APPLICATION OF NEAR OPTIMUM GUIDANCE EQUATIONS OVER TWO BOOSTER PROPULSION STAGES OF ANY SPACE BOOSTER,

Abstract

The purpose of this document is to present additional equations that are necessary to simplify the application of the single pitch program across two thrust stages. These guidance equations could then be mechanized for explicit guidance during the guidance phase of the first stage and, in addition, for the entire second stage; or, alternatively, they could be used on a general-purpose computer before flight to determine the nominal optimum pitch-time equation that could then be flown open-loop up to the initiation of the final propulsive stage--which would then be flown closedloop, using the explicit solution obtained in AD-602 651. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 15, 1964
Accession Number
AD0602698

Entities

People

  • F. M. Perkins

Organizations

  • The Aerospace Corporation

Tags

DTIC Thesaurus Topics

  • Computers
  • Equations
  • Guidance

Fields of Study

  • Physics

Readers

  • Control Systems Engineering.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Spacecraft Maneuvers