Acta Astronautica最新文献_第9页

UV degradation of poly(ether imide) film under vacuum condition and its examination by chemical analyses 真空条件下聚醚亚胺膜的紫外降解及其化学分析检验

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-05 DOI: 10.1016/j.actaastro.2026.01.012

Shogo Yamane , Kazuki Yukumatsu , Yuki Horiuchi , Hideaki Hagihara , Yugo Kimoto , Junji Mizukado

Polymers are widely used in space as thermally controlled materials. Among them, polyetherimide (PEI) stands out and is a promising candidate as a thermally controllable material because of its high durability and transparency. However, the degradation mechanism under ultraviolet (UV) light in the space environment is not completely known. In this study, we monitored the degradation of PEI under UV light irradiation in a vacuum atmosphere to simulate the space environment. Chemical analyses were performed using X-ray photoelectron spectroscopy (XPS), surface attenuated total reflectance infrared (ATR-IR) measurement, and cross-sectional ATR-IR measurement. The relationship between the solar absorptance with increasing irradiation dose and chemical degradation was also a subject of study. XPS measurements revealed that structural changes occurred within a few nanometers of the surface in a relatively short time after irradiation. Additionally, there was nearly no change even when the irradiation dose was increased thereafter. Surface ATR-IR measurements demonstrated that a region of several micrometers on the surface gradually underwent structural changes owing to the formation of a crosslinked structure upon UV irradiation, and cross-sectional ATR-IR measurements indicated that were more closely correlated with the value of solar absorptance.

聚合物作为热控制材料在太空中被广泛使用。其中，聚醚酰亚胺（PEI）因其高耐久性和高透明度而成为热可控材料的一个很有前途的候选者。然而，空间环境中紫外光的降解机理尚不完全清楚。在本研究中，我们监测了真空大气中紫外光照射下PEI的降解情况，以模拟空间环境。化学分析采用x射线光电子能谱（XPS）、表面衰减全反射红外（ATR-IR）测量和横断面ATR-IR测量进行。太阳吸收率随辐照剂量的增加与化学降解的关系也是一个研究课题。XPS测量显示，辐照后在相对较短的时间内，在表面几纳米内发生了结构变化。此外，即使此后辐照剂量增加，也几乎没有变化。表面ATR-IR测量表明，在紫外线照射下，表面上几微米的区域由于形成交联结构而逐渐发生结构变化，截面ATR-IR测量表明，该区域与太阳吸收率的关系更为密切。

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引用次数: 0

Model reduction of pogo suppression for liquid launch vehicles via decoupled modal cost selection 基于解耦模态成本选择的液体运载火箭弹跳抑制模型简化

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-05 DOI: 10.1016/j.actaastro.2026.01.008

Wang Zhao , Shujun Tan

A dimensionality reduction method addressing the high-dimensional and singular nature of Pogo state-space models is studied, beneficial for advancing active suppression techniques. A comprehensive approach integrating eigenspace transformation with Modal Cost Analysis (MCA) is proposed. Direct modal analysis of the coupled Pogo system yields unreliable modal costs due to distinct propulsion and structural system characteristics. Therefore, the coupling between systems is explicitly considered. Suitable inputs and outputs are designed for each system. Specifically, the Pogo system is first decoupled via eigenspace transformation. MCA is then performed, retaining high-cost modes within the Pogo system to construct the reduced-dimensional model. Validation through frequency domain analysis and time domain simulation demonstrates that the method effectively retains high-cost modes under varying conditions, yielding a more accurate reduced-dimensional model. The framework offers generalized applicability to reusable rocket development.

