检索结果-内蒙古大学图书馆

36th Chinese control and Decision Conference (CCDC)

作者： Wu, Lijie Dong, Ting Sun, Qi Zhang, Yang Aerosp Univ Coll Civil Aviat Shenyang Shenyang Peoples R China Qingyun Digital Hefei Technol Co Ltd Hefei 230088 Peoples R China Cleveland State Univ Dept Elect Engn & Comp Sci Cleveland OH 44115 USA Shanghai Jiao Tong Univ Antai Coll Econ & Management Shanghai Peoples R China

ISBN: (纸本)9798350387780;9798350387797

This study introduces a novel Composite Vertical Takeoff and Landing Fixed-Wing Unmanned Aerial Vehicle (VTOL-FW UAV) tailored for inland waterway missions. Combining multirotor hovering capabilities with fixed-wing cruising efficiency, the UAV addresses challenges specific to these environments. Aerodynamic analysis guides the development of a bespoke propulsion and control system, validated through simulations and waypoint tracking. A dual-mode control strategy facilitates precise trajectory planning, integrating vertical takeoff in multirotor mode and horizontal cruising in fixed-wing mode, using a dual-loop PID control structure. Additionally, Federated Learning theory optimizes operational efficiency and decision-making intelligence while maintaining data privacy.

关键词： dual-mode control strategy inland waterway surveillance federated learning flight control algorithms data privacy in UAV operations

来源：评论

学校读者我要写书评

暂无评论

Piloted Simulator Evaluation Results of New Fault-Tolerant flight control Algorithm

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 2009年第6期32卷 1747-1765页

作者： Lombaerts, T. J. J. Smaili, M. H. Stroosma, O. Chu, Q. P. Mulder, J. A. Joosten, D. A. Delft Univ Technol Fac Aerosp Engn Control & Simulat Div NL-2600 GB Delft Netherlands Natl Aerosp Lab Training Human Factors & Cockpit Operat Dept NL-1006 BM Amsterdam Netherlands Delft Univ Technol Delft Ctr Syst & Control NL-2600 GB Delft Netherlands

A high-fidelity aircraft simulation model, reconstructed using the digital flight data recorder of the 1992 Amsterdam Bijlmermeer aircraft accident (flight 1862), has been used to evaluate a new fault-tolerant flight control algorithm in an online piloted evaluation. This paper focuses on the piloted simulator evaluation results. Reconfiguring control is implemented by making use of adaptive nonlinear dynamic inversion for manual fly-by-wire control. After discussing the modular adaptive controller setup, the experiment is described for a piloted simulator evaluation of this innovative reconfigurable control algorithm applied to a damaged civil transport aircraft. The evaluation scenario, measurements, and experimental design, as well as the real-time implementation are described. Finally, reconfiguration test results are shown for damaged aircraft models including component as well as structural failures. The evaluation shows that the fault-tolerant flight control algorithm is able to restore conventional control strategies after the aircraft configuration has changed dramatically due to these severe failures. The algorithm supports the pilot after a failure by lowering workload and allowing a safe return to the airport. For most failures, the handling qualities are shown to degrade less with a failure than the baseline classical control system does.

关键词： flight control algorithms Test Pilots Handling Qualities Transport Aircraft control System Design Nonlinear Dynamic Inversion Digital flight Data Recorder Aircraft Configurations Aircraft Accidents control Algorithm

来源：评论

学校读者我要写书评

暂无评论

Self-Organizing Radial Basis Function Networks for Adaptive flight control

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 2011年第3期34卷 783-794页

作者： Shankar, Praveen Yedavalli, Rama K. Burken, John J. Arizona State Univ Sch Engn Matter Transport & Energy Tempe AZ 85287 USA Ohio State Univ Dept Mech & Aerosp Engn Columbus OH 43210 USA NASA Dryden Flight Res Ctr Edwards AFB CA USA

