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AIAA SciTech Forum and Exposition, 2023

作者： Takarics, Béla Patartics, Bálint Luspay, Tamás Vanek, Bálint Poussot-Vassal, Charles Vuillemin, Pierre Wüstenhagen, Matthias Systems and Control Lab Institute for Computer Science and Control Budapest1111 Hungary Onera - The French Aerospace Lab ToulouseF-31055 France Department of System Dynamics and Control DLR - Institute of System Dynamics and Control Wessling82234 Germany

ISBN: (数字)9781624106996

ISBN: (纸本)9781624106996

The main goal of the paper is to develop automatic control design methods for flexible aircraft. The motivation for the research is that such automatic control generation enables the inclusion of the control design algorithms into the multidisciplinary design optimization (MDO) of aircraft design. In such an extended MDO framework, called co-design, the sizing, structural dynamics, aerodynamics and the controllers of the aircraft are optimized in one single step. This way control technologies can be included early-on in the preliminary design stage of aircraft design. Since the control design is model based, first a control oriented aeroservoelastic (ASE) model needs to be developed. The modeling is done via the bottomup modelling approach. The model generation also needs to be automatic due to parameter changes resulting from the MDO process. The research focuses on flexible aircraft, therefore, the control algorithms include baseline, manoeuvre load alleviation, gust load alleviation and flutter suppression controllers. All of these algorithms needs to be developed in such way that they can automatically executed in the MDO process. The overall MDO framework is implemented in the Remote Component Environment (RCE) and the aircraft investigated is the T-Flex demonstrator of the FLIPASED project. The paper presents the main concepts of the modeling and control synthesis, analysis for the above mentioned four controllers and the most important aspects of integrating such automatic control design methods into the RCE environment. © 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： controllers

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Numerical Study of High-Energy Spark Ignition Characteristics in a Scramjet Combustor

SSRN

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SSRN 2024年

作者： Gao, Ziyan Zhang, Meng Zhang, Zhibo Wu, Yun Zheng, Xing Miao, Huifeng National Key Lab of Aerospace Power System and Plasma Technology Xi’an Jiaotong University Xi’an710049 China State Key Laboratory of Multiphase Flow in Power Engineering Xi'an Jiaotong Universiy Xi’an710049 China National Key Lab of Aerospace Power System and Plasma Technology Air Force Engineering University Xi’an710038 China Shaanxi Key Laboratory of Environment and Control for Flight Vehicle School of Aerospace Engineering Xi’an Jiaotong University Shaanxi 710049 China

Reliable ignition is a fundamental prerequisite for the scramjet engines. In order to improve the reliability of ignition, further enhance the application of spark ignition in engineering, and improve the ignition ability in the field of supersonic combustion, an innovative long electrode distance high-energy spark igniter (LHSI) system was proposed by our research team. To reveal the instantaneous ignition characteristics of the LHSI, a simulation model of the LHSI is established and verified by experiments. Based on this, the formation and development of the initial fire core of vaporized kerosene and the ignition characteristics of LHSI in a scramjet combustor were simulated and compared with the conventional high-energy spark igniter (HSI). The analysis revealed that the success of the cavity ignition is greatly influenced by the local equivalent ratio of the initial flow field and the penetration depth of the initial flame core. Meanwhile, the fore recirculation zone of the cavity plays a key role in stabilization and development of the initial fire core. Compared with the HSI, the LHSI can produce initial flame core with higher penetration and greater size, which is the main reason for why LHSI has a broader ignition boundary. © 2024, The Authors. All rights reserved.

关键词： Ignition

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Adaptive Backstepping control for Underactuated 6-DoF USV with Uncertain Dynamics

IEEE Transactions on Intelligent Vehicles

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IEEE Transactions on Intelligent Vehicles 2024年 1-9页

作者： Yu, Kunting Li, Yongming Lv, Maolong Tong, Shaocheng Navigation College Dalian Maritime University Dalian China National Key Laboratory of Unmanned Aerial Vehicle Technology National Key Lab of Aerospace Power System and Plasma Technology the College of Air Traffic Control and Navigation Air Force Engineering University Xi'an China

