Interplanetary gravity-assist fuel-optimal trajectory optimization with planetary and Solar radiation pressure perturbations

Saghamanesh, Mohammadreza; Taheri, Ehsan; Baoyin, Hexi

doi:10.1007/s10569-020-9955-8

Cited by 4 publications

(4 citation statements)

References 33 publications

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“…In an Ephemeris model, it is essential to take into account perturbing accelerations resulting from: 1) 𝓕 : solar radiation pressure, 2) 𝓕 : oblateness impacts of celestial bodies, and 3) 𝓕 : other celestial bodies of the Solar System. The disturbing accelerations are conceptualized as [28] ( ) where 𝒓 and 𝜇 show the position vector and the gravitational constant of a planet, 𝜕𝑧 𝜕𝒓 ⁄ = [0 0 1] , 𝜑 represents the planet-centric latitude, 𝜎 is a constant flight loading (𝜎=𝑚 𝐴 ⁄ where 𝐴 is the unit area), 𝜎 * is determined as 1.53 (gm -2 ), 𝛽 and 𝒓 signify the solar radiation pressure and the spacecraft position vector, in the Heliocentric Equatorial Reference Frame (HERF). The dynamics system is modeled as follows [28]:…”

Section: System Descriptionmentioning

confidence: 99%

“…The first aspect of this study concerns the design of an optimal Earth-to-Mars mission, which involves identifying launch windows and minimizing fuel consumption while considering various factors and constraints [24][25][26][27][28][29]. A low-thrust trajectory mission from Earth to Mars is analyzed, taking into account gravitational perturbations due to all planets in the Solar System, solar radiation pressure, and non-spherical perturbations of all planets.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

MeSat Mission: Revolutionizing Mars Exploration with THz Radiometer Payload and Optimal Trajectory

Rastinasab,

Hu,

Saghamanesh

et al. 2023

Preprint

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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. 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 forming a constellation. Each CubeSat carries distinct payloads: a THz radiometer for water detection, a high-resolution surface camera, a top-tier spectrometer, and a Fourier Transform Spectrometer (FTS) for wind speed readings. This paper focuses on two pivotal innovations: the development of a 183GHz radiometer payload for detecting water on Mars and a optimal mission design algorithm that analyzes a fuel-efficient low-thrust trajectory from Earth to Mars. Regarding the THz payload for water detection, a subharmonic Schottky diode-based mixer is meticulously designed to efficiently down-convert radio signals. The down-converted signals are carefully analyzed using a customized Do-It-Yourself (DIY) spectrum meter, which facilitated the capture and processing of acquired data. To provide the necessary Local Oscillator signals for the mixer, a Tripler employing three-anode Schottky diodes is developed. Additionally, the Tripler requires a signal generator for its entry frequency, which is addressed by developing a DIY signal generator. Together, these components, comprising the Schottky diode mixer, Tripler, and DIY circuits, collectively form the complete THz payload, demonstrating exceptional power efficiency with a total consumption of only 3.7W. 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.

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Section: System Descriptionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

MeSat Mission: Revolutionizing Mars Exploration with THz Radiometer Payload and Optimal Trajectory

Rastinasab,

Hu,

Saghamanesh

et al. 2023

Preprint

View full text Add to dashboard Cite

show abstract

“…The FTS payload measures wind velocity and direction, assisting in the study of geological weather circulation in Mars' atmosphere and determining suitable locations for wind power plant construction and climate study on Mars. The THz payload is for water vapor detection in Mars' atmosphere, delivering a study on Martian atmospheric properties [50].…”

Section: Introductionmentioning

confidence: 99%

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

Rastinasab,

Hu,

Saghamanesh

et al. 2024

Remote Sensing

View full text Add to dashboard Cite

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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“…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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Interplanetary gravity-assist fuel-optimal trajectory optimization with planetary and Solar radiation pressure perturbations

Cited by 4 publications

References 33 publications

MeSat Mission: Revolutionizing Mars Exploration with THz Radiometer Payload and Optimal Trajectory

MeSat Mission: Revolutionizing Mars Exploration 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

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