针对Pogo状态空间模型的高维性和奇异性，研究了一种降维方法，有利于主动抑制技术的发展。提出了一种将特征空间变换与模态成本分析相结合的综合方法。耦合Pogo系统的直接模态分析由于不同的推进和结构系统特性而产生不可靠的模态代价。因此，明确地考虑了系统之间的耦合。为每个系统设计合适的输入和输出。具体来说，Pogo系统首先通过特征空间变换解耦。然后执行MCA，在Pogo系统中保留高成本模式以构建降维模型。频域分析和时域仿真验证表明，该方法在不同条件下有效地保留了高成本模式，得到了更精确的降维模型。该框架为可重用火箭开发提供了广泛的适用性。

引用次数: 0

Digital maximum power point tracking for electrical power system of CubeSats based on bat algorithm 基于bat算法的立方体卫星电力系统最大功率点数字跟踪

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-05 DOI: 10.1016/j.actaastro.2026.01.010

Zhi Yin , Tianxing Chen , Xueqin Chen , Ming Liu , Jian Chen

Size constraints restrict the surface area of solar arrays and thus the generated power for CubeSats. Therefore, the efficiency of the electrical power system (EPS) is the most important feature in the design of CubeSats. To maintain a high efficiency over long-term use of CubeSats, this work describes the implementation of a digital maximum power point tracking (MPPT) technique devised for EPS, which is based on an improved bat algorithm (BA) and runs on the lower computer. To ensure the universality of the designed control method, a typical system of a 6U CubeSat is constructed for subsequent simulations and experiments. The new proposed MPPT method utilizes the predicted degradation and telemetry temperature of solar arrays to change the initial population of BA, and refers to the convergence process of gray wolf optimization (GWO) to optimize tracking speed. Numerical simulation results show that the average efficiency of the new proposed algorithm is 97.29% across all simulations, compared to 94.48% for conventional BA. Meanwhile, the proposed algorithm shows a marked reduction in both standard deviation and coefficient of variation, providing a more stable tracking. Finally, a hardware testing system is established to validate the MPPT method based on the improved BA, and it can approach the maximum power point (MPP) of the simulated solar array within about 30 ms with a 2.5 ms control cycle.

尺寸限制限制了太阳能电池阵列的表面积，从而限制了立方体卫星的发电量。因此，电力系统（EPS）的效率是立方体卫星设计中最重要的特征。为了在长期使用CubeSats的过程中保持高效率，本工作描述了为EPS设计的数字最大功率点跟踪（MPPT）技术的实现，该技术基于改进的bat算法（BA），并在低层计算机上运行。为了保证所设计控制方法的通用性，构建了6U立方体卫星的典型系统进行后续仿真和实验。该方法利用太阳能电池阵的预测退化和遥测温度来改变BA的初始种群，并利用灰狼优化（GWO）的收敛过程来优化跟踪速度。数值模拟结果表明，该算法的平均效率为97.29%，而传统BA算法的平均效率为94.48%。同时，该算法在标准差和变异系数上都有明显的减小，提供了更稳定的跟踪。最后，建立了一个硬件测试系统来验证基于改进BA的MPPT方法，该方法可以在约30 ms内接近模拟太阳能电池阵的最大功率点，控制周期为2.5 ms。

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引用次数: 0

Multi-to-multi spacecraft impulsive cooperative interception based on reachable domain coverage 基于可达域覆盖的多对多航天器脉冲协同拦截

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-05 DOI: 10.1016/j.actaastro.2026.01.013

Chen Qing, Gang Zhang

This paper studies the multi-interceptor and multi-target impulsive cooperative interception problem based on reachable domain coverage. Two problems are mainly solved including the multi-to-multi target assignment problem and the multi-to-one cooperative interception problem. According to the linearized uncertainty propagation model, the envelopes of fixed-time reachable domains for both the interceptors and the targets are described by ellipsoidal equation. Then, for the one-to-one interception case, an analytical method is proposed to obtain the impulse magnitude for covering the target’s reachable domain with given impulse time. Based on the rapid estimations of fuel consumption for the one-to-one case, the particle swarm optimization technique is employed to resolve the multi-to-multi target assignment problem. In addition, the multi-to-one reachable domain coverage constraint is converted into the inequality constraint, which is easy to judge in the optimization process. Finally, the multi-to-one cooperative interception problem for optimal fuel consumption is optimized through the interior-point algorithm. Numerical results show that the proposed multi-to-multi target assignment method can rapidly obtain the assignment scheme, and the multi-to-one cooperative interception strategy can reduce the fuel consumption when compared with the one-to-one interception.

