Acta Astronautica最新文献_第8页

A logical dimensional reinforcement learning approach for component-level collaborative planning in cluster satellites 星群卫星组件级协同规划的逻辑维度强化学习方法

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

Acta Astronautica

Pub Date : 2026-01-10 DOI: 10.1016/j.actaastro.2026.01.021

Zhihua Liang , Wudong Deng , Yunfeng Dong

Cluster satellites' component-level collaborative observation enables on-demand stitching of the observation chain. By responding directly to dynamic targets and environmental changes, this capability represents a key trend in meeting future complex observation requirements. Mission planning is critical to realizing this collaboration. Existing methods typically employ subsystem-level models and reinforcement learning algorithms to plan missions under deterministic operational flows. However, realizing on-demand stitching requires mission planning to address the challenge of nested space sparsity optimization while accurately reflecting component-level characteristics. To address this, this paper utilizes multi-granularity digital twin models to achieve component-level on-demand modeling. We introduce the logical dimension from systems engineering to decouple nested space sparsity. Following the self-similar logical steps of synthesis, analysis, and assessment, the optimization problem is transformed into a set of high-cohesion, low-coupling sub-problems, thereby guiding the reinforcement learning process. By switching computational models based on the specific requirements of logical dimensional reinforcement learning, we established the multi-granularity digital twin logical dimensional reinforcement learning method to realize on-demand stitching of the observation chain. To validate this capability, this paper designed typical cluster satellite observation scenarios corrected by real telemetry parameters. Using the number of confirmed unknown moving targets as a performance indicator, we tested the ability of our method and deterministic planning methods to respond to complex demands under dynamic environmental conditions. Furthermore, sparsity and feature analyses were conducted to verify the rationality of the proposed approach in optimizing nested space sparsity. The results demonstrate that the proposed method successfully achieves on-demand stitching of the observation chain for cluster satellites. This approach provides an effective pathway for adapting to future complex observation requirements and serves as an exemplar for applying systems engineering to guide machine learning in solving complex problems.

集群卫星的组件级协同观测使观测链的按需拼接成为可能。通过直接响应动态目标和环境变化，这种能力代表了满足未来复杂观测需求的关键趋势。任务规划对于实现这种合作至关重要。现有方法通常采用子系统级模型和强化学习算法来规划确定性操作流程下的任务。然而，实现按需拼接需要任务规划，以解决嵌套空间稀疏性优化的挑战，同时准确反映组件级特性。为了解决这个问题，本文利用多粒度数字孪生模型来实现组件级按需建模。我们从系统工程中引入逻辑维度来解耦嵌套空间稀疏性。通过自相似的逻辑合成、分析和评估步骤，将优化问题转化为一组高内聚、低耦合的子问题，从而指导强化学习过程。根据逻辑维度强化学习的具体要求，通过切换计算模型，建立了多粒度数字孪生逻辑维度强化学习方法，实现了观察链的按需拼接。为了验证这一能力，本文设计了经实际遥测参数校正的典型星群观测场景。以确定的未知运动目标数量作为性能指标，测试了该方法和确定性规划方法在动态环境条件下响应复杂需求的能力。通过稀疏度分析和特征分析，验证了该方法优化嵌套空间稀疏度的合理性。结果表明，该方法成功地实现了星群观测链的按需拼接。该方法为适应未来复杂的观测需求提供了有效的途径，并为应用系统工程指导机器学习解决复杂问题提供了范例。

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引用次数: 0

Feasibility assessment of formation flight control by differential drag in eccentric orbit for the FACTORS mission 因子任务偏心轨道差阻编队飞行控制的可行性评估

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

Acta Astronautica

Pub Date : 2026-01-09 DOI: 10.1016/j.actaastro.2026.01.017

Maximilien Berthet , Yusuke Maru , Yoshifumi Saito , Takefumi Mitani , Iku Shinohara , Kazushi Asamura

FACTORS is an M-class mission proposal led by JAXA/ISAS. It aims to elucidate energy coupling mechanisms and mass transport between Earth and space, at around 350–3500 km altitude in high latitude regions. Measurements of the electromagnetic field, particle sampling, and auroral imaging are planned. Simultaneous data at several kilometres to tens of kilometres apart will be obtained, using two satellites in formation flight in an eccentric polar orbit. Differential aerodynamic drag offers a promising resource for propellant-free formation control, since the perigee is located in the atmosphere. A control method for an in-track linear formation is developed and tested using a high-fidelity numerical orbit simulator. Disturbances are added to represent attitude control error, aerodynamic lift, and open-loop command uplink with space weather prediction error. Good performance is obtained even for close-proximity operations with km-scale separation. Based on the results, fully aerodynamic control is possible, though a thruster is desirable for perigee altitude adjustment and out-of-plane manoeuvring. To the authors’ knowledge, this is the first detailed study on formation flight control via differential drag in an eccentric orbit.

