《航空航天工程杂志》致力于发表有关飞机和航天器及其支持系统的应用科学和技术的所有分支的高质量研究。 “我们的作者是真正的国际作者，我们尽一切努力确保每篇论文都以最好的方式呈现并覆盖广泛的受众。” 编辑委员会由代表十五个国家的技术社区的知名专家组成。董事会成员与编辑、审稿人和作者密切合作，以达到一致的标准，撰写和发表的论文都很好。”西班牙马德里理工大学 RODRIGO MARTINEZ-VAL 教授 本期刊是出版委员会的成员道德（COPE）。

The Journal of Aerospace Engineering focuses on publishing high-quality research related to the applied sciences and technologies of aircraft, spacecraft, and their support systems. Our authors are truly international, and we strive to present each paper in the best possible way to reach a wide audience. The editorial board consists of renowned experts from technical communities across fifteen countries, who work closely with editors, reviewers, and authors to achieve consistent high standards in the writing and publication of papers. Professor RODRIGO MARTINEZ-VAL from the Polytechnic University of Madrid states, 'We are committed to ensuring that every paper receives the attention and recognition it deserves.' This journal is a member of the Committee on Publication Ethics (COPE).

《航空航天工程杂志》专注于发表与飞机、航天器及其支持系统相关的应用科学和技术的高质量研究。我们的作者来自全球各地，我们努力确保每篇论文以最佳方式呈现，覆盖广泛的受众。编辑委员会由来自十五个国家的知名专家组成，他们与编辑、审稿人和作者密切合作，以确保撰写和发表的论文达到一致的高标准。西班牙马德里理工大学的RODRIGO MARTINEZ-VAL教授表示：‘我们致力于确保每篇论文都得到充分的关注和认可。’本期刊是出版委员会道德（COPE）的成员。

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

The effectiveness of exoatmospheric interceptor is analyzed in this paper based on the reachable set model. Firstly, the connotations of the reachable set model, including its precise definition, mathematic description and analysis algorithms are briefly introduced. Secondly, concerning the problem of interceptor system deployment, the defense zone is introduced as a metric of effectiveness. The factors that influence the configurations of defense zone are explored. Thirdly, concerning the problem of incoming target assignment, an index system composed of earliest intercept moment, interception time window and radar support distance is drawn to capture the effectiveness. The selection of optimal intercept plan is treated as a multi-alternatives sequencing problem and addressed by the multiple attribute decision making method. Simulation examples prove the efficiency of the raised approach. The reachable set-based approach proposed in this paper serves as a ready support to other studies related to interceptor capability.

Chai Hua

Wang Lei

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering

Effectiveness analysis of exoatmospheric interceptor using reachable set model

外大气层拦截器可达集模型的有效性分析

Typical challenges of supersonic flight include wave drag, acoustic signature, and aerodynamic heating due to the formation of shock waves ahead of the vehicle. Efforts in the form of sleek aerodynamic designs, better propulsion systems, and the implementation of passive and active techniques are generally adopted to achieve a weaker shock wave system. Shock reduction can improve flight range, reduce fuel consumption, and provide thermal protection of the forebody region. This paper briefly reviews shock reduction techniques, including passive, active, and hybrid flow control. Airfoil shape optimization, mechanical spike, and forebody cavities are studied as passive flow control approaches. For active flow control, developments in the area of opposing jets and energy deposition are explored. The combination of active and passive flow control and the hybrid flow techniques are discussed in the end. The discussions include the principle of operation, physics of fluid behavior, and overall contribution to flight stability characteristics. The implications in the usage of these technologies, along with potential gaps, are also identified. This comprehensive review can serve as the basis for contemporary solutions to realize sustainable supersonic travel for the aviation industry.

Shagufta Rashid

Fahad Nawaz

Adnan Maqsood

Shuaib Salamat

Rizwan Riaz

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

This article deals with the issue of designing a flight tracking controller for an unmanned aerial vehicle type of quadrotor based on an optimal model-free fuzzy logic control approach. The main design objective is to perform an automatic flight trajectory tracking under multiple model uncertainties related to the knowledge of the nonlinear dynamics of the system. The optimal control is also addressed taking into consideration unknown external disturbances. To achieve this goal, we propose a new optimal model-free fuzzy logic–based decentralized control strategy where the influence of the interconnection term between the subsystems is minimized. A model-free controller is firstly designed to achieve the convergence of the tracking error. For this purpose, an adaptive estimator is proposed to ensure the approximation of the nonlinear dynamic functions of the quadrotor. The fuzzy logic compensator is then introduced to deal with the estimation error. Moreover, the optimization problem to select the optimal design parameters of the proposed controller is solved using the bat algorithm. Finally, a numerical validation based on the Parrot drone platform is conducted to demonstrate the effectiveness of the proposed control method with various flying scenarios.

