On the Solution of Two-Point Boundary-Value Problems Associated with Spacecraft Trajectories,
Abstract
The problem of calculating spacecraft trajectories between fixed points in a given time is approached through Hamilton's principle, and numerical optimization methods are used to extremize the integral of the Lagrangian. The conclusion derived from this analysis is that the iteration schemes obtained in this fashion are identical with standard iteration schemes applied to the differential equations, that is, Picard iteration and Newton iteration. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1971
- Accession Number
- AD0732924
Entities
People
- David G. Hull
Organizations
- University of Texas at Austin