Aerospace Systems最新文献_第8页

Stability of a dielectric rectangular plate in a longitudinal magnetic field in the presence of a supersonic flow field 在超音速流场存在下的纵向磁场中介电矩形板的稳定性

Aerospace Systems Pub Date : 2023-05-02 DOI: 10.1007/s42401-023-00217-6

Andrei Panteleev, Marine Mikilyan, Iren Vardanyan

{"title":"Stability of a dielectric rectangular plate in a longitudinal magnetic field in the presence of a supersonic flow field","authors":"Andrei Panteleev, Marine Mikilyan, Iren Vardanyan","doi":"10.1007/s42401-023-00217-6","DOIUrl":"10.1007/s42401-023-00217-6","url":null,"abstract":"<div><p>In this paper, we investigate the critical magneto-aeroelastic behavior of dielectric rectangular isotropic plates. The incident flow of a perfectly conducting supersonic gas and a magnetic field cause the perturbed pressure, which we can determine using magneto-aero-elastic stability and dynamic models as well as find the critical flutter speed of the flowing stream. Here, we present the analytical description of the generalized formula of pressure obtained from the “piston theory” of the classical theory of gas dynamics for the case of elastic plates in a magneto-hydro-dynamic flow. We implemented some parametric studies to show the influence of the magnetic field on the flutter boundary. Influence of magnetic field on the dependency “amplitude–frequency” is investigated for several geometrical parameters of examined plate. It is shown that the noted dependency can be as a single-value, as well as a multi-value function. It is shown also that strong magnetic fields have a great influence on the nature of the amplitude–frequency dependence, which is inherent to the case of nonlinear natural oscillations of shells.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88790862","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

Three-axis high-accuracy spacecraft attitude estimation via sequential extended Kalman filtering of single-axis magnetometer measurements 基于单轴磁强计测量序列扩展卡尔曼滤波的三轴高精度航天器姿态估计

Aerospace Systems Pub Date : 2023-04-28 DOI: 10.1007/s42401-023-00221-w

Tamer Mekky Ahmed Habib

{"title":"Three-axis high-accuracy spacecraft attitude estimation via sequential extended Kalman filtering of single-axis magnetometer measurements","authors":"Tamer Mekky Ahmed Habib","doi":"10.1007/s42401-023-00221-w","DOIUrl":"10.1007/s42401-023-00221-w","url":null,"abstract":"<div><p>Magnetometer is a highly advantageous sensor for determining a spacecraft’s attitude. This article provides a solution to the problem of spacecraft attitude estimation using magnetometer measurements only. To ensure full observability of spacecraft attitude states, it is necessary to use at least two types of sensors. Consequently, utilizing a single sensor, such as the magnetometer, poses a significant challenge for any attitude estimation algorithm, including the extended Kalman filter (EKF). Moreover, implementing the EKF algorithm, or any other attitude estimation algorithm, is computationally intensive. To address these issues, an algorithm has been developed that estimates spacecraft attitude angles and attitude rates using a sequential extended Kalman filter (SEKF). This algorithm offers numerous benefits over those found in the literature such as high accuracy, low computational resource requirements, the ability to converge even with large initial attitude and angular velocity estimation errors, and the ability to function even if two of the three measurement channels of the magnetometer are not functioning. With these benefits, the developed SEKF algorithm is capable of operating in all spacecraft operational modes, delivering accurate performance and computation time. In spite of measurements with large noise values, the high accuracy achieved by the SEKF algorithm enables the magnetometer to serve as the sole source of attitude information, even if one or two magnetometer measurement channels are not functioning.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-023-00221-w.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50519454","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

Robust attitude consensus control of multi-spacecraft with stochastic link failure 多航天器随机链路故障鲁棒姿态一致控制

Aerospace Systems Pub Date : 2023-04-28 DOI: 10.1007/s42401-023-00204-x

Yumeng Zhu, Zeyu Kang, Hongxu Zhu, Shufan Wu, Xingqun Zhan, Qiang Shen, Chao Zhong