FACTORS是由JAXA/ISAS领导的m级任务提案。它的目的是阐明能量耦合机制和地球和空间之间的质量输运，在350-3500公里高的高纬度地区。计划进行电磁场测量、粒子采样和极光成像。利用在偏心极轨道上编队飞行的两颗卫星，将获得相隔数公里至数十公里的同步数据。由于近地点位于大气中，差分气动阻力为无推进剂编队控制提供了一个很有前途的资源。提出了一种轨道内线性编队的控制方法，并在高保真数值轨道模拟器上进行了试验。加入扰动来表示姿态控制误差、气动升力和带空间天气预报误差的开环命令上行链路。即使在km尺度的近距离操作中也能获得良好的性能。基于结果，完全气动控制是可能的，尽管需要一个推进器来进行近地点高度调整和面外操纵。据作者所知，这是第一次对偏心轨道上通过差阻进行编队飞行控制的详细研究。

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引用次数: 0

Anthropogenic Space Object attitude and material characterisation through multi-colour light curve inversion 基于多色光曲线反演的人为空间物体姿态和材料表征

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

Acta Astronautica

Pub Date : 2026-01-08 DOI: 10.1016/j.actaastro.2025.12.060

Luís Filipe Pino Gonçalves , Nevan Simone , A.K. de Almeida Jr , Domingos Barbosa , Moriba Jah , Timothée Vaillant , Bruno Coelho , Alexandre C.M. Correia

Light-curve inversion for anthropogenic space objects (ASOs) is ill-posed when performed in a single band, which leads to non-unique combinations of attitude and material parameters. We present a physically grounded forward model based on a Cook–Torrance bidirectional reflectance distribution function, explicit shadowing by Earth and self-occlusion, and a satellite-centred geometry. We cast attitude–material retrieval as a constrained optimisation problem and use multi-colour light curves (Johnson–Cousins

B

,

V

,

R

) to regularise the inversion by coupling wavelength-invariant parameters. On four space objects of distinct morphology, the multi-colour constraint improves fit quality and narrows the admissible solution set relative to panchromatic inversions. We report parameter uncertainties from multi-start annealing and provide sensitivity of the fit to key BRDF and attitude parameters. Results support multi-colour optical surveys as an efficient path to unambiguous ASO characterisation from a single site.

人为空间目标的光曲线反演在单波段进行时存在病态性，导致姿态和材料参数的非唯一组合。我们提出了一个基于Cook-Torrance双向反射分布函数、地球和自遮挡的显式阴影以及以卫星为中心的几何形状的物理接地正演模型。我们将姿态-材料检索作为一个约束优化问题，并使用多色光曲线（Johnson-Cousins B， V， R）通过耦合波长不变参数来规范反演。在四个不同形态的空间对象上，多色约束提高了拟合质量，缩小了相对全色反演的可接受解集。我们报告了多起点退火的参数不确定性，并提供了对关键BRDF和姿态参数的拟合灵敏度。结果支持多色光学测量作为单一地点明确ASO特征的有效途径。

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引用次数: 0

The feasibility of potentially hazardous asteroids flybys using multiple Venus gravity assists 利用多个金星引力辅助，潜在危险小行星飞掠的可行性