The performance of nonlinear flight-control algorithms, such as feedback linearization and dynamic inversion, is heavily dependent on the fidelity of the dynamic model being inverted. Incomplete or incorrect knowledge of the aircraft dynamics results in reduced performance and may lead to instability. A self-organizing parametrization structure is developed to augment the baseline dynamic inversion controller for a high-performance military aircraft. This algorithm is proven to be stable and can guarantee arbitrary tracking error performance. The training algorithm to grow the network and adapt the parameters is derived from Lyapunov theory. In addition to growing the network of basis functions, a pruning strategy is incorporated to keep the size of the network as small as possible. The controller is simulated for different situations, including control surface failures, modeling errors, and external disturbances. A performance measure of maximum tracking error is specified for the controllers a priori. Excellent tracking error minimization to a prespecified level using the adaptive component is achieved. The performance of the self-organizing radial-basis-function network-based controller is also compared with a fixed radial-basis-function network-based adaptive controller. While the fixed radial-basis-function network-based controller, which is tuned to compensate for control surface failures, fails to achieve the same performance under modeling uncertainty and disturbances, the self-organizing radial-basis-function network is able to achieve good tracking convergence under all specified error conditions.

关键词： Radial Basis Function Network Aircraft flight control High Performance Military Aircraft Feedback Linearization Aircraft Dynamics flight control algorithms Longitudinal control control Surfaces Stability Derivatives Stabilator

来源：评论

学校读者我要写书评

暂无评论

Gain Design for an INDI-based flight control Algorithm for a Conceptual Lift-to-Cruise Vehicle

Gain Design for an INDI-based Flight Control Algorithm for a...

引用

AIAA SciTech Forum

作者： Surmann, Denis Myschik, Stephan UnivBundeswehr Munich Inst Aeronaut Engn Dept Flight Mech & Flight Controls D-85577 Munich Neubiberg Germany UnivBundeswehr Munich Inst Aeronaut Engn Chair Flight Mech & Flight Controls D-85577 Munich Neubiberg Germany

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

This paper presents the gain design process for a nonlinear control algorithm used in a conceptual electrical vertical-take-off-and-landing (eVTOL) vehicle with a fixed wing configuration. The control strategy is based on the incremental nonlinear dynamic inversion (INDI) approach, which ensures effective control throughout all flight phases. This research endeavors to develop the controller further into a primary flight controller (PFC) by considering real-world scenarios involving measurement errors and availability. To address these challenges, the estimation of measurements and computation of necessary controller states are performed using various filters, which are incorporated into the controller design. Moreover, the gain design considers the presence of these filters. By optimizing the gain configuration within the error controller (EC), a robust and performance controller design is achieved, allowing for comprehensive investigations in both the time and frequency domains without decoupling the aircraft dynamics. The results of the gain design process are then validated through nonlinear simulations, providing empirical evidence of the effectiveness of the gain and filter concepts.

关键词： flight Mechanics eVTOL Incremental Nonlinear Dynamic Inversion flight control algorithms Vertical Take off and Landing Wing Configurations Frequency Domain Aircraft Dynamics control Allocation Simulink

来源：评论

学校读者我要写书评

暂无评论

Synthesis of optimal control and flight testing of an autonomous circular parachute

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 2004年第1期27卷 29-40页

作者： Yakimenko, OA Dobrokhodov, VN Kaminer, II Dellicker, SH USN Postgrad Sch Dept Aeronaut & Astronaut Monterey CA 93943 USA US Army Yuma Proving Ground Yuma AZ 85365 USA

Development of guidance and control algorithms for autonomous solid circular parachutes is addressed. This effort is a part of the Affordable Guided Airdrop System that integrates a low-cost guidance and control system into fielded cargo air delivery systems. First, the underlying Affordable Guided Airdrop System concept, architecture, and components are described. Then a synthesis of a classical optimal control based on Pontrjagin's maximum principle is suggested. Then the development of a practical control algorithm is detailed. Simulation and flight-test results of the final Affordable Guided Airdrop System demonstration are also presented.

