Preliminary Design of Debris Removal Missions by Means of Simplified Models for Low-Thrust, Many-Revolution Transfers
This paper presents a novel approach for the preliminary design of Low-Thrust, many-revolution transfers. The main feature of the novel approach is a considerable reduction in the control parameters and a consequent gain in computational speed. Each spiral is built by using a predefined pattern for...
Saved in:
| Main Authors: | , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
Wiley
2012-01-01
|
| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2012/836250 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| _version_ | 1849469478970064896 |
|---|---|
| author | Federico Zuiani Massimiliano Vasile |
| author_facet | Federico Zuiani Massimiliano Vasile |
| author_sort | Federico Zuiani |
| collection | DOAJ |
| description | This paper presents a novel approach for the preliminary design of Low-Thrust, many-revolution transfers. The main feature of the novel approach is a considerable reduction in the control parameters and a consequent gain in computational speed. Each spiral is built by using a predefined pattern for thrust direction and switching structure. The pattern is then optimised to minimise propellant consumption and transfer time. The variation of the orbital elements due to the thrust is computed analytically from a first-order solution of the perturbed Keplerian motion. The proposed approach allows for a realistic estimation of ΔV and time of flight required to transfer a spacecraft between two arbitrary orbits. Eccentricity and plane changes are both accounted for. The novel approach is applied here to the design of missions for the removal of space debris by means of an Ion Beam Shepherd Spacecraft. In particular, two slightly different variants of the proposed low-thrust control model are used for the different phases of the mission. Thanks to their low computational cost they can be included in a multiobjective optimisation problem in which the sequence and timing of the removal of five pieces of debris are optimised to minimise propellant consumption and mission duration. |
| format | Article |
| id | doaj-art-fda9afd86fa94530a48d910eafda6ba9 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2012-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-fda9afd86fa94530a48d910eafda6ba92025-08-20T03:25:27ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742012-01-01201210.1155/2012/836250836250Preliminary Design of Debris Removal Missions by Means of Simplified Models for Low-Thrust, Many-Revolution TransfersFederico Zuiani0Massimiliano Vasile1School of Engineering, University of Glasgow, James Watt South Building, Glasgow G12 8QQ, UKDepartment of Mechanical & Aerospace Engineering, University of Strathclyde, 75 Montrose Street, Glasgow G1 1XJ, UKThis paper presents a novel approach for the preliminary design of Low-Thrust, many-revolution transfers. The main feature of the novel approach is a considerable reduction in the control parameters and a consequent gain in computational speed. Each spiral is built by using a predefined pattern for thrust direction and switching structure. The pattern is then optimised to minimise propellant consumption and transfer time. The variation of the orbital elements due to the thrust is computed analytically from a first-order solution of the perturbed Keplerian motion. The proposed approach allows for a realistic estimation of ΔV and time of flight required to transfer a spacecraft between two arbitrary orbits. Eccentricity and plane changes are both accounted for. The novel approach is applied here to the design of missions for the removal of space debris by means of an Ion Beam Shepherd Spacecraft. In particular, two slightly different variants of the proposed low-thrust control model are used for the different phases of the mission. Thanks to their low computational cost they can be included in a multiobjective optimisation problem in which the sequence and timing of the removal of five pieces of debris are optimised to minimise propellant consumption and mission duration.http://dx.doi.org/10.1155/2012/836250 |
| spellingShingle | Federico Zuiani Massimiliano Vasile Preliminary Design of Debris Removal Missions by Means of Simplified Models for Low-Thrust, Many-Revolution Transfers International Journal of Aerospace Engineering |
| title | Preliminary Design of Debris Removal Missions by Means of Simplified Models for Low-Thrust, Many-Revolution Transfers |
| title_full | Preliminary Design of Debris Removal Missions by Means of Simplified Models for Low-Thrust, Many-Revolution Transfers |
| title_fullStr | Preliminary Design of Debris Removal Missions by Means of Simplified Models for Low-Thrust, Many-Revolution Transfers |
| title_full_unstemmed | Preliminary Design of Debris Removal Missions by Means of Simplified Models for Low-Thrust, Many-Revolution Transfers |
| title_short | Preliminary Design of Debris Removal Missions by Means of Simplified Models for Low-Thrust, Many-Revolution Transfers |
| title_sort | preliminary design of debris removal missions by means of simplified models for low thrust many revolution transfers |
| url | http://dx.doi.org/10.1155/2012/836250 |
| work_keys_str_mv | AT federicozuiani preliminarydesignofdebrisremovalmissionsbymeansofsimplifiedmodelsforlowthrustmanyrevolutiontransfers AT massimilianovasile preliminarydesignofdebrisremovalmissionsbymeansofsimplifiedmodelsforlowthrustmanyrevolutiontransfers |