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

Acta Astronautica

Pub Date : 2026-01-08 DOI: 10.1016/j.actaastro.2026.01.016

Vladislav Zubko

This work develops low-energy spacecraft (SC) trajectories using Venus gravity assists to study asteroids during heliocentric transfer segments between planetary encounters. The study focuses on potentially hazardous asteroids (PHAs) as primary exploration targets. This paper proposes a method for calculating SC trajectories that enable asteroid flybys after a Venus gravity assist. The method involves formulating and solving an optimization problem to design trajectories incorporating flybys of selected asteroids and Venus. Trajectories are calculated using two-body dynamics by solving the Lambert problem. A preliminary search for candidate asteroids uses an algorithm to narrow the search space of the optimization problem. This algorithm uses the V-infinity globe technique to connect planetary gravity assists with resonant orbits. The resonant orbit in this case serves as an initial approximation for the SC’s trajectory between two successive planetary flybys. Four flight schemes were analyzed, including multiple flybys of Venus and asteroids, with the possibility of an SC returning to Earth. The proposed solutions reduce flight time between asteroid approaches, increase gravity assist frequency, and enhance mission design flexibility. The use of Venus gravity assists and resonant orbits ensures a close encounter with at least one asteroid during the SC’s trajectory between two consecutive flybys of Venus, and demonstrates the feasibility of periodic Venus gravity assists and encounters with PHAs. The developed method was applied to construct trajectories that allow an SC to approach both co-orbital asteroids with Venus and PHAs via multiple Venus gravity assists. An additional study was carried out to identify asteroids accessible during the Earth–Venus segment in launch windows between 2029 and 2050.

这项工作开发了低能航天器（SC）的轨迹，利用金星引力辅助研究小行星在行星相遇之间的日心转移段。这项研究将潜在危险小行星（PHAs）作为主要的探测目标。本文提出了一种计算金星重力辅助后小行星飞掠的SC轨迹的方法。该方法包括制定和解决一个优化问题，以设计包含选定小行星和金星飞越的轨迹。通过求解朗伯问题，利用二体动力学计算轨迹。对候选小行星的初步搜索使用了一种算法来缩小优化问题的搜索空间。该算法使用v无限球技术将行星引力辅助与共振轨道连接起来。在这种情况下，共振轨道作为SC在两次连续的行星飞掠之间的轨迹的初始近似。分析了四种飞行方案，包括多次飞越金星和小行星，以及SC返回地球的可能性。提出的解决方案减少了小行星接近之间的飞行时间，增加了重力辅助频率，并增强了任务设计的灵活性。金星引力辅助和共振轨道的使用确保了在连续两次飞越金星之间的SC轨道上至少与一颗小行星近距离接触，并证明了金星引力辅助和周期性接触pha的可行性。该方法被应用于构建轨道，允许SC通过多个金星重力辅助来接近与金星和pha共轨道的小行星。另一项研究是在2029年至2050年的发射窗口期间，确定地球-金星段可到达的小行星。

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引用次数: 0

Attitude stabilization of slender payloads in partial space elevator transport by super-twisting sliding mode control 基于超扭转滑模控制的部分空间电梯运输细长有效载荷姿态稳定

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

Acta Astronautica

Pub Date : 2026-01-07 DOI: 10.1016/j.actaastro.2026.01.004

Gefei Shi , Zheng H. Zhu

This work develops the rigid-flexible coupled dynamic model of a partial space elevator transporting a slender structural payload by the climber during cross-orbit payload transfer. The payload is modeled by Euler–Bernoulli beam theory, and analysis shows that even small bending deformation of the payload can induce large attitude motion of the climber-payload assembly due to strong orbit-rigid–flexible coupling. To quantify this behavior, a closed-form expression is derived for the steady bending deformation of the payload under the gravity-gradient effect. Building on this analytical insight, a nonlinear compensation control torque is formulated to suppress attitude motion caused by rigid–flexible coupling without requiring impractically large control torques. To enhance control robustness, a super-twisting sliding mode control scheme is proposed by embedding the forward control law within a Lyapunov stability framework. This combined strategy eliminates residual dynamics and reduces the chattering inherent in sliding mode control while ensuring global attitude stability. Numerical simulations verify that the proposed strategy significantly reduces the attitude excursions of the climber-payload assembly while keeping the required control torques within the capacity of reaction wheels on the climber (rigid body). Overall, this work establishes a nonlinear dynamic framework for tethered transport systems with slender structure payloads and provides the first validated control solution enabling safe, stable, and efficient operation of partial space elevator transporting slender structure payloads.

