The terminal phase of an unmanned Mars soft lander is defined as that portion of the descent trajectory bridging the gap between the high speed entry trajectory and the very low speed soft landing. This paper presents the results of a parametric analysis comparing the performance and capability of several candidate deceleration systems considered for use during the terminal phase. System comparison is made on the basis of total decelerator system weight requirements and system capability to cope with the mission uncertainties. The mission mode is entry from orbit.
Two general types of terminal phase decelerator systems are analyzed; aerodynamic and allretro systems. The aerodynamic decelerators considered include both subsonic type parachutes and (supersonic) ballutes. Subsonic type parachutes are limited to a maximum deployment Mach No. of 1.6. Supersonic ballutes are assumed deployed at Mach Nos. from 3.0 to 5.0. Both groups use a propulsive retro vernier system for final deceleration and landing. The all-retro system analysis assumes a rocket propulsion system with two phases - initial braking followed by a vertical descent
