Acta Astronautica最新文献_第3页

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 3.5 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

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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引用次数: 0

Piecewise rational Padé and Hermite approximations for the elliptic Kepler equation 椭圆开普勒方程的分段有理Pad ' e和Hermite近似

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.2026.01.014

Manuel Calvo , Antonio Elipe, Luis Rández

Accurate and efficient solution of the Elliptic Kepler Equation (EKE) is fundamental in orbital mechanics and spacecraft trajectory analysis. In this work, we present a family of piecewise rational approximations for solving the EKE,

F (E; e) \equiv E - e sin E = M,

based on Padé and Hermite-type formulations. The proposed approaches replaces the transcendental term

sin E

with Hermite and Piecewise Padé-Type (PPT) approximants, the later originally introduced by Brezinski, providing higher accuracy than the traditional Piecewise Padé (PP) method of Wu et al. without increasing computational cost. With these approximants, the resulting rational form reduces the EKE to a cubic equation that can be solved analytically, making it suitable for onboard implementations or large-scale orbit propagation tasks. Numerical experiments demonstrate that the PPT-based solution significantly improves accuracy for moderate and high eccentricities, including near-parabolic cases. Additionally, optimized parameter selection in general [3/2] rational representations yields further accuracy gains. These results show that the proposed piecewise rational method offers a reliable and computationally efficient alternative for precise orbital position determination across a wide range of eccentricities.

精确、高效地求解椭圆开普勒方程是轨道力学和航天器轨道分析的基础。在这项工作中，我们提出了一组分段有理近似来求解EKE， F(E； E)≡E−esinE=M，基于pad和hermite型公式。本文提出的方法用Hermite和Piecewise pad - type （PPT）近似代替了超越项sin，后者最初是由Brezinski引入的，在不增加计算成本的情况下，提供了比Wu等人的传统Piecewise pad - type （PP）方法更高的精度。通过这些近似，得到的有理形式将EKE简化为可以解析求解的三次方程，使其适合于机载实现或大规模轨道传播任务。数值实验表明，基于ppt的解决方案显著提高了中、高偏心率的精度，包括近抛物线情况。此外，在一般[3/2]理性表示中优化的参数选择可以进一步提高精度。这些结果表明，所提出的分段合理方法提供了一种可靠且计算效率高的替代方法，可以在大范围的偏心距范围内精确确定轨道位置。

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引用次数: 0

Progress in metal additive manufacturing for space applications: A comprehensive review 金属增材制造空间应用研究进展综述

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.2026.01.003

Jieguang Huang , Xiaonan Cheng , Linhai Hao , Qian Wang , Jun Luo , Lehua Qi

Metal additive manufacturing (MAM) offers transformative potential for producing complex, high-performance components directly in space. However, a systematic understanding of which MAM processes are truly viable for in-space deployment, their current maturity levels, and the critical challenges that constrain further advancement remains limited. This review provides a comprehensive assessment of the adaptability of major MAM technologies, including Direct Energy Deposition (DED), Powder Bed Fusion (PBF), Material Extrusion (MEX), Material Jetting (MJT), and Vat Photopolymerization (VPP), to the unique conditions of microgravity and vacuum. By integrating dispersed findings into a unified framework that links process physics with environmental constraints, we offer a comparative analysis of terrestrial versus in-space operation, emphasizing how microgravity and vacuum reshape system architectures, melt-pool behavior, interlayer bonding, defect formation, and overall process capabilities. Key challenges related to equipment miniaturization and space adaptation, process monitoring and control, melt-solidification dynamics, and post-processing and quality assurance are critically examined, together with their implications for process-structure-property relationships under non-terrestrial conditions. Building on these insights, a technology-readiness roadmap is proposed to highlight priority research directions required to transition from isolated laboratory demonstrations toward robust, flight-ready MAM systems. This work establishes an integrated understanding of the state of the art and outlines future pathways for advancing metallic additive manufacturing in extreme space environments.

