Aerospace Systems最新文献_第4页

Robots and manipulators for structure assembly, spacecraft maintenance and space debris transportation 用于结构装配、航天器维修和空间碎片运输的机器人和操作手

Aerospace Systems Pub Date : 2025-10-14 DOI: 10.1007/s42401-025-00411-8

Victoria V. Svotina

引用次数: 0

Continuous high-latitude solar observation using sailcraft 用帆船进行连续高纬度太阳观测

Aerospace Systems Pub Date : 2025-10-07 DOI: 10.1007/s42401-025-00408-3

Alessandro A. Quarta

{"title":"Continuous high-latitude solar observation using sailcraft","authors":"Alessandro A. Quarta","doi":"10.1007/s42401-025-00408-3","DOIUrl":"10.1007/s42401-025-00408-3","url":null,"abstract":"<div><p>The peculiar characteristics of a photonic solar sail–propelled spacecraft (sailcraft) enable the design of scientific mission scenarios that are difficult to achieve with conventional propulsion systems, whether chemical or electric. In this context, a particularly challenging case, feasible only through the use of a high-performance solar sail, is the creation and maintenance of an equilibrium point in heliocentric space. At this point, the sailcraft’s velocity is zero, and the thrust provided by the photonic solar sail balances the Sun’s gravitational attraction. When a sailcraft reaches such a heliostationary point, thus becoming a statite (a term coined by Robert Forward), it can maintain this condition until the sail membrane degrades. This paper analyzes the transfer trajectories and mission performance of a sailcraft targeting a heliostationary point located above the Sun’s poles, at a given distance from the star’s center of mass. Such a statite would enable both continuous observation of the Sun’s poles and high-latitude regions, as well as uninterrupted communication with ground stations without the risk of radio occultation by the solar disk. The study considers a three-dimensional scenario starting from an elliptical parking orbit and accounts for incomplete reflections of the sail’s thin membrane in modeling the thrust vector. In particular, a new mission strategy is proposed in which the sailcraft’s heliocentric trajectory to the target heliostationary point is divided into two optimized phases.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 3","pages":"693 - 705"},"PeriodicalIF":0.0,"publicationDate":"2025-10-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148871741","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Parametric aerodynamic characterization of tail geometry variations in fixed-wing UAVs 固定翼无人机尾翼几何变化的参数气动特性研究

Aerospace Systems Pub Date : 2025-09-24 DOI: 10.1007/s42401-025-00406-5

Ali J. Dawood Al-Khafaji, Luttfi A. Al-Haddad

{"title":"Parametric aerodynamic characterization of tail geometry variations in fixed-wing UAVs","authors":"Ali J. Dawood Al-Khafaji, Luttfi A. Al-Haddad","doi":"10.1007/s42401-025-00406-5","DOIUrl":"10.1007/s42401-025-00406-5","url":null,"abstract":"<div><p>The evolution of unmanned aerial vehicle (UAV) systems continues to accelerate due to the integration of advanced simulation environments that enable rapid design iteration and aerodynamic optimization. This study presents a parametric investigation into the influence of empennage configuration—specifically cant tail angle and vertical tailplane height—on the aerodynamic performance of fixed-wing UAVs. A total of thirty-six full-scale three-dimensional UAV models were developed using SOLIDWORKS, each utilizing the SD8020 airfoil for both the main and tail wings. The models incorporate combinations of three cant angles (30°, 45°, 60°), three tail heights (1.0 m, 1.5 m, 2.0 m), and four angles of attack (2°, 3°, 4°, 5°). High-fidelity aerodynamic analysis was conducted using steady-state Reynolds-averaged Navier–Stokes (RANS) simulations with the SST k–ω turbulence model in ANSYS Fluent. The results reveal that the configuration with a cant angle of 60°, tail height of 1.0 m, and angle of attack of 4° yielded the highest aerodynamic efficiency, exhibiting a 39% improvement in lift-to-drag ratio compared to the lowest-performing configuration. The findings provide actionable insight for UAV tail architecture design, supporting more efficient performance-driven development of autonomous aerial platforms.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 1","pages":"89 - 104"},"PeriodicalIF":0.0,"publicationDate":"2025-09-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147375337","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Comparative analysis of hypersonic flow characteristics over spiked re-entry bodies with counterflow jets using CFD 利用CFD对带逆流射流的尖顶再入体高超声速流动特性进行对比分析