研究了基于可达域覆盖的多拦截器、多目标脉冲协同拦截问题。主要解决了多对多目标分配问题和多对一协同拦截问题。根据线性化的不确定性传播模型，用椭球方程描述了拦截弹和目标弹的定时可达域包络。然后，针对一对一拦截情况，提出了在给定脉冲时间下覆盖目标可达域的脉冲幅度的解析方法。基于一对一情况下燃料消耗的快速估计，采用粒子群优化技术解决多对多目标分配问题。此外，将多对一可达域覆盖约束转化为不等式约束，便于优化过程中的判断。最后，通过内点算法对多对一协同拦截问题进行优化。数值结果表明，所提出的多对多目标分配方法能够快速获得目标分配方案，多对一协同拦截策略与一对一拦截策略相比能够降低燃油消耗。

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引用次数: 0

Numerical investigation of gas transpiration cooling for rotating detonation combustor 旋转爆震燃烧室气体蒸腾冷却的数值研究

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-05 DOI: 10.1016/j.actaastro.2026.01.007

Yingxin Zhang , Jia Tian , Shufeng Zhang , Xiaoming Tan , Jingzhou Zhang , Fulei Zhu , Zhengwei Fan , Jingyang Li , Wenqian Hao

The extreme thermal loads induced by rotating detonation waves pose critical challenges to the thermal protection of rotating detonation combustors (RDCs). This study investigates the feasibility of gas transpiration cooling for RDC thermal protection, establishing a localized physical model of axial porous media to simulate detonation wave-coolant interactions. By comparing transpiration cooling characteristics under varying coolant mass flow rates and porosities, the study reveals distinct cooling mechanisms between rotating detonation wave and oblique shock wave regions. Numerical results indicate that transpiration cooling forms a 200–720 K porous wall thermal barrier, isolates the 2280–2800 K detonation core, and reduces wall heat flux by 72 % and pressure peaks by 20–83 %. Optimal cooling performance requires partitioned porosity: a sloping shock zone of 0.5 maximizes efficiency, while a detonation zone of 0.4 avoids increased heat flux due to flow instability. A 0.5 % coolant-to-mainstream mass flow ratio provides continuous thermal protection with a cooling efficiency of 0.72, while 1.0 % causes film breakage and temperature fluctuations. The porous medium acts as a chemical regulator to inhibit combustion and increase water vapor concentration through reverse osmosis to achieve inert gas buffering. The pressure dissipates within 12μs, but the thermal decay lags due to solid-phase inertia, which underscores the need for zonal porosity design and precise coolant control to achieve RDC stability.

旋转爆震波引起的极端热负荷对旋转爆震燃烧室的热防护提出了严峻的挑战。本研究探讨了气体蒸腾冷却用于RDC热防护的可行性，建立了轴向多孔介质的局部物理模型来模拟爆震波与冷却剂的相互作用。通过比较不同冷却剂质量流量和孔隙率下的蒸腾冷却特性，揭示了旋转爆震波区和斜激波区的不同冷却机制。数值结果表明，蒸腾冷却形成200-720 K的多孔壁面热障，隔离了2280-2800 K的爆轰核心，使壁面热流密度降低72%，压力峰值降低20 - 83%。最佳的冷却性能要求孔隙度的分割：0.5的倾斜激波区使效率最大化，而0.4的爆震区则避免了由于流动不稳定而增加的热流密度。0.5%的冷却剂与主流质量流量比提供了连续的热保护，冷却效率为0.72，而1.0%的冷却剂会导致膜破裂和温度波动。多孔介质作为化学调节剂，通过反渗透作用抑制燃烧，增加水蒸气浓度，实现惰性气体缓冲。压力在12μs内消散，但由于固相惯性，热衰减滞后，因此需要进行层状孔隙度设计和精确的冷却剂控制来实现RDC稳定性。

