Download Aeroassisted Orbital Transfer: Guidance and Control by D.Subbaram Naidu PDF

By D.Subbaram Naidu

The proposal of aeroassisting for orbital move has been well-known as one of many serious applied sciences for pioneering the distance frontier. In house transportation platforms, aeroassisting (or aerobraking), outlined because the deceleration as a result of the results of atmospheric drag upon a automobile in the course of orbital operations, opens new undertaking possibilities, particularly in regards to the institution of the everlasting house Station Freedom and house explorations to different planets reminiscent of Mars. the most components of analysis suggested during this monograph are atmospheric access challenge by way of the tactic of matched asymptotic expansions, coplanar and non-coplanar orbital transfers with aeroassist know-how, orbital plan swap with aerocruise, and neighbouring optimum advice. a different function is the bibliography with the intention to give you the reader with a literature prestige for extra research.

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Additional info for Aeroassisted Orbital Transfer: Guidance and Control Strategies

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Finally, at point C, a tangential circularizing bum AV. is imparted to achieve the Cl desired LEO. In this transfer, the idealizations are (i) the atmospheric density at Ra is sufficient to generate enough drag to slow the vehicle in a reasonable amount of time, and (ii) the vehicle has sufficient lifting capability to maintain flight along the atmospheric boundary. The following relations for the characteristic velocities are obtained by using the principles of conservation of angular momentum and the conservation of energy.

2]. Thus, the vehicle leaves HEO at R,lWith a tangential deorbit impulse AVoi and enters into an elliptic orbit with its perigee at Ra and flight path angle T¢= 0. , along the circular orbit of radius Ra). This grazing flight is continued along the atmospheric boundary to point F until sufficient velocity has been depleted by atmospheric drag such that upon reducing the lift to zero, the vehicle ascends with yf = 0 on an elliptic orbit to an apogee at R¢. Finally, at point C, a tangential circularizing bum AV.

Shen, "Series solution of equations for re-entry vehicles with variable lift and drag coefficients,"A/AA Journal,l, 2487-2490, 1963. [2] Y. Y. Shi and M. C. Eckstein, "Ascent or descent from satellite orbit by low thrust," A/AA Journal, 4, 2203-2209, 1966. [3] R. E. Willcs, M. C. Francisco, J. G. Reid, and W. K. Lim, "An application of matched asymptotic expansions to hypcrvelocity flight mechanics," AIAA Guidance, Control, and Flight Mechanics Conference, Huntsville, AL, Aug. 1967. -Y. Shi and L.

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