Terminal rendezvous analysis and design for the mars 2003/2005 sample return mission

摘要

This paper describes the mission design and analysis for the terminal rendezvous of the proposed mars 2003/2005 Sample Return Mission in which a Mars Sample Return orbiter is to rendezvous with an Orbiting Sample (OS) canister. Two different terminal rendezvous phase strategies are described. The first is an appproach along the OS velocity vector (V-bar), from ahead of the OS, with stationkeeping at key standoff points of 2 km, 180 m, 18 m and 3 m from the OS. A Lambert transfer from the 2 km point to the 180 m standoff point is followed by a sequence of slow closing maneuvers to effect capture. The second approach is a coelliptic strategy in which the orbiter approaches the OS from an orbit below and behind such that the first coelliptic orbit is, for example, 400 km behind and 2 km below that of the OS and the second is 200 m below. At a range of 400 m on the second coelliptic orbit, the orbiter performs a maneuver to transfer to the V-bar 80 m ahead of the OS. The terminal rendezvous sensor suite consisting of an IMU, a Radio Direction Finder 9RDF), and a LIDAR is described. The guidance and navigation subsystems associated with the terminal rendezvous phase are presented. Monte Carlo results for the first approach are presented along with preliminary resutls for the second approach.