This paper introduces a target tracking control approach for an underactuated Unmanned Surface Vehicle (USV) with 6 Degrees of Freedom (6-DoF), characterized by unknown dynamics and disturbances. Notably, the system inertia matrix of this 6-DoF USV is positive definite and non-diagonal, implying the presence of intricate coupling relationships within the input vector components. To address the challenges posed by underactuation, we present an adaptive control methodology utilizing a novel transverse function and backstepping procedure. Furthermore, we introduce a dynamic signal to compensate for external dynamic uncertainties and disturbances. Leveraging Lyapunov stability theory, we establish that the target tracking error converges to a small neighborhood near the origin, and all signals within the closed-loop system remain bounded. Lastly, we showcase the effectiveness of the proposed control methodology through simulation results involving a 6-DoF supply vehicle. IEEE

关键词： Target tracking

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Multi-Objective Design Optimization and Sensitivity Analysis of Field Emission Electric Propulsion for Cubesat Platforms

SSRN

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SSRN 2024年

作者： Yeo, Suk Hyun Dinaol, Gadisa Ogawa, Hideaki Bang, Hyo-Choong Department of Aeronautics and Astronautics Graduate School of Engineering Kyushu University 744 Motooka Nishi-ku Fukuoka819-0395 Japan Department of Aerospace Engineering The Korea Advanced Institute of Science and Technology KAIST 291 Daejoen34141 Korea Republic of Space Systems Engineering Japan Aerospace System and Control Lab Korea Republic of

Field-emission electric propulsion is an electrostatic space electric propulsion technology that offers various advantageous features including efficient design, high specific impulse, and versatile thrust capabilities ranging from micro-Newton to milli-Newton levels. These characteristics make FEEP a promising technology for small satellite platforms, enabling precise attitude control, orbit maintenance, and de-orbiting through ionization and acceleration of a liquid metal propellant. The growing demand for small propulsion systems in CubeSat platforms has spurred significant progress in modeling and characterizing FEEP thrusters with the aim to enhance their overall performance. However, little study has been conducted to investigate the effect of geometric configurations on electric fields or expelled ion trajectories for design optimization. In this study, multi-objective design optimization is performed by incorporating electrostatic simulation coupled with an analytical performance model into evolutionary algorithms based on prediction from surrogate modeling, aiming to optimize the thruster emission design to maximize thruster performance. Physical insights into the key design factors influencing the performance of FEEP have been gained by probing into the interaction between ion particles and electric field behavior within the thruster. It has been found that the length of the emitter tip has a significant effect on plume divergence, \textit{i.e.,} a longer emitter tip under the influence of electric field at higher emitter current tends to result in lower initial acceleration of emitted ions and subsequently wider spread or divergence of the ion beam. A shorter emitter tip, on the other hand, generates a sharper E-field gradient, resulting in a more focused and narrower ion beam. Additionally, sensitivity analysis has identified the mass flow rate and potential distributions as the most influential design factors on performance due to the active roles they

关键词： Sensitivity analysis

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Design and Flight Test of a Compact and Rapidly-Deployable Air-Launched Inflatable-Winged Aircraft

Design and Flight Test of a Compact and Rapidly-Deployable A...

引用

AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Ge, Hang Xu, Yixiang Sun, Donglei Chen, Xinmin Chen, Boyang School of Aerospace Faculty of Science and Engineering University of Nottingham Ningbo China Zhejiang Ningbo315100 China Department of Mechanical Materials and Manufacturing Engineering UNNC-NFTZ Blockchain Laboratory University of Nottingham Ningbo China Zhejiang Ningbo315100 China Advanced Intelligent Manufacturing Research Group Control System Lab University of Nottingham Ningbo China Zhejiang Ningbo315100 China Zhejiang Provincial Engineering Research Center of Special Aircraft Ningbo Institute of Materials Technology & Engineering Chinese Academy of Sciences Zhejiang Ningbo315100 China

