Accession Number : ADA267498


Title :   A Guidance and Navigation System for Two Spacecraft Rendezvous in Translunar Halo Orbit


Descriptive Note : Doctoral thesis


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH


Personal Author(s) : Jones, Brian L


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a267498.pdf


Report Date : May 1993


Pagination or Media Count : 204


Abstract : This research considers the design of a representative end-to-end guidance and navigation system for the terminal phase rendezvous of two spacecraft in the circular restricted three-body problem. It assumes the target vehicle is in a small radius translunar halo orbit; the target vehicle remains passive with respect to the rendezvous profile. The chaser vehicle is in an independent small radius translunar halo orbit and executes all rendezvous maneuvers. First, the halo orbit guidance problem is formulated in the frequency-domain from which an output feedback guidance law is developed using H2 control theory. Linear simulation results validate the guidance law and provide data which quantify the effect of control inputs, noise characteristics and halo orbit characteristics on the steady state halo orbit station-keeping costs. Secondly, a two spacecraft terminal phase rendezvous targeting law is derived; nonlinear simulation results validate the targeting law


Descriptors :   *N BODY PROBLEM , *RENDEZVOUS GUIDANCE , NAVIGATION , RENDEZVOUS SPACECRAFT , THESES


Subject Categories : Celestial Mechanics
      Navigation and Guidance
      Spacecraft Trajectories and Reentry


Distribution Statement : APPROVED FOR PUBLIC RELEASE