplanar flights with low thrust from elliptical to geosynchronous orbits for different control accelerations are solved. Recommendations for...