Control Strategies for Formation Flight In the Vicinity of the Libration Points

Marchand, Belinda G.; Howell, Kathleen C.

doi:10.2514/1.11016

Cited by 51 publications

(24 citation statements)

References 15 publications

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“…In regard to the planetary orbit scenario, an example of formation is the pair of satellites Landsat 7 with EO-1, mission designed to enable the development of future Earth imaging observatories that will have a signicant increase in performance while reducing cost and mass (Flick, 2012). For outer space scenario, there exists interest of major space agencies to position SFF in halo orbits around Lagrangian points L 1 and L 2 (Farquhar, 1968;Gómez et al, 2001a;Howell and Marchand, 2005;Marchand and Howell, 2005;Héritier and Howell, 2014) or L 4 and L 5 (Simó et al, 1987). An interesting example of this kind of formation ying mission is the New Worlds Observer (NWO) (Cash et al, 2009).…”

Section: Introductionmentioning

confidence: 99%

“…In the case of non-natural formations, Howell and Marchand (2005) use continuous and discrete control strategies to maintain the formations near the L 1 and L 2 libration points in the Sun-Earth/Moon ephemeris system. Similarly, Marchand and Howell (2005) provide a decentralized control strategy based on existing linear and nonlinear techniques.…”

Section: Introductionmentioning

confidence: 99%

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Zero drift regions and control strategies to keep satellite in formation around triangular libration point in the restricted Sun–Earth–Moon scenario

Salazar

Winter

Macau

et al. 2015

Advances in Space Research

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Assume that a group of two or more satellites are ying close a given nominal trajectory around Earth-Moon triangular point, in such a way that, there is some freedom in the selection of the geometry of the constellation. We are interested in avoiding large variations of the mutual distances between spacecraft and controlling the conguration of the formation. Previous studies about triangular libration points have determined the existence of regions of zero relative radial acceleration with respect to the nominal trajectory that prevent from the expansion or contraction of the formation. In this work, we carry out two dierent control strategies for a formation near a given nominal trajectory around L4: a bang-o-bang control and a minimum weighted total ∆V consumption. This study involves a linear approximation of the equations of motion relative to the bounded solutions around the triangular libration point, and it considers dierent geometrical possibilities in the zero drift regions. To investigate the inuence of the gravitational force of the Sun, the Bicircular Four Body Problem is studied. According to the results obtained, some suggestions on the design of the geometric conguration in the formation are given.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Zero drift regions and control strategies to keep satellite in formation around triangular libration point in the restricted Sun–Earth–Moon scenario

Salazar

Winter

Macau

et al. 2015

Advances in Space Research

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“…Interest in libration point formations has motivated significant work [42][43][44][45][46][47][48][49][50][51][52][53][54][55][56][57][74][75][76][77] to characterize and negotiate this unstable and highly sensitive regime. For interferometry missions, the formation requirements are even more restrictive, and existing literature highlights the difficulties in designing trajectories and control strategies to effectively operate in this en- In summary, the work to date can be characterized by…”

Section: B12 Libration Point Trajectories and Formationsmentioning

confidence: 99%

“…Interest in space-based interferometry has motivated many investigations [42][43][44][45][46][47][48][49][50][51][52][53][54][55][56][57] into the feasibility of spacecraft formations near the libration points of the SunEarth/Moon system. A survey of many of these efforts is provided for refererence in Appendix B.…”

Section: Motivationmentioning

confidence: 99%

Finite Set Control Transcription for Optimal Control Applications

Stanton

2010

Journal of Spacecraft and Rockets

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“…For outer space scenario, there exists interest of major space agencies to position SFF in halo orbits around Lagrangian points L 1 and L 2 (Faquar, 1968;Gómez et al, 2001a;Howell and Marchand, 2005;Marchand and Howell, 2005;Héritier and Howell, 2014) or L 4 and L 5 (Simó et al, 1987). In the case of Earth-Moon system, L 4 and L 5 points could be excellent locations to place space telescopes for astronomical observations or a space station (Schutz, 1977).…”

Section: Introductionmentioning

confidence: 99%

Natural formations at the Earth–Moon triangular point in perturbed restricted problems

Salazar

Winter

Macau

et al. 2015

Advances in Space Research

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Previous studies for small formation flying dynamics about triangular libration points have determined the existence of regions of zero and minimum relative radial acceleration with respect to the nominal trajectory, that prevent from the expansion or contraction of the constellation. However, these studies only considered the gravitational force of the Earth and the Moon using the Circular Restricted Three Body Problem (CRTBP) scenario. Although the CRTBP model is a good approximation for the dynamics of spacecraft in the Earth-Moon system, the nominal trajectories around equilateral libration points are strongly affected when the primary orbit eccentricity and solar gravitational force are considered. In this manner, the goal of this work is the analysis of the best regions to place a formation that is flying close a bounded solution around L 4 , taking into account the Moon's eccentricity and Sun's gravity. This model is not only more realistic for practical engineering applications but permits to determine more accurately the fuel consumption to maintain the geometry of the formation.

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Control Strategies for Formation Flight In the Vicinity of the Libration Points

Cited by 51 publications

References 15 publications

Zero drift regions and control strategies to keep satellite in formation around triangular libration point in the restricted Sun–Earth–Moon scenario

Zero drift regions and control strategies to keep satellite in formation around triangular libration point in the restricted Sun–Earth–Moon scenario

Finite Set Control Transcription for Optimal Control Applications

Natural formations at the Earth–Moon triangular point in perturbed restricted problems

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