《航空杂志》包含有关飞机和航天器的研究、设计和开发、建造和运营各个方面的原创论文。因此，征集有关飞机和航天器的研究、设计和开发、建造和运营的各个方面的论文。论文也受到欢迎，这些论文全面地回顾了上述任何主题的最新研究进展。

The Aeronautical Journal publishes original papers on all aspects of the research, design, development, construction, and operation of aircraft and spacecraft. We invite submissions related to the research, design, development, construction, and operation of aircraft and spacecraft. Papers that provide comprehensive reviews of the latest research developments in any of the aforementioned topics are also welcome.

《航空杂志》发表关于飞机和航天器的研究、设计、开发、建造和运营等各个方面的原创论文。我们欢迎提交与飞机和航天器相关的研究、设计、开发、建造和运营的论文。同时，全面回顾上述主题最新研究进展的论文也受到欢迎。

Aeronautical Journal

Abstract A new parameter estimation method based upon neural network is proposed. The method proposed here uses feed forward neural networks to establish a neural model that could be used to predict subsequent time histories given the suitable measured initial conditions. The proposed neural model would not represent a generic flight dynamic model. The neural model in this case develops point to point fitting of the input and the output data. Thus, it could at best be referred to as flight dynamic model in restricted sense. Gauss-Newton method is then used to obtain optimal values of the aerodynamic parameters by minimising a suitable defined error cost function. The method has been validated using longitudinal and lateral-directional flight data of various test aircraft. The results thus obtained were compared with those obtained through wind tunnel test, or those obtained using Maximum likelihood and/or Filter error methods. Unlike, most of the parameter estimation methods, the proposed method does not require a prior description of the model. It also bypasses the requirement of solving equations of motion. This feature of the proposed method may have special significance in handling flight data of an unstable aircraft.

N. K. Peyada

A. K. Ghosh

The Aeronautical Journal

Aircraft parameter estimation using a new filtering technique based upon a neural network and Gauss-Newton method

基于神经网络和高斯-牛顿法的新滤波技术在飞机参数估计中的应用

An onboard three-dimensional (3D) trajectory generation approach based on the reinforcement learning (RL) algorithm and deep neural network (DNN) is proposed for hypersonic vehicles in glide phase. Multiple trajectory samples are generated offline through the convex optimisation method. The deep learning (DL) is employed to pre-train the DNN for initialising the actor network and accelerating the RL process. Based on the offline deep policy deterministic actor-critic algorithm, a flight target-oriented reward function with path constraints is designed. The actor network is optimised by the end-to-end RL and policy gradients of the critic network until the reward function converges to the maximum. The actor network is considered as the onboard trajectory generator to compute optimal control values online based on the real-time motion states. The simulation results show that the single-step online planning time meets the real-time requirements of onboard trajectory generation. The significant improvement in terminal accuracy of the online trajectory and the better generalisation under biased initial states for hypersonic vehicles in glide phase is observed.

C.Y. Bao

X. Zhou

P. Wang

R.Z. He

G.J. Tang

Aeronaut. j.

A deep reinforcement learning-based approach to onboard trajectory generation for hypersonic vehicles

基于深度强化学习的乘波体轨迹生成方法

Abstract To study the performance of the main windshield of a commercial aircraft that has been verified to be airworthy by bird-strike tests against unmanned aerial vehicle (UAV) impact at high-speed, a typical light UAV with various possible flight postures and the main windshield of a commercial aircraft are considered. The transient impact responses at critical moments, energy change and contact force of a multi-layer windshield impacted by a UAV with different postures are investigated using a simulation method based on the models verified by the high-speed impact test between the whole UAV and the full-size nose. This study shows that the flight posture of the UAV has a significant effect on the damage to the windshield. When the abdomen of a typical light UAV maintains a posture parallel to the plane of the windshield, the high-speed impact would cause catastrophic damage to the windshield and no longer be airworthy. Simultaneously, the damage to the aircraft windshield caused by UAV collision is far more serious than that caused by bird strikes under similar collision conditions. The mass-concentrated components of the UAV and their high-hardness characteristics are the main factors of affecting multi-layer glass of windshield damage. The degree of damage to the windshield is positively related to the absorbed energy rather than the impact contact force. In this study, the impact simulation results between the windshield and UAV with different flight postures are verified qualitatively by testing, which provides a rational understanding and technical pre-research support for emerging and increasingly frequent potential safety hazards in air transport practice.

X.H. Lu

Y.C. Zhang

Z.G. Zhang

Effect on damage of aircraft windshield impacted by light UAV with different postures

轻型无人机以不同姿态撞击飞机风挡的损伤影响

Abstract The challenging tracking control issue for a space manipulator subject to parametric uncertainty and unknown disturbance is addressed in this paper. An observer-based fixed-time terminal sliding mode control methodology is put forward. Firstly, a nonlinear disturbance observer is introduced for exactly reconstructing the lumped uncertainty without requiring any prior knowledge of the lumped uncertainty. Meanwhile, the estimation time’s upper bound is not only irrelevant to the initial estimation error but can be directly predicted in advance via a specific parameter in the observer. Invoking the estimated information, a fast fixed-time tracking controller with strong robustness is designed, where a novel sliding mode surface incorporated enables faster convergence. The globally fixed-time stability of the closed-loop tracking system is rigorously demonstrated through Lyapunov stability analysis. Finally, numerical simulations and comparisons verify the validity and superiority of the suggested controller.

