A Guidance and Navigation System for Two Spacecraft Rendezvous in Translunar Halo Orbit
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
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1993
- Accession Number
- ADA267498
Entities
People
- Brian L. Jones
Organizations
- Air Force Institute of Technology