3 edition of Evaluation of on-line pulse control for vibration suppression in flexible spacecraft found in the catalog.
Evaluation of on-line pulse control for vibration suppression in flexible spacecraft
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va
Written in English
|Other titles||Evaluation of on line pulse control for vibration suppression in flexible spacecraft, Evaluation of online pulse control for vibration suppression in flexible spacecraft|
|Statement||by G.A. Bekey, S.F. Masri, R.K. Miller|
|Series||NASA contractor report -- NASA CR-180391|
|Contributions||Masri, S. F, Miller, R. K, United States. National Aeronautics and Space Administration|
|The Physical Object|
Figure 1. Flexible spacecraft simulator (FSS). can be obtained prior to the control design via FEM analysis and experimental testing, PPF is used to achieve fast damping of the vibration of a particular mode. Application of PPF to multi-mode vibration suppression was also studied. The PPF controller was implemented. dynamics modeling, research progress of structure vibration-attitude coordinated control of flexible spacecraft have been discussed respectively. Finally, future research on application of structure vibration-attitude coordinated control of spacecraft has been recommended. Key words: spacecraft, vibration-attitude coordinated control, overview 1.
Vibration Reduction for Flexible Spacecraft Attitude Control using PWPF Modulator and Smart Structures Gangbing Song Department of Mechanical Engineering The University of Akron Akron, Ohio Brij N. Agrawal Aeronautics and Astronautics Department US Naval Postgraduate School Monterey, California Abstract-This paper presents a new approach to vibration. Three neural networks are developed, one for system identification, the second for on-line state estimation, and the third for vibration suppression. It is shown both in analysis and in experiment that these neural networks can identify, estimate, and suppress the vibration of a composite structure by the embedded piezoelectric sensor and by:
 Q. Hu and G. Ma. Variable structure control and active vibration suppression of flexible spacecraft during attitude maneuver. Aerospace Science and Technology, , 9, DOI: /ed by: 1. Adaptive Feedforward Vibration Control of Flexible Structure With Discrete Sliding Mode Controller J. Fei. J. Fei. Vibration suppression of a spacecraft flexible appendage using smart materials ”, Research on Residual Vibration Suppression of Trajectory Glue Based on Adaptive Pulse Reshape Filter.
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Evaluation of on-line Pulse Control for Vibration Suppression in Flexible Spacecraft b-mm, 4 cwcor 0, 8 m t- gr Building on the results of a feasibility study conducted under NASA Research Grant No. t-* w V' Ir, CI e w b bran evaluation was performed on a vibration suppression technique developed by the Principal cb m.
A numerical simulation was performed, by means of a large-scale finite element code capable of handling large deformations and/or nonlinear behavior, to investigate the suitability of the nonlinear pulse-control algorithm to suppress the vibrations induced in the Spacecraft Control Laboratory Experiment (SCOLE) components under realistic : Sami F.
Masri. On-line pulse control for vibration suppression in a flexible spacecraft was evaluated. A continuous beam vs. a truss was modeled. A linear finite element model was used to determine the truss : G.
Bekey, R. Miller and S. Masri. Vibration suppression of a large flexible spacecraft for on-orbit operation. Abstract. Flexible appendages, such as solar panels, communication antennas and other large structures, are mounted on the base of a space robot and target satellite.
The vibration of the flexible structure is excited by operations of a space by: 5. Vibration Suppression of the Flexible Spacecraft During Attitude Control. This paper presents a new approach to vibration reduction of flexible spacecraft during attitude control by using pulse width pulse frequency (PWPF) modulator for thruster firing and smart materials for active vibration suppression.
space control method, mode localization, and optimum control based on the minimization of power supplied to the beam. Figure 1. Flexible spacecraft model and parameters. In this paper, a new hybrid control strategy is extended for ﬂexible spacecraft rotational maneuver control as well as vibration suppression of the ﬂexible sandwich appendagesCited by: 2.
The method for evaluating the vibration isolation performance of discrete whole-spacecraft vibration isolation of flexible spacecrafts is studied in the paper.