关键词： Time Optimal control flight Testing Affordable Guided Airdrop System control Algorithm control Systems Pneumatic Muscle Actuators Yaw Hysteresis GNC Systems flight control algorithms

来源：评论

学校读者我要写书评

暂无评论

Guidance and control of a Projectile with Reduced Sensor and Actuator Requirements

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 2011年第6期34卷 1757-1766页

作者： Fresconi, Frank USA Res Lab Precis & Guided Flight Dynam Team Weap & Mat Res Directorate Aberdeen Proving Ground MD 21015 USA

Successfully guiding a projectile launched from a gun is an extremely challenging task. Striking a balance between performance and affordability requires innovative solutions. This paper introduces a unique guidance and control strategy that enables precision and trajectory shaping with reduced Sensor and actuator needs. The derivation of this guidance and control algorithm is based on flight dynamics. flight experiments were conducted to verify that the algorithm guided the projectile to the target and to demonstrate its application to different airframes. Features of the algorithm (such as expected precision, maneuver conservation, and trajectory shaping) were investigated through modeling and simulation. Position bias errors drove the precision;errors due to the guidance and control algorithm were on the order of 0.1 m. An analysis was conducted on the lateral acceleration available from the airframe, lateral acceleration required for this algorithm, and lateral acceleration required for classic proportional navigation. For control-authority-limited munitions proportional navigation was unable to intercept the target point, whereas the current guidance algorithm successfully hit the target. Trajectory shaping with this algorithm is demonstrated through simulation.

关键词： Spin Stabilized Projectiles Actuators Sensors Airframes Algorithm Performance Proportional Navigation flight Dynamics flight control algorithms Angle of Attack GPS

来源：评论

学校读者我要写书评

暂无评论

Vertical Takeoff and Landing of Flexible Wing Kite Power Systems

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 2018年第11期41卷 2386-2400页

作者： Rapp, Sebastian Schmehl, Roland Delft Univ Technol Fac Aerosp Engn Kluyverweg 1 NL-2629 HS Delft Netherlands

In this work, a novel vertical takeoff and landing methodology for flexible wing kite power systems is presented. Starting from a basic mast-based launching and landing concept, the operational envelope will be enlarged using the external assistance of a multicopter. The multicopter is used to drag the kite along a specified launching path until the operational altitude is reached, where the kite is detached and steered to its characteristic parking position while the multicopter lands. The landing of the kite will be conducted without multicopter assistance, and solely the winch will be used to pull the kite toward the ground station. For all maneuvers, flight control algorithms are presented, and the feasibility of the proposed methodology is analyzed using a developed simulation environment incorporating models for the kite, multicopter, ground station, and the tethers that connect the individual subsystems.

关键词： Flexible Wings Energy Density VTOL Multicopter Ground Station flight control algorithms Aerodynamic Properties Newton's Second Law Angle of Attack Wind Shear

来源：评论

学校读者我要写书评

暂无评论

Increasing Operator Situational Awareness During Transition Procedures for Fixed-Wing VTOL UAV Operations

Increasing Operator Situational Awareness During Transition ...

引用

AIAA Science and Technology Forum and Exposition (AIAA SciTech Forum)

作者： Dollinger, Daniel Marvakov, Valentin A. Holzapfel, Florian Tech Univ Munich Inst Flight Syst Dynam D-85748 Garching Bavaria Germany

ISBN: (数字)9781624106095

ISBN: (纸本)9781624106095

Situational awareness towards system automation's behavior in highly automated aircraft is a central requirement as a breakdown in the operator's situational awareness can lead to critical situations and hazardous flight states. In the case of any system failures, the arising decision-making process with faults can be more complex and time critical, hence requires more attention and adequate information representation. This paper implements an operator interaction concept, concerning the Human-Machine-Interface (HMI) to increase situational awareness during transition and re-transition procedures of an unmanned experimental fixed-wing VTOL aircraft. From a human operator point of view, requirements are placed towards the system automation's state observability and proper feedback mechanisms for the state information are selected, comprising intuitive indications. The HMI and operator interaction concept are verified in a closed-loop simulation environment, so called Model-in-the-Loop (MIL), showing that the HMI functions are correctly implemented. For validation purposes, a real-time Hardware-in-the-Loop (HIL) environment is setup. The validation demonstrates that the proposed HMI and operator interaction concept can increase situational awareness during transition procedures for the experimental unmanned fixed-wing VTOL aircraft.

