Mars exploration rover parachute decelerator system program overview

17th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar

Volumn , Issue , 2003, Pages

  Witkowski, Allen ^a   Bruno, Robin ^b  

^a Pioneer Aerospace Corporation   (United States)

^b CALIFORNIA INSTITUTE OF TECHNOLOGY   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

EID: 84883087273     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (11)

1. The Mars Exploration Rovers Entry, Descent, and Landing Phase and the Use of Aerodynamic Decelerators, Steltzner et al, AIAA-2003-2125
2. Opportunities and Limitations in Low-Earth Subsonic Testing and Qualification of Extraterrestrial Supersonic Parachute Designs, Steltzner et al, AIAA-2003-2135
3. Mars Exploration Rovers Airbag Landing System Design and Development, Steltzner et al, AIAA- 2003-2136
4. Mars Exploration Rover Mortar Deployer Development, Vasas, Ray, Pioneer Aerospace Corporation, Styner, James, General Dynamics Ordnance and Tactical Systems, AIAA-2003-2137
5. Flight Reconstruction of the Mars Pathfinder Disk-Gap-Band Parachute Drag Coefficient, Desai et al, AIAA-2003-2126
6. A Summary of Dynamic Testing of the Mars Exploration Rover Parachute Decelerator System, Taeger, Yaro, Witkowski, Allen, Pioneer Aerospace Corporation, AIAA-2003-2127
7. Wind Tunnel Testing of Various Disk-Gap-Band Parachutes, Cruz et al, NASA Langley Research Center, AIAA-2003-2129
8. System Design Overview of the Mars Pathfinder Parachute Decelerator Subsystem, Fallon, Edward, Pioneer Aerospace Corporation, AIAA-97-1511
9. Opening Loads Analysis for Various Disk-Gap- Band Parachutes, Cruz, Juan, NASA Langley Research Center, Kandis, Michael, Pioneer Aerospace Corporation, AIAA-2003-2131
10. Design and Analysis of the Drop Test Vehicle for the Mars Exploration Rover Parachute Structural Tests, Way et al, NASA Langley Research Center, AIAA-2003-2128
11. Structural Testing of Parachutes in the National Full-Scale Aerodynamics Complex 80 by 120 foot Wind Tunnel at NASA Ames, Zell et al, AIAA- 2003-2130.