Hossam E Glida

Latifa Abdou

Abdelghani Chelihi

Chouki Sentouh

Gabriele Perozzi

Optimal model-free fuzzy logic control for autonomous unmanned aerial vehicle

自主无人机的最优无模型模糊逻辑控制

In this paper, the attitude tracking control of spacecraft has been investigated by taking into account the input saturation constraint and an oscillatory dynamic model for the actuators. A dual-mode control scheme is presented, which has a low computational cost. The command signals are calculated by defining power reaching laws and reference filtering method. For this purpose, a new projection operator is used to determine the best possible references based on system and actuator dynamics and saturation constraints. The Lyapunov stability of the closed-loop system as well as the convergence of the filtered references to the desired references were analyzed. The dual-mode-based command signals have been determined based on minimizing the one-step predictive attitude error by combining the two controllers. The efficacy of the algorithm for tracking control has been demonstrated through numerical simulations.

Mohammad Reza Homaeinezhad

Mahdi Nesaeian

Discrete-time low-computation spacecraft attitude tracking control algorithm design considering actuation stiff constraints

考虑执行刚性约束的离散时间低计算量航天器姿态跟踪控制算法设计

Mixing promoting capability of a pair of tabs with truncated projections located asymmetrically on a rectangular stem fixed diametrically opposite at the exit of a circular nozzle has been investigated experimentally for the Mach numbers of 0.6, 0.8, and 1.0. The centerline pressure decay of the sonic jet at under-expanded conditions corresponding to nozzle pressure ratios (NPR) 2, and 3 was also considered in this study. It is found that the mixing promoting small-scale vortices shed by the tabs appreciably promotes the jet mixing at all Mach numbers. The highest mixing promotion is for the correctly expanded sonic jet, leading to a core length reduction of about 87%. In contrast, for Mach 0.8 and 0.6 jets, the core length reduction achieved is about 85% and 77%, respectively. The favourable pressure gradient at the nozzle exit is found to be of no effect on the mixing promotion caused by the tabs. At NPRs 2 and 3, the core length reduction induced by the tabs is only 85% and 88%, comparable to that at correctly expanded sonic state. The shadowgraph images of the under-expanded sonic jet show that the shock waves in the jet core become weaker due to the enhanced mixing caused by the tabs. Also, the tabs weaken the Mach disc formed in the core of a highly under-expanded sonic jet operating at NPR 4.

S B Jabez Richards

S Thanigaiarasu

Parvathy Rajendran

Ethirajan Rathakrishnan

An innovative vortex generator for promoting subsonic and sonic jet mixing

一种促进亚音速和音速射流混合的创新涡流发生器

Aero-engines are required to maintain stable operation under adverse weather conditions, such as heavy rain ingestion. Excessive water ingestion can significantly impact the aerodynamic performance of compressor, potentially leading to performance degradation and even stall. Current investigations reveal that rain ingestion causes losses in both total pressure and total temperature, contributing to the overall deterioration of the performance of compressor. However, these theoretical findings lack robust experimental validation, and the precise relationship between total pressure and temperature losses, alongside the heat and mass transfer mechanisms within the two-phase flow field inside the compressor, remains to be fully established. In this study, a comprehensive experimental and numerical investigation is conducted on a 1.5-stage compressor to assess the effects of water ingestion on compressor performance and internal flow characteristics with varying droplet size distributions and liquid water content (LWC). The results demonstrate that key performance indicators, such as total pressure ratio, efficiency, and the compressor’s stable operating range, are influenced by LWC, droplet size, and the spatial distribution of water ingestion at the inlet. Water ingestion induces non-uniformities in both total pressure and total temperature, with the extent of these distortions governed by factors such as droplet size, concentration, and ingestion patterns across different stages of the compressor. Specifically, increasing water ingestion rates and a concentrated droplet distribution exacerbate total pressure distortions, while simultaneously mitigating total temperature distortions due to the saturation of water vapor. Furthermore, the location and extent of the distorted regions are also influenced by these parameters.