关键词： VTOL Aircraft Closed Loop Propulsion System flight control algorithms Pilot Vertical Take off and Landing flight control System flight Phases Aerodynamic Lift Aircraft Operations

来源：评论

学校读者我要写书评

暂无评论

Model-Based control Reconfiguration of a Multirotor UAV using Online System Identification by Sparse Regression (SINDYc)

Model-Based Control Reconfiguration of a Multirotor UAV usin...

引用

AIAA Aviation Forum

作者： Kelm, Benjamin Myschik, Stephan Niggemann, Oliver Helmut Schmidt Univ Inst Automat Technol Flight Mech & Flight Control Hamburg Germany Univ Bundeswehr Munchen Chair Flight Mech & Flight Control Neubiberg Germany

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

Multirotor platforms are increasingly deployed for safety-critical tasks. To increase their safety and availability an automated fault handling is required. For severe faults, a mere fault accommodation with robust or adaptive control architectures is insufficient, requiring a reconfiguration of the controller structure. To make use of the explicit and analytical redundancies of the system in the reconfiguration process, an up-to-date dynamic model of the faulty system is required. In this paper we apply a sparse regression algorithm (SINDYc) to identify the system dynamics of a Redundant Multirotor Testbed (RMT), an octocopter in X8 configuration, to facilitate rapid online control reconfiguration after the sudden loss of one or multiple actuators. The control reconfiguration approach is implemented within a nonlinear simulation in MATLAB/Simulink.

关键词： Multicopter Closed Loop System Identification Unmanned Aerial Vehicle Actuators Simulink Dynamic Modelling Quadcopter flight control Computer Feedback Linearization flight control algorithms

来源：评论

学校读者我要写书评

暂无评论

A Reconfigurable flight Simulation Framework Aimed at Novel flight Vehicle Concepts

A Reconfigurable Flight Simulation Framework Aimed at Novel ...

引用

AIAA Aviation Forum

作者： Chakraborty, Imon Leonard, Cameron Comer, Anthony Mishra, Aashutosh Dewey, Jacob Auburn Univ Dept Aerosp Engn Vehicle Syst Dynam & Design Lab Auburn AL 36849 USA

ISBN: (数字)9781624105982

ISBN: (纸本)9781624105982

A large number of novel flight vehicle concepts aimed at the Urban Air Mobility and On-Demand Mobility concepts of operations are currently under development. Most have configurations that differ significantly from conventional fixed- and rotary-wing aircraft, as well as multi-rotor/distributed propulsion systems that are electric or hybrid-electric in nature. The first generation designs will likely be highly-augmented vehicles operated by pilots with less training than commercial airline pilots. There is, therefore, a strong need for flight simulation aimed at thoroughly analyzing (i) the stability and control characteristics of these configurations;(ii) the development of suitable flight control algorithms aimed at Simplified Vehicle Operations;and (iii) the interactions of pilots with the flight control and other vehicle systems. The Reconfigurable flight Simulator (RFS), a simulation framework for the above applications has been developed at the Vehicle Systems, Dynamics, and Design Laboratory at Auburn University's Department of Aerospace Engineering. Given the multitude of possibilities for vehicle configuration, flight control architecture, inceptor layouts and function, and cockpit display designs, it has significant hardware and software reconfigurability. This paper gives an overview of the design of the simulator, illustrates some of its current capabilities, demonstrates its potential use for human-in-the-loop flight simulation studies, and concludes by highlighting avenues for further development and future work.

关键词： flight Simulation flight Vehicle Throttle Lever flight control System Urban Air Mobility Human In The Loop Rotary Wing Aircraft Propulsion System flight control algorithms Aerospace Engineering

来源：评论

学校读者我要写书评

暂无评论

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案：

请选择收藏分类：

通借通还

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：