Optimal finite-thrust time-limited direct-ascent interception

James R. Downey, Bruce A. Conway

Research output: Contribution to conferencePaper

Abstract

Minimum-time and maximum final mass solutions are obtained for the problem of direct-ascent interception, from a launch point on the surface of the Earth, of a target in a circular orbit. The intercepting rocket is assumed to have finite thrust and is subject to aerodynamic forces including lift and drag. The effect of Earth rotation is included and an initial “coast arc” is allowed. The problem is formulated as an optimal control problem and direct collocation with nonlinear programming is used to find numerical solutions. Both time-open and time-fixed problems are considered. Optimal solutions include both posigrade and retrograde intercept trajectories. Solutions are obtained for a range of target orbit radii, inclinations, launch points, and initial target phase angles relative to the launch point.

Original languageEnglish (US)
Pages281-291
Number of pages11
StatePublished - Jan 1 1992
EventAstrodynamics Conference, 1992 - Hilton Head Island, United States
Duration: Aug 10 1992Aug 12 1992

Other

OtherAstrodynamics Conference, 1992
CountryUnited States
CityHilton Head Island
Period8/10/928/12/92

ASJC Scopus subject areas

  • Astronomy and Astrophysics

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  • Cite this

    Downey, J. R., & Conway, B. A. (1992). Optimal finite-thrust time-limited direct-ascent interception. 281-291. Paper presented at Astrodynamics Conference, 1992, Hilton Head Island, United States.