建立了由爬升器运输细长结构载荷的部分空间升降机跨轨道载荷转移的刚柔耦合动力学模型。利用欧拉-伯努利梁理论对载荷进行了建模，分析表明，由于轨道-刚柔耦合较强，即使载荷发生很小的弯曲变形，也会引起爬坡-载荷组件较大的姿态运动。为了量化这种行为，导出了重力梯度作用下载荷稳态弯曲变形的封闭表达式。基于这一分析见解，制定了非线性补偿控制力矩来抑制由刚柔耦合引起的姿态运动，而不需要不切实际的大控制力矩。为了提高控制鲁棒性，提出了一种将前向控制律嵌入Lyapunov稳定性框架的超扭转滑模控制方案。该组合策略在保证全局姿态稳定性的同时，消除了滑模控制中固有的残余动力学和抖振。数值仿真结果表明，该策略在保证爬升器（刚体）上反力轮所能承受的所需控制力矩的同时，显著降低了爬升器-载荷组件的姿态漂移。总体而言，本研究建立了细长结构有效载荷系留运输系统的非线性动力学框架，并提供了第一个经过验证的控制方案，使部分空间电梯运输细长结构有效载荷能够安全、稳定、高效地运行。

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引用次数: 0

Evaluating launcher options for Europe in a world of Starship 在星际飞船世界中评估欧洲的发射器选项

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

Acta Astronautica

Pub Date : 2026-01-07 DOI: 10.1016/j.actaastro.2026.01.018

Martin Sippel, Jascha Wilken, Ingrid Dietlein, Moritz Herberhold, Kevin Bergmann, Leonid Bussler

As soon as the SpaceX Starship & SuperHeavy launcher configuration is operationally available it likely will cause a fundamental shift to space transportation. In a first step, the paper provides a thorough technical analysis of Starship's estimated capabilities in its early operational phase, based on independent modeling with openly available data.

The main part of the paper is dedicated to the technical evaluation of European options for serving a roughly similar payload class above 20 Mg up to approaching 100 Mg in single launch to LEO. A launcher system analysis looks into Ariane 6 evolution options and explores the technical limits based on the assumption of expendable stages. A significantly better performance perspective can be achieved through a completely new architecture. In case of these new architecture launchers, all first stages are reusable and exclusively liquid cryogenic propellants are chosen. Fully reusable configurations have been addressed in the small ESA-funded PROTEIN-study for which some complementary concepts are summarized.

The different launcher options show a broad range in payload performance. As these diverse vehicles come with significantly different cost, the NRC and RC are modeled for reasonable European heavy-lift transportation scenarios.

The paper concludes with a comparative evaluation of main technical characteristics of the launch vehicle options and an indication of promising development roadmaps.

一旦SpaceX公司的超重型发射装置配置投入使用，它可能会导致太空运输的根本性转变。首先，本文基于独立建模和公开数据，对星舰早期作战阶段的估计能力进行了全面的技术分析。论文的主要部分致力于欧洲方案的技术评估，在单次发射到近地轨道时，提供大致相似的负载等级，从20毫克以上到接近100毫克。发射系统分析着眼于阿丽亚娜6的进化选择，并探讨了基于消耗性阶段假设的技术限制。通过全新的体系结构可以实现更好的性能透视图。在这些新结构的发射器中，所有的第一级都是可重复使用的，并且只选择液体低温推进剂。在esa资助的小型蛋白质研究中，已经解决了完全可重复使用的配置，其中总结了一些补充概念。不同的发射装置选项在有效载荷性能上显示了广泛的范围。由于这些不同的车辆成本差异很大，因此NRC和RC模型适用于合理的欧洲重型运输方案。最后，本文对各种运载火箭的主要技术特性进行了比较评价，并指出了有希望的发展路线图。

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引用次数: 0

Investigation of aluminum ignition dynamics with lower initial particle temperature 较低初始颗粒温度下铝点火动力学研究

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

Acta Astronautica

Pub Date : 2026-01-07 DOI: 10.1016/j.actaastro.2026.01.009

Zhan Wen , Yanfeng Jiang , Huisi Wang , Weichen Qu , Jiawei Yan , Peijin Liu , Wen Ao