金属增材制造（MAM）为直接在太空中生产复杂、高性能的部件提供了变革性的潜力。然而，对于哪些MAM工艺在太空部署中真正可行、它们当前的成熟度水平以及限制进一步发展的关键挑战，系统的理解仍然有限。本文综述了包括直接能量沉积（DED）、粉末床熔融（PBF）、材料挤压（MEX）、材料喷射（MJT）和还原光聚合（VPP）在内的主要MAM技术在微重力和真空条件下的适应性。通过将分散的研究结果整合到一个统一的框架中，将过程物理与环境约束联系起来，我们对地面与空间操作进行了比较分析，强调微重力和真空如何重塑系统架构、熔池行为、层间键合、缺陷形成和整体过程能力。关键挑战涉及设备小型化和空间适应性，过程监测和控制，熔体凝固动力学，后处理和质量保证，以及它们对非地面条件下工艺-结构-性能关系的影响。在这些见解的基础上，提出了技术准备路线图，以突出从孤立的实验室演示过渡到强大的飞行准备MAM系统所需的优先研究方向。这项工作建立了对技术现状的综合理解，并概述了在极端空间环境中推进金属增材制造的未来途径。

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引用次数: 0

Optimization of vacuum arc thruster efficiency through inductive energy storage circuit control 通过电感储能电路控制优化真空电弧推力器效率

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.2025.12.063

Ping-Han Huang , Yueh-Heng Li

This study explores the optimization of vacuum arc thruster (VAT) performance through precise control of an inductive energy storage circuit. Two experimental approaches were investigated: (1) By varying the inductor charging time under single-pulse ignition, this experiment aims to determine the relationship between the circuit components and the performance of the VAT. (2) Implementing a dual-pulse ignition scheme with controlled inter-pulse delays, which aims to determine whether two ignitions interact with each other. In the single-pulse tests, maximum thrust performance occurred when the inductor current reached its peak. Reducing the charging current to approximately 76 % of this peak resulted in decreases of 28 %, 38 %, and 42 % in discharge energy, plasma plume, and mass ablation rate, respectively. These results demonstrate that VAT performance is strongly dependent on the energy stored in the inductor and the magnitude of the induced voltage generated upon IGBT turn-off.

In the dual-pulse tests, triggering two identical inductive circuits with a 3 μs inter-pulse delay significantly enhanced performance. Compared to a 3000 μs delay, this shortest delay resulted in a 68.74 % lower breakdown voltage for the second pulse, a 15.22 % increase in total discharge energy, a 98.7 % extension in discharge duration, and a 356 % increase in the ablation rate.

The highest thrust of 12.07 μN s and thrust-to-power ratio of 29.97 μN s/W were achieved at this shortest delay. These findings highlight that both induced voltage characteristics and short inter-pulse plasma dynamics play critical roles in maximizing VAT performance, offering practical insights for high-efficiency pulsed electric propulsion system design.

本研究通过精确控制电感储能电路来优化真空电弧推力器（VAT）的性能。研究了两种实验方法：(1)通过改变单脉冲点火下电感充电时间，确定电路元件与VAT性能之间的关系。(2)实现可控脉冲间延迟的双脉冲点火方案，确定两个点火是否相互作用。在单脉冲试验中，最大推力性能出现在电感电流达到峰值时。将充电电流降低到峰值的76%左右，放电能量、等离子体羽流和质量烧蚀率分别降低了28%、38%和42%。这些结果表明，增值性能强烈依赖于存储在电感的能量和感应电压的大小产生的IGBT关断。在双脉冲测试中，触发两个相同的电感电路，脉冲间延迟3 μs，显著提高了性能。与3000 μs延时相比，最短延时使第二脉冲击穿电压降低了68.74%，总放电能量增加了15.22%，放电时间延长了98.7%，烧蚀率提高了356%。在此延时下，系统的最大推力为12.07 μN s，推功率比为29.97 μN s/W。这些发现强调了感应电压特性和短脉冲间等离子体动力学在最大化增值性能方面发挥着关键作用，为高效脉冲电力推进系统的设计提供了实用的见解。

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引用次数: 0

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