引用次数: 0

Prediction method for shear stability of composite hat-stringer stiffened panel 复合材料帽筋加筋板抗剪稳定性预测方法

Aerospace Systems Pub Date : 2023-04-28 DOI: 10.1007/s42401-023-00220-x

Shui Han, Yu Yin, Hu YiLe, Xiao Hao, Xu YunYao

{"title":"Prediction method for shear stability of composite hat-stringer stiffened panel","authors":"Shui Han, Yu Yin, Hu YiLe, Xiao Hao, Xu YunYao","doi":"10.1007/s42401-023-00220-x","DOIUrl":"10.1007/s42401-023-00220-x","url":null,"abstract":"<div><p>In this paper, the shear stability of a composite hat-stringer stiffened panel was studied by the means of both shear frame test and theoretical analysis. The test specimen is a typical flat composite stiffened panel composed of skin, five hat-shaped stringers, two Z-shaped transverse frames and reinforcement layers. Firstly, a method that can quantitatively capture the buckling load and buckling morphology was proposed. Then, considering the shear-loading fixture as an elastic system with hinged and bolted connections, a finite element model including both shear-loading fixture and specimen was established. The linear buckling analysis was carried out using the subspace method. The first-order buckling mode was in good agreement with the buckling morphology obtained from the test. Furthermore, the deformed configuration of the first buckling mode was multiplied by the mode scale factor, and then introduced into the model as the initial defect. Based on this model, the nonlinear buckling analysis was performed via arc length method. The analysis results were in good agreement with the test. The relative errors between the predicted buckling loads and the test results were 7.0<span>(%)</span> and <span>(-)</span>3.8<span>(%)</span> from linear and nonlinear buckling analyses, respectively. Nonlinear buckling analysis has higher accuracy and tends to be conservative than linear buckling analysis.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-04-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74337769","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 numerical study on the bending performance of GFRP/Kraft honeycomb panel after natural aging 自然老化后 GFRP/牛皮纸蜂窝板弯曲性能的实验和数值研究

Aerospace Systems Pub Date : 2023-04-26 DOI: 10.1007/s42401-023-00219-4

Z. Kong, N. S. Kalutskiy, H. Shan, Z. Yang

引用次数: 0

Backstepping sliding mode-based anti-skid braking control for a civil aircraft 基于反步滑模的民用飞机防滑制动控制

Aerospace Systems Pub Date : 2023-04-21 DOI: 10.1007/s42401-023-00205-w

Zhenjie Ma, Shiqian Liu, Weizhi Lyu, Kuan Wang

{"title":"Backstepping sliding mode-based anti-skid braking control for a civil aircraft","authors":"Zhenjie Ma, Shiqian Liu, Weizhi Lyu, Kuan Wang","doi":"10.1007/s42401-023-00205-w","DOIUrl":"10.1007/s42401-023-00205-w","url":null,"abstract":"<div><p>Taking off and landing are critical phases and it is easy to happen flight disaster for them due to complex environment and weather. To improve flight safety of the aircraft, an anti-skid control method is proposed. First, the ground dynamics model of the civil aircraft is established. Second, a baseline controller is designed to control the velocity and yaw angle of the civil aircraft by Proportional-Integral (PI) technique. Meanwhile, considering high-speed factor during the braking phase, the braking force of the aircraft is over large, and the wheels are easy to skid. To overcome this, an anti-skid system is built, and the dynamic model of the aircraft anti-skid braking system is established. A backstepping sliding mode control algorithm is proposed to control the braking speed. And the slip ratio of the aircraft wheel is controlled by adjusting braking coefficient <span>({mu }_{Brake})</span> and the optimal slip ratio is achieved. Stability of the closed-loop system is proved by Lyapunov stability theory. Simulation results show that the proposed controller can track the desired trajectory well and the braking efficiency is optimal, which effectively shortens the braking distance of the aircraft, reduces wear of tire, and prevents puncture caused by wheel slip.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-04-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-023-00205-w.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50500554","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: 0

State estimation of radar tracking system using a robust adaptive unscented Kalman filter 基于鲁棒自适应无迹卡尔曼滤波器的雷达跟踪系统状态估计