This work utilized a technique known as single-particle laser ignition, paired with high-speed photography, spectrum to explore the ignition and combustion properties under −60 °C. The results indicate that while a decrease in temperature does not significantly alter the overall combustion processes—comprising melting expansion, rupture of the oxide film, stable combustion, and eventual extinction—it does diminish the intensity of the reactions occurring during ignition. When the temperature decreases, the ignition delay time for particles of the same size tends to increase, directly correlating with particle size. For instance, at −60 °C compared to 20 °C, Al particles with a diameter of 1000 μm show a notable rise in ignition delay time from 674 ms to 1098 ms, indicating a 62.9 % increase. In contrast, smaller Al particles are less sensitive to temperature changes. For 500 μm Al particles, the time it takes for ignition to occur increases from 163 ms to 218 ms as the temperature changes within the same range, resulting in a smaller percentage increase of 33.7 %. To better understand the ignition process, a model was created that accounts for the effects of both particle size and temperature on ignition behaviour. In the early stages of ignition, the main source of heat is convective heat transfer, which plays a crucial role in initiating the ignition process. Once the Al particles have melted completely, surface chemical reactions become a significant source of heat. This model accurately describes the influence of the initial temperature on the ignition process and energy transfer, showing an average deviation of 7.03 % between predicted ignition delay times for different temperatures and particle sizes compared to experimental data. Overall, this study enhances our understanding of the ignition and combustion processes of Al particles across a range of temperatures.

这项工作利用了一种被称为单粒子激光点火的技术，结合高速摄影，光谱来探索- 60°C下的点火和燃烧特性。结果表明，虽然温度的降低不会显著改变整个燃烧过程——包括熔化膨胀、氧化膜破裂、稳定燃烧和最终熄灭——但它确实降低了点火过程中发生的反应的强度。当温度降低时，相同粒径颗粒的点火延迟时间有增加的趋势，且与粒径成正比。例如，与20℃相比，在−60℃时，直径为1000 μm的Al颗粒的点火延迟时间从674 ms显著增加到1098 ms，增加了62.9%。相比之下，较小的Al颗粒对温度变化不太敏感。对于500 μm Al颗粒，随着温度的变化，其着火时间从163 ms增加到218 ms，增加幅度较小，为33.7%。为了更好地理解点火过程，研究人员创建了一个模型，该模型考虑了颗粒大小和温度对点火行为的影响。在点火初期，主要的热源是对流换热，对流换热在点火过程中起着至关重要的作用。一旦铝颗粒完全熔化，表面化学反应就成为一个重要的热源。该模型准确地描述了初始温度对点火过程和能量传递的影响，在不同温度和颗粒尺寸下，预测的点火延迟时间与实验数据的平均偏差为7.03%。总的来说，这项研究增强了我们对铝颗粒在一定温度范围内的点火和燃烧过程的理解。

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引用次数: 0

Active spinning control for a flexible photonic electric solar wind sail spacecraft 柔性光子电太阳风帆航天器的主动自旋控制

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

Acta Astronautica

Pub Date : 2026-01-07 DOI: 10.1016/j.actaastro.2025.12.044

Shengjun Zeng, Wei Fan, Hui Ren

Motivated by a hybrid motivation mechanism, the photonic electric solar wind sail (E-sail) spacecraft is regarded as an innovative propellant-free propulsion concept for interstellar missions. Under typical operating conditions, the solar wind dynamic pressure (SWDP) interacts with the charged main tether to generate the primary thrust, while the solar radiation pressure (SRP) acts on the photonic film at the end of each main tether to generate attitude adjustment torque. Compared with the classical E-sail spacecraft, the photonic E-sail spacecraft enables active spinning control by regulating the inclination of the extra photonic films, while an effective spinning control strategy for the rigid–flexible coupled model remains underexplored. Based on the full-scale dynamical model derived by the referenced nodal coordinate formulation (RNCF) approach, this work investigates an active spinning control strategy for the photonic E-sail spacecraft. The reflectance control device (RCD) is integrated into the structural design of the photonic film, which enables active optical parameters modulation to regulate the solar radiation pressure (SRP) induced thrust. A practical spin rate feedback control strategy for the photonic E-sail spacecraft is proposed, where the reflectance distribution across its partitions drives the photonic film inclination, thereby indirectly manipulating the overall spin rate. By numerical simulations with different configurations, the dynamical characteristics of the varying optical parameters on the full-scale photonic E-sail spacecraft model are analyzed. Plus, the effectiveness of the proposed active spinning manipulation mechanisms is validated. Furthermore, the collaborative simulation on the spinning control module and the orientation control module demonstrates the feasibility of the simultaneous manipulation of the spin rate and the sail plane rotation parameters. The proposed spinning control strategy provides an accurate and efficient approach for comprehensive attitude control for the spinning spacecrafts.