Yonghao Yu

Shuguang Chu

Ziyi Wang

Kim Tiow Ooi

Mingcong Luo

Qun Zheng

Study on the total pressure and total temperature distortion of axial flow compressor based on different rain ingestion forms

基于不同雨水吸入形式的轴流压缩机总压和总温畸变研究

3D airfoil optimization is a widely used and beneficial method for upgrading axial turbines. However, the reviewed literature shows that it does not yield significant efficiency gains in high-pressure reaction stages of steam turbines. We concluded that the followed optimization approaches were not proper enough. In this paper, we used numerical simulations to study the structure of longitudinal vortices in these stages and find main phenomena causing aerodynamic losses. After that, we perused the existing 3D airfoil optimization methods to affect these phenomena significantly. In this way we planned and used an optimization approach to weaken the phenomena which are main sources of aerodynamic losses. We found that besides the well-known secondary vortices, there are two influential vortices called “ Mixing vortex” and “ Incidence vortex”, which are investigated in detail. The mixing vortex is the largest longitudinal vortex in a high-pressure steam turbine stage. To enhance the aerodynamic efficiency and reduce these longitudinal vortices, we used a combination of lean, twist and “ Endwall Section Scaling (ESS)” which is introduced in this paper. To capture the effect of longitudinal vortices more accurately, the optimization is applied to a 1.5-stage HP turbine. In the optimized configuration, the efficiency of the 1.5-stage HP turbine increases by 0.61% while mass flow rate and pressure ratio are kept constant.

Jafar Jafari

Ali M Amini

Mohammad Alizadeh

Steam turbine high-pressure reaction stages; new 3D vortices breakdown and airfoil optimization method

汽轮机高压反动级；新型三维涡流破裂与叶片优化方法

Positioning accuracy affects flight safety. In this study, aiming to address the issue of how ground station deployment affects the accuracy of multilateration, an optimal deployment strategy based on real terrain factors is proposed. This method comprehensively considers practical geographical terrain factors, constructs a geographical terrain grid model, and generates initial candidate sites through this model. Subsequently, the Xdraw algorithm is utilized to assess the coverage of ground stations and conduct preliminary screening of initial sites. Then, the optimal deployment combination is computed by integrating GA. Finally, experiments are conducted to validate site selection in irregularly shaped areas. Random geographical terrain is generated within the site selection area, resulting in a 31.25% reduction in initial candidate points through preliminary screening, obtaining the final deployment approach. Comparative experiments with traditional deployment methods indicate that the RMSE of the deployment combination computed by this method is 4.0159 m smaller than that of the traditional diamond-deployment method with the minimum error. Additionally, its GDOP remains the lowest within 10 km. This method accounts for real terrain conditions and is suitable for irregular station deployment areas. By using the Xdraw algorithm for preliminary filtering, it accelerates the solution process, effectively optimizing deployment results and improving positioning accuracy. This approach holds practical significance for multilateration ground station deployment considering real terrain factors.

Xinmin Tang

Yifu Liao

Junwei Gu

Yang Zhou

Xiangmin Guan

Optimization of wide-area multilateration ground station deployment based on genetic algorithm

基于遗传算法的广域多边定位地面站部署优化

Abbreviation	Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng.
Journal Impact	0.93
Quartiles(Global)	ENGINEERING, MECHANICAL(Q4)

ISSN	0954-4100, 2041-3025
h-index	53

Publication Information	Publisher: SAGE Publications Ltd，Publishing cycle: Bimonthly，Journal Type: journal，Open Access Journals: No
Basic data	Year of publication: 1989，Proportion of original research papers: 99.16%，Self Citation Rate:10.00%， Gold OA Rate: 2.61%
Average review cycle	网友分享经验：平均3.0个月
Average recruitment ratio	网友分享经验：容易

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

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Effectiveness analysis of exoatmospheric interceptor using reachable set model

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Optimal model-free fuzzy logic control for autonomous unmanned aerial vehicle

Discrete-time low-computation spacecraft attitude tracking control algorithm design considering actuation stiff constraints

An innovative vortex generator for promoting subsonic and sonic jet mixing

An innovative vortex generator for promoting subsonic and sonic jet mixing

Discrete-time low-computation spacecraft attitude tracking control algorithm design considering actuation stiff constraints

Study on the total pressure and total temperature distortion of axial flow compressor based on different rain ingestion forms

Steam turbine high-pressure reaction stages; new 3D vortices breakdown and airfoil optimization method

Optimization of wide-area multilateration ground station deployment based on genetic algorithm