Aerospace Systems最新文献_第10页

Research on reliability of aero-engine nacelle based on survival analysis 基于生存分析的航空发动机机舱可靠性研究

Aerospace Systems Pub Date : 2023-03-03 DOI: 10.1007/s42401-023-00195-9

Zhili Chen, Xiuhua Chen, Xiaobo Zhang, Jian Chen, Yong Liang

引用次数: 0

Numerical study of fatigue damage accumulation in composite wing panels of prospective supersonic transport aircraft 超音速运输机复合材料翼板疲劳损伤累积的数值研究

Aerospace Systems Pub Date : 2023-03-01 DOI: 10.1007/s42401-023-00200-1

N. V. Turbin, K. A. Shelkov

引用次数: 0

A comparison between filtering approach and spline approximation method in smoothing flight data 滤波法与样条逼近法在飞行数据平滑中的比较

Aerospace Systems Pub Date : 2023-02-26 DOI: 10.1007/s42401-023-00201-0

O. N. Korsun, Sekou Goro, M. H. Om

引用次数: 1

Novel empirical models for estimating aerodynamic coefficients of small UAV propellers 估算小型无人机螺旋桨气动系数的新经验模型

Aerospace Systems Pub Date : 2023-02-24 DOI: 10.1007/s42401-023-00203-y

Siddhardha Kedarisetty, Joel George Manathara

{"title":"Novel empirical models for estimating aerodynamic coefficients of small UAV propellers","authors":"Siddhardha Kedarisetty, Joel George Manathara","doi":"10.1007/s42401-023-00203-y","DOIUrl":"10.1007/s42401-023-00203-y","url":null,"abstract":"<div><p>Designers of small UAVs are often faced with a hurdle in the propeller selection stage in preliminary design due to the lack of simple yet accurate models to estimate small propellers’ performance (thrust coefficient, power coefficient, and efficiency variation with advance ratio). It might even seem impossible to have accurate propeller performance models as the performance depends on the propeller geometry, and small propellers have complex geometries that are not readily available. Nonetheless, by analyzing the performance data of over 170 propellers (diameters ranging from 2 to 18 inches) from different manufacturers, we show that: (a) the thrust and power coefficient curves can be approximated as second and third-order polynomials in advance ratio, respectively, and (b) the coefficients of these polynomials depend predominantly on the pitch ratio. Leveraging this observation, we develop novel empirical relations that determine the coefficients of the polynomial performance curves as functions of the propeller pitch ratio alone. The efficacy of the proposed performance estimation models is demonstrated by accurately predicting the performance curves of several propellers that were not used to construct the empirical relations. Further, using the developed empirical relations, we propose a method to select a suitable propeller that provides high efficiency for a given set of preliminary UAV design parameters like the required thrust and operating velocity.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-02-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-023-00203-y.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50509243","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

Enhanced composite nonlinear extended state observer based on trajectory linearization control in presence of external and internal disturbance 内外扰动下基于轨迹线性化控制的增强型复合非线性扩展状态观测器

Aerospace Systems Pub Date : 2023-02-22 DOI: 10.1007/s42401-023-00198-6

Javid Hosseinpour, Seyed Hossein Sadati, Yosef Abbasi

{"title":"Enhanced composite nonlinear extended state observer based on trajectory linearization control in presence of external and internal disturbance","authors":"Javid Hosseinpour, Seyed Hossein Sadati, Yosef Abbasi","doi":"10.1007/s42401-023-00198-6","DOIUrl":"10.1007/s42401-023-00198-6","url":null,"abstract":"<div><p>This paper investigates a novel compound control scheme combined with the advantages of trajectory linearization control (TLC) and alternative enhanced composite nonlinear extended state observer (ECNESO) in presence external and internal disturbance. First, an improved generalized tracking differentiator (IGTD) is applied to realize differentiation and filtering for the reference command. Second, ECNESO are constructed to estimate the uncertainties acting on the LTV. In addition, combining the novel observer with TLC strategy, a method is developed to force the controlled output to track the reference signal, rather than just stabilizing it around zero. Moreover, for the first time, this paper gives a rigorous proof of enhanced extended state observer (EESO) for nonlinear systems. The proposed TLC- ECNESO strategy is guaranteed the robustness of closed-loop system in the presence of parametric uncertainties and internal and external disturbances, in addition, the simplicity of the proposed strategy can meet the real-time computational requirement in practical air vehicle control systems. Stability analysis verifies that all signals in the closed-loop system are uniformly ultimately bounded. Finally, numerical simulation studies demonstrate the feasibility and efficacy of the proposed method.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-02-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50504770","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

Derivation and exploration of permeability function for contact of wedge-shaped edge of metal seal with flange 金属密封楔边与法兰接触渗透函数的推导与探索

Aerospace Systems Pub Date : 2023-02-09 DOI: 10.1007/s42401-023-00196-8

Andrei Boikov, Olga Rod

引用次数: 0

Design of load-bearing anisotropic wing box panels ensuring static strength in the post-buckling state 确保后屈曲状态下静态强度的承载各向异性翼板设计