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引用次数: 0

Orbit maneuver planning of earth observation satellite swarm for unreachable targets 不可达目标下对地观测卫星群的轨道机动规划

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-05 DOI: 10.1016/j.actaastro.2025.12.058

Yuqi Sun , Xiande Wu , Hyuk Park , Chao Dong

A method for integrated task allocation and orbital maneuver planning is devised to address scenarios where a satellite swarm responds to unreachable targets. To observe more targets earlier and at a lower maneuver cost, this paper proposes an improved tabu search algorithm for remote sensing satellite swarm task planning. The proposed method improves the tabu search algorithm by incorporating the parallel dynamic dual-search strategy to optimize target allocation in the satellite swarm and observation sequence of swarm members. By dynamically grouping and refactoring the code, the parallel search strategy reduces the search space and enhances computational efficiency. A simulation scenario is provided to verify the efficiency and feasibility of the proposed algorithm in responding to multiple unreachable targets. The results show the fitness trend with 15 satellites and 150–300 targets. Besides its feasibility, the proposed method results in a more than ten-fold improvement in calculation efficiency.

针对卫星群对不可达目标的响应，提出了一种任务分配与轨道机动规划相结合的方法。为了更早、更低的机动成本观测到更多的目标，提出了一种改进的禁忌搜索算法用于遥感卫星群任务规划。该方法对禁忌搜索算法进行改进，采用并行动态双搜索策略优化卫星群目标分配和群成员观测顺序。并行搜索策略通过对代码进行动态分组和重构，减少了搜索空间，提高了计算效率。通过仿真场景验证了该算法在多目标不可达情况下的有效性和可行性。结果显示了15颗卫星和150 ~ 300个目标的适应度趋势。该方法不仅可行，而且计算效率提高了10倍以上。

引用次数: 0

Numerical study on zonal combustion characteristics in supersonic combustor under asymmetric injection scheme 非对称喷射方案下超声速燃烧室分区燃烧特性数值研究

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-03 DOI: 10.1016/j.actaastro.2025.12.064

Xiaosi Li , Junlong Zhang , Guowei Luan , Youyin Wang , Hongchao Qiu , Wen Bao

The injection scheme has a significant effect on the mixing and combustion of the fuel, as well as the spatial distribution of the main combustion zone, which is crucial for the performance of the scramjet. In this study, the zonal combustion under several typical asymmetric strut/wall combined fuel injection schemes was numerically investigated. The flow field characteristics, mixing and combustion performance, the combustor parameters distributions, as well as the impact of zonal combustion on the aerodynamic performance of the nozzle were analyzed. The results indicate that zonal combustion can be established in a supersonic combustor through zonal fuel injection, wherein combustion zones and non-reacting zones coexist in the circumferential direction of the combustor while exhibiting distinct flow and combustion characteristics. Besides, at an identical equivalence ratio, zonal fuel injection schemes not only yield lower mixing and combustion efficiencies compared to a uniform injection scheme, but also alters both the wall pressure distribution along the combustor and the gas parameter distribution at combustor outlet. Ultimately, zonal combustion affects the aerodynamic performance of scramjet nozzles, such as lift and lateral force. The analysis results of zonal combustion in this paper were beneficial to the optimization of asymmetric injection scheme in supersonic combustor for future investigations and offer a novel perspective for flight control in hypersonic vehicles.

喷射方案对燃料的混合和燃烧以及主燃烧区的空间分布有重要影响，这对超燃冲压发动机的性能至关重要。本文对几种典型的非对称支板/壁面组合喷射方案下的区域燃烧进行了数值模拟。分析了喷嘴的流场特性、混合燃烧性能、燃烧室参数分布以及分区燃烧对喷嘴气动性能的影响。结果表明：超声速燃烧室通过区域喷油可以建立区域燃烧，燃烧区和非反应区在燃烧室周向同时存在，并表现出明显的流动和燃烧特性。此外，在等量比相同的情况下，区域喷射方案不仅比均匀喷射方案的混合效率和燃烧效率低，而且改变了沿燃烧室壁面压力分布和燃烧室出口气体参数分布。区域燃烧最终会影响超燃冲压发动机喷管的升力和侧向力等气动性能。本文的区域燃烧分析结果有利于超声速燃烧室非对称喷射方案的优化，为高超声速飞行器的飞行控制提供了新的研究视角。

