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International Test Conference in Asia (ITC-Asia)

作者： Ince, Mehmet Yilmaz, Ender Jeong, Jae Woong Winemberg, Leroy Ozev, Sule Arizona State Univ Tempe AZ 85281 USA NXP Semicond Austin TX USA

ISBN: (纸本)9781538630518

Embedded power regulators, such as low dropout regulators (LDOs), are generally tested for DC behavior and are rarely characterized dynamically. However, LDO loop dynamics play an important role in the overall behavior of the system. Dynamic characterization of LDOs based directly on LDO specifications requires measurement of output transient response with a step input at various points in the circuit. Such characterization is both difficult and costly. Alternatively, LDOs can be characterized by measuring loop dynamics in the form of a transfer function. Since the system is highly non-linear, transfer function can be characterized around a given operating point in terms of poles and zeros. The stability of the system can be inferred from the loop transfer function. This indirect characterization is more feasible but may result in test escapes. In this paper, we investigate the dynamic LDO characterization by closed loop transfer function and evaluate the test coverage with respect to modeled faults in the circuit. We show that faults that are not detectable with DC tests only become detectable with dynamic testing. We also show that the majority of undetectable faults are redundant with regards to the overall operation in terms of step response.

关键词： Evaluation loop transfer function Dynamic Testing dynamic testing loop transfer functions transfer functionS test coverage step input faults Circuit faults

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Small-Signal transfer function Model of Multi-Cycle Controller for High-Frequency SMPSs

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IEEJ JOURNAL OF INDUSTRY APPLICATIONS 2025年第2期14卷 301-311页

作者： Funaki, Hideaki Shoyama, Masahito Yoshida, Takashi Yonezawa, Yu Miyazawa, Akihiko Kyushu Univ Dept Informat Sci & Elect Engn 744 Motooka Fukuoka Fukuoka 8190395 Japan Nagoya Univ Inst Mat & Syst Sustainabil Chikusa Ku Nagoya Aichi 4648601 Japan Model Core Labs Ltd 2-6-20 HigashifuchinobeChuou Ku Sagamihara Kanagawa 2520203 Japan

Increasing the switching frequency of SMPSs (Switched-Mode Power Supplies) can reduce their size and weight;However, developing high-frequency SMPSs with digital controllers is challenging. In conventional digital controllers, control outputs are updated every switching cycle, and therefore, if the switching period is shorter than the calculation time of the controller, the control cannot be achieved. Recently, multi-cycle control has been proposed to address this issue, where control outputs are periodically updated every multiple switching cycles. Despite its potential, the dynamic characteristics of multi-cycle controllers have not been thoroughly investigated. This study employs a multicycle voltage-mode PID controller in a trailing-edge modulated buck converter and investigates its small-signal transfer functions. The derived transfer functions are compared with the transfer characteristics obtained from circuit simulations and real circuit experiments in the form of Bode diagrams and time-domain waveforms, which validate the proposed model. The feedback gain is designed using the proposed model, and the results of the real circuit experiments indicate that this feedback gain achieves the design goal. The obtained results confirm that the proposed model is effective for controller design.

关键词： DC-DC converter digital controller multi-cycle control modeling loop transfer function

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MODERN CONTROL-THEORY FOR DESIGN OF AUTOPILOTS FOR BANK-TO-TURN MISSILES

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1987年第4期10卷 378-386页

作者： WILLIAMS, DE FRIEDLAND, B MADIWALE, AN MIT LINCOLN LABLEXINGTONMA 02173

The state-space techniques of modern control theory are used to develop a methodology for the design of autopilots for bank-to-turn missiles. The methodology accommodates the gyroscopic and coriolis cross-coupling between the pitch and the yaw axes that result from the high roll rates that may be present. The design assumes that the roll rate is constant but not zero, and it results in an autopilot structure in which there are cross-couplings between the pitch and yaw channels that are dependent on the roll rate. The autopilot gains are also scheduled as functions of the dynamic pressure. A reduced-order extended Kalman filter with fixed gains is used to estimate the actuator states and the commanded acceleration. The performance of an autopilot designed by this methodology was evaluated in a six-degree-of-freedom simulation using the dynamics of a typical high-performance tactical missile. Excellent performance in terms of low miss distance and small sideslip is obtained.

