Reachable domain with a single coplanar impulse considering the target-visit constraint

Xia, Cunyan; Zhang, Gang; Geng, Yunhai

doi:10.1016/j.asr.2022.02.042

Cited by 7 publications

(3 citation statements)

References 23 publications

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“…In astrodynamics, reachability problems for both chemical rockets and electric propulsion spacecraft are studied. Chemical rocket propulsion reachability largely focuses on single-impulse maneuvers and has been studied within the cislunar environment [22][23][24][25][26][27][28][29][30][31][32][33][34][35]. Electric propulsion or continuous-thrust reachability problems have been proposed for low-Earth, cislunar, and interplanetary mission planning applications [15,17,[36][37][38][39].…”

Section: Introductionmentioning

confidence: 99%

Rapid Approximation of Low-Thrust Spacecraft Reachable Sets within Complex Two-Body and Cislunar Dynamics

Bowerfind,

Taheri

2024

Aerospace

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The reachable set of controlled dynamical systems is the set of all reachable states from an initial condition over a certain time horizon, subject to operational constraints and exogenous disturbances. In astrodynamics, rapid approximation of reachable sets is invaluable for trajectory planning, collision avoidance, and ensuring safe and optimal performance in complex dynamics. Leveraging the connection between minimum-time trajectories and the boundary of reachable sets, we propose a sampling-based method for rapid and efficient approximation of reachable sets for finite- and low-thrust spacecraft. The proposed method combines a minimum-time multi-stage indirect formulation with the celebrated primer vector theory. Reachable sets are generated under two-body and circular restricted three-body (CR3B) dynamics. For the two-body dynamics, reachable sets are generated for (1) the heliocentric phase of a benchmark Earth-to-Mars problem, (2) two scenarios with uncertainties in the initial position and velocity of the spacecraft at the time of departure from Earth, and (3) a scenario with a bounded single impulse at the time of departure from Earth. For the CR3B dynamics, several cislunar applications are considered, including L1 Halo orbit, L2 Halo orbit, and Lunar Gateway 9:2 NRHO. The results indicate that low-thrust spacecraft reachable sets coincide with invariant manifolds existing in multi-body dynamical environments. The proposed method serves as a valuable tool for qualitatively analyzing the evolution of reachable sets under complex dynamics, which would otherwise be either incoherent with existing grid-based reachability approaches or computationally intractable with a complete Hamilton–Jacobi–Bellman method.

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Section: Introductionmentioning

confidence: 99%

Rapid Approximation of Low-Thrust Spacecraft Reachable Sets within Complex Two-Body and Cislunar Dynamics

Bowerfind,

Taheri

2024

Aerospace

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“…Gong et al (2020) investigated the pursuit-evasion differential game for satellites with continuous thrust from the viewpoint of reachable domain. Xia et al (2022) proposed a simple numerical method to solve the spacecraft reachable domain problem with a single coplanar impulse, considering the target-visit constraint and the impulse-magnitude constraint, then the correctness and the effectiveness of the proposed methods were verified by comparing with the traditional Lambert traversal method. The majority of these literatures mainly considered the absolute reachable domain (RD) for spacecrafts with single impulse.…”

Section: Introductionmentioning

confidence: 99%

Research on relative reachable domain in target orbit for maneuvering spacecraft

Li,

Zhang

2024

AEAT

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Purpose Lots of successful space missions require that the maneuvering spacecraft can reach the target spacecraft. Therefore, research on relative reachable domain (RRD) in target orbit for maneuvering spacecraft is particularly important and is currently a hot-debated topic in the field of aerospace. This paper aims at analyzing and simulating the RRD in target orbit for maneuvering spacecrafts with a single fixed-magnitude impulse and continuous thrust, respectively, to provide a basis for analyzing the feasibility of spacecraft maneuvering missions and improving the design efficiency of spacecraft maneuvering missions. Design/methodology/approach Based on the kinematics model of relative motion, RRD in target orbit for maneuvering spacecraft with a single fixed-magnitude impulse can be calculated via analyzing the relationship between orbital elements, position vector and velocity vector of spacecrafts, and relevant studies are introduced to compare simulation results for the same case and validate the method proposed in the paper. With analysis of the dynamic model of relative motion, the calculation of RRD in target orbit for maneuvering spacecraft with continuous thrust can be transformed as the solution of the optimal control problem, and example emulations are carried out to validate the method. Findings For the case with a single fixed-magnitude impulse, simulation results show preliminarily that the method is in agreement with the method in Ref. (Wen et al., 2016), which treats the same case and thus is plausibly correct and feasible. For the case with continuous thrust, analysis and simulation results confirm the validity of the proposed method. The methods based on relative motion in this paper can efficiently determining the RRD in target orbit for maneuvering spacecraft. Originality/value Both theoretical analyses and simulation results indicate that the method proposed in this paper is comparatively simple but efficient for determine the RRD in target orbit for maneuvering spacecraft swiftly and precisely.

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“…In terms of the spacecraft near the Earth, reachable domain is defined as the space position set which the spacecraft can reach when the constraints are satisfied (Wen et al 2014). As an intuitive concept to describe the reachable position of the spacecraft, some research progress has been made in the reachable domain with a single coplanar impulse considering the target-visit constraint (Xia et al 2022), reachable domain after gravity assists of planets in elliptical orbits (Chen et al 2020) and space debris removal on the basis of reachable domain (Liu et al 2021). For lunar exploration missions, unlike the near-Earth trajectory, reachable domain of an Earth-Moon transfer trajectory is usually featured as the lunar surface reachable region, that is, the lunar surface which can be reached by the spacecraft under certain trajectory constraints, such as the longitude and latitude distribution of lunar landing points (Orloff 2000).…”

Section: Introductionmentioning

confidence: 99%

Investigation on reachable domain of contingency return trajectories in the circumlunar flight phase based on interval analysis

Zhou²,

et al. 2022

Preprint

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The investigation on reachable domain based on interval analysis is performed, which is aimed for the contingency return trajectories during the circumlunar flight stage for manned lunar landing engineering. First, the issue of contingency return trajectory which adopts a non-coplanar maneuver during the circumlunar flight phase is described. The mathematics model of the reachable domain of contingency return trajectories is established. Second, the contingency return trajectory is designed. An improved interval branch and bound algorithm is introduced and a reachable domain calculation method of the contingency return trajectories is proposed. Third, in numerical simulations, by comparing the reachable domain obtained by the traditional brute force method, the accuracy of the method presented in this paper is verified. It also indicates that this method has a higher calculation efficiency. Finally, abundant simulations are performed to discuss the parameter characteristic of reachable domain by adopting this method. The study conclusions can serve as an important reference for the selection and decision of contingency return trajectory plans in the future manned lunar landing engineering.

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Reachable domain with a single coplanar impulse considering the target-visit constraint

Cited by 7 publications

References 23 publications

Rapid Approximation of Low-Thrust Spacecraft Reachable Sets within Complex Two-Body and Cislunar Dynamics

Rapid Approximation of Low-Thrust Spacecraft Reachable Sets within Complex Two-Body and Cislunar Dynamics

Research on relative reachable domain in target orbit for maneuvering spacecraft

Investigation on reachable domain of contingency return trajectories in the circumlunar flight phase based on interval analysis

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