Trajectory correction for lunar flyby transfers to libration point orbits using continuous thrust

Qi, Yi; Ruiter, Anton de

doi:10.1007/s42064-020-0097-2

Cited by 8 publications

(5 citation statements)

References 26 publications

(43 reference statements)

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“…For functional requirements of communication, navigation and positioning, timing, information services, scientific detection, and expanded applications of the comprehensive constellation, focusing on achieving full-month communication coverage and supporting subsequent unmanned and manned lunar exploration and other mission requirements, the Earth-Moon integrated constellation system track plan design and plan iteration optimization should be developed. Yi Qi et al investigated trajectory corrections for lunar flyby transfers to Sun-Earth/Moon libration point orbits (LPOs) with continuous thrusts using an ephemeris model [104]. Muralidharan et al investigated stretching directions in cislunar space to apply to departures and transfer design [105].…”

Section: High-precision Dynamic Modelmentioning

confidence: 99%

Summary of Lunar Constellation Navigation and Orbit Determination Technology

Zhang,

Sun,

Chen

et al. 2024

Aerospace

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The Moon is the closest celestial body to the Earth. Its rich unique resources are an important supplement to the Earth’s resources and have a profound impact on the sustainable development of human society. As large-scale exploration missions gradually progress, demands for communication, navigation, surveying and other services of lunar-space probes have significantly increased. Constellation navigation and orbit determination technology will become an indispensable part of future lunar exploration infrastructure. This article systematically analyzes the current status of lunar relay navigation satellite networks at home and abroad, summarizes the technical principles of single-satellite and constellation navigation and orbit determination, discusses the technical difficulties in lunar navigation constellation orbit determination and navigation, and analyzes possible solutions. Finally, the development trend of research on high-precision orbit determination and navigation methods for lunar navigation constellations is proposed.

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Section: High-precision Dynamic Modelmentioning

confidence: 99%

Summary of Lunar Constellation Navigation and Orbit Determination Technology

Zhang,

Sun,

Chen

et al. 2024

Aerospace

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“…Then, the unit vectors of the B-plane coordinate system S, R, and T are calculated by Equation (25). The target B-plane parameters BT t and BR t are calculated by replacing B with B t in Equation (26).…”

Section: Design Of Lunar Swingbymentioning

confidence: 99%

“…It is obvious that the optimal transfer design of heliocentric formation reduces the fuel requirement for the GW observation mission. To achieve this purpose, a practical approach is to fully consider and exploit the effects of multi-body dynamics [24,25]. However, among the existing studies on the transfer design of the GW detectors, most are based on the two-body dynamical model, but few consider multi-body effects.…”

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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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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“…To avoid solving the Riccati equation repetitively in the classic LQR control, Nazari et al [31] combined the backstepping technique with the LQR control in the station-keeping of halo orbits. Qi and Ruiter [32,33] extended this technique to halo orbits, vertical Lyapunov orbits, Lissajous orbits, and transfer orbits in the ephemeris model, and more practical constraints are included in their investigations. As a representative station-keeping strategy with impulsive thrust in the second category, the target point approach was developed by Howell and Pernicka [34].…”

Section: Introductionmentioning

confidence: 99%

Continuous-Thrust Station-Keeping of Cis-Lunar Orbits Using Optimal Sliding Mode Control with Practical Constraints

Zhang

2022

International Journal of Aerospace Engineering

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The cis-lunar space has been more and more attractive for human beings, and different kinds of missions have been proposed. For cis-lunar missions with long durations, the stationing-keeping is a pivotal problem. In this paper, the station-keeping problem with continuous thrust for different cis-lunar orbits, including distant retrograde orbits (DROs), near rectilinear halo orbits (NRHOs), and halo orbits, are investigated in the ephemeris model. The optimal sliding mode control (OSMC) based on the linear quadrant regulator (LQR) control is designed for the station-keeping problem. Simulations only considering the initial insertion error are conducted first to show performances of the OSMC controller, and the Jupiter gravity and solar radiation pressure (SRP) are then included as unknown perturbations to test the controller’s robustness. Then, with considerations of more practical constraints caused by the navigation and propulsion systems, Monte-Carlo simulations are carried out to provide more realistic results, and station-keeping performances are compared and analyzed for different nominal orbits. The results can provide useful references for the selection of station-keeping strategy in future long-term lunar missions.

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Trajectory correction for lunar flyby transfers to libration point orbits using continuous thrust

Cited by 8 publications

References 26 publications

Summary of Lunar Constellation Navigation and Orbit Determination Technology

Summary of Lunar Constellation Navigation and Orbit Determination Technology

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

Continuous-Thrust Station-Keeping of Cis-Lunar Orbits Using Optimal Sliding Mode Control with Practical Constraints

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