CHANDRAYAAN-3 POWER DESCENT 6DOF SIMULATION SOFTWARE

Paper number

IAC-24,A3,IP,106,x89985

Author

Mr. Goruputi Chaitanya, ISRO Satellite Centre (ISAC), India

Coauthor

Mr. Aditya Rallapalli, U R RAO SATELLITE CENTRE (URSC), India

Coauthor

Mr. Suraj Kumar, ISRO Satellite Centre (ISAC), India

Coauthor

Mr. Asish Kumar Mishra, Indian Space Research Organization (ISRO), India

Coauthor

Mrs. Pratibha Srivastava, U R RAO SATELLITE CENTRE (URSC), India

Coauthor

Mr. Saurabh Sharma, U R RAO SATELLITE CENTRE (URSC), India

Coauthor

Mr. G.V.P. Bharat Kumar, Indian Space Research Organization (ISRO), India

Coauthor

Mr. Sudhakar S, U R RAO SATELLITE CENTRE (URSC), India

Year

2024

Abstract

\begin{document}

On 23\textsuperscript{rd} August, 2023 Chandrayaan-3 Vikram Lander
spacecraft soft landed on moon south pole at a pre-determined location
using an autonomous on-board NGC (navigation, guidance and control). To
validate the NGC design, simulate the trajectory, generate the required
pre-flight parameters and to carry out simulations for various perturbed
conditions an indigenous software (Six DOF Software for Chandrayaan-3)
is developed in C++ software language at ISRO, URSC. Software played a
crucial role in success of Chandrayaan-3 by providing statistical
analysis and details of various critical parameters such as landing
error ellipse, touchdown stability parameters, propellant margins,
navigation guidance and control margins, system behaviour under various
failure scenarios and many more. This paper details the 6dof software
architecture for simulating end to end power descent trajectory, MC
(Monte Carlo) test cases, extreme perturbation of trajectory and
spacecraft parameters test cases, contingency test cases, single point
and multi point failure test cases. The 6dof software contains
mathematical modules of NGC algorithm, sensors, engines, thrusters, DEM
(digital elevation module) of Moon surface, dynamics for propagation of
6dof state vector using high fidelity moon gravity module. These modules
are validated using ground test data. The pre-flight simulated reference
trajectory is used for tracking the lander from ground tracking stations
and as reference trajectory in telemetry displays during real time
descent. Post flight trajectory data matched with the simulation results
of the software there by validating the individual modules and the whole
software architecture. This validation is critical to use the software
for the future missions.

Keywords: NGC, 6Dof, MC simulations

\end{document}

Abstract document

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