Accession Number:

AD0602651

Title:

OPTIMUM GUIDED ASCENT,

Descriptive Note:

Corporate Author:

AEROSPACE CORP EL SEGUNDO CALIF

Personal Author(s):

Report Date:

1964-06-25

Pagination or Media Count:

33.0

Abstract:

Presented in this paper are simple approximate closedform equations for the thrust attitude pitch program to minimize propellant consumption for any spacecraft or missile ascending in a vacuum. A small amount of aerodynamic force, such as frequently occurs in the early part of guided flight, should not invalidate these equations. Also presented are explicit guidance equations for the optimum pitch program, which were developed specifically for the case of constant thrust and propellant flow rate. Since the form of the optimum pitch angle-versus-time equation is independent of the variation of thrust acceleration with time, continuous application of this program is permitted through more than one propulsion stage to achieve maximum performance. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE