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INTEGRATION OF 4-DIMENSIONAL GUIDANCE WITH total energy control-system

JOURNAL OF GUIDANCE control AND DYNAMICS 1991年第3期14卷 564-573页

作者： KAMINER, I OSHAUGHNESSY, P BOEING COMMERCIAL AIRPLANE CO AVION GUIDANCE & CONTROL RESSEATTLEWA 98124

Presented here is a design of the four-dimensional mode for an integrated autopilot/autothrottle control system named total energy control system. This design involves integrating a four-dimensional flight trajectory generator with the total energy control system to create an outer-loop time error control law and integrating spoilers with the total energy control system to increase the energy bleedoff capacity of the system during descent. The resulting system follows a precomputed four-dimensional profile in cruise, except if there is a large time error when the system is engaged. In such a case, the system generates a speed profile to null out the time error by the top of descent. During descent, the system follows a fixed profile by employing both throttles and spoilers. The system was tested on a full nonlinear simulation and all portions of the system were shown to perform as desired.

关键词： total energy control system Boeing 737 Elevator Flight Path Angle energy Distribution Pilot Pitching Moment Elevator Deflection McDonnell Douglas Flight Management Computer

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Analysis and tuning of a 'total energy control system' control law using eigenstructure assignment

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AEROSPACE SCIENCE AND TECHNOLOGY 1999年第3期3卷 127-140页

作者： Faleiro, LF Lambregts, AA DLR Deutsch Zentrum Luft & Raumfahrt eV Inst Robot & Syst Dynam D-82234 Oberpfaffenhofen Germany Fed Aviat Author Adv Controls Seattle WA USA

The total energy control system (TECS) is a complete airplane longitudinal dynamics flight control concept for autopilot operational control modes and Fly-By-Wire command augmentation for civil airplanes. Unlike conventional strategies, it facilitates fully integrated control of the airplane elevator and engines. This system, which is based on simple proportional and integral control of the energy states of the airplane, is much easier to design and understand than most conventional airplane controllers. This paper describes why the high visibility of the two input, two output command augmentation structure of TECS is an improvement over current flight control system architectures. Deriving a control law for TECS is currently a heuristic process. However, there is potential for tuning to be done more systematically, and this is examined by using eigenstructure analysis and assignment. To illustrate the concepts, a linear model of the longitudinal dynamics of the Aerospace Technologies Demonstrator (ATD) airplane is used. A heuristically designed TECS controller for this model is first described. The controlled airplane is then analysed using eigenstructure analysis and the results are utilised to produce an improved TECS controller for the ATD model using eigenstructure assignment. (C) Elsevier, Paris.

关键词： total energy control system eigenstructure assignment integrated flight control control decoupling

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Experimental Validation of an Adaptive total energy control system Strategy for the Longitudinal Dynamics of a Fixed-Wing Aircraft

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JOURNAL OF AEROSPACE ENGINEERING 2016年第1期29卷 04015024-04015024页

作者： Brigido-Gonzalez, J. D. Rodriguez-Cortes, H. Inst Politecn Nacl Ctr Invest & Estudios Avanzados Mexico City 07360 DF Mexico Inst Politecn Nacl Ctr Desarrollo Aeroespacial Mexico City 06010 DF Mexico

This paper presents the experimental validation of an adaptive total energy control strategy to regulating the airspeed and the flight path angle of a fixed-wing aircraft. The control strategy is developed from a nonlinear description of the total energy control system approach. An open source computational fluid dynamics software is used to estimate the aerodynamic characteristics of the experimental aircraft. The stability properties are analyzed considering the linearized closed-loop dynamics around an equilibrium point. (C) 2015 American Society of Civil Engineers.

关键词： total energy control system Fixed-wing aircraft Adaptive control

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total energy Based Flight control system Design for a Lift-Plus-Cruise Urban Air Mobility Concept

Total Energy Based Flight Control System Design for a Lift-P...

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

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

ISBN: (数字)9781624106095

ISBN: (纸本)9781624106095

The novel Urban Air Mobility and On-Demand Mobility aircraft being actively developed today 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. It is likely that the first generation designs will be highly-augmented vehicles operated by pilots who have less training than commercial airline pilots. As a result, there is a strong need for research on (i) stability and control characteristics of these configurations;(ii) development of flight control systems aimed at Simplified Vehicle Operations;and (iii) interactions of pilots with the flight control and other vehicle systems. This paper discusses the design of a total energy control system and total Heading control system for a lift-plus-cruise Urban Air Mobility vehicle concept. Both inner and outer loop control design are discussed for the vehicle's entire flight regime, with a focus on achieving seamless transition between vertical and forward flight modes without adding to pilot workload. Some aspects of the flight control system and its characteristics are demonstrated through some piloted simulations performed using one of the Vehicle systems, Dynamics, and Design Laboratory's flight simulators.

关键词： Flight control Design Urban Air Mobility energy Distribution total energy control system Flight Simulation Pilot Propulsion system control systems Rotary Wing control Surfaces

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More Integrated total energy control Law for Longitudinal Automatic Flight control system Design

More Integrated Total Energy Control Law for Longitudinal Au...

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AIAA Science and Technology Forum and Exposition (AIAA SciTech)

作者： Degaspare, Thiago G. Kienitz, Karl H. Inst Tecnol Aeronaut Sao Jose Dos Campos SP Brazil Inst Tecnol Aeronaut Elect Engn Div Sao Jose Dos Campos SP Brazil

ISBN: (数字)9781624105951

ISBN: (纸本)9781624105951

This article proposes an extension of the total energy control system (TECS), originally developed in the early 1980s. It proposes modifications on the TECS flight control law throttle control channel in terms of its command variable and feedback loops, accounting for integration aspects related to the flight and engine control systems, especially the consideration of engine related variables. This is achieved by adopting a two degree of freedom multivariable control law architecture. The methods used provide a systematic procedure for the TECS design problem and also allow for an extension of the original architecture preserving its core features. The controllers are computed using linear design methods issued from robust control theory. This paper presents how this framework allows for the consideration of control law robustness and performance properties as well as the evaluation of uncertainty regarding the plant modeling, when dealing with highly integrated control systems. The results are illustrated and discussed with the help of a set of simulations which accounts for dedicated aircraft and engine models.

