Systematic low-thrust trajectory design to Mars based on a full Ephemeris modeling

Saghamanesh, Mohammadreza; Taheri, Ehsan; Baoyin, Hexi

doi:10.1016/j.asr.2019.08.013

Cited by 9 publications

(5 citation statements)

References 22 publications

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“…It is worth noting that 𝜆𝜆 0 represents one of the unknown parameters, remaining constant throughout the homotopic algorithm. The application of Pontryagin's minimum principle, in conjunction with primer vector theory, results in the following extremal controls [69]:…”

Section: Low-thrust Trajectory Optimization Descriptionmentioning

confidence: 99%

MeSat Mission: Exploring Martian Environment with THz Radiometer Payload and Optimal Trajectory

Rastinasab,

Hu,

Saghamanesh

et al. 2024

Remote Sensing

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Space exploration presents vast prospects for scientific, industrial, and economic progress. This paper introduces the MeSat mission as a pioneering approach to Mars exploration. The MeSat aims to deepen our understanding of Martian conditions and resources by employing an optimized Earth-to-Mars trajectory, enabling a comprehensive study of the Martian atmosphere and surface. The mission comprises a cargo microsatellite hosting three 6U CubeSats and two 3U CubeSats, deployed into four separate Mars orbits to form a constellation. Each CubeSat carries distinct payloads: a THz radiometer for Martian water vapor atmospheric observation, a high-resolution surface camera, a high-tech spectrometer, and a Fourier transform spectrometer (FTS) for wind speed readings. This paper includes the majority of the key parameters; however, we focus our discussion more on two aspects of this pioneering mission: the first aspect contains the proposal of four distinct payloads for the study of Mars’ atmosphere and the second aspect proposes an optimal mission design algorithm that analyzes a fuel-efficient low-thrust trajectory from Earth to Mars. Regarding the payloads, the THz radiometer requires a specific design; hence, we explain this payload in more depth; the rest of the payloads, we suggest utilizing commercially available elements for the cost-effective manufacture of a whole system. For mission trajectory optimization, the study employs a dual-step hybrid optimization algorithm (PSO-homotopy) to analyze fuel-efficient low-thrust trajectories from Earth to Mars, incorporating the ephemeris dynamics model to account for gravitational perturbations in the entire Solar System. In practical mission design, crucial factors like hyperbolic excess velocity, diverse opportunities for Earth launch and Mars rendezvous, varied propulsion systems, and time of flight (TOF) play vital roles in trajectory optimization. In summary, for the MeSat mission, we propose a comprehensive Mars environmental mission design. We consider all aspects of the mission from trajectory design to engineering detail design, since we would like to inspire future Mars missions with a complete report.

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Section: Low-thrust Trajectory Optimization Descriptionmentioning

confidence: 99%

MeSat Mission: Exploring Martian Environment with THz Radiometer Payload and Optimal Trajectory

Rastinasab,

Hu,

Saghamanesh

et al. 2024

Remote Sensing

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“…( 8), the increment in GA velocity required for the numerical analysis is determined. (34) As previously stated, the constraint embodied in Eq. ( 26) is eliminated from the shooting function delineated in Eq.…”

Section: Numerical Analysismentioning

confidence: 99%

“…Some alternative methods tackle this challenge by initializing co-states through particle swarm optimization (PSO) [21,30], optimal auxiliary unconstrained solutions [31], and the adjoint variable method [32]. Subsequent refinements by Jiang et al [30] and Saghamanesh and Baoyin [21,[33][34][35][36] have further improved this approach using various effective-practical techniques.…”

Section: Introductionmentioning

confidence: 99%

Low-Thrust Trajectory Optimization for Earth-Mars-Jupiter Gravity-Assist Spacecraft Mission

Saghamanesh,

Hu,

Rastinasab

2024

Preprint

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Recent advancements have revolutionized interplanetary spacecraft missions by combining low-thrust propulsion systems with planetary Gravity-Assist (GA) maneuvers. This study investigates/improved a novel dual-step efficient-robust homotopy algorithm, grounded in indirect optimal control principles, to analyze fuel-optimal bang-bang control problems. The methodology integrates efficient techniques, including the homotopic method, compatible normalization, and improved switching function detection, aimed at enhancing optimal convergence in solving low-thrust gravity-assist spacecraft missions. To illustrate practical application, an Earth-to-Jupiter interplanetary scenario utilizing Mars-GA is examined. Results demonstrate the algorithm's superior efficacy in achieving fuel efficiency, robust convergence, and remarkable accuracy compared to existing solutions.

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“…The presented framework is capable of linking with various optimization algorithms for solving spacecraft trajectory optimization problems such as interplanetary transfers [36] and space rendezvous [37]. In this section, a multi-impulse trajectory optimization problem is optimized and simulated to illustrate the capability of this tool.…”

Section: Autonomous Space Rendezvousmentioning

confidence: 99%

Simulation Framework for Orbit Propagation and Space Trajectory Visualization

Shirazi

Ceberio

Lozano

2021

IEEE Aerosp. Electron. Syst. Mag.

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In this paper, an interactive tool for simulation of satellites dynamics and autonomous spacecraft guidance is presented. Different geopotential models for orbit propagation of Earth-orbiting satellites are provided, which consider Earth's gravitational field with various accuracies. The presented software is a 3D visualization platform for space orbit simulation with analytical capabilities through various modules. Taking advantage of a graphical user interface, it can evaluate, analyze and illustrate the motion of satellite based on different orbit propagation schemes. Several cases of satellites and autonomous spacecraft in the space rendezvous mission are simulated regarding different propagation models to demonstrate the performance of the application in space mission analysis, ground track visualization and trajectory optimization. Results are validated by comparing with other state-of-the-art tools, such as AGI System Toolkit (STK).

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Systematic low-thrust trajectory design to Mars based on a full Ephemeris modeling

Cited by 9 publications

References 22 publications

MeSat Mission: Exploring Martian Environment with THz Radiometer Payload and Optimal Trajectory

MeSat Mission: Exploring Martian Environment with THz Radiometer Payload and Optimal Trajectory

Low-Thrust Trajectory Optimization for Earth-Mars-Jupiter Gravity-Assist Spacecraft Mission

Simulation Framework for Orbit Propagation and Space Trajectory Visualization

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