Aerospace Systems Pub Date : 2025-09-15 DOI: 10.1007/s42401-025-00405-6

Divij Arora, Sachin Srivastava, Suryaprakash Gairola

{"title":"Comparative analysis of hypersonic flow characteristics over spiked re-entry bodies with counterflow jets using CFD","authors":"Divij Arora, Sachin Srivastava, Suryaprakash Gairola","doi":"10.1007/s42401-025-00405-6","DOIUrl":"10.1007/s42401-025-00405-6","url":null,"abstract":"<div><p>By adopting the CFD based approach, the hypersonic flow nature is investigated under a Free-stream Mach number of 6 for two distinct re-entry configurations; namely, a spiked conical-nosed body, and a spiked T-shaped blunt-nosed body, each coupled with counterflow jets. A high-fidelity structured mesh and the SST k-omega Turbulence model within the Ansys Fluent framework are employed to capture flow phenomena like bow shock detachment, recirculation, and wake formation with finer precision. The analysis is performed on vital performance parameters such as aerodynamic drag, surface pressure and temperature distributions, and the effect of counterflow jets on shock stand-off distance and thermal load reduction. We find results indicating drag reduction of 52% by the conical blunt-nosed configuration compared to the T-Shape nose configuration and an increase in shock stand-off distance by 0.0175. Moreover, counterflow jets reduce the surface temperature by a maximum of 300 K at critical forebody regions, while the total pressure recovery improves by 50%. These findings affirm that nose shape is a critical parameter influencing the hypersonic flow control and thus offers new perspectives for the design optimization, with T-shaped configuration providing improved thermal protection and aerodynamic efficiency.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 1","pages":"79 - 88"},"PeriodicalIF":0.0,"publicationDate":"2025-09-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147375332","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Coupling interactions in aeroelastic analysis of 3D aircraft wings with control surface during flight 三维飞机机翼控制面气动弹性分析中的耦合相互作用

Aerospace Systems Pub Date : 2025-09-09 DOI: 10.1007/s42401-025-00395-5

Emad Q. Hussein, Farhan Lafta Rashid, Khalid M. Sowoud, Karrar A. Hammoodi, Ephraim Bonah Agyekum

{"title":"Coupling interactions in aeroelastic analysis of 3D aircraft wings with control surface during flight","authors":"Emad Q. Hussein, Farhan Lafta Rashid, Khalid M. Sowoud, Karrar A. Hammoodi, Ephraim Bonah Agyekum","doi":"10.1007/s42401-025-00395-5","DOIUrl":"10.1007/s42401-025-00395-5","url":null,"abstract":"<div><p>This work investigates the dynamic characteristics of a system susceptible to flutter phenomena during aircraft flight operation while considering fluctuations in critical system parameters, including stiffness, damping, flap angle, angle of attack, and yaw angle. A parametric analysis was conducted to quantify the influence of each parameter on the system response, particularly focusing on bending and torsional mode. To substantiate the findings, comparing simulated, theoretical, and experimental results shows good agreement in overall trends. The results show that increasing stiffness from 100 N/m to 300 N/m reduced the peak bending displacement by approximately 80%, demonstrating a strong stabilizing effect. Similarly, increasing the damping coefficient from 0.1 to 1 resulted in a 40% reduction in torsional angle amplitude, highlighting the importance of damping in controlling the system’s oscillatory behavior. Additionally, aerodynamic variations such as yaw angle shifts from 0<sup>o</sup> to 5<sup>o</sup> increased bending displacement amplitude by 70%, revealing the system’s sensitivity to aerodynamic conditions. Similarly, increasing the angle of attack from 0<sup>o</sup> to 10<sup>o</sup> increases the bending displacement amplitude by 50%<span>(:.)</span> Emplacing the perturbative effect that elevated angles of attack exert on the system. The flap angle was also found to have a significant impact, with 60% increase in flutter speed observed when the flap angle was increased from 0<sup>o</sup> to 30<sup>o</sup>, reducing the system’s susceptibility to instability.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 1","pages":"67 - 77"},"PeriodicalIF":0.0,"publicationDate":"2025-09-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147375334","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Research on imaging satellite mission planning method for multi-mode and multi-point target tasks 多模式、多点目标任务的成像卫星任务规划方法研究

