Correction of spacecraft trajectory during its transition into circular satellite orbit using atmospheric braking with uncertain atmospheric parameters

The current stage of space exploration is characterized by complication of the problems being solved in space that require quite cumbersome auxiliary systems and tools. A considerable mass of fuel is consumed during the spacecraft transition from the planet gravitation assist trajectory into the planet satellite orbit. The use of an intermediate elliptical orbit with the pericenter located in the planet’s upper atmosphere can reduce the fuel consumption. The article is devoted to the use of the planet’s atmosphere for slowing down the spacecraft during its transition into the satellite orbit with uncertain atmospheric parameters.

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