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The trajectory is optimised to maximise the number of visited asteroids of the Atira group using the minimum propellant consumption.
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For both propulsion strategies, minimum propellant pole-sitter orbits are designed.
A significant reduction in total propellant consumption in comparison with a baseline benchmark solution is observed.
The same difference could also be achieved using only 44 g of propellant in 245 days for the minimum propellant trajectory.
On the other hand, the conventional PPT has the following problems: contamination, low thrust performance and non-uniform propellant consumption.
We evaluate this strategy in terms of its propellant consumption compared to the rhumb-line control method.
The transfers between asteroids are designed using a low-thrust analytical model that provides a good estimation of the propellant consumption and transfer time.
This problem can be seen as a Time-Dependant Traveling Salesman Problem (TDTSP) with two objective functions to minimize: the total mission duration and the total propellant consumption.
The disposal design is formulated as a multi-objective optimization problem in order to take into account other goals in addition to propellant consumption minimization.
Three different simulations were studied, defined as the minimum time trajectory, minimum propellant trajectory and a hybrid trajectory, consisting of reaching a higher altitude orbit, but actively changing the RAAN using the propulsion system instead of drifting.
An in-depth analysis of the results is carried out to understand the conditions leading to a fast reentry with minimum propellant.
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