The Multi-Stage-Lambert Scheme for steering a satellite-launch vehicle (SLV)

Kamal, Syed Arif

doi:10.1109/inmic.2008.4777752

Cited by 2 publications

(1 citation statement)

References 6 publications

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“…Estimation and prediction of ballistic missiles are discussed in [2]. Some recent research work about ballistic missiles and satellite launch vehicles can be found in [3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18]. Escobal [19] and Nguyen and Dixson [20] have formulated the problem to calculate range of a ballistic missile over the none-rotating oblate spheroid Earth model.…”

Section: Introductionmentioning

confidence: 99%

An Efficient Computation of Effective Ground Range Using an Oblate Earth Model

Maturi

Ullah

Ahmad

et al. 2014

Abstract and Applied Analysis

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An effcient method is presented to calculate the ground range of a ballistic missile trajectory on a nonrotating Earth. The spherical Earth model does not provide good approximation of distance between two locations on the surface of Earth. We used oblate spheroid Earth model because it provides better approximations. The effective ground range of a ballistic missile is an arc-length of a planner elliptic (or circle) curve which passes through the launch and target points on the surface of Earth model. A general formulation is presented to calculate the arc-length of an elliptic (or circle) curve which is the intersection of oblate Earth model and a plane. Explicit formulas are developed to calculate the coordinates of center of the ellipse as well as major and minor axes which are necessary ingredients for the calculation of effective ground range.

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Section: Introductionmentioning

confidence: 99%

An Efficient Computation of Effective Ground Range Using an Oblate Earth Model

Maturi

Ullah

Ahmad

et al. 2014

Abstract and Applied Analysis

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Air Drag Effects on the Missile Trajectories

El-Salam

2011

Journal of Applied Mathematics

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The equations of motion of a missile under the air drag effects are constructed. The modified TD88 is surveyed. Using Lagrange's planetary equations in Gauss form, the perturbations, due to the air drag in the orbital elements, are computed between the eccentric anomalies of the burn out and the reentry points E bo , 2π − E bo , respectively. The range equation is expressed as an infinite series in terms of the eccentricity e and the eccentric anomaly E. The different errors in the missile-free range due to the drag perturbations in the missile trajectory are obtained.

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The Multi-Stage-Lambert Scheme for steering a satellite-launch vehicle (SLV)

Cited by 2 publications

References 6 publications

An Efficient Computation of Effective Ground Range Using an Oblate Earth Model

An Efficient Computation of Effective Ground Range Using an Oblate Earth Model

Air Drag Effects on the Missile Trajectories

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