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引用次数: 0

Mission concept for SURROUND: Operational space weather detection and tracking using small spacecraft 环绕任务概念：使用小型航天器进行操作空间天气探测和跟踪

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-03 DOI: 10.1016/j.actaastro.2025.12.055

Alejandro Macario-Rojas , Dale M. Weigt , L. Alberto Cañizares , Shane A. Maloney , Sophie A. Murray , Peter T. Gallagher , Nicholas H. Crisp , Ciara N. McGrath

One of the greatest challenges facing current space weather monitoring operations is forecasting the arrival of coronal mass ejections (CMEs) and solar energetic particles (SEPs). This paper presents a mission concept for operational detection and monitoring of solar weather events as a means of forecasting the arrival of potentially hazardous CMEs and SEPs at Earth-like distances. Foregrounding the operational (rather than scientific) requirements of the system, this work proposes a high-level mission design that could provide detection of solar weather events by tracking associated solar radio bursts, enabling advanced warning of their arrival at Earth. This work concludes that 3–5 small spacecraft equipped with radio spectrometers positioned at the Sun–Earth Lagrange points and in Earth-leading/-trailing orbits could be used to provide this capability, with the

L_{4}

and

L_{5}

Lagrange points most advantageous for mission performance. While technical developments in CubeSat survivability would be required to enable the SURROUND mission, suitable launch, injection and communication options are identified, indicating its potential feasibility in the near future.

当前空间气象监测业务面临的最大挑战之一是预测日冕物质抛射（cme）和太阳高能粒子（sep）的到来。本文提出了一个任务概念，用于操作探测和监测太阳天气事件，作为预测潜在危险的日冕物质抛射和sep到达类地距离的手段。展望系统的操作（而不是科学）需求，这项工作提出了一个高水平的任务设计，可以通过跟踪相关的太阳射电爆发来提供太阳天气事件的探测，从而实现它们到达地球的提前预警。这项工作的结论是，3-5个配备无线电光谱仪的小型航天器，定位在太阳-地球拉格朗日点和地球领先/落后轨道上，可以用来提供这种能力，L4和L5拉格朗日点对任务性能最有利。虽然立方体卫星生存能力的技术发展将需要实现环绕任务，但确定了合适的发射、注入和通信选择，表明其在不久的将来的潜在可行性。

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引用次数: 0

An interactive gated-attention network with dual streams for semantic understanding of Martian surface images 面向火星表面图像语义理解的双流交互式门控网络

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-03 DOI: 10.1016/j.actaastro.2026.01.002

Shan Lin , Quanke Hu , Hongwei Guo , Miao Dong , Xitailang Cao , Hong Zheng

Mars surface semantic segmentation faces three key challenges: complex terrain boundaries, small-scale target omission, and costly manual annotation. To address these issues, we propose an integrated framework that combines feature attention, cross-domain transfer learning, and interactive optimization. First, we construct Mars_5000, a new multi-modal dataset that fuses real Mars rover imagery with high-precision pixel annotations. The dataset significantly improves fine-grained labeling accuracy across five terrain categories, including rocks and dunes. Second, we design DualPath-Net, a dual-path network that employs gated attention fusion blocks (GAFB) to dynamically balance local details and global context. This results in a 14.2 % improvement in rock edge segmentation IoU compared to baseline models. Additionally, a transfer learning strategy is introduced to adapt to the scale sensitivity of distant scene views. Furthermore, we develop the interactive annotation system MarsAnno, which combines dynamic confidence sampling and contour optimization algorithms, increasing annotation efficiency by 4.5 times while achieving an annotation reuse rate of 89.3 %, significantly enhancing the model's generalization ability in unseen scenarios. Experimental results demonstrate that the proposed method achieves 88.1 % mIoU and 94 % mPA on the full-scene test set, significantly improving segmentation accuracy compared to existing models, highlighting its value for Mars exploration tasks and related applications.