光子-电-太阳风帆（E-sail）航天器采用混合动力机制驱动，是一种创新的无推进剂星际任务推进概念。在典型工况下，太阳风动压（SWDP）与带电的主系绳相互作用产生一次推力，太阳辐射压（SRP）作用于每根主系绳末端的光子膜产生姿态调节扭矩。与传统的E-sail航天器相比，光子E-sail航天器通过调节额外光子膜的倾角实现主动自旋控制，而刚性-柔性耦合模型的有效自旋控制策略还有待研究。基于参考节点坐标公式（RNCF）方法建立的全尺寸动力学模型，研究了光子E-sail航天器的主动自旋控制策略。将反射率控制装置（RCD）集成到光子薄膜的结构设计中，实现了主动光学参数调制来调节太阳辐射压力（SRP）诱导推力。提出了一种实用的光子E-sail航天器自旋速率反馈控制策略，该策略利用航天器各隔板间的反射率分布驱动光子膜倾角，从而间接控制整体自旋速率。通过不同构型的数值模拟，分析了全尺寸光子E-sail模型上不同光学参数的动力学特性。此外，还验证了所提出的主动旋转操纵机构的有效性。此外，对旋转控制模块和方向控制模块进行了协同仿真，验证了同步控制旋转速率和帆面旋转参数的可行性。所提出的自旋控制策略为自旋航天器的姿态综合控制提供了一种准确、有效的方法。

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引用次数: 0

MEMS Gyroscope technology for Low-Earth orbit aerospace: technologies, environmental challenges, and emerging design strategies 低地球轨道航空航天MEMS陀螺仪技术：技术、环境挑战和新兴设计策略

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

Acta Astronautica

Pub Date : 2026-01-06 DOI: 10.1016/j.actaastro.2026.01.011

Donghua Chen , Yusen Guo , Pengyu Huo , Qiliang Li

The rapid expansion of commercial Low-Earth Orbit (LEO) missions and mega-constellations has created stringent requirements for compact, cost-effective, and highly reliable inertial sensors. Micro-Electro-Mechanical Systems (MEMS) gyroscopes have emerged as pivotal components in Attitude Determination and Control Systems (ADCS) due to their superior SWaP-C advantages over traditional optical gyroscopes. However, the LEO environment imposes severe constraints, including extreme thermal fluctuations, ionizing radiation, vacuum-induced outgassing, and launch-induced mechanical stresses, all of which degrade long-term stability and reliability. This review provides a comprehensive analysis of recent advancements in MEMS gyroscope design, with emphasis on structural innovations, radiation-hardened electronics, advanced packaging, and data-driven signal processing methods that have been predominantly demonstrated through ground-based simulations and laboratory validations. This paper further examines their adoption in commercial satellite constellations, remote sensing, and reusable platforms, and highlights emerging trends such as hybrid fiber-optic/MEMS systems and digital-twin concepts for design optimization and performance assessment, while explicitly distinguishing demonstrated results from conceptual or simulation-based studies. Special attention is given to LEO-specific environmental degradation mechanisms and mitigation strategies through material selection, circuit hardening, and redundant architecture. The review concludes by outlining future directions in sensor miniaturization, intelligent self-calibration, and resilient system integration, and by identifying key validation gaps for learning-based and digital-twin-enabled approaches under space environmental constraints, underscoring MEMS gyroscopes’ critical role in enabling next-generation spaceborne navigation and control. This work aims to guide researchers and developers in creating robust, space-grade MEMS inertial solutions for commercial aerospace applications.

