Acta Astronautica最新文献

Multi-objective low-thrust transfer strategies from an earth-moon NRHO to the sun-earth system 从地月NRHO到日地系统的多目标低推力转移策略

IF 3.5 2区物理与天体物理

Acta Astronautica Pub Date : 2026-09-02 DOI: 10.1016/j.actaastro.2026.08.067

Carrie G. Sandel, Rohan Sood

{"title":"Multi-objective low-thrust transfer strategies from an earth-moon NRHO to the sun-earth system","authors":"Carrie G. Sandel, Rohan Sood","doi":"10.1016/j.actaastro.2026.08.067","DOIUrl":"https://doi.org/10.1016/j.actaastro.2026.08.067","url":null,"abstract":"Within the last several decades, there has been a growing interest in cislunar trajectory design—amplified by NASA’s plans to maintain a long-term lunar presence, introducing several unique trajectory design challenges. Most notably, future spacecraft may depart directly from cislunar space rather than Earth. Thus, small spacecraft, like CubeSats, may deploy from orbits such as a 9:2 L2 near rectilinear halo orbit (NRHO) as a secondary payload. This work explores the trade space for both fuel-optimal and time-optimal trajectories for a low-thrust CubeSat, with 8 <mml:math altimg=\"si1.svg\" display=\"inline\"><mml:mrow><mml:mi>μ</mml:mi><mml:mi>g</mml:mi></mml:mrow></mml:math> of acceleration, transferring from an NRHO to target L1 Sun-Earth halo orbits. This research determined that spacecraft departing from an NRHO under patched bicircular restricted four-body problem (BCR4BP)/circular restricted three-body problem (CR3BP) dynamics can reach orbits in the L1 Sun-Earth region in as little as 72 days. Moreover, when prioritizing low-cost transfers, these transfers have <mml:math altimg=\"si207.svg\" display=\"inline\"><mml:mrow><mml:mi>Δ</mml:mi><mml:mi>V</mml:mi></mml:mrow></mml:math> costs as low as 16 m/s. A subset of point cases are converted to a full ephemeris model to check for consistency with the selected simplified solutions. A dispersion analysis is also performed to assess re-contact risks between a chief spacecraft and an outbound CubeSat to the Sun-Earth system, subject to maneuver execution error. The conclusions of the uncertainty analysis and reachability study establish a preliminary set of departure conditions specific to a low-thrust spacecraft. By establishing initial fuel and time-of-flight limits in a simplified regime for low-thrust spacecraft departing from an NRHO, this work provides a comprehensive transfer design method to reach the Sun-Earth system to inform future operational mission design strategies.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"43 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2026-09-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148883987","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Prediction of Hydrogen Mixing and Velocity Fields Behind a Strut Injector with Multi-Lobe Nozzles at scramjet engine using POD+LSTM technique 基于POD+LSTM技术的超燃冲压发动机多叶喷管支杆喷油器后氢混合及速度场预测

IF 3.5 2区物理与天体物理

Acta Astronautica Pub Date : 2026-09-01 DOI: 10.1016/j.actaastro.2026.08.076

Mostafa Barzegar Gerdroodbary, Iman Shiryanpoor, J.C. Pascoa, Mohammadmahdi Abdollahzadehsangroudi

{"title":"Prediction of Hydrogen Mixing and Velocity Fields Behind a Strut Injector with Multi-Lobe Nozzles at scramjet engine using POD+LSTM technique","authors":"Mostafa Barzegar Gerdroodbary, Iman Shiryanpoor, J.C. Pascoa, Mohammadmahdi Abdollahzadehsangroudi","doi":"10.1016/j.actaastro.2026.08.076","DOIUrl":"https://doi.org/10.1016/j.actaastro.2026.08.076","url":null,"abstract":"This work proposes a hybrid data-driven reduced-order modeling (ROM) approach that combines Proper Orthogonal Decomposition (POD) with Long Short-Term Memory (LSTM) networks to efficiently predict unsteady hydrogen mixing and supersonic flow fields downstream of a strut injector. The study considers three annular nozzle configurations—2-lobe, 3-lobe, and 4-lobe—under high-speed, non-reacting hydrogen injection conditions. The full-order model (FOM) data used for training and validation were generated via Unsteady Reynolds-averaged Navier–Stokes (URANS) simulations employing the turbulence model, capturing the transient flow features and scalar transport in detail. POD was employed to obtain the dominant spatial modes from the computational results, while LSTM networks were trained on the temporal evolution of the modal coefficients to forecast the flow and scalar fields. The ROM performance was evaluated under various training-to-testing ratios (70%, 80%, and 90%), and the results were benchmarked against full-order contours of hydrogen mass and Mach number on a representative downstream plane. The proposed POD+LSTM framework demonstrated accurate predictions when trained with at least 80% of the dataset, with near-exact reconstruction achieved at 90% training. Contour comparisons showed that both the velocity and scalar fields were well captured in terms of jet penetration, shock structures, and mixing layer development, particularly for the more complex 3-lobe and 4-lobe nozzles. The results demonstrate the potential of POD–LSTM as an efficient reduced-order tool for rapid prediction of unsteady hydrogen mixing and flow structures in high-speed fuel-injection systems, with substantially reduced computational requirements relative to repeated full-order CFD simulations.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"46 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2026-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148883988","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Radiofrequency-induced degradation of GaAs solar cells in space wireless power transmission 空间无线电力传输中砷化镓太阳能电池的射频诱导退化

