Add to ORKGAbstract: In this work, two direct methods of low-thrust trajectory optimization are implemented and compared. The first method is based on optimization of the thrust acceleration, whereas the second method optimizes the impulses that approximate the thrust arcs. The methods are applied to the sample problem of a transfer from the Earth to Mars. The results are obtained on a personal computer in MATLAB and on a multiprocessing computing system.Note: Research direction:Theoretical and applied problems of mechanic
The indirect optimization method, which has been used at the Politecnico di Torino to compute the tr...
Scientists involved in space exploration are always looking for ways to accomplish more with their l...
Low-thrust interplanetary spacecraft trajectory optimization poses a uniquely difficult problem to s...
The application of the usual optimization techniques to the computation of low thrust interplanetary...
The application of the usual optimization techniques to the computation of low thrust interplanetary...
Due to the character of the original source materials and the nature of batch digitization, quality ...
A tool developed for the preliminary design of low-thrust trajectories is described. The trajectory ...
The spacecraft trajectory design process frequently includes the optimization of a quantity of impor...
Optimization of low thrust Earth transference orbits suppose a great mathematical and computational...
The design of interplanetary trajectories requires the solution of an optimization problem typically...
International audienceTrajectory optimization has always been of great interest in space exploration...
The aim of this thesis is to provide a number of tools and methodologies that allow the designer to ...
The optimal control problem of the spacecraft (SC) interplanetary transfer from the Earth to Mars is...
Low-thrust propulsion systems are growing in popularity for both Earth orbiting satellites and scien...
Low-thrust propulsion systems are growing in popularity for both Earth orbiting satellites and scien...
The indirect optimization method, which has been used at the Politecnico di Torino to compute the tr...
Scientists involved in space exploration are always looking for ways to accomplish more with their l...
Low-thrust interplanetary spacecraft trajectory optimization poses a uniquely difficult problem to s...
The application of the usual optimization techniques to the computation of low thrust interplanetary...
The application of the usual optimization techniques to the computation of low thrust interplanetary...
Due to the character of the original source materials and the nature of batch digitization, quality ...
A tool developed for the preliminary design of low-thrust trajectories is described. The trajectory ...
The spacecraft trajectory design process frequently includes the optimization of a quantity of impor...
Optimization of low thrust Earth transference orbits suppose a great mathematical and computational...
The design of interplanetary trajectories requires the solution of an optimization problem typically...
International audienceTrajectory optimization has always been of great interest in space exploration...
The aim of this thesis is to provide a number of tools and methodologies that allow the designer to ...
The optimal control problem of the spacecraft (SC) interplanetary transfer from the Earth to Mars is...
Low-thrust propulsion systems are growing in popularity for both Earth orbiting satellites and scien...
Low-thrust propulsion systems are growing in popularity for both Earth orbiting satellites and scien...
The indirect optimization method, which has been used at the Politecnico di Torino to compute the tr...
Scientists involved in space exploration are always looking for ways to accomplish more with their l...
Low-thrust interplanetary spacecraft trajectory optimization poses a uniquely difficult problem to s...