商业低地球轨道（LEO）任务和巨型星座的快速扩张对紧凑、经济、高可靠的惯性传感器提出了严格的要求。微机电系统（MEMS）陀螺仪由于其优于传统光学陀螺仪的SWaP-C优势，已成为姿态确定与控制系统（ADCS）的关键部件。然而，低轨道环境施加了严重的限制，包括极端的热波动、电离辐射、真空引起的放气和发射引起的机械应力，所有这些都降低了长期的稳定性和可靠性。这篇综述全面分析了MEMS陀螺仪设计的最新进展，重点是结构创新、抗辐射电子、先进封装和数据驱动的信号处理方法，这些方法主要通过地面模拟和实验室验证来证明。本文进一步研究了它们在商业卫星星座、遥感和可重复使用平台中的应用，并强调了新兴趋势，如混合光纤/MEMS系统和用于设计优化和性能评估的数字孪生概念，同时明确区分了演示结果与概念或基于仿真的研究。通过材料选择、电路硬化和冗余结构，特别关注leo特定的环境退化机制和缓解策略。最后，概述了传感器小型化、智能自校准和弹性系统集成的未来方向，并确定了空间环境约束下基于学习和数字孪生方法的关键验证差距，强调了MEMS陀螺仪在实现下一代星载导航和控制方面的关键作用。这项工作旨在指导研究人员和开发人员为商业航空航天应用创建强大的空间级MEMS惯性解决方案。

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引用次数: 0

Kinematic orbit determination for BDS-3 satellites with inter-satellite link data 基于星间链路数据的BDS-3卫星运动学定轨

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

Acta Astronautica

Pub Date : 2026-01-06 DOI: 10.1016/j.actaastro.2026.01.015

Chao Yang , Jing Guo , Xiaolong Mi , Yuanfan Deng , Xuexi Liu , Qile Zhao , Wu Chen

Kinematic orbit determination offers an efficient and highly accurate alternative to traditional methods by eliminating the need for time-consuming orbit integration and complex satellite dynamics modeling (e.g., solar radiation pressure, earth radiation pressure, etc.). Leveraging the Ka-band inter-satellite link (ISL) payloads deployed on the BeiDou global navigation satellite system (BDS-3), this study presents, for the first time, kinematic orbit determination results for BDS-3 satellites using real ISL measurements. The analysis reveals that the position dilution of precision (PDOP) for Medium Earth Orbit (MEO) satellites ranges from 0.8 to 2.0, while for Inclined Geosynchronous Orbit (IGSO) and Geostationary (GEO) satellites, PDOP values remain within 1.2–2.5 and 1.2–2.0, respectively. The mean 3D RMS values of kinematic orbits are approximately 13.6 cm, 23.5 cm, and 33.7 cm for MEO, IGSO and GEO satellites, respectively, when the orbits of all satellites except one are constrained to the precise dynamic solutions. The mean cross-track accuracy of BDS-3 satellites is 7.3 cm, which is more than 1.5 cm larger than that of the along-track and radial directions. Furthermore, this work systematically investigates the impact of the number of fixed satellites on kinematic solutions, demonstrating that fixing two satellites improves orbit accuracy by 29 % over fixing just one, and that constraining all IGSO and GEO satellites yields optimal results for MEO satellites, with mean 3D RMS values of 15.8 cm (along-track), 14.5 cm (cross-track), and 14.0 cm (radial). Notably, the kinematic orbit accuracy remains robust, as no significant decrease is detected during eclipse seasons.

运动学定轨方法消除了耗时的轨道整合和复杂的卫星动力学建模（如太阳辐射压力、地球辐射压力等），为传统方法提供了一种高效、高精度的替代方案。利用部署在北斗全球导航卫星系统（BDS-3）上的ka波段星间链路（ISL）有效载荷，本研究首次展示了使用实际ISL测量的BDS-3卫星的运动学定轨结果。分析表明，中地球轨道（MEO）卫星的位置精度稀释系数（PDOP）在0.8 ~ 2.0之间，而倾斜地球同步轨道（IGSO）和静止地球轨道（GEO）卫星的位置精度稀释系数（PDOP）分别在1.2 ~ 2.5和1.2 ~ 2.0之间。除1颗卫星外，MEO、IGSO和GEO卫星在精确动力学解约束下的运动轨道三维均方根值分别约为13.6 cm、23.5 cm和33.7 cm。北斗三号卫星的平均横航迹精度为7.3 cm，比顺航迹和径向精度高1.5 cm以上。此外，本工作系统地研究了固定卫星数量对运动学解的影响，表明固定两颗卫星比只固定一颗卫星可提高29%的轨道精度，并且约束所有IGSO和GEO卫星对MEO卫星产生最佳结果，平均3D均方根值为15.8 cm（沿轨道），14.5 cm（交叉轨道）和14.0 cm（径向）。值得注意的是，由于在日食季节没有检测到明显的下降，运动学轨道精度保持稳定。

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