Fractional Describing Function Analysis of PWPF Modulator

Wang, Xinsheng; Wang, Danwei; Zhu, Senqiang; Poh, Eng Kee

doi:10.1155/2013/287040

Cited by 7 publications

(9 citation statements)

References 19 publications

(17 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Static analysis indicates that the modulator, for a fixed input, has a quasi-linear (almost linear) performance. In order to analyze the stability, a dynamic analysis for a nonlinear input is required, and one can make use of the approach of fractional describing function [12]. In the present paper, the jet performance is controlled via the modulator; that is, the modulator, in appropriate intervals, International Journal of Aerospace Engineering provides us with the situation to monitor the jet performance (on and off).…”

Section: Modulatormentioning

confidence: 99%

Designing a Control System for an Airplane Wing Flutter Employing Gas Actuators

Ansari

Novinzadeh

2017

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

The wing flutter is a dynamic instability of a flight vehicle associated with the interaction of aerodynamic, elastic, and inertial forces (aeroelastics phenomena). In this study, just the primary control is investigated. Also, in order to control the two-dimensional wing flutter, the force jet and pulse width pulse frequency (PWPF) are suggested. The PWPF modulator has the advantage of almost linear operation, low jet gas consumption, flexibility in addressing various needs, and good accuracy in presence of oscillations. This scheme makes use of quasi-steady dynamic premises and incompressible flow, as well as the thin airfoil theory. It should be noted that, to justify the application of the aerodynamic theory, we have speculated that the thruster jet ejected through a nozzle with a diameter smaller than several millimeters has a supersonic regime (with Mach number of the order of ≈ 3.5). Consequently, the interference of the thruster jet in the boundary layer, flow, and circulation around the airfoil which are characterized by low speed would be negligible. The operation of the jet as a thruster is handled by the PWPF modulator, and the process output is fed back to the system via a PD controller. In order to control the wing flutter oscillation, the location of installing the actuator on the airfoil is investigated.

show abstract

Section: Modulatormentioning

confidence: 99%

Designing a Control System for an Airplane Wing Flutter Employing Gas Actuators

Ansari

Novinzadeh

2017

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

show abstract

“…[24][25][26]. Dealing with PWPF-based controllers, persistently, has been an interesting subject in the six past decades [22,[26][27][28][29][30][31][32][33]. It has had historical analogous applications in the aerospace control systems and its features have been well known for designers [27,28,34].…”

Section: Problem Statementmentioning

confidence: 99%

“…Progressively, PWPF-based controllers are getting more popular in control engineering literature [6,7,[29][30][31][32][33]. Hu and co-workers have examined several control methods such as variable structure and fault tolerant controller for flexible spacecraft implemented by PWPF [6,7,29,30].…”

Section: Fig 2 Pulse-width Pulse-frequency (Pwpf) Modulatormentioning

confidence: 99%

See 1 more Smart Citation

Tuning of Pulse-Width Pulse-Frequency Modulator using PSO: An Engineering Approach to Spacecraft Attitude Controller Design

Khosravi

Sarhadi²

2016

Automatika

View full text Add to dashboard Cite

“…Consequently, RCS is a better solution scheme to provide efficient control performance. Currently, a lot of research studies on RCS are focused on RCS thruster configuration [2], RCS nozzle selection logic [3,4], and RCS combined with pneumatic rudder surface control [5,6]. Liu provides a new method to obtain necessary and sufficient conditions for impulse controllability in continuous linear dynamics, which performs discrete-time actions for spacecraft maneuvering [7].…”

Section: Introductionmentioning

confidence: 99%

Reaction Control System Optimization for Maneuverable Reentry Vehicles Based on Particle Swarm Optimization

Gui

Sun

Chen

et al. 2020

Discrete Dynamics in Nature and Society

View full text Add to dashboard Cite

This paper presents a new parametric optimization design to solve a class of reaction control system (RCS) problem with discrete switching state, flexible working time, and finite-energy control for maneuverable reentry vehicles. Based on basic particle swarm optimization (PSO) method, an exponentially decreasing inertia weight function is introduced to improve convergence performance of the PSO algorithm. Considering the PSO algorithm spends long calculation time, a suboptimal control and guidance scheme is developed for online practical design. By tuning the control parameters, we try to acquire efficacy as close as possible to that of the PSO-based solution which provides a reference. Finally, comparative simulations are conducted to verify the proposed optimization approach. The results indicate that the proposed optimization and control algorithm has good performance for such RCS of maneuverable reentry vehicles.

show abstract

Fractional Describing Function Analysis of PWPF Modulator

Cited by 7 publications

References 19 publications

Designing a Control System for an Airplane Wing Flutter Employing Gas Actuators

Designing a Control System for an Airplane Wing Flutter Employing Gas Actuators

Tuning of Pulse-Width Pulse-Frequency Modulator using PSO: An Engineering Approach to Spacecraft Attitude Controller Design

Reaction Control System Optimization for Maneuverable Reentry Vehicles Based on Particle Swarm Optimization

Contact Info

Product

Resources

About