Evaluation of a pulse control law for flexible spacecraft

final technical report : reporting period 1 June 1984 - 31 May 1985
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National Aeronautics and Space Administration, National Technical Information Service, distributor , [Washington, DC, Springfield, Va
SeriesNASA contractor report -- NASA CR-176233
ContributionsUnited States. National Aeronautics and Space Administration
The Physical Object
FormatMicroform
Pagination1 v
ID Numbers
Open LibraryOL14985898M

Get this from a library. Evaluation of a pulse control law for flexible spacecraft: final technical report: reporting period 1 June May [United States. National Aeronautics and.

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Here a leading researcher provides a comprehensive treatment of the design of automatic control logic for spacecraft and aircraft. In this book Arthur Bryson describes the linear-quadratic-regulator (LQR) method of feedback control synthesis, which coordinates multiple controls, producing graceful maneuvers comparable to those of an expert by: The function of probability distribution density is obtained for random values of elastic oscillations of constraction flexible spacecraft arising with controller switchings in an open space of system phase coordinates.

The method of polynomial equations is used for the analitical synthesis of the digital control law of aircraft flight path. Flexible Spacecraft Dynamics, Control and Guidance: Technologies by Giovanni Campolo (Springer Aerospace Technology) - Kindle edition by Mazzini, Leonardo.

Download it once and read it on your Kindle device, PC, phones or tablets. Use features like bookmarks, note taking and highlighting while reading Flexible Spacecraft Dynamics, Control and Guidance: Technologies by Giovanni Campolo Manufacturer: Springer.

This book is an up-to-date compendium on spacecraft attitude and orbit control (AOC) that offers a systematic and complete treatment of the subject with the aim of imparting the theoretical and practical knowledge that is required by designers, engineers, and researchers.

Magnetic Attitude Control for Spacecraft with Flexible Appendages Julian Pierre Stellini Master of Applied Science Graduate Department of Aerospace Science and Engineering University of Toronto Abstract The design of an attitude control system for a flexible spacecraft using magnetic actuation is Author: Julian Pierre Stellini.

A new design of attitude control system for flexible spacecraft was described; The control system has two parts, a rigid body attitude controller and a hinge controller. The latter was supposed to suppress the oscillation of flexible appendages.

A rotational motion of spacecraft that has a large flexible solar array was modeled and analysed. In [8], smart material actuators and thrusters driven by a pulse width pulse frequency modulation (PWPF) are used to control both the attitude and the vibrations of a flexible spacecraft.

In [9. The problem of a spacecraft tracking a desired trajectory is defined and addressed using adaptive feedback control. The control law, which has the form of a sixth-order dynamic compensator, does. Assessing and Controlling Spacecraft Charging Effects ().

Design for control and mitigation of internal charging, the buildup of charge on the interior parts of a spacecraft from higher energy particles, was treated in detail in the original version of NASA-HDBK, Avoiding Problems Caused by Spacecraft On-Orbit Internal Charging Effects. Read "Flexible Spacecraft Dynamics, Control and Guidance Technologies by Giovanni Campolo" by Leonardo Mazzini available from Rakuten Kobo.

This book is an up-to-date compendium on spacecraft attitude and orbit control (AOC) that offers a systematic and comple Brand: Springer International Publishing.

MODELING AND SLEW-MANEUVER CONTROL OF A FLEXIBLE SPACECRAFT By Jeremy Eckhart This thesis was prepared under the direction of the candidate's thesis committee chair, Dr. Mahmut Reyhanoglu, Department of Physical Sciences, and has been approved by the members of his thesis committee. It was submitted to the Department of Physical.

spacecraft dynamics transfer function shown in Figure (a) is in the factorised attitude angle reference controller K s-plane attitude B denote JCD denote direction of increasing K. A constraint equation-based control law design for large angle attitude maneuvers of flexible spacecraft is addressed in this paper.

The tip displacement of the flexible spacecraft model is prescribed in the form of a constraint equation. The controller design is attempted in the way that the constraint equation is satisfied throughout the Cited by: 4.

This paper addresses a composite two-time-scale control system for simultaneous three-axis attitude maneuvering and elastic mode stabilization of flexible spacecraft.

By choosing an appropriate time coordinates transformation system, the spacecraft dynamics can be divided into double time-scale subsystems using singular perturbation theory (SPT).Cited by: 3. stability criteria for idealized spinning flexible spacecraft, and 2) Analytical support of a Marshall Space Flight Center computational study of the dynamics of Skylab B.