火星表面语义分割面临三个关键挑战：复杂的地形边界、小尺度目标遗漏和昂贵的人工标注。为了解决这些问题，我们提出了一个结合特征注意、跨领域迁移学习和交互优化的集成框架。首先，我们构建了一个新的多模态数据集Mars_5000，该数据集融合了真实的火星探测器图像和高精度的像素注释。该数据集显著提高了五种地形类别（包括岩石和沙丘）的细粒度标记精度。其次，我们设计了DualPath-Net，这是一个采用门控注意力融合块（GAFB）来动态平衡局部细节和全局上下文的双路径网络。与基线模型相比，这使得岩石边缘分割IoU提高了14.2%。此外，还引入了一种迁移学习策略，以适应远处景物的尺度敏感性。此外，我们开发了交互式标注系统MarsAnno，该系统结合了动态置信度采样和轮廓优化算法，将标注效率提高了4.5倍，实现了89.3%的标注重用率，显著增强了模型在未知场景下的泛化能力。实验结果表明，该方法在全场景测试集上达到了88.1%的mIoU和94%的mPA，与现有模型相比，分割精度显著提高，突出了其在火星探测任务及相关应用中的价值。

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引用次数: 0

Numerical simulation and experimental study of lunar surface drilling sampling based on JKR contact model 基于JKR接触模型的月球表面钻孔取样数值模拟与实验研究

IF 3.4 2区物理与天体物理 Q1 ENGINEERING, AEROSPACE

Acta Astronautica

Pub Date : 2026-01-02 DOI: 10.1016/j.actaastro.2025.12.062

Jia Fu , Haitao Luo , Yuxin Li , Huadong Li , Dehui Li , Teijun Wang

With the smooth progress of lunar exploration programs, lunar sampling has become a major research focus in current deep space missions. Sampling techniques and methods are the key to lunar surface sampling tasks. However, conventional drilling simulation analyses are often difficult to accurately match with experimental results, which makes research on drilling simulation modeling highly significant. For the simulation of lunar regolith drilling and sampling, the accurate calibration of discrete element parameters of lunar soil was systematically carried out based on the Johnson-Kendall-Roberts (JKR) contact theory. A discrete element model consistent with the lunar highland regolith characteristics returned by the Apollo missions was established and verified through angle of repose experiments. Subsequently, an external helical hollow drill rod was designed as the drilling-sampling tool, and a coupled discrete element–multibody dynamics simulation model of the interaction between the drilling-sampling tool and lunar soil particles was established to predict the variation of drilling loads during penetration. A drilling-sampling experimental platform was then designed and built to explore the relationship between drilling torque variation and feed rate, rotation speed, as well as the physical properties of lunar regolith. The results were compared with numerical simulation outcomes, showing errors below 20 %. These research findings provide important technical support and parameter references for practical lunar surface sampling missions.

随着月球探测计划的顺利进行，月球采样已成为当前深空探测任务的主要研究热点。采样技术和方法是月球表面采样任务的关键。然而，常规的钻井仿真分析往往难以与实验结果准确匹配，这使得钻井仿真建模研究具有重要意义。针对月壤钻探与采样模拟，基于JKR （Johnson-Kendall-Roberts）接触理论，系统地进行了月壤离散元参数的精确定标。建立了符合阿波罗任务返回的月球高原风化层特征的离散元模型，并通过休止角实验进行了验证。随后，设计了外螺旋空心钻杆作为钻采工具，建立了钻采工具与月壤颗粒相互作用的离散元-多体耦合动力学仿真模型，预测了钻采过程中钻井载荷的变化。设计并搭建钻井取样实验平台，探讨钻井扭矩变化与进给速率、转速及月壤物理性质的关系。结果与数值模拟结果进行了比较，误差在20%以下。这些研究成果为实际的月球表面采样任务提供了重要的技术支撑和参数参考。

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引用次数: 0