ISBN: (数字)9781624107238

ISBN: (纸本)9781624107238

In this research, a high-altitude, compact and rapidly deployable, air-launched, inflatablewinged aircraft is designed, developed, and flight-tested to investigate the flight characteristics of inflatable-winged aircraft as well as the in-flight inflation and dynamic deployment properties when launched from various carriers. To start with, two types of inflatable wings employing different materials have been designed, fabricated, and tested, the tests including structural characteristics tests, inflation properties tests, and low-Reynolds-number wind-tunnel tests. A full-scale 30-kilogram prototype unmanned aerial vehicle with inflatable wings was then designed, assembled and tested with some basic low-altitude flights to verify the feasibility of the aerodynamic layout and the trim and stability and control characteristics. Finally, low- and high-altitude in-flight launches will be conducted to study the dynamic deployment properties and high-altitude flight characteristics of this design. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Wind tunnels

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A Study for UAV Autonomous Safe Landing-Site Selection on Rough Terrain 2021

A Study for UAV Autonomous Safe Landing-Site Selection on Ro...

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2nd International Conference on Computing and Data Science, CONF-CDS 2021

作者： Zheng, Wenlong Yi, Jianjun Xiang, Haojie Zhou, Bo Wang, Danwei Zhao, Changchun Department of Mechanical Engineering East China University of Science and Technology Shanghai200237 China Intelligent Unmanned System Control Technology Joint Lab Shanghai201109 China School of Electrical and Electronic Engineering Nanyang Technological University Singapore639798 Singapore Shanghai Aerospace Control Technology Institute Shanghai201109 China

ISBN: (纸本)9781450389570

Autonomous safe landing of UAV is an important function in many scenarios such as force landing and delivery. This paper proposes a method to autonomously select a safe landing site for vertical take-off and landing (VTOL) UAV based on point cloud, which can minimize combined risks posed during touch down at the chosen landing site. The most suitable landing site of a landing zone is selected according to the terrain complexity. In this paper, (1) fine-grained grid elevation map converted from the terrain point cloud is used to calculate the potential risk such as slope, roughness and maximum height difference. (2) A comprehensive risk model is designed to consider all above risks to recognize obstacles and risk areas, and combine the flight distance factors to obtain the final cost map. (3) We process cost map as image by OpenCV to accelerate the processing and reduce reaction time. Terrain point clouds of simulation scene and real world are used for experiments and experimental results show that the selected landing sites can meet the safety requirements, which demonstrate the effectiveness and feasibility of our proposed method. © 2021 ACM.

关键词： Unmanned aerial vehicles (UAV)

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An Object Reconstruction Method Based on Point Cloud with Range Camera 2021

An Object Reconstruction Method Based on Point Cloud with Ra...

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2nd International Conference on Computing and Data Science, CONF-CDS 2021

作者： Yan, Sunchao Yi, Jianjun Ding, Hongkai Wang, Danwei Zhao, Changchun Department of Mechanical Engineering East China University of Science and Technology Shanghai200237 China Intelligent Unmanned System Control Technology Joint Lab Shanghai201109 China School of Electrical and Electronic Engineering Nanyang Technological University Singapore639798 Singapore Shanghai Aerospace Control Technology Institute Shanghai201109 China

ISBN: (纸本)9781450389570

We present an object reconstruction approach based on point cloud. To accurately estimate sensor pose, a combination of frame-to-frame registration and frame-to-model registration is used in our approach with integration to produce the model of reconstructed object. The global optimization used in the approach distributes residual registration errors through the sensor trajectory. Our results demonstrate that the approach is fast and robust to reconstruct objects with a consumer-grade range camera. © 2021 ACM.

关键词： Global optimization

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Dynamic Characteristics of Ion Concentration Distribution for Pulse Combustion with Different Injection Schemes

SSRN

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SSRN 2024年

作者： Du, Minglong Liu, Jinxin Ma, Zhuang Song, Jun Li, Jizhen School of Mechanical Engineering Xi’an Jiaotong University Xi’an710049 China National Key Lab of Aerospace Power System and Plasma Technology Xi’an Jiaotong University Xi’an710049 China Xi’an Modern Control Technology Research Institute Xi’an710065 China Xi’an Modern Chemistry Research Institute Xi’an710065 China