Aerospace Systems Pub Date : 2025-09-03 DOI: 10.1007/s42401-025-00376-8

Wei Wang, Xiaowei Shao, Wan Liu, Dexin Zhang

{"title":"Research on imaging satellite mission planning method for multi-mode and multi-point target tasks","authors":"Wei Wang, Xiaowei Shao, Wan Liu, Dexin Zhang","doi":"10.1007/s42401-025-00376-8","DOIUrl":"10.1007/s42401-025-00376-8","url":null,"abstract":"<div><p>The imaging satellite task of multi-mode and multi-point targets is widely used in military reconnaissance, environmental monitoring, meteorological forecasting and other fields. To address the multi-task observation conflict and strip sequence decision-making problem under constrained conditions, and to effectively resolve observation conflicts between different task modes, this paper proposes a greedy algorithm based on Heuristic Dynamic Programming (HDPGA). The objective is to maximize task value while minimizing time expenditure, ensuring all tasks are completed with reduced time costs, thereby achieving optimal overall efficiency. Using dynamic programming can decompose tasks into subtasks and store solutions to subproblems to avoid redundant calculations, retain the advantages of greedy algorithms (GA) in efficient computation, and efficiently complete the entire task by solving subtasks. This study first analyzes the demand characteristics of multi-mode and multi-point target tasks, establishes a model to ensure that task constraints are met, then uses a greedy algorithm based on heuristic dynamic programming to solve the model, and finally conducts simulation experiments and result analysis. The experimental results show that when paying for 7 cycles of time cost during single orbit operation, using HDPGA algorithm can obtain all values, while using traditional GA algorithm can only obtain 63.64% of all values. When all tasks are completed and all value benefits are obtained, HDPGA algorithm can reduce time costs by more than 30% compared to GA algorithm.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 3","pages":"661 - 673"},"PeriodicalIF":0.0,"publicationDate":"2025-09-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148871583","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Experimental and theoretical investigation of combustion efficiency, regression rate, and thrust characteristics of a hybrid rocket engine using PVC/DBP fuel 聚氯乙烯/DBP混合燃料火箭发动机燃烧效率、回归率和推力特性的实验与理论研究

Aerospace Systems Pub Date : 2025-08-04 DOI: 10.1007/s42401-025-00392-8

Akash Pawar, Aneena Praveen, Harikrishna Chavhan, Amit Kumar Thakur

{"title":"Experimental and theoretical investigation of combustion efficiency, regression rate, and thrust characteristics of a hybrid rocket engine using PVC/DBP fuel","authors":"Akash Pawar, Aneena Praveen, Harikrishna Chavhan, Amit Kumar Thakur","doi":"10.1007/s42401-025-00392-8","DOIUrl":"10.1007/s42401-025-00392-8","url":null,"abstract":"<div><p>Hybrid-rocket propulsion, which combines the benefits of both liquid and solid propulsion, has gained attention for its safety, throttling capability, and cost-effectiveness. This study presents a combined experimental and theoretical investigation of a hybrid rocket engine using PVC/DBP as fuel and gaseous oxygen as the oxidizer. Four successive firings were conducted to analyze thrust, regression rate, chamber pressure, and specific impulse. NASA CEA was used to model the ideal combustion parameters. The PVC-DBP fuel formulation offers advantages such as ease of processing, availability, and controlled burning behavior. A series of experimental static tests were conducted using a hybrid-rocket engine equipped with a showerhead injector and a convergent-divergent nozzle. The findings demonstrate an inverse correlation between the mass flux of the oxidizer and the regression rate, with measurements dropping from 0.94 to 0.70 mm/s. over successive firings as port diameter increased from 15 to 28.15 mm. Thrust measurements followed a similar trend, declining from 220 to 50 N, reflecting reduced combustion intensity due to oxidizer dilution. Combustion efficiency improved from 52.16 to 59.55%, suggesting enhanced fuel regression dynamics across multiple firings. Additionally, comparative analysis reveals significant deviations from ideal behavior due to combustion inefficiencies and thermal losses, highlighting the need for nozzle and chamber optimization in practical hybrid engine systems.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 1","pages":"53 - 66"},"PeriodicalIF":0.0,"publicationDate":"2025-08-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147375333","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Nonlinear ({mathcal {H}}_infty ) control for spacecraft formation flight 航天器编队飞行非线性({mathcal {H}}_infty )控制

