This paper assumes a requirement for an unmanned multiunit satellite to be assembled in orbit. The requirement to be met is to bring the satellites together so tha t they do not collide but actually rendezvous. The equations of motion of the rendezvous satellite in a relative coordinate system are derived and used to compute a final injection velocity which would effect collision after a time r. The velocity is corrected periodically by a command guidance system and just before impact retrothrust is applied. A terminal infrared homing sj^stem is required to actually accomplish physical contact and joining of the satellites. The first satellite placed in orbit is the "control satellite" and controls all the satellites to be assembled and contains the ccmputer, command guidance equipment, precision orientation equipment, and other features necessary to effect rendezvous. The succeeding satellites contain a propulsion system, a rough at t i tude control system, and a command receiver plus whatever scientific equipment they carry to perform their basic mission. This paper presents the following:

Terminal Guidance System for Satellite Rendezvous

5. M. Green, J. Schwarz, and E. Witten, Superstring theory, Cambridge Univ. Press, 1987. 6. J. Isenberg, P. Yasskin, and P. Green, Non-self-dual gauge fields, Phys. Lett. 78B (1978), 462-464. 7. B. Kostant, Graded manifolds, graded Lie theory, and prequantization, Differential Geometric Methods in Mathematicas Physics, Lecture Notes in Math., vol. 570, SpringerVerlag, Berlin and New York, 1977. 8. C. LeBrun, Thickenings and gauge fields, Class. Quantum Grav. 3 (1986), 1039-1059. 9. , Thickenings and conformai gravity, preprint, 1989. 10. C. LeBrun and M. Rothstein, Moduli of super Riemann surfaces, Commun. Math. Phys. 117(1988), 159-176. 11. Y. Manin, Critical dimensions of string theories and the dualizing sheaf on the moduli space of (super) curves, Funct. Anal. Appl. 20 (1987), 244-245. 12. R. Penrose and W. Rindler, Spinors and space-time, V.2, spinor and twistor methods in space-time geometry, Cambridge Univ. Press, 1986. 13. R. Ward, On self-dual gauge fields, Phys. Lett. 61A (1977), 81-82. 14. E. Witten, An interpretation of classical Yang-Mills theory, Phys. Lett. 77NB (1978), 394-398. 15. , Twistor-like transform in ten dimensions, Nucl. Phys. B266 (1986), 245-264. 16. , Physics and geometry, Proc. Internat. Congr. Math., Berkeley, 1986, pp. 267302, Amer. Math. Soc, Providence, R.I., 1987.

Infinite-Dimensional Dynamical Systems in Mechanics and Physics (Roger Temam)

Numerical simulation of large-scale dynamical systems plays a fundamental role in studying a wide range of complex physical phenomena; however, the inherent large-scale nature of the models often leads to unmanageable demands on computational resources. Model reduction aims to reduce this computational burden by generating reduced models that are faster and cheaper to simulate, yet accurately represent the original large-scale system behavior. Model reduction of linear, nonparametric dynamical systems has reached a considerable level of maturity, as reflected by several survey papers and books. However, parametric model reduction has emerged only more recently as an important and vibrant research area, with several recent advances making a survey paper timely. Thus, this paper aims to provide a resource that draws together recent contributions in different communities to survey the state of the art in parametric model reduction methods. Parametric model reduction targets the broad class of problems for wh...

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A Survey of Projection-Based Model Reduction Methods for Parametric Dynamical Systems

A new method for performing a balanced reduction of a high-order linear system is presented. The technique combines the proper orthogonal decomposition and concepts from balanced realization theory. The method of snapshotsisused to obtainlow-rank,reduced-rangeapproximationsto thesystemcontrollability and observability grammiansineitherthetimeorfrequencydomain.Theapproximationsarethenusedtoobtainabalancedreducedorder model. The method is particularly effective when a small number of outputs is of interest. It is demonstrated for a linearized high-order system that models unsteady motion of a two-dimensional airfoil. Computation of the exact grammians would be impractical for such a large system. For this problem, very accurate reducedorder models are obtained that capture the required dynamics with just three states. The new models exhibit far superiorperformancethanthosederived using a conventionalproperorthogonal decomposition. Although further development is necessary, the concept also extends to nonlinear systems.