Aerospace Systems Pub Date : 2023-04-15 DOI: 10.1007/s42401-023-00216-7

Manav Kumar, Sharifuddin Mondal

引用次数: 2

Expediency of using moving-base flight simulators in research on pilot aids evaluation 移动基地飞行模拟器在飞行员辅助评估研究中的便利性

Aerospace Systems Pub Date : 2023-04-08 DOI: 10.1007/s42401-023-00215-8

Tatyana Voronka, Mikhail Tiaglik

{"title":"Expediency of using moving-base flight simulators in research on pilot aids evaluation","authors":"Tatyana Voronka, Mikhail Tiaglik","doi":"10.1007/s42401-023-00215-8","DOIUrl":"10.1007/s42401-023-00215-8","url":null,"abstract":"<div><p>Ground-based simulation has become an integral stage in the design of aviation technology. When solving most problems, flight simulators are increasingly used to simulate the piloting process with the participation of human operators on the ground. For example, flight simulators are used to test out the laws of control systems, study the information display systems, and creating prototypes. When forming a ground-based simulation system, an attempt is made to recreate visual, kinesthetic, and motion information for the pilot (operator). It should be noted, however, that not all tasks require simulating all of the above types of information perceived by the pilot, which significantly reduces the cost of creating a flight simulator. This present work is devoted to substantiating the need to use one of the most expensive systems—a motion cue simulation system—in the tasks of evaluating the effectiveness of next-generation flight information display equipment under various types of atmospheric disturbances. During the experiments, the most dangerous types of disturbances for aircraft in the takeoff and landing modes were simulated, such as a wake vortex from a previously passing aircraft and wind shear caused by a microburst. It is shown that not all types of atmospheric disturbances require simulating motion information.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-04-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-023-00215-8.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50460697","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

Investigation of the local area damage influence on the load-bearing capacity of the reinforced composite panels 局部损坏对加固复合板承载能力影响的研究

Aerospace Systems Pub Date : 2023-04-08 DOI: 10.1007/s42401-023-00214-9

Aleksandr Bolshikh, Dmitrii Borovkov, Bogdan Ustinov

{"title":"Investigation of the local area damage influence on the load-bearing capacity of the reinforced composite panels","authors":"Aleksandr Bolshikh, Dmitrii Borovkov, Bogdan Ustinov","doi":"10.1007/s42401-023-00214-9","DOIUrl":"10.1007/s42401-023-00214-9","url":null,"abstract":"<div><p>In this paper, a method is proposed for calculating the bearing capacity of composite reinforced wing box panels under compression after impact, which has improved calculation accuracy and accelerated analysis time. The paper describes a method for two-phase calculation of the bearing capacity of reinforced panels, taking into account defects, based on the transfer of the stress–strain state from the global model to the local one. To implement the method, a discrete finite element mesh of the study area and a local model of the reinforced skin are created. The method of two-phase analysis of the bearing capacity of reinforced skins with applied impact defects consists of two main components. The first phase is a static calculation of the global shell model of the entire structure under critical loading conditions—the design case that takes place during the flight of the aircraft at small positive angles of attack, in which the aircraft realizes the maximum lift and torque for a given aircraft. In the second phase, a detailed local solid model of the studied area of the reinforced skin is prepared and a dynamic impact analysis is performed. Next, compressive force flows or displacements are transferred from the global model to the closed contour of the local zone and a solution is made in a dynamic or static formulation. This article presents the developed method of global–local modeling, which makes it possible to analyze the bearing capacity of reinforced skin after impact with a more detailed grid without sampling the global model, which speeds up and refines the calculation.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-04-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"87284657","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

Aerodynamic performance improvement of a blended wing-body re-entry vehicle using ANSYS CFX 利用 ANSYS CFX 提高混合翼身再入飞行器的气动性能

Aerospace Systems Pub Date : 2023-04-06 DOI: 10.1007/s42401-023-00213-w

Shakil Hossan, G. Srinivas

引用次数: 0