This paper analyzes the potential second stage guidance strategies and ignition triggers for the Mars Ascent Vehicle (MAV) that can improve the orbit insertion accuracy, increase the payload capacity, and reduce the fuel cost. Three guidance laws are analyzed in this work – (i) Q-guidance (NASA's current choice), (ii) Local Vertical Local Horizontal (LVLH)- guidance (a variant of the Powered Explicit Guidance), and (iii) Second Order Cone Program (SOCP)-guidance. The proposed SOCP-guidance law is computational and based on the developments in the field of lossless convexification. The paper evaluates and compares the performance of the above guidance schemes together with the appropriate ignition triggers in both nominal and Monte Carlo settings.
Analytic and Computational Guidance Strategies for the Second-Stage Mars Ascent Vehicle
05.03.2022
2139166 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Guidance Concept for a Mars Ascent Vehicle First Stage
NTIS | 2000
|Guidance Concept for a Mars Ascent Vehicle First Stage
NTRS | 2000
|