Trajectory Analysis and Design for Planetary Powered Descent and Orbital Ascent Maneuvers
Date
2019
Authors
Contributor
Advisor
Department
Instructor
Depositor
Speaker
Researcher
Consultant
Interviewer
Narrator
Transcriber
Annotator
Journal Title
Journal ISSN
Volume Title
Publisher
University of Hawaii at Manoa
Volume
Number/Issue
Starting Page
Ending Page
Alternative Title
Abstract
NASA’s past Mars missions such as Mars Pathfinder, the Mars Exploration Rovers and the Mars Science Laboratory projects have led to the necessity of designing the next generation of landers, one of the goals of which is to achieve safe, velocity of less than 1 m/s and precise landing, within 100 m from the designated landing site. Previous studies focused on the formulation of manifolds of initial and final points for atmospheric entry, powered descent and landing. These manifolds can be generated by a construction of envelopes of the maneuver trajectories using a vast range of terminal conditions for the trajectory and lander’s parameters. This paper describes the design, analysis and construction of trajectory envelopes for accurate landing maneuvers. A family of envelopes is generated by varying a vast range of terminal conditions to satisfy the proposed design space based on previous Mars missions. The following phases are considered in the landing maneuvers: exoatmospheric thrust phase, atmospheric transit phase and powered descent and landing phase. The entry velocity components were compared in two cases where the velocity component in the y-direction, vy0 is zero or a nonzero constant with several fixed conditions to analyze the overall profile of the entry trajectory. From case B, where vy0 is a nonzero constant, one of the trajectories achieved a landing altitude of 0.3891 m, velocity of 0.0015 m/s and distance of 88. 02559 m from the designated landing site. Specific parameters are designated to satisfy the proposed design space and achieve accurate landing. The continuity conditions at the junction points have been presented and analyzed to provide smooth and continuous change of these parameters except for the control variables. The proposed design and construction of trajectory envelopes can be used in the mission design analysis for landing missions. This study also proposes rudimentary solutions for lunar descent and ascent maneuvers in anticipation for sample return missions on the Moon.
Description
Keywords
Trajectory optimization, Space vehicles--Landing, Space trajectories
Citation
Extent
Format
Geographic Location
Time Period
Related To
Related To (URI)
Table of Contents
Rights
Rights Holder
Local Contexts
Collections
Email libraryada-l@lists.hawaii.edu if you need this content in ADA-compliant format.