Analytical low-thrust transfer design based on velocity hodograph
Analytical low-thrust transfer design based on velocity hodograph
Shape-based models can be used to approximate low-thrust transfer orbits between celestial bodies. Here, a new model is proposed, which is based on simple analytical base functions that together represent the velocity of the spacecraft. After integration, these base functions also yield analytical expressions for distances traveled. As a result, both the velocity and the trajectory of a transfer can be modeled analytically with a series of such base functions, which can be chosen and scaled at will. Constraints (i.e. conditions on initial and final position and velocity) can be satisfied directly, and a constraint on the final polar angle can be met with a straightforward, fast numerical integration. The technique allows for direct solutions with no degrees of freedom, but also facilitates a more extensive analytical modeling where certain aspects of the resulting transfer trajectory (e.g. required
?V , maximum acceleration) can be optimized. The main characteristics of the technique are illustrated in a number of cases: transfers to Mars and Mercury
Gondelach, D.J.
693aa9ad-3625-4ec6-867c-101fa9c98b00
Noomen, R.
7b04ffa4-6e97-4bf2-a82d-b8b9df511a73
Gondelach, D.J.
693aa9ad-3625-4ec6-867c-101fa9c98b00
Noomen, R.
7b04ffa4-6e97-4bf2-a82d-b8b9df511a73
Gondelach, D.J. and Noomen, R.
(2015)
Analytical low-thrust transfer design based on velocity hodograph.
AAS/AIAA Astrodynamics Specialist Conference,, Vail, United States.
09 - 13 Aug 2015.
20 pp
.
Record type:
Conference or Workshop Item
(Paper)
Abstract
Shape-based models can be used to approximate low-thrust transfer orbits between celestial bodies. Here, a new model is proposed, which is based on simple analytical base functions that together represent the velocity of the spacecraft. After integration, these base functions also yield analytical expressions for distances traveled. As a result, both the velocity and the trajectory of a transfer can be modeled analytically with a series of such base functions, which can be chosen and scaled at will. Constraints (i.e. conditions on initial and final position and velocity) can be satisfied directly, and a constraint on the final polar angle can be met with a straightforward, fast numerical integration. The technique allows for direct solutions with no degrees of freedom, but also facilitates a more extensive analytical modeling where certain aspects of the resulting transfer trajectory (e.g. required
?V , maximum acceleration) can be optimized. The main characteristics of the technique are illustrated in a number of cases: transfers to Mars and Mercury
Text
ANALYTICAL LOW-THRUST TRANSFER DESIGN BASED ON .pdf
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e-pub ahead of print date: 15 August 2015
Venue - Dates:
AAS/AIAA Astrodynamics Specialist Conference,, Vail, United States, 2015-08-09 - 2015-08-13
Organisations:
Aeronautics, Astronautics & Comp. Eng
Identifiers
Local EPrints ID: 404654
URI: http://eprints.soton.ac.uk/id/eprint/404654
PURE UUID: 14461146-64e2-4d9d-8e15-8475144cfc9e
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Date deposited: 16 Jan 2017 14:30
Last modified: 15 Mar 2024 04:13
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Contributors
Author:
D.J. Gondelach
Author:
R. Noomen
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