Low-Thrust Variable-Specific-Impulse Transfers and Guidance to Unstable Periodic Orbits

Senent, Juan; Ocampo, Cesar A.; Capella, Antonio

doi:10.2514/1.6398

Cited by 63 publications

(35 citation statements)

References 9 publications

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“…Thanks to numerical efficiency, each BVP has been solved in fractions of a second. Furthermore, the LMPM has been applied to solve an open problem in astrodynamics (Senent et al 2005) concerning the design of trajectories reaching the halo orbits by combining low thrust and invariant manifolds. The associated optimal control problem, stated by the Euler-Lagrange system of equations, have been solved comfortably.…”

Section: Final Remarksmentioning

confidence: 99%

A sixth-order accurate scheme for solving two-point boundary value problems in astrodynamics

Armellín

Topputo

2006

Celestial Mech Dyn Astr

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A sixth-order accurate scheme is presented for the solution of ODE systems supplemented by two-point boundary conditions. The proposed integration scheme is a linear multi-point method of sixth-order accuracy successfully used in fluid dynamics and implemented for the first time in astrodynamics applications. A discretization molecule made up of just four grid points attains a O(h 6) accuracy which is beyond the first Dahlquist's stability barrier. Astrodynamics applications concern the computation of libration point halo orbits, in the restricted three- and four-body models, and the design of an optimal control strategy for a low thrust libration point mission

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Section: Final Remarksmentioning

confidence: 99%

A sixth-order accurate scheme for solving two-point boundary value problems in astrodynamics

Armellín

Topputo

2006

Celestial Mech Dyn Astr

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“…Recently, some works present a method to derive optimal low-thrust orbits in n-body dynamical frameworks using invariant manifolds as first guess solutions for low-thrust trajectories (Anderson and Lo 2009), later on optimised with sophisticated algorithms (Whiffen and Sims 2002). Moreover, low-thrust propulsion has been used within the restricted three-body problem to design interplanetary transfers (Dellnitz et al 2006(Dellnitz et al , 2007Mingotti and Gurfil 2010;Mingotti et al 2011a), transfers to the Moon (Mingotti et al 2007(Mingotti et al , 2009aMingotti 2010;Mingotti and Topputo 2011;Pierson and Kluever 1994;Kluever and Pierson 1995;Herman and Conway 1998;Yang 2007) and transfers to LPOs (both in the Sun-Earth and Earth-Moon systems) (Starchville 1997;Topputo 2007;Mingotti et al 2007;Ozimek and Howell 2010;Martin et al 2010;Sukhanov and Eismont 2002;Senent et al 2005) The latter take advantage of the three-body dynamics, where lowthrust orbits have to target a point belonging to the stable manifold associated to the final orbit.…”

Section: Introductionmentioning

confidence: 99%

Combined low-thrust propulsion and invariant manifold trajectories to capture NEOs in the Sun–Earth circular restricted three-body problem

Mingotti

Sánchez

McInnes

2014

Celest Mech Dyn Astr

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In this paper, a method to capture near-Earth objects (NEOs) incorporating low-thrust propulsion into the invariant manifolds technique is investigated. Assuming that a tugboat-spacecraft is in a rendez-vous condition with the candidate asteroid, the aim is to take the joint spacecraft-asteroid system to a selected periodic orbit of the Sun–Earth restricted three-body system: the orbit can be either a libration point periodic orbit (LPO) or a distant prograde periodic orbit (DPO) around the Earth. In detail, low-thrust propulsion is used to bring the joint spacecraft-asteroid system from the initial condition to a point belonging to the stable manifold associated to the final periodic orbit: from here onward, thanks to the intrinsic dynamics of the physical model adopted, the flight is purely ballistic. Dedicated guided and capture sets are introduced to exploit the combined use of low-thrust propulsion with stable manifolds trajectories, aiming at defining feasible first guess solutions. Then, an optimal control problem is formulated to refine and improve them. This approach enables a new class of missions, whose solutions are not obtainable neither through the patched-conics method nor through the classic invariant manifolds technique

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“…This can be achieved with a simple predictor-corrector method. Alternatively, low-thrust propulsion has also been used to find optimal transfers to eight-shaped orbits (Senent et al 2005).…”

Section: By Integrating Andmentioning

confidence: 99%

Natural and sail-displaced doubly-symmetric Lagrange point orbits for polar coverage

Ceriotti

McInnes

2012

Celest Mech Dyn Astr

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This paper proposes the use of doubly-symmetric, eight-shaped orbits in the circular restricted three-body problem for continuous coverage of the high-latitude regions of the Earth. These orbits, for a range of amplitudes, spend a large fraction of their period above either pole of the Earth. It is shown that they complement Sun-synchronous polar and highly eccentric Molniya orbits, and present a possible alternative to low thrust pole-sitter orbits. Both natural and solar-sail displaced orbits are considered. Continuation methods are described and used to generate families of these orbits. Starting from ballistic orbits, other families are created either by increasing the sail lightness number, varying the period or changing the sail attitude. Some representative orbits are then chosen to demonstrate the visibility of high-latitude regions throughout the year. A stability analysis is also performed, revealing that the orbits are unstable: it is found that for particular orbits, a solar sail can reduce their instability. A preliminary design of a linear quadratic regulator is presented as a solution to stabilize the system by using the solar sail only. Finally, invariant manifolds are exploited to identify orbits that present the opportunity of a ballistic transfer directly from low Earth orbit.2

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Low-Thrust Variable-Specific-Impulse Transfers and Guidance to Unstable Periodic Orbits

Cited by 63 publications

References 9 publications

A sixth-order accurate scheme for solving two-point boundary value problems in astrodynamics

A sixth-order accurate scheme for solving two-point boundary value problems in astrodynamics

Combined low-thrust propulsion and invariant manifold trajectories to capture NEOs in the Sun–Earth circular restricted three-body problem

Natural and sail-displaced doubly-symmetric Lagrange point orbits for polar coverage

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