VARIABLE POINT GUIDANCE AND TARGETING. VOLUME I. PART 1. BASIC PRINCIPLES AND RESULTS
Abstract
The primary objective of the development of the Variable Point Guidance and Targeting Technique is to devise a quick reaction guidance and targeting system for space vehicles which does not limit the intrinsic propulsion capability of the booster and upper stages in applications involving arbitrary rendezvous missions. Logic and equations for such a system which operate in real time and which fit a modern aerospace computer have been developed and simulated. The system is provided with the ability of accepting a revised target ephemeris or the ephemeris of a completely new target after lift- off, giving the operational flexibility which permits in-flight changing of mission objectives at any time. The purpose of the present work has been (1) to improve the efficiency and effectiveness of the techniques, (2) to verify the modifications by a detailed simulation containing a representation of a typical booster and upper-stage configuration, (3) document the complete program and (4) to code an aerospace computer to the extent that an accurate sizing and timing estimate can be made. The program was exercised by complete simulation of twelve rendezvous missions against four widely different target situations. An evaluation of the results of the rendezvous simulation studies indicates that the efficiency, effectiveness and general applicability of the computer program was improved and extended so that any satellite rendezvous mission that is within the potential capability of the booster and its associated hardware can successfully be initiated and completed by the insertion of the target ephemeris.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 28, 1967
- Accession Number
- AD0817471
Entities
People
- A. Baker
- E. E. Hammond
- E. P. Wallner
- E. W. Devecka
- Edward B. Capen
- J. W. Stosick
- Joseph J. Camiel
- Ruth J. Mcnaughton
- T. G. O'brien
- V. K. Brenton