Title :
DSENDS - A high-fidelity dynamics and spacecraft simulator for entry, descent and surface landing
Author :
Balaram, J. ; Austin, R. ; Banerjee, P. ; Bentley, T. ; Henriquez, D. ; Martin, B. ; McMahon, E. ; Sohl, G.
Author_Institution :
Jet Propulsion Lab., California Inst. of Technol., Pasadena, CA, USA
Abstract :
The Jet Propulsion Laboratory (JPL) is developing a high-fidelity spacecraft simulator for entry, descent and landing (EDL) on planetary and small-bodies. This simulator, DSENDS (Dynamics Simulator for Entry, Descent and Surface landing), is an EDL-specific extension of a JPL multi-mission simulation toolkit (Darts/Dshell) which is capable of modeling spacecraft dynamics, devices, and subsystems, and is in use by interplanetary and science-craft missions such as Cassini, Galileo, SIM, and Starlight. DSENDS is currently in use by the JPL Smart Lander project to provide a high-fidelity testbed for the test of precision landing and hazard avoidance functions for future Mars missions. We first briefly describe the core tool capabilities in dynamics, instrument/actuator device models, and real-time simulation engineering. These allow the modeling of the flight-train elements during various phases of EDL and all of the spacecraft responses. We then address the various EDL-specific aspects of the simulator. These include the high-fidelity entry-body and parachute aerodynamic models and supporting atmospheric models.
Keywords :
aerodynamics; aerospace simulation; real-time systems; space vehicles; vehicle dynamics; DSENDS; EDL; Jet Propulsion Laboratory; flight-train elements; hazard avoidance functions; high-fidelity dynamics simulator; multi-mission simulation toolkit; parachute aerodynamic models; real-time simulation engineering; science-craft missions; spacecraft dynamics; spacecraft responses; spacecraft simulator; Actuators; Aerodynamics; Atmospheric modeling; Hazards; Instruments; Laboratories; Mars; Propulsion; Space vehicles; Testing;
Conference_Titel :
Aerospace Conference Proceedings, 2002. IEEE
Print_ISBN :
0-7803-7231-X
DOI :
10.1109/AERO.2002.1035313