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Electric Sail Performance Analysis

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TLDR
In this article, the minimum-time rendezvous/transfer problem between circular and coplanar orbits is considered, and an optimal steering law is found using an indirect approach, and the main differences between electric sail and solar sail performances are also emphasized.
Abstract
These values render the electric sail a potentially competitive propulsion means for future mission applications The aim of this paper is to provide a preliminary analysis of the electric sail performance and to investigate the capabilities of this propulsion system in performing interplanetary missions To this end, the minimum-time rendezvous/transfer problem between circular and coplanar orbits is considered, and an optimal steering law is found using an indirect approach The main differences between electric sail and solar sail performances are also emphasized

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Journal ArticleDOI

Electric Sail Mission Analysis for Outer Solar System Exploration

TL;DR: The Interstellar Heliopause Probe mission is used as a reference mission to further quantify the electric sail capabilities for an optimal transfer towards the heliopause nose (200 AU), and a medium performance electric sail is shown to have the potentialities to reach the heliosheath in about fifteen years.
Journal ArticleDOI

Non-Keplerian orbits for electric sails

TL;DR: In this paper, the authors analyzed the electric sail capabilities of generating a class of displaced non-Keplerian orbits, useful for the observation of the Sun's polar regions, using an indirect approach.
Journal ArticleDOI

Electric solar wind sail mass budget model

TL;DR: In this paper, a mass breakdown and a performance model for an E-sail spacecraft that hosts a mission-specific payload of prescribed mass is presented, in particular, the model is able to estimate the total spacecraft mass and its propulsive acceleration as a function of various design parameters such as the number of tethers and their length.
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Increased electric sail thrust through removal of trapped shielding electrons by orbit chaotisation due to spacecraft body

TL;DR: In this paper, physical arguments and test particle calculations indicate that in a realistic three-dimensional electric sail spacecraft there exist a natural mechanism which tends to remove the trapped electrons by chaotising their orbits and causing them to eventually collide with the conducting tethers.
References
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Book

Applied optimal control

Journal ArticleDOI

Solar wind flow about the terrestrial planets 1. Modeling bow shock position and shape

TL;DR: In this paper, a three-parameter method for modeling the position and shape of planetary bow waves was chosen to model the near portion of the Venus, earth and Mars bow shocks, and its results were compared with those of models using one to six free variables.
Journal ArticleDOI

Electric Sail for Spacecraft Propulsion

TL;DR: Chinzei et al. as mentioned in this paper investigated the effects of injector geometry on Scramjet Combustor performance and found that injector geometrical geometry has a negative effect on ScRAMJET performance.
Book

Space sailing

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