The performance of the aerospace vehicles directly depends on the operation of their large combustion propulsion device. In the development of large combustion propulsion device, combustion instability has long been an inevitable and thorny problem. In this paper, the dynamic characteristics of combustion instability under different injection schemes in a Helmholtz pulse combustor were experimentally investigated. The ion concentration signals in different location of the combustor were acquired to characterize the dynamic process of unsteady combustion with different injection parameters. Results show that the injection schemes with large incident angle and nozzle-hole spacing are not conducive to combustion stability. Large incident angle and nozzle-hole spacing will prevent the fuel jets convergence, thus dividing the central flame front into two parts: one is located near the nozzle outlet with fuel rich combustion and the other is close to the combustor wall with fuel lean combustion. The fuel rich state is easier to stimulate combustion instability than the fuel lean state. Compared to the original converging jet, the newly established fuel rich combustion zone increase the occurrence of combustion instability. On the other hand, the large incident angle and nozzle-hole spacing would cause the combustion heat release to exceed the pressure oscillation, leading to combustion instability. © 2024, The Authors. All rights reserved.

关键词： Combustion

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FPGA implementation of hog-based space target distance measurement 2

FPGA implementation of hog-based space target distance measu...

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2nd IEEE Asia-Pacific Conference on Image Processing, Electronics and Computers, IPEC 2021

作者： Ma, Yue Yi, Jianjun Xu, Gengshu Chen, Yuanhao Wang, Danwei Zhao, Changchun East China University of Science and Technology School of Mechanical and Power Engineering Shanghai200237 China Nanyang Technological University School of Electrical and Electronic Engineering Singapore639798 Singapore Shanghai Aerospace Control Technology Institute Shanghai201109 China Intelligent Unmanned System Control Technology Joint Lab Shanghai201109 China

ISBN: (纸本)9781728190181

This paper focuses on space cooperative target identification and ranging using monocular CMV4000 CMOS sensor and Xilinx Zynq-7000 Soc based platform without the operating system that adopts Histograms of Oriented Gradients (HOG) descriptor and Support Vector Machine (SVM) for classification. With Vivado High-Level Synthesis to accelerate IP creation by enabling C specifications to be directly targeted into devices, this implementation allows for two high-resolution images (2048 times2048 pixels) processing per second. The hardware and software co-design of Xilinx Zynq7000 promises the accuracy of space target classification and distance measurement and thus meets the requirement of real-time space application. © 2021 IEEE.

关键词： Field programmable gate arrays (FPGA)

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A 4-Channel Ultrafast Wavelength-Swept REC-DFB Laser Array for Fiber Bragg Grating Interrogation

A 4-Channel Ultrafast Wavelength-Swept REC-DFB Laser Array f...

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2023 Asia Communications and Photonics Conference/2023 International Photonics and Optoelectronics Meetings, ACP/POEM 2023

作者： Meng, Lingxin Dai, Pan Ban, Qilu Xu, Kaichuan Wang, Jiacheng Li, Zhen Wang, Feng Zeng, Jie Li, Shaobo Ma, Xiang Chen, Xiangfei Res. Center of Precision Photonics Integration and System Application of the Ministry of Education College of Engineering and Applied Sciences Nanjing University Key Lab. of Intelligent Optical Sensing and Manipulation of the Ministry of Education Engineering National Laboratory of Solid State Microstructures Nanjing210023 China Nanjing University of Aeronautics and Astronautics State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing210016 China The 54th Research Institute of China Electronics Technology Group Corporation Optical Communication Research and Development Center Shijiazhuang050081 China

ISBN: (纸本)9798350312614

We present a four-channel ultrafast wavelength-swept distributed feedback (DFB) semiconductor laser array based on the reconstruction-equivalent-chirp (REC) technique using instantaneous injection current modulation. With the aid of our designed laser driving circuit system consists of the microcontroller unit (MCU), field-programmable gate array (FPGA) and negative metal-oxide-semiconductor field effect transistors (n-MOSFETs), the precise pulse driving current for the 4-channel wavelength-swept REC-DFB laser array can be generated and a fast tuning of 16.424 nm within 10 μs is achieved. To further investigate the tuning performance of the proposed wavelength-swept laser source, we then applied it to the fiber Bragg grating (FBG) interrogation system and four FBG temperature sensor arrays were successfully demodulated. The development of high-efficient optical sensing systems heavily relies on the significance of the ultrafast wavelength-swept laser source, which has the potential to greatly enhance FBG interrogator performance in the future. © 2023 IEEE.

关键词： DFB laser array fast wavelength-swept fiber Bragg grating interrogation REC technique

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