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Balanced Model Reduction via the Proper Orthogonal Decomposition

On the use of higher-order finite-difference schemes on curvilinear and deforming meshes

Interior Noise Studies for Single- and Double-Walled Cylindrical Shells

References Stable, C. V., "Transonic Effects on T-tail Flutter," RM-24, 1959, The Martin Company, Baltimore, Md. Stark, V. J. E., "Aerodynamic Forces on a Combination of a Wing and a Fin Oscillating in Subsonic Flow," SAAB TN54, Feb. 1964, Likoping, Sweden. Laschka, B. and Schmid, H., "Unsteady Aerodynamic Forces on Coplanar Lifting Surfaces in Subsonic Flow (Wing-Horizontal Tail Interference)," AGARD Structures and Materials Panel Meeting, Sept. 25-27,1967, Ottawa, Canada. Topp, L. J., Rowe, W. S., and Shattuck, A. W., "Aeroelastic Considerations in the Design of Variable Sweep Airplanes," 1C AS Paper 66-12, Sept. 1966, London, England. Sensberg, O. and Laschka, B., "Flutter Induced by Aerodynamic Interference between Wing and Tail," Journal of Aircraft, Vol. 7, No. 4, July-Aug. 1970, p. 319-324. Mykytow, W. J., Noll, T. E., Huttsell, L. J., and Shirk, M. H., "Investigations Concerning the Coupling Wing-Fuselage-Tail Flutter Phenomenon," Journal of Aircraft, Vol. 9, No. 1, Jan. 1972, pp. 48-54. Albano, E. and Rodden, W. P., "A Doublet Lattice Method for Calculating Lift Distributions on Oscillating Surfaces in Subsonic Flow," AIAA Journal, Vol. 7, No. 2, Feb. 1969, pp. 279-285. Albano, E., Perkinson, F., and Rodden, W. P., "Subsonic Lifting Surface Theory Aerodynamics and Flutter Analysis of Interfering Wing/Horizontal Tail Configurations," AFFDL-TR-70-59, Sept. 1970, Air Force Flight Dynamics Lab., Wright-Patterson Air Force Base, Ohio. Triplett, W. E., Burkhart, T. H., and Birchfield, E. B., "A Comparison of Methods for the Analysis of Wing-Tail Interaction Flutter," AIAA Paper 70-80, 1970, New York. Goetz, R. C., "Lifting and Control Surface Flutter," TMX52876, Vol. Ill, July 1970, NASA. ^Rodden, W. P., Giesing, J. P., and Kalman, T. P., "New Developments and Applications of the Subsonic Doublet-Lattice Method for Nonplanar Configurations," AGARD Symposium, Tonsberg, Oslofjorden, Norway, Nov. 1970. Chipman, R. R., "Interference Flutter on Space Shuttle Configurations," Paper presented at Aerospace Flutter and Dynamics Council Meeting, May 1972, New York. Bisplinghoff, R. L. and Ashley, H., Principles of Aeroelasticity, J. Wiley and Sons, New York, 1962.

Aerodynamic Boundary Layer Effects on Flutter and Damping of Plates

Panel flutter is a self-excited aeroelastic phenomenon in which a panel's oscillations are derived from energy absorbed from the flow over the panel. Linear and nonlinear structural responses of panels with supports on all four sides have been studied for many years. This effort addresses the nonlinear response of a square, cantilevered isotropic panel subject to quasi-steady supersonic aerodynamics over the upper surface and a time invariant temperature differential between the panel and its surroundings. Rayleigh-Ritz assumed modes are employed to describe the in-plane and transverse displacements. In-plane and transverse modal convergence analyses are conducted. The transverse displacement response may decay exponentially to z = 0, decay exponentially to a buckled state, oscillate harmonically about z = 0, oscillate harmonically about a buckled state, oscillate periodically, or oscillate nonperiodically. The steady state response is dependent upon the initial conditions, the panel and flow parameters, and the temperature differential.

Limited amplitude panel flutter with a temperature differential

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Nonlinear Responses of Inextensible Cantilever and Free-Free Beams Undergoing Large Deflections

Keywords: aeroelasticite ; statique ; dynamique ; flottement : subsonique Reference Record created on 2005-11-18, modified on 2016-08-08

Earl H. Dowell

Papers

Interior Noise Studies for Single- and Double-Walled Cylindrical Shells

Aerodynamic Boundary Layer Effects on Flutter and Damping of Plates

Limited amplitude panel flutter with a temperature differential

Nonlinear Responses of Inextensible Cantilever and Free-Free Beams Undergoing Large Deflections

A modern course in aeroelasticity (third revised and enlarged edition)