The latter study is continuing, while the former has been the basis of the Ph. dissertation of Frank J. Barbera, which constitutes the present report. The scope. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA paper, a nonlinear control scheme is proposed as a solution of these problems in attitude control of a flexible spacecraft.

In particular, to cope with the existing model uncertainty, an adaptive version of the control law is proposed. The model of the spacecraft considered as a. OF A FLEXIBLE SPACECRAFT MODEL By W.

Noonan and J. Daiber Prepared under Contract No. NAS by MCDONNELL DOUGLAS ASTRONAUTICS COMPANY St. Louis, Mo. for Langley Research Center NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the Clearinghouse for Fedsrol Scientific and Technical Information.

Spacecraft Research and Design Center at the Naval Postgraduate School (NPS). He received his Ph.D. degree in Mechanical Engineering from Syracuse University. At NPS he has developed research programs in computer aided spacecraft design, Attitude control of flexible spacecraft, “Smart” sensors and structures, and space robotics, and.

PD state-feedback controller has been adopted in many spacecraft for attitude tracking and presents good performance. 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 Author: Ya Nan Yu, Xiu Yun Meng, Li Chao Ma.

Evaluation of a pulse control law for flexible spacecraft [microform]: final technical report: reporti Attitude control/momentum management and payload poInting in advanced space vehicles [microform] / Alexa Streamlined design and self reliant hardware for.

This paper investigates the fixed-time attitude tracking control problem for flexible spacecraft with unknown bounded disturbances. First, with the knowledge of norm upper bounds of external disturbances and the coupling effect of flexible modes, a novel robust fixed-time controller is designed to deal with this problem.

Second, the controller is further enhanced by an adaptive law to avoid Cited by: 3. TECHNIQUES FOR SLEW MANEUVERS OF FLEXIBLE SPACECRAFT Jeffrey A. ~aile~*, Christopher D. ort tun* and Brij N.

AgrawaP Naval Postgraduate School Monterey, California Abstract This paper presents experimental verification of modern and classical control laws on flexible spacecraft structures. The Flexible Spacecraft Simulator at the.

Details Evaluation of a pulse control law for flexible spacecraft EPUB

spacecraft with flexible appendage during attitude tracking demonstrate the effectiveness a nd feasibility of the method. FLEXIBLE SPACECRAFT AND CONTROL PROBLEM Using the extended Hamilton s principle, the equations of motion for the flexible spacecraft with surface mounted PZT sensors and actuators can be written as (Hu and Ma, ).

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.

Vibration Suppression of Flexible Spacecraft During Attitude Control Song, G. Acta Astronautica Vol. 49, No. 2,pp. Modern spacecraft often employ large exible hand, pulse modulators are commonly employed.

right ascetlsion a and declination 6 of the thust pointing vector, and the duration of thrusting) which achieves the targets with a minimum fuel usage. Since this process is dependent on several fact,ors, including t,he launch dat,e and available power from the solar array, t,he nominal trajectory is coustantly being revised as new data (especially about solar army performance) is.

PhD Dissertation. Longman, A Generalized Approach to Gravity-Gradient Sil tab ization of Gyrostat Satellites, available from The RAND Corporation, RMPR, November Guest Editor Special Issue on System Modeling and Control of Flexible Space Structures The Journal of the Astronautical Sciences, Vol.

21, No. 3, July Methods covered by the Robust Control Toolbox in MATLAB shall be the basis for the selection.

Description Evaluation of a pulse control law for flexible spacecraft EPUB

CONTROL SYNTHESIS INCLUDING SELECTION OF WEIGHT FILTERS Using the selected control synthesis method, a robust control design shall be established that fulfils certain performance specifications and that guarantees this performance in the. Book Corrections for Fundamentals of Spacecraft Attitude Determination and Control F.

Landis Markley and John L. Crassidisy Febru This document provides corrections for the book: Markley, F.L., and Crassidis, J.L., Fundamentals of Spacecraft Attitude Determination and Control, Springer, New York, NY, Any other corrections are.ANEW generation of spacecraft designs involving actively controlled systems with extremely light, flexible ap-pendages has motivated increased research aimed at produc-ing accurate models of such systems for purposes of simulation, structural verification, and control law design.

A basic requirement of any such model intended for general.Design Guidelines for ‘ * Assessing and Controlling Spacecraft Charging Effects Carolyn K.

Purvis Lewis Research Center Cleveland, Ohio used early in the design process so that the control of spacecraft charging can be easily and economically achieved.

It should be stressed that, if such control is to discharge pulse to individual.