IF 3.5 2区物理与天体物理

Acta Astronautica Pub Date : 2026-09-01 DOI: 10.1016/j.actaastro.2026.08.062

Zekang Huang, Xingjun Ge, Yang Zhang, Jun Zhang, Zhao Zhang, Yiqun Zhang

引用次数: 0

The public funding of the New Space Economy. Confronting public procurement and public-private partnership 新太空经济的公共资金。应对政府采购和公私伙伴关系

IF 3.5 2区物理与天体物理

Acta Astronautica Pub Date : 2026-09-01 DOI: 10.1016/j.actaastro.2026.08.078

M. Dal Molin,M. Landoni

引用次数: 0

Hybrid neural-physical modeling and enhanced multi-objective motion planning with neuro-fuzzy adaptive sliding mode control for dual-arm space robots 双臂空间机器人神经-物理混合建模与神经模糊自适应滑模控制增强多目标运动规划

IF 3.5 2区物理与天体物理

Acta Astronautica Pub Date : 2026-09-01 DOI: 10.1016/j.actaastro.2026.08.071

Bingquan Wang,Changlong Zhang,Shaoxuan Suo,Chenxi Wang,Zhi Zhai,Jinxin Liu,Naijin Liu,Xuefeng Chen

引用次数: 0

End-to-end testbed validation of periodic and probabilistic-aware constellation scheduling for Non-Terrestrial Networks 非地面网络周期性和概率感知星座调度的端到端试验台验证

IF 3.5 2区物理与天体物理

Acta Astronautica Pub Date : 2026-09-01 DOI: 10.1016/j.actaastro.2026.08.074

Arnau Singla,Anna Calveras,Juan A. Fraire,Joan A. Ruiz-de-Azua

引用次数: 0

Academy transaction note ”two-stage automatic mass balancing and attitude control for 3-DoF spacecraft attitude simulators” 学院交易记录“三自由度航天器姿态模拟器的两级自动质量平衡和姿态控制”

IF 3.5 2区物理与天体物理

Acta Astronautica Pub Date : 2026-09-01 DOI: 10.1016/j.actaastro.2026.08.066

Yong-Hwan Kim, Kyungryeung Min, Yangchan Cho

引用次数: 0

Governed parasitic ISRU for secondary utility chemicals at early Mars outposts: The LOGUE-10 Ethanol example 在早期的火星前哨站用于二次公用化学品的受控寄生ISRU: LOGUE-10乙醇的例子

IF 3.5 2区物理与天体物理

Acta Astronautica Pub Date : 2026-09-01 DOI: 10.1016/j.actaastro.2026.08.069

Richard T. Logue

引用次数: 0

Accuracy Analysis and Optimization Design of Spatial Modular Deployable Antenna Mechanism 空间模块化可展开天线机构精度分析与优化设计

IF 3.5 2区物理与天体物理

Acta Astronautica Pub Date : 2026-09-01 DOI: 10.1016/j.actaastro.2026.08.070

Jing Zhang,Qiying Li,Chuang Shi,Yaliang Dou,Xinshuo Wang,Hongwei Guo,Rongqiang Liu,Zongquan Deng

引用次数: 0

Performance Investigation of A Sulfur Propellant Z-pinch Pulsed Plasma Thruster for Microsatellite Propulsion 用于微卫星推进的硫推进剂z箍缩脉冲等离子体推力器性能研究

IF 3.5 2区物理与天体物理

Acta Astronautica Pub Date : 2026-08-31 DOI: 10.1016/j.actaastro.2026.08.075

Jiaxu Lu, Jian Li, Yuanzheng Zhao, Chaofan Duan, Zitong Shen, Yuqiang Cheng, Jianjun Wu

{"title":"Performance Investigation of A Sulfur Propellant Z-pinch Pulsed Plasma Thruster for Microsatellite Propulsion","authors":"Jiaxu Lu, Jian Li, Yuanzheng Zhao, Chaofan Duan, Zitong Shen, Yuqiang Cheng, Jianjun Wu","doi":"10.1016/j.actaastro.2026.08.075","DOIUrl":"https://doi.org/10.1016/j.actaastro.2026.08.075","url":null,"abstract":"Power-limited microsatellites require propulsion systems capable of delivering high impulse output per unit input power for rapid maneuvering. Conventional PTFE-based pulsed plasma thrusters (PPTs) suffer from limited thrust-to-power ratio and carbon deposition under low-power operation. In this study, a novel sulfur-propellant Z-pinch PPT is proposed to address these challenges, and its discharge characteristics, ablation behavior, propulsion performance, and plume evolution are experimentally investigated. Results show that the single-pulse ablation mass of sulfur is approximately 2–3 times that of PTFE. Within a discharge energy range of 0.72–2.32 J, the thruster achieves an impulse bit of 89.0–310.6 μN·s and a thrust-to-power ratio of 123.5–133.7 μN/W. The specific impulse and propulsion efficiency reach 330–355 s and 20.0–23.2%. The maximum thrust-to-power ratio is about twice that of PTFE systems and is among the highest values reported in the open literature. Compared with PTFE, sulfur exhibits higher peak discharge current, greater instantaneous power deposition, and lower effective plasma resistance, indicating improved plasma conduction and energy coupling capability. High-speed imaging shows that the sulfur plume maintains a stable conical structure, while plume brightness, expansion scale, and leading-edge jet intensity increase with discharge voltage. These results demonstrate that the sulfur-propellant Z-pinch PPT is promising for rapid maneuvering in power-limited microsatellite missions.","PeriodicalId":44971,"journal":{"name":"Acta Astronautica","volume":"5 1","pages":""},"PeriodicalIF":3.5,"publicationDate":"2026-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148883991","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":2,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0