Y.X. Yan

H. Cui

P. Han

Disturbance observer-based fixed-time tracking control for space manipulators with parametric uncertainty and unknown disturbance

基于扰动观测器的空间机械臂参数不确定性和未知扰动下的固定时间跟踪控制

Abstract As avionics systems become increasingly complex, traditional fault prediction methods are no longer sufficient to meet modern demands. This paper introduces four advanced fault prediction methods for avionics components, utilising a multi-step prediction strategy combined with a stacking regressor. By selecting various standard regression models as base regressors, these base regressors are first trained on the original data, and their predictions are subsequently used as input features for training a meta-regressor. Additionally, the Tree-structured Parzen Estimator (TPE) algorithm is employed for hyperparameter optimisation. The experimental results demonstrate that the proposed stacking regression methods exhibit superior accuracy in fault prediction compared to traditional single-model approaches.

W.H. Li

G. Li

Y. Liu

J.T. Ma

Z.D. Wu

X. Tang

W.C. Sun

T.Z. Wen

Method of fault prediction for avionics components based on stacking regression

基于堆叠回归的航空电子部件故障预测方法

Abstract This paper proposes a cooperative midcourse guidance law with target changing and topology switching for multiple interceptors intercepting targets in the case of target loss and communication topology switching. Firstly, a three-dimensional guidance model is established and a cooperative trajectory shaping guidance law is given. Secondly, the average position consistency protocol of virtual interception points is designed for communication topology switching, and the convergence of the average position of virtual interception points under communication topology switching is proved by Lyapunov stability theory. Then, in the case of the target changing, the target handover law and the handover phase guidance law are designed to ensure the acceleration smoothing, at last, the whole cooperative midcourse guidance law is given based on the combination of the above guidance laws. Finally, numerical simulation results show the effectiveness and the superiority of the proposed cooperative midcourse guidance law.

R. Zhang

Y. Fang

Z. Chen

H. Guo

W. Fu

Cooperative midcourse guidance law with target changing and communication topology switching

目标变化与通信拓扑切换下的协同中段制导律

Abstract So much has been written about Frederick W. Lanchester over the years, it is hard to imagine finding something new to discuss about his efforts in aerodynamics. Many of the previous Lanchester Memorial Lectures discussed topics such as wing aerodynamics, aircraft concepts and design, unsteady rotor aerodynamics, aerodynamics research and a wide variety of other related aerodynamic topics. However, there has never been a lecture about Lanchester’s book Aerodynamics as a tool for aerodynamics education in the early 20th century. The lecture will discuss his book relative to other aerodynamics books before and after 1907, and uncover how Lanchester’s book had a very distinct, and important, contribution to make for aerodynamic education.

R.M. Cummings

Frederick W. Lanchester and <i>Aerodynamics</i>: why an automotive engineer wrote a book for aerodynamic education

弗雷德里克·W·兰彻斯特与《空气动力学》：为何一位汽车工程师撰写了一本空气动力学教育书籍

Abstract In a competitive market, airlines continually seek solutions that can reduce their operational costs. Flight path optimisation is a commonly pursued approach to this but requires a large amount of data about the flight environment including the weather information, the aircraft performance and the air traffic control (ATC) requirements. Existing programmes require the user to provide this aircraft performance data in advance and are incapable of generating the information on their own. In this study, using a multidisciplinary approach and numerical optimisations, a novel standalone flight path optimiser (SAFPO) solution is proposed and developed to choose the best flight path for a flight between two points in accordance with the cost objectives. SAFPO uses its own performance calculator, predefined ATC routes, and known weather information to find the optimum flight path which minimises fuel consumption and/or flight time. The aerodynamic characteristics of the aircraft are determined using a validated semi-empirical programme called MAPLA, previously developed for light aircraft analysis. Furthermore, the optimisation process consists of a multidisciplinary-feasible (MDF) framework that employs a genetic algorithm (GA) optimiser. The resulting performance characteristics of the aircraft and the optimisation process are compared with the actual information provided within the flight manual of a Beechcraft Baron G58 aircraft. The optimisation results show that SAFPO can be used to make advances in the daily operations of small and local airlines suffering from a lack of aircraft performance data and help them to choose the scenario that best accomplishes their cost objectives.

M. Rostami

J. Bardin

D. Neufeld

J. Chung

Small aircraft flight trajectory optimisation using a multidisciplinary approach

小型飞机飞行轨迹优化的多学科方法

Abbreviation	Aeronaut. j.
Journal Impact	1.36
Quartiles(Global)	ENGINEERING, AEROSPACE(Q2)

ISSN	0001-9240, 2059-6464
h-index	50

Publication Information	Publisher: Cambridge University Press，Publishing cycle: Monthly，Journal Type: journal，Open Access Journals: No
Basic data	Year of publication: 1994，Proportion of original research papers: 98.04%，Self Citation Rate:14.30%， Gold OA Rate: 27.56%
Average review cycle	网友分享经验：较慢,6-12周
Average recruitment ratio	网友分享经验：容易

Aeronautical Journal

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Share Submission Experience

Aircraft parameter estimation using a new filtering technique based upon a neural network and Gauss-Newton method

A deep reinforcement learning-based approach to onboard trajectory generation for hypersonic vehicles

Effect on damage of aircraft windshield impacted by light UAV with different postures

Disturbance observer-based fixed-time tracking control for space manipulators with parametric uncertainty and unknown disturbance

Method of fault prediction for avionics components based on stacking regression

Method of fault prediction for avionics components based on stacking regression

Cooperative midcourse guidance law with target changing and communication topology switching

Disturbance observer-based fixed-time tracking control for space manipulators with parametric uncertainty and unknown disturbance

Frederick W. Lanchester and Aerodynamics: why an automotive engineer wrote a book for aerodynamic education

Small aircraft flight trajectory optimisation using a multidisciplinary approach