关键词： Aerodynamic Characteristics loop transfer function Missiles Roll Control Autopilot Dynamic Pressure Angle of Sideslip Extended Kalman Filter Actuators Six Degree of Freedom

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Stability and flying qualities robustness of a dynamic inversion aircraft control law

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1996年第6期19卷 1270-1277页

作者： Brinker, JS Wise, KA McDonnell Douglas Aerospace St. Louis Missouri 63166

Dynamic inversion, or feedback linearization theory, represents a commonly used nonlinear control method for designing aircraft control laws. This method has the ability to control a highly nonlinear plant but suffers from the lack of guaranteed robustness. The stability and flying qualities robustness of a dynamic inversion based control law, designed for a prototype aircraft, to uncertain aerodynamic parameters is analyzed. The results indicate that the pitch plane stability and dying qualities are robust to parameter uncertainties, but the lateral directional dying qualities are sensitive to uncertain stability derivatives.

关键词： Aircraft Control Flying Qualities Feedback Linearization Aerodynamic Stability Nonlinear Control Angle of Attack Control Surfaces loop transfer function Aircraft Flight Control Sideslip Angle

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ROBUST CONTROLLER SYNTHESIS FOR A LARGE FLEXIBLE SPACE ANTENNA

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1987年第2期10卷 201-208页

作者： SUNDARARAJAN, N JOSHI, SM ARMSTRONG, ES OLD DOMINION UNIV RES FDNNORFOLKVA 23508 NASA LANGLEY RES CTRDIV GUIDANCE & CONTROLHAMPTONVA 23665

The linear-quadratic Gaussian/loop-transfer-recovery method is used to synthesize a fine-pointing control system for a large space antenna. A finite-element model for the 122-m hoop/column antenna is employed, and a compensator, utilizing attitudes sensors and torque actuators, is designed which achieves pointing performance while maintaining stability robustness to unmodeled dynamics. Inclusion of the rigid-body modes plus the first three elastic modes is found to be necessary to achieve a 0.1-rad/s bandwidth. Results are obtained by employing a modification of the standard robustness recovery procedure, which reduces the conservative nature of the design methodology. Performance degradation is encountered due to the presence of unavoidable invariant zeros within the design bandwidth. (Author)

关键词： Space Antenna Algebraic Riccati Equation loop transfer function Sensors Antennas Finite Element Analysis Actuator Torque Control Systems Kalman Filter Gain Frequency Domain

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Improved Modal Damping Characterization for Small-Scale Heliogyro Blades

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JOURNAL OF SPACECRAFT AND ROCKETS 2020年第4期57卷 642-655页

作者： Cook, Sarah M. Lawrence, Dale A. Warren, Jerry E. Wilkie, W. Keats Univ Colorado Ann & HJ Smead Aerosp Engn Sci Boulder CO 80309 USA NASA Langley Res Ctr Struct Dynam Branch Hampton VA 23666 USA

The heliogyro solar sail maneuvers by actuating high-aspect-ratio blades at their root with sinusoidal pitch profiles, producing spin-averaged forces and moments. The lightweight blade material has little inherent damping, requiring active control to attenuate blade vibration caused by maneuvering. Paradoxically, some amount of inherent damping at the blade's higher-frequency modes is needed to add damping to the larger-magnitude low-frequency modes, and so the control design's robustness depends on the accuracy of the blade damping model. Therefore, characterization of blade damping is critical for increasing the Technology Readiness Level for the heliogyro. This paper describes damping characterization tests performed on small-scale heliogyro blades hanging in a high-vacuum chamber, the closest analog possible for centrifugally loaded blades in space. Improvements to the measurements and a new modal damping algorithm, which the authors call the incremental and reduced frequency response function method, allowed separate flap and twist damping ratios to be calculated for the first three modes of these lightly damped blades to within +/- 2% error. This unprecedented precision enables definitive conclusions that the residual air damping is insignificant and that an assumption of a linear viscous torsional blade damping model is insufficient for the design of a robust proximal blade twist feedback controller.

关键词： Free Body Diagram Chemical Propulsion High Aspect Ratio Frequency Response functions loop transfer function Technology Readiness Level Finite Element Modeling Band Pass Filter Accelerometer Piezoelectric Actuators

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PULSE-MODULATED CONTROL SYNTHESIS FOR A FLEXIBLE SPACECRAFT

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1990年第6期13卷 1014-1022页

作者： ANTHONY, TC WIE, B CARROLL, S NASA GEORGE C MARSHALL SPACE FLIGHT CTRDIV CONTROL SYSTHUNTSVILLEAL 35812

The describing function method is employed for the nonlinear control analysis and design of a flexible spacecraft equipped with pulse-modulated reaction jets. The method provides a means of characterizing the pulse modulator in terms of its gain and phase for structural mode limit-cycle analysis. Although the describing function method is inherently inexact and is not widely used in practice, a new way of utilizing it for practical control design problems is presented. It is shown that the approximations inherent in the method can be accounted for as a modeling uncertainty for the nonlinear control robustness analysis. The pulse-modulated control system of the INTELSAT 5 spacecraft is used as an example to illustrate the concept and methodology developed in the paper. The nonlinear stability margins predicted by the describing function analysis are verified from nonlinear simulations.

