Solving complex optimal control problems at no cost with PSOPT

Becerra, Victor M.

doi:10.1109/cacsd.2010.5612676

Cited by 124 publications

(97 citation statements)

References 10 publications

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“…BOCOP [58], ACADO [59], and PSOPT [60] are free C++ implementations of the direct method. MISER [61], DIRCOL [62], SNCTRL [63] , OTIS [64], and POST [65] are free Fortran implementations of the direct method, while GESOP [66] and SOS [67] are commercial Fortran implementations of the direct method.…”

Section: Discussionmentioning

confidence: 99%

Constraint Control of Nonholonomic Mechanical Systems

Putkaradze¹,

Rogers²

2017

J Nonlinear Sci

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We derive an optimal control formulation for a nonholonomic mechanical system using the nonholonomic constraint itself as the control. We focus on Suslov's problem, which is defined as the motion of a rigid body with a vanishing projection of the body frame angular velocity on a given direction ξ. We derive the optimal control formulation, first for an arbitrary group, and then in the classical realization of Suslov's problem for the rotation group SO(3). We show that it is possible to control the system using the constraint ξ(t) and demonstrate numerical examples in which the system tracks quite complex trajectories such as a spiral.

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Section: Discussionmentioning

confidence: 99%

Constraint Control of Nonholonomic Mechanical Systems

Putkaradze¹,

Rogers²

2017

J Nonlinear Sci

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“…PSOPT can deal with endpoint constraints, path constraints, and interior point constraints. Bounds on the states and controls can be enforced, as well as intervals for initial and final states [34]. It makes use of the ADOL-C library for the automatic differentiation of objective, dynamics and constraint functions.…”

Section: Mission Phasesmentioning

confidence: 99%

Mission analysis and systems design of a near-term and far-term pole-sitter mission

et al. 2014

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Mission analysis and systems design of a near-term and far-term pole-sitter mission. Acta Astronautica, 94 (1). pp. [455][456][457][458][459][460][461][462][463][464][465][466][467][468][469] Copyright © 2013 IAA.A copy can be downloaded for personal non-commercial research or study, without prior permission or chargeThe content must not be changed in any way or reproduced in any format or medium without the formal permission of the copyright holder(s) This paper provides a detailed mission analysis and systems design of a near-term and far-term polesitter mission. The pole-sitter concept was previously introduced as a solution to the poor temporal resolution of polar observations from highly inclined, low Earth orbits and the poor high-latitude coverage from geostationary orbit. It considers a spacecraft that is continuously above either the north or south pole and, as such, can provide real-time, continuous and hemispherical coverage of the polar regions. Being on a non-Keplerian orbit, a continuous thrust is required to maintain the pole-sitter position. For this, two different propulsion strategies are proposed, which result in a near-term pole-sitter mission using solar electric propulsion (SEP) and a far-term pole-sitter mission where the SEP thruster is hybridized with a solar sail. For both propulsion strategies, minimum propellant pole-sitter orbits are designed. In order to maximize the spacecraft mass at the start of the operations phase of the mission, the transfer from Earth to the pole-sitter orbit is designed and optimized assuming either a Soyuz or an Ariane 5 launch. The maximized mass upon injection into the pole-sitter orbit is subsequently used in a detailed mass budget analysis that will allow for a trade-off between mission lifetime and payload mass capacity. Also, candidate payloads for a range of applications are investigated. Finally, transfers between north and south pole-sitter orbits are considered to overcome the limitations in observations due to the tilt of the Earth's rotational axis that causes the poles to be alternately situated in darkness. It will be shown that in some cases these transfers allow for propellant savings, enabling a further extension of the pole-sitter mission.

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“…Here, a particular implementation of a direct pseudospectral method is chosen: PSOPT, see (Becerra, 2010 …”

Section: Optimal Control Solvermentioning

confidence: 99%

Optimal solar sail transfers between Halo orbits of different Sun-planet systems

Heiligers¹,

Mingotti²,

McInnes³

2015

Advances in Space Research

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This paper investigates time-optimal solar sail trajectories between Libration Point Orbits (LPOs) of different circular restricted Sun-planet three-body systems. Key in the investigations is the search for transfers that require little steering effort to enable the transfers with low-control authority solar sail-like devices such as SpaceChips. Two transfers are considered: 1) from a Sun-Earth L 2 -Halo orbit to a Sun-Mars L 1 -Halo orbit and 2) from a Sun-Earth L 1 -Halo orbit to a Sun-Mercury L 2 -Halo orbit. The optimal control problem to find these time-optimal transfers is derived, including a constraint to mimic limited steering capabilities, and is solved with a direct pseudospectral method for which novel first guess solutions are developed. For a near-term sail performance comparable to that of NASA's Sunjammer sail, the results show transfers that indeed require very little steering effort: the sail acceleration vector can be bounded to a cone around the Sun-sail line with a half-angle of 7.5 deg. These transfers can serve a range of novel solar sail applications covering the entire spectrum of sail length-scales: micro-sized SpaceChips could establish a continuous Earth-Mars communication link, a traditional-sized sail provides opportunities for in-situ observations of Mercury and a future kilometer-sized sail could create an Earth-Mars cargo transport gateway for human exploration of Mars.

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Solving complex optimal control problems at no cost with PSOPT

Cited by 124 publications

References 10 publications

Constraint Control of Nonholonomic Mechanical Systems

Constraint Control of Nonholonomic Mechanical Systems

Mission analysis and systems design of a near-term and far-term pole-sitter mission

Optimal solar sail transfers between Halo orbits of different Sun-planet systems

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