By D.Subbaram Naidu

The idea that of aeroassisting for orbital move has been well-known as one of many severe applied sciences for pioneering the distance frontier. In area transportation platforms, aeroassisting (or aerobraking), outlined because the deceleration due to the consequences of atmospheric drag upon a automobile in the course of orbital operations, opens new project possibilities, specially in regards to the institution of the everlasting area Station Freedom and area explorations to different planets comparable to Mars. the most components of study pronounced during this monograph are atmospheric access challenge through the strategy of matched asymptotic expansions, coplanar and non-coplanar orbital transfers with aeroassist know-how, orbital plan swap with aerocruise, and neighbouring optimum tips. a distinct characteristic is the bibliography so one can give you the reader with a literature prestige for additional study.

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Extra info for Aeroassisted Orbital Transfer: Guidance and Control Strategies (Lecture Notes in Control and Information Sciences)

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X. Vinh, "Minimum-fuel aeroassisted coplanar orbit transfer using lift modulation," J. Guidance, Control, and Dynamics, 8, 134-141, 1985. [4] A. Miele, V. K. Basapur, and W. Y. Lee, "Optimal trajectories for aeroassisted coplanar orbit transfer," J. Opt. , 52, 1-24, 1987. [5] M. H. Kaplan, Modern Spacecraft Dynamics and Control, John Wiley & Sons, New York, 1976. [6] J. P. Maree, Optimal Space Trajectories, Elsevier Scientific Publishing Company, Amsterdam, 1979. [7] J. Stoer, and R. Bulirsch, Springer-Verlag, New York, 1980.

0 ...... 5 m Fig. 5 w 0 100 200 300 400 O ~L- n O n- . yy= ACLVexp(_H~) + [V/R - IM(R2V)]cosy dt (6) where A = Sp /2m , H = R-R , p = p cxp(-Hl3) and C D = CDO+ KC~. _yy= Abrl~v + bvcosy dx (b-l+h) b2eosy (b. 4 Optimal Control For an optimal control problem with minimum fuel consumption, it is required to choose the performance index to minimize the total characteristic velocity, which is the sum of the initial characteristic velocity AVa, the deorbit impulse from HEO, and the final characteristic velocity A V , the circularization impulse into LEO.

Culp, "Solution of the exact equations for three-dimensional atmospheric entry using directly matched CHAPTER 2: ATMOSPHERIC ENTRY PROBLEM 29 asymptotic expansions," NASA Contractor Report, CR-2643, University of Colorado, Boulder, CO, March 1976. [10] F. Frostic and N. X. Vinh, "Optimal aerodynamic control by matched asymptotic expansions," Acta Astronautica, 3, 319-332, 1976. [11] K. D. Mease, and F. A. McGreary, "Atmospheric guidance law for planar skip trajectories," I A A 12th Atmospheric Flight Mechanics Conference, Snowmass, CO, Aug.

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