Low thrust transfer optimisation of satellites formations to heliocentric Earth trailing orbits through a gradient restoration algorithm

Bastante, J. C.; Caramagno, Augusto; Peñín, Luis F.; Belló-Mora, Miguel; Rodríguez-Canabal, J.

doi:10.1016/j.actaastro.2004.05.035

Cited by 7 publications

(4 citation statements)

References 2 publications

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“…In the original LISA mission, the total velocity increment of three main transfer maneuvers in 16 months of transfer duration is estimated between 1.5∼2.1 km/s [18]. Bastante et al proposed a transfer strategy of five impulses for adjusting the inclination, eccentricity, and phase angle to give a solution guess for solving the low-thrust transfer optimization problem through a gradient restoration algorithm [19]. Sweetser analyzed the end-to-end impulsive transfer process of a constellation of three spacecraft launched together into a heliocentric orbit trailing the Earth's orbit by 20 degrees [20].…”

Section: Introductionmentioning

confidence: 99%

“…The adaptive model continuation technique is proposed in this paper to obtain quantitatively the influence of each perturbation on the velocity increment of the transfer. On the other hand, most existing studies have only completed the design of heliocentric transfer orbits, assuming that the starting of the transfer is on the Earth escape orbit [19,20,23]. However, the transfer within the Earth's sphere of influence (SOI) should be elaborately designed to reduce the overall launch and transfer costs [28], especially to increase the energy to escape the Earth's SOI by the lunar swingby [29][30][31].…”

Section: Introductionmentioning

confidence: 99%

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Low-Energy Transfer Design of Heliocentric Formation Using Lunar Swingby on the Example of LISA

et al. 2022

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Space-based gravitational wave (GW) detection at low frequencies is of great scientific significance and has received extensive attention in recent years. This work designs and optimizes the low-energy transfer of the heliocentric formation of GW detectors, which starts from a geosynchronous transfer orbit and targets an Earth-like orbit. Based on the example of the Laser Interferometer Space Antenna (LISA), the transfer is first designed in two-body dynamical models and then refined in simplified high-fidelity dynamical models that only consider the major orbital perturbations evaluated here. The main contributions of this work are to present an adaptive model continuation technique and to exploit the lunar swingby technique to reduce the problem-solving difficulty and velocity increment of orbital transfer, respectively. The adaptive model continuation technique fully reveals the effect of perturbations and rapidly iterates the solutions to the simplified models. The simulation results show that the lunar swingby does reduce the energy needed to escape the Earth’s sphere of influence. It is found that the gravitation of the Earth–Moon system has a significant contribution to reducing the velocity increment. The solution of low-energy transfer in the simplified models is that the duration is 360.6615 days and the total velocity increment is 0.8468 km/s.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Low-Energy Transfer Design of Heliocentric Formation Using Lunar Swingby on the Example of LISA

et al. 2022

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“…Reduced mission costs by working out the optimal paths for low-thruster have been one of the traditional solutions for space missions. 16,17 Spacecrafts that use low-thrust propulsions are generally lighter than those that employ common chemical propulsions. It should be noted that these thrusters may not be used for strong single-impulse maneuvers.…”

Section: Introductionmentioning

confidence: 99%

Introducing a novel algorithm for minimum-time low-thrust orbital transfers with free initial condition

Shafieenejad

Novinzadeh

Molazadeh

2014

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this work, a new algorithm is presented with regard to the free initial condition for solving optimal control problems. The reason for presentation of such an algorithm is to develop a suitable method that simplifies difficulties of the optimal control problems that researchers face in common methods of optimal control theory. Also, initial condition as true anomaly is considered to be free in this optimal control problem. To do so, issues such as optimal control theory, orthogonal functions in the Hilbert space, and evolutionary optimizations such as genetic algorithm-particle swarm optimization and imperial competition algorithm are utilized. The algorithm was solved for low-thrust orbital transfer problems which included nonlinear dynamic equations. To validate the algorithm, simplified Edelbaum low-thrust equations are compared with the proposed analytical solutions. Next, the algorithm is investigated for the low-thrust orbital transfers with respect to the equinoctial orbital equations of the minimum-time problem. Results are achieved for two evolutionary optimization methods genetic algorithm-particle swarm optimization and imperial competition algorithm and three orthogonal functions such as Fourier, Chebyshev, and Legendre. Two optimization methods and three orthogonal functions are covered and compared precisely. With respect to the results, this algorithm has the capability to overcome difficulties of the optimal control problems and can be considered as a novelty in this field for the free initial condition problems.

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“…The evolution of low-thrust propulsion technologies has reached a point where such systems have become an economical option for many space mission applications. Also, the development of efficient control laws has received an increasing amount of attention in recent years, and finally a number of studies have examined the subject of inclination changing manoeuvers [1][2][3].…”

Section: Introductionmentioning

confidence: 99%

Analytical solutions for two-point boundary value problems: Optimal low-thrust orbit transfers

Shafieenejad

Novinzadeh

2010

Proceedings of the Institution of Mechanical Engineers, Part G:

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A new guidance scheme for the problem of low-thrust transfer between inclined orbits is developed within the framework of optimal control theory. The objective of the guidance scheme is to provide the appropriate thrust steering program that will transfer the vehicle from inclined low earth orbits to high earth orbits. The presented guidance scheme is determined using Pontryagin's principle such that three desired performance measures are minimized and boundary conditions for this unspecified final time problem are satisfied. One of the novelties of this work is changing the independent variable from time to thrust angle and considering properties of autonomous system equations to reduce to one where an exact analytical solution is obtained. Finally, three performance measure results are compared and the best policy is proposed.

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Low thrust transfer optimisation of satellites formations to heliocentric Earth trailing orbits through a gradient restoration algorithm

Cited by 7 publications

References 2 publications

Low-Energy Transfer Design of Heliocentric Formation Using Lunar Swingby on the Example of LISA

Low-Energy Transfer Design of Heliocentric Formation Using Lunar Swingby on the Example of LISA

Introducing a novel algorithm for minimum-time low-thrust orbital transfers with free initial condition

Analytical solutions for two-point boundary value problems: Optimal low-thrust orbit transfers

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