关键词： Automatic Flight control systems energy Distribution Open Loop Transfer Function total energy control system Full State Feedback control system Design Multivariable control system Flight control Law Flight Path Angle Frequency Domain

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Optical Tracklet-to-Tracklet Correlation with control-Distance Metrics

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JOURNAL OF GUIDANCE control AND DYNAMICS 2025年第3期48卷 646-655页

作者： Mao, Xuejian Zhou, Zihan Chen, Pei Beihang Univ Sch Astronaut Beijing 102206 Peoples R China

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A bio-inspired flight control strategy for a tail-sitter unmanned aerial vehicle

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Science China(Information Sciences) 2020年第7期63卷 88-97页

作者： Bin ZHU Jianzhong ZHU Qingwei CHEN Institute of Automation Nanjing University of Science and Technology Department of Energy and Power Engineering Tsinghua University

Wingbeat behavior and intermittent flight path are the two main characteristics of many *** this paper, to improve the efficiency of energy use and cruise range, a bio-inspired intermittent flight strategy with a whole flight envelope has applied to a tail-sitter aircraft. A total energy control system based transition control law has been proposed. The energy efficiency is investigated in terms of energy consumption per unit distance of different cruising modes, and the effectiveness and stability of proposed flight mode transition control law are verified by simulation. The mean mechanical power in flap-gliding flight is reduced compared with steady flight.

关键词： tail-sitter aircraft climb-glide total energy control system energy consumption minimization flight path

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OPTIMUM FLIGHT TRAJECTORY GUIDANCE BASED ON total-energy control OF AIRCRAFT

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JOURNAL OF GUIDANCE control AND DYNAMICS 1994年第2期17卷 291-296页

作者： WU, SF GUO, SF Nanjing Univ. of Aeronautics and Astronautics China

The guidance technique for optimal vertical flight trajectory with a total energy control system (TECS) is discussed. The flight profile is optimized based on the point-mass energy state approximation model of aircraft with direct operating cost as its index function. The guidance law is developed with the total energy control concept used in TECS. To improve the guidance precision, several methods are adopted in the optimization and tracking process, and two preprocessing algorithms, the lead-compensation algorithm and the smooth filtering algorithm, are developed for the ideal optimal trajectory. Satisfactory digital simulation results for a Boeing-707 transport model are finally obtained.

关键词： Commercial Aircraft energy Distribution Flight Trajectory total energy control system Aircraft Flight Dynamics Flight Profile Guidance Laws Trajectory Optimization Elevator Integrated Flight Management system

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total energy-Based control Design and Optimization for Lift-Plus-Cruise Aircraft

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JOURNAL OF GUIDANCE control AND DYNAMICS 2024年第7期47卷 1414-1436页

作者： Comer, Anthony Chakraborty, Imon Auburn Univ Dept Aerosp Engn VSDDL Auburn AL 36849 USA

This paper presents a methodology for optimizing a total energy-based control system architecture for a lift-plus-cruise vertical takeoff and landing urban air mobility concept. The total energy control system algorithm, which was originally developed for fixed-wing applications, is extended to also be applicable to hovering and transitioning flight. control system parameters are optimized using a genetic algorithm optimization scheme, subject to constraints on dynamic stability and control response characteristics. control system optimization and flight simulations are performed using the Modular Aircraft Dynamics and control Algorithm Simulation Platform. Results presented include simulations of the optimized flight control system operation for maneuvering scenarios representative of hover, transition, and forward flight conditions as well as during transitions between vertical and forward flight modes. The presented results demonstrate the effectiveness of the proposed control system architecture and the demonstrated optimization methodology.

关键词： Single Input Single Output Vertical Takeoff and Landing Genetic Algorithm Flight Simulation total energy control system Flight control system Aircraft Dynamics Urban Air Mobility Simplified Vehicle Operations Lift-Plus-Cruise

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DESIGN OF A total energy control AUTOPILOT USING CONSTRAINED PARAMETER OPTIMIZATION

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JOURNAL OF GUIDANCE control AND DYNAMICS 1991年第5期14卷 927-935页

作者： VOTH, C LY, UL UNIV WASHINGTON DEPT AERONAUT & ASTRONAUTSEATTLEWA 98195

The application of a multivariable control design method based on constrained parameter optimization to the design of a multiloop aircraft flight control system is described. Specifically, the design method is applied to the direct synthesis of a multivariable "inner-loop" feedback control system based on total energy control principles. The design procedure offers a structured approach for the determination of a set of controller gains that meet design specifications in closed-loop stability, command tracking performance, disturbance rejection, and limits on control activities. The presented approach may be applied to a broader class of multiloop flight control systems. Direct tradeoffs between many real design goals are rendered systematic by this method following proper formulation of the design objectives and constraints. Performance characteristics of the optimized design have been improved over the current autopilot design on the B737-100 Transport systems Research Vehicle at the landing approach and cruise conditions, particularly in the areas of closed-loop damping and control activity in the presence of turbulence.

关键词： energy Distribution Autopilot Linear Time Invariant Feedback control system Transport systems Research Vehicle Integrated Flight control system Multivariable control Elevator total energy control system Flight Path Angle

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