Orbit period modulation for relative motion using continuous low thrust in the two-body and restricted three-body problems

Arnot, C. S. and McInnes, C. R. and McKay, R. J. and Macdonald, M. and Biggs, J. (2018) Orbit period modulation for relative motion using continuous low thrust in the two-body and restricted three-body problems. Celestial Mechanics and Dynamical Astronomy, 130 (12). ISSN 0923-2958

[img]
Preview
 Text (Arnot-etal-CMDA2017-Orbit-period-modulation-for-relative-motion-using-continuous-low)
Arnot_etal_CMDA2017_Orbit_period_modulation_for_relative_motion_using_continuous_low.pdf
Final Published Version
License: Creative Commons Attribution 4.0 logo
Download (1MB)| Preview

    Abstract

    This paper presents rich new families of relative orbits for spacecraft formation ight generated through the application of continuous thrust with only minimal intervention into the dynamics of the problem. Such simplicity facilitates implementation for small, low-cost spacecraft with only position state feedback, and yet permits interesting and novel relative orbits in both two- and three-body systems with potential future applications in space-based interferometry, hyperspectral sensing, and on-orbit inspection. Position feedback is used to modify the natural frequencies of the linearised relative dynamics through direct manipulation of the system eigenvalues, producing new families of stable relative orbits. Specifically, in the Hill-Clohessy-Wiltshire frame, simple adaptations of the linearised dynamics are used to produce a circular relative orbit, frequency-modulated out-of-plane motion, and a novel doubly-periodic cylindrical relative trajectory for the purposes of on-orbit inspection. Within the circular restricted three-body problem, a similar minimal approach with position feedback is used to generate new families of stable, frequency-modulated relative orbits in the vicinity of a Lagrange point, culminating in the derivation of the gain requirements for synchronisation of the in-plane and out-of-plane frequencies to yield a singly-periodic tilted elliptical relative orbit with potential use as a Lunar far-side communications relay. The deltav requirements for the cylindrical relative orbit and singly-periodic Lagrange point orbit are analysed, and it is shown that these requirements are modest and feasible for existing low-thrust propulsion technology.

    Creators(s): Arnot, C. S. ORCID logoORCID: https://orcid.org/0000-0003-3051-6270, McInnes, C. R., McKay, R. J., Macdonald, M. ORCID logoORCID: https://orcid.org/0000-0003-4499-4281 and Biggs, J.;
    Item type:Article
    ID code:62397
    Keywords:non-Keplerian orbits, continuous low thrust, relative spacecraft motion, orbit period modulation, Hill-Clohessy-Wiltshire equations, restricted three-body problem, Mechanical engineering and machinery, Mechanical Engineering
    Subjects:Technology > Mechanical engineering and machinery
    Department:Faculty of Engineering > Mechanical and Aerospace Engineering
    Technology and Innovation Centre > Advanced Engineering and Manufacturing
    Depositing user: Pure Administrator
    Date deposited:21 Nov 2017 12:27
    Last modified:25 May 2020 04:55
    Related URLs:
    URI:https://strathprints.strath.ac.uk/id/eprint/62397
    Export data:
    CORE (COnnecting REpositories)