Aerospace Systems Pub Date : 2025-08-04 DOI: 10.1007/s42401-025-00377-7

Parker Stewart, Christopher J. Damaren

引用次数: 0

Integrated vibration suppression-based attitude tracking control of a flexible satellite in rapid imaging maneuver 基于综合减振的柔性卫星快速成像机动姿态跟踪控制

Aerospace Systems Pub Date : 2025-07-30 DOI: 10.1007/s42401-025-00388-4

Mohammad Zarourati, Mehran Mirshams, Morteza Tayefi

{"title":"Integrated vibration suppression-based attitude tracking control of a flexible satellite in rapid imaging maneuver","authors":"Mohammad Zarourati, Mehran Mirshams, Morteza Tayefi","doi":"10.1007/s42401-025-00388-4","DOIUrl":"10.1007/s42401-025-00388-4","url":null,"abstract":"<div><p>A deployable solar array provides electrical power to many remote sensing satellites. The deployable solar arrays are long, wide, and thin, resulting in high flexibility. This flexibility poses some challenges to satellite attitude control. Nevertheless, remote sensing satellites require rapid maneuvers to take images from targets with imaging time constraints. To meet these challenges, satellites must perform rapid maneuvers. This rapid maneuver causes oscillation of the deployable solar array, which decreases the image quality. This study proposes an attitude control to eliminate the uncertainties caused by deploying solar array vibrations. Based on the uncertainties of the satellite model and environmental disturbances, an adaptive robust attitude controller is employed. The adaptive robust attitude control performs well in low maneuver rates. However, in rapid attitude maneuvers, the high-frequency vibration amplitude of the angular velocities increases. Therefore, an integrated control approach is used to suppress the vibrations. The input shaping technique is based on employing a command signal that eliminates vibrations generated in the satellite’s flexible components. The proposed control method is an adaptive robust attitude controller based on the input shaping technique. As a result, our work improves the jitter in imaging missions and reduces the remaining vibrations of the flexible components by utilizing the zero vibration input shaping technique. Finally, numerical simulations demonstrate that the proposed control method can improve pointing accuracy and stability and is robust to uncertainty.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 3","pages":"555 - 571"},"PeriodicalIF":0.0,"publicationDate":"2025-07-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148871605","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Flow mechanism of subharmonic resonance for a finite-span wing 有限跨机翼次谐波共振的流动机理

Aerospace Systems Pub Date : 2025-07-21 DOI: 10.1007/s42401-025-00379-5

Lei Chen, Jie Wu, Dechuan Ma, Bo Zeng, Gaohua Li, Junjie Peng, Fuxin Wang

{"title":"Flow mechanism of subharmonic resonance for a finite-span wing","authors":"Lei Chen, Jie Wu, Dechuan Ma, Bo Zeng, Gaohua Li, Junjie Peng, Fuxin Wang","doi":"10.1007/s42401-025-00379-5","DOIUrl":"10.1007/s42401-025-00379-5","url":null,"abstract":"<div><p>To clarify the coupling mechanism between the aeroelastic responses and flow fields of helicopter blades experiencing subharmonic resonance, the experimental and numerical investigations are performed on a three-dimensional (3D) aeroelastic system that incorporates the tip vortex effect. The experimental results reveal subharmonic resonance phenomena occurring when the natural frequency is 1.45 times the driving frequency. For obtaining the 3D global flow fields, the high-fidelity numerical simulations are conducted under the conditions of subharmonic resonance. The dominant modes of flow fields and their spatio-temporal evolution are identified by proper orthogonal decomposition. It is shown that the subharmonic components in aeroelastic responses and aerodynamic loads result from the evolution of the flow fields. The decrease in reduced frequency leads to attenuation of the dynamic stall vortex, simultaneously enhancing flow stability and suppressing subharmonic components, which explains the saddle-node bifurcation of limit cycles during dynamical evolution. The formation of counter-rotating vortex pairs further enhances this stabilization mechanism.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 1","pages":"39 - 52"},"PeriodicalIF":0.0,"publicationDate":"2025-07-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147375277","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0