Acta Astronautica最新文献_第9页

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

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