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3 edition of Nonlinear dynamic analysis of deploying flexible space booms found in the catalog.

Nonlinear dynamic analysis of deploying flexible space booms

Nonlinear dynamic analysis of deploying flexible space booms

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  • 39 Currently reading

Published by National Aeronautics and Space Administration, Langley Research Center, For sale by the National Technical Information Service in Hampton, Va, [Springfield, Va .
Written in English

  • Space frame structures.,
  • Kinematics.

  • Edition Notes

    StatementPaul E. McGowan and Jerrold M. Housner.
    SeriesNASA technical memorandum -- 87617.
    ContributionsHousner, Jerrold M., Langley Research Center.
    The Physical Object
    Pagination1 v.
    ID Numbers
    Open LibraryOL17672759M

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Nonlinear dynamic analysis of deploying flexible space booms Download PDF EPUB FB2

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American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Transient Dynamic Analysis of Gossamer-Appendage Deployment Using Nonlinear Finite Element Method September Journal of Spacecraft and Rockets 48(5) Deployment dynamic analysis and control of the hoop truss deployable antenna are carried out taking into account the stiffness of torsional spring, damping in joints, gravity and the pretension Author: Tuanjie Li.

The status and some recent developments in computational modeling of flexible multibody systems are summarized. Discussion focuses on a number of aspects of flexible multibody dynamics including: modeling of the flexible components, constraint modeling, solution techniques, control strategies, coupled problems, design, and experimental by:   The deployment dynamics of a simplified solar sail quadrant consisting of two Euler–Bernoulli beams and a flexible membrane are studied.

Upon prescribing the in-plane motion and modeling the tension field based on linearly increasing stresses assumed on the attached boundaries, the coupled equations of motion that describe the system's transverse deflections are by: 1.

A relatively general formulation, based on Lagrange's approach, for studying the nonlinear dynamics and control of a flexible, space based, Mobile Deployable Manipulator (MDM) has been developed.

The formulation has the following distinctive features: (i) it is applicable to a two-link deployable manipulator translating along a flexible space platform in any desired orbit; (ii) the revolute.

Compliant bistable mechanisms are monolithic devices with two stable equilibrium positions separated by an unstable equilibrium position. They show promise in space applications as nonexplosive release mechanisms in deployment systems, thereby eliminating friction and improving the reliability and precision of those mechanical devices.

This paper presents both analytical and numerical models Cited by: A Nonlinear dynamic analysis of deploying flexible space booms book formulation is presented for the librational dynamics of satellites having an arbitrary number, type, and orientation of flexible appendages, each capable of deploying independently.

In particular, the case of beam-type appendages deploying from a satellite in an arbitrary orbit is considered. The governing nonlinear, nonautonomous, coupled system equations are not amenable to any. Fig. 2(a) shows the REXUS rocket spinning in a positive de-spinning mechanism of the rocket was intrinsically important to the control method used for the web deployment.

If the experiment was mounted on a rocket which did not de-spin, assuming the angular velocity initially was 3–4 Hz, the time span for full deployment would be too short to guarantee post-deployment stability Cited by: 4. Dynamic Design Space Partitioning for Optimization of an Integrated Thermal Protection System.

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In order to illustrate the shape of the tensegrity-membrane systems studied in this work, the folded shape and the deployed shape of a system with 4 bars, 12 tendons, and a membrane (i.e. a 1–4(F) system) are depicted in Fig.

that the rotational joints located at bar ends A 1j are not depicted. It can be clearly seen that the attached membrane is slack when the system is folded, and Cited by: 1. A typical deployment mechanism with a large exhibition ratio includes STACER, a tape spring and the storable tubular extendible member (STEM) [10,11,12,13].The current research on such a mechanism mainly focuses on the optimization of configuration parameters, the analysis of mechanical characteristics during the deploying and gathering processes, and the influence of environmental factors on.

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