The dynamic model of the discrete whole-spacecraft system is built and model reduction Cited by: 2. Introduction to Dynamics and Control of Flexible Structures. Active Vibration Suppression of Spacecraft with Rate-Weighted Optimal Control and Multi-Mode Command Shaping. On-line Fault Detection, Diagnosis, Isolation and Accommodation of Dynamical Systems with Actuator Failures.
Input Shaping for Reducing Vibrations Following Orbit Adjustment and Slewing of Spacecraft Arun K. Banerjee Consulting Scientist, L /Lockheed Martin Advanced Technology Center, Palo Alto, CAUSA Abstract This paper considers two problems requiring vibration suppression, one following.
Vibration Testing Rocket boosters and spacecraft are subject to intense acoustic environments during launch, which induce high levels of vibration in structural elements and equipment. In addition, elastic structural interactions with propulsion systems and flight control systems can produce low-frequency, high-deflection flight instabilities.
This paper presents a novel control strategy for attitude control and vibration suppression of flexible spacecraft. A set of control moment gyroscopes are distributed on the flexible structure of the spacecraft to provide control torques.
The interactions between the control moment gyroscopes and the flexibilities of the structure are incorporated in the equations of. A simple PD feedback control has been addressed to stabilize the attitude control system of flexible spacecraft.
However, it is not effective in modal vibration suppression. Then, an attractively smooth approximation of sign function has been introduced to modify the admissible PD control by: 1. Control strategy The control system for vibration reduction of the flexible spacecraft during attitude maneuvers consists of two sub- systems, the attitude control subsystem using PWPF mod- ulation based on VSC and the active vibration suppression subsystem using smart materials, as shown in by: Get this from a library.
Evaluation of on-line pulse control for vibration suppression in flexible spacecraft. [George A Bekey; S F Masri; R K Miller; United States. National Aeronautics and Space Administration.]. Positive position feedback control for large space structures.
Hybrid PD and effective multi-mode positive position feedback control for slewing and vibration suppression of a smart flexible manipulator. Vibration suppression of flexible spacecraft using smart materials and path planning during attitude by: A hybrid control scheme for vibration reduction of ﬂexible spacecraft during rotational maneuvers is investigated by using variable structure output feedback control (VSOFC) for attitude control and smart materials for active vibration suppression.
The proposed control design process is twofold: design of the attitude controller using VSOFC. This paper presents a hybrid control design approach for simultaneous three axis attitude manoeuvre and active vibration suppression of a flexible spacecraft, in the presence of sensor noises and.
Gaussian (LQG) control for vibration suppression of a flexible structure using piezoceramics. Experiments were conducted on the U.S. Naval Postgraduate Schools Flexible Spacecraft Simulator (FSS), which is comprised of a rigid central body and a flexible appendage.
To suppress the vibration of the flexible appendage is the objective of the this. For flexible spacecraft, the controller can be designed with a term which takes into account the flexible dynamics.
However, duo to nonlinearity and coupling, how to determine state-feedback control parameters which ensure fast attitude tracking and significant vibration suppression must be : Ya Nan Yu, Xiu Yun Meng, Li Chao Ma. vibration suppression of a flexible spacecraft. It is assumed that the system parameters are unknown.
The design approach presented here treats the problem of spacecraft attitude control separately from the elastic vibration suppression problem.
As a stepping stone, a state feedback sliding mode control command is. Output Stabilization of Flexible Spacecraft with Active Vibration Suppression S. DI GENNARO Universita di L’Aquila` Italy Addressed here is the problem of designing a dynamic controller capable of performing rest-to-rest maneuvers for flexible spacecraft, by .anti-symmetrically.
For the configuration of the spacecraft, Attitude Tracking and Vibration Suppression of Flexible Spacecraft Using Implicit Adaptive Control Law Morteza Shahravi, Mansour Kabganian T American Control Conference JunePortland, OR, USA /05/$ © AACC WeB 2. Dynamic Modeling. Figure 1 demonstrates the schematic of the hub with two flexible appendages.
A spacecraft model and rigid main body with two clamped loaded Euler-Bernoulli beams bounding with PZT layers are considered to model the elastic deformations of the flexible parts in multiaxis attitude by: 3.