Accession Number:

ADA170896

Title:

A Method for Governing Spacecraft Evasive Maneuvering.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1986-06-01

Pagination or Media Count:

251.0

Abstract:

In this paper, I will describe research I conducted to develop a method for governing spacecraft evasive maneuvering through a computer program incorporating many of the techniques of astrodynamics. Because of the critical time constraints prevailing in a typical intercept scenario, a means of providing information top the spacecraft concerning the predicted position of the missile and the transfer time-to-intercept is required. I intend to show that the methods of astrodynamics can provide the timely, accurate information needed by the spacecraft to predict intercept and calculate velocity-to-be-gained requirements to achieve a miss-distance of a desired magnitude and direction at the predicted intercept time. These calculations will be based on two vector position fixes of the missile over time, which could be obtained from an infrared detector and a laser-rangefinder, and the position and velocity vectors of the spacecraft, as could be obtained from on-board guidance and navigation instruments.

Subject Categories:

  • Spacecraft Trajectories and Reentry

Distribution Statement:

APPROVED FOR PUBLIC RELEASE