Aerospace Systems Pub Date : 2023-02-06 DOI: 10.1007/s42401-023-00193-x

Oleg Mitrofanov, Maksim Shkurin

{"title":"Design of load-bearing anisotropic wing box panels ensuring static strength in the post-buckling state","authors":"Oleg Mitrofanov, Maksim Shkurin","doi":"10.1007/s42401-023-00193-x","DOIUrl":"10.1007/s42401-023-00193-x","url":null,"abstract":"<div><p>The use of composite materials for the smooth load-bearing wing box panels of low-capacity aircraft can increase their weight efficiency. The present study considers thin smooth load-bearing panels of anisotropic structure, which can be used as the upper load-bearing wing box panels of forward-swept wings. The case of the maximum bending moment acting on the wing is considered, with wing box panels primarily subjected to compression at insignificant torque shear forces. The paper aims to develop a procedure for determining the thickness of thin anisotropic panels while allowing for the post-buckling behaviour under the action of near-expected compressive and shear flows. In accordance with the methodology for designing load-bearing panels for the post-buckling state, an analytical solution to a geometrically nonlinear problem was considered for anisotropic rectangular panels with hinged support; a procedure was proposed for designing panels that relies on the limiting static stresses of the composite cover exhibiting post-buckling behaviour. The obtained analytical expression was analysed to determine normal membrane stresses, and an expression was presented to ascertain the minimum thickness of the panel. A special attention was paid to the problem of determining the potentially critical points of an anisotropic panel exhibiting post-buckling behaviour, in which stresses can reach the maximum absolute values. The proposed procedure can be used to ascertain the thickness of thin load-bearing anisotropic panels under compressive and shear forces.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-02-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-023-00193-x.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50455170","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 5

Fatigue life of engineering structures with regard to aerospace welding joint 航空航天焊接接头工程结构的疲劳寿命

Aerospace Systems Pub Date : 2023-02-02 DOI: 10.1007/s42401-023-00197-7

Elena Vlasova, Aleksandr Sidorenko, Alexey Amosov, Ayubjon Vokhidov

引用次数: 0

The coupled impact-freezing mechanism of supercooled droplet on superhydrophobic surface 超疏水表面过冷液滴的耦合冲击冻结机制

Aerospace Systems Pub Date : 2023-01-30 DOI: 10.1007/s42401-023-00192-y

Haocheng Wu, Weiliang Kong, Peixiang Bian, Hong Liu

{"title":"The coupled impact-freezing mechanism of supercooled droplet on superhydrophobic surface","authors":"Haocheng Wu, Weiliang Kong, Peixiang Bian, Hong Liu","doi":"10.1007/s42401-023-00192-y","DOIUrl":"10.1007/s42401-023-00192-y","url":null,"abstract":"<div><p>The coupled effect of dynamics and nucleation during supercooled droplet’s collision on superhydrophobic surface plays an important role in the anti-icing capability of different superhydrophobic surface, however, without any method to evaluate it. In this work, the impact-freezing behaviors of supercooled droplets on surfaces with different wettability, including two typical hydrophobic surfaces, were investigated experimentally. The morphology, size, velocity, and nucleation rate of freezing on each surface at different temperatures were extracted, based on which emphasis was put on discussing the discrepancy of freezing processes and the formation mechanism of freezing morphologies on different superhydrophobic surfaces. The main findings are: (1) The freezing morphology on superhydrophobic surface was independent of contact angle and supercooling degree, but depended on the surface roughness; (2) the interaction between the fast motion of unfrozen water and the generation of ice nucleus dominates in the formation of freezing morphology, while the ice growth process has less influence. On smooth surface, multiple ice nucleus generating before bounce impeded the fast retraction of droplet, forming irregular-hill freezing shape whose size enlarged with decreasing temperature. On rough surface, because of the later nucleation after retraction process finished, the freezing morphology showed convergent sphere shape with supercooling-independent freezing size; (3) considering more complicated impact dynamics, including breaking and bouncing, on different superhydrophobic surfaces, an impact-freezing model was established and could be used to estimate the average frozen spreading ratio.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-01-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82883264","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

Filter and sensor delay synchronization in incremental flight control laws 增量飞行控制律中的滤波器和传感器延迟同步

Aerospace Systems Pub Date : 2023-01-19 DOI: 10.1007/s42401-022-00186-2

Rasmus Steffensen, Agnes Steinert, Zoe Mbikayi, Stefan Raab, Jorg Angelov, Florian Holzapfel

{"title":"Filter and sensor delay synchronization in incremental flight control laws","authors":"Rasmus Steffensen, Agnes Steinert, Zoe Mbikayi, Stefan Raab, Jorg Angelov, Florian Holzapfel","doi":"10.1007/s42401-022-00186-2","DOIUrl":"10.1007/s42401-022-00186-2","url":null,"abstract":"<div><p>This paper introduces and investigates several methods of filtering and delay synchronization in incremental control law structures. It is shown that proper filter and delay synchronization is of great importance for both the performance and stability of the control laws. It is derived how to synthesize complementary filters in case of sensor dynamics, sensor delays and internal control law filtering such as roll-off filters and notch filters. The complementary filters are compared to common synchronization approaches previously applied in incremental control laws. It is shown that the proposed methods are beneficial for Multiple Input Multiple Output (MIMO) systems in case that different delays and filtering is present in the different measurement signals. In case of strongly coupled input effectiveness, the synchronization on the actuator feedback may become even unstable, where the complementary filter approach recovers the design closed-loop behavior. In addition, it is derived how to initialize the complementary filters for a transient-free engagement in non-steady-state conditions. The results are compared in simulation with a roll rate control law for a fixed wing aircraft.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-01-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-022-00186-2.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50496333","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 2