TY - GEN
T1 - Mars entry guidance and navigation analysis using linear covariance techniques for the safe and precise landing – integrated capabilities evolution (Splice) project
AU - Williams, James W.
AU - Woffinden, David C.
AU - Putnam, Zachary R.
N1 - Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - Flight performance of a Mars entry, descent, and landing system depends on the complex interaction between the guidance, navigation, and control system, mission concept of operations, trajectory design, vehicle configuration, actuators, disturbance accelerations and torques, environment modeling and atmospheric uncertainty, and top-level mission constraints. Consequently, analyzing a closed-loop, six degree-of-freedom guidance, navigation, and control system for atmospheric entry and powered descent and landing has traditionally required Monte Carlo analysis which generally implies extensive computational resources. This paper employs a previously derived linear covariance analysis formulation to quickly and reliably evaluate the guidance and navigation performance for a notional Mars entry, descent, and landing system to demonstrate precision landing. The analysis includes navigation performance, trajectory dispersions, propellant usage, and sensitivity analysis. A preliminary comparison between the linear covariance analysis and Monte Carlo results is provided. Results indicate good agreement between the linear covariance and Monte Carlo techniques.
AB - Flight performance of a Mars entry, descent, and landing system depends on the complex interaction between the guidance, navigation, and control system, mission concept of operations, trajectory design, vehicle configuration, actuators, disturbance accelerations and torques, environment modeling and atmospheric uncertainty, and top-level mission constraints. Consequently, analyzing a closed-loop, six degree-of-freedom guidance, navigation, and control system for atmospheric entry and powered descent and landing has traditionally required Monte Carlo analysis which generally implies extensive computational resources. This paper employs a previously derived linear covariance analysis formulation to quickly and reliably evaluate the guidance and navigation performance for a notional Mars entry, descent, and landing system to demonstrate precision landing. The analysis includes navigation performance, trajectory dispersions, propellant usage, and sensitivity analysis. A preliminary comparison between the linear covariance analysis and Monte Carlo results is provided. Results indicate good agreement between the linear covariance and Monte Carlo techniques.
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U2 - 10.2514/6.2020-0597
DO - 10.2514/6.2020-0597
M3 - Conference contribution
AN - SCOPUS:85091904706
SN - 9781624105951
T3 - AIAA Scitech 2020 Forum
SP - 1
EP - 19
BT - AIAA Scitech 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2020
Y2 - 6 January 2020 through 10 January 2020
ER -