关键词： Flexible Spacecrafts Nonlinear Control Schmitt Trigger Reaction Control System Feedback Control System Frequency Response functions loop transfer function Nonlinear Systems Orbital Maneuvering Vehicle Attitude Control System

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Voluntary Pilot Action Through Biodynamics for Helicopter Flight Dynamics Simulation

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2015年第3期38卷 431-441页

作者： Masarati, Pierangelo Quaranta, Giuseppe Bernardini, Andrea Guglieri, Giorgio Politecn Milan Dipartimento Sci & Tecnol Aerospaziali Via La Masa 34 I-20156 Milan Italy Politecn Torino Dipartimento Ingn Meccan & Aerospaziale I-10129 Turin Italy

This work presents the integration of detailed models of a pilot controlling a helicopter along the heave axis through the collective control inceptor. The action on the control inceptor is produced through a biomechanical model of the pilot's limbs, by commanding the activation of the related muscle bundles. Such activation, in turn, is determined by defining the muscle elongations required to move the control inceptor in order to obtain the control of the vehicle according to a high-level model of the voluntary action of the pilot acting as a regulator for the vehicle. The biomechanical model of the pilot's limbs and the aeromechanical model of the helicopter are implemented in a general-purpose multibody simulation. The helicopter model, the biomechanical model of the pilot's limbs, the cognitive model of the pilot, and their integration are discussed. The integrated model is applied to the simulation of simple, yet representative, mission task elements.

关键词： Aircraft Pilot Main Rotor Hub Flight Control System Multibody Simulation Helicopter Flight Dynamics Pilot Modeling Airframes Rotary Wing Aircraft Biomechanics loop transfer function

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The μ-k method for robust flutter solutions

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JOURNAL OF AIRCRAFT 2004年第5期41卷 1209-1216页

作者： Borglund, D Royal Inst Technol Dept Aeronatu & Vehicle Engn SE-10044 Stockholm Sweden

A straightforward frequency-domain method for robust flutter analysis is presented. First, a versatile uncertainty description for the unsteady aerodynamic forces is derived by assigning uncertainty to the frequency-domain pressure coefficients. The uncertainty description applies to any frequency-domain aerodynamic method, benefits from the same level of geometric detail as the underlying aerodynamic model, exploits the modal formulation of the flutter equation, and is computed by simple postprocessing of standard aerodynamic data. Next, structured singular value analysis is applied to derive an explicit criterion for robust flutter stability based on the flutter equation and a parametric uncertainty description. The resulting procedure for computation of a worst-case flutter boundary resembles a p-k or g-method flutter analysis, produces match-point flutter solutions and allows for detailed aerodynamic uncertainty descriptions. Finally, the proposed method is successfully applied to a wind-tunnel model in low-speed airflow.

关键词： Wing Tip Aerodynamics Flutter Analysis Pressure Coefficient Frequency Response functions Trailing Edge Flap Low Speed Wind Tunnel Aeroservoelastic Systems Flight Testing Influence Coefficients loop transfer function

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Thrust Evaluation in Wide Frequency Range Using Active Control and Disturbance Observer

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JOURNAL OF PROPULSION AND POWER 2013年第6期29卷 1274-1281页

作者： Kakami, Akira Tachibana, Takeshi Miyazaki Univ Dept Mech Design Syst Engn Miyazaki 8892192 Japan Kyushu Inst Technol Dept Mech Engn Kitakyushu Fukuoka 8048550 Japan

In this paper, a new method is proposed for evaluating thrust in the wide-frequency range from 0 Hz beyond the pendulum resonant frequency. The proposed method uses position control and a disturbance observer based on pendulum acceleration and solenoid-actuator current. A controller monitors pendulum motion and adjusts the force of a solenoid actuator in such a way that the pendulum angular displacement is kept constant. Simultaneously, the disturbance observer evaluates both invariant and time-varying components of thrust by use of pendulum acceleration and solenoid-actuator current. Spring and damping coefficients originating from wires, tubes, and the thrust stand can be ignored due to the position control. A calibrator, yielding both constant and periodically varying, biased forces, was also prototyped to show that the proposed method can evaluate thrust in a wide-frequency range from 0 Hz beyond the resonant frequency. The prototype thrust stand successfully measured thrust in the frequency range from 0 to 65 Hz with errors less than 16%, whereas the conventional null-balance method yielded 810% overestimation of thrust amplitude at a resonant frequency of approximately 15 Hz.

关键词： Thrust loop transfer function Transverse Vibrations Solenoids Actuators Kalman Filter Numerical Simulation Acceleration Sensors Accelerometer Elasticity

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