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Integrated Precision Landing Performance and Technology Assessments of a Human-Scale Mars Lander Using a Generalized Simulation Framework
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InSight – Robotics Instrument Deployment System Surface Operations for the InSight Mars Lander
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Soft lander, part 3 - Mars soft lander capsule study /entry from orbit/ - Parametric studies continued
Parametric studies for Mars soft lander capsule for 1973 launching, capsule parametric analysis, and Mars environment effects
Soft lander, part 2 - Mars soft lander capsule study /entry from orbit/ - Introduction and parametric studies
Mission and systems parametric studies for Mars soft lander to define entry and landing capsule suitable for Mars probe in 1970 time period
Soft lander, part 1 - Mars soft lander capsule study /entry from orbit/ - Summary
Selection of capsule for 1973 launching of Mars soft lander mission
Soft lander, part 4 - Mars soft lander capsule study /entry from orbit/ - Conceptual design 1
Conceptual design 1 for capsule for Mars soft lander for 1973 launching
Soft lander, part 5 - Mars soft lander capsule study /entry from orbit/ - Conceptual design 2
Conceptual design 2 for capsule for Mars soft lander for 1973 launching
Soft lander, part 7 - Mars soft lander capsule study /entry from orbit/ - Conceptual design 5
Conceptual design 5 for capsule for Mars soft lander for 1973 launching
Soft lander. Part 9 - Mars soft lander capsule study /entry from orbit/ analysis of inflatable landing systems
Analysis of inflatable landing systems - Mars soft lander capsule study
Soft lander, part 6 - Mars soft lander capsule study /entry from orbit/ - Conceptual design 3 and 4
Conceptual design 3 for capsule for Mars soft lander for 1973 launching
Landing Site Dispersion Analysis and Statistical Assessment for the Mars Phoenix Lander
The Mars Phoenix Lander launched on August 4, 2007 and successfully landed on Mars 10 months later on May 25, 2008. Landing ellipse predicts and hazard maps were key in selecting safe surface targets for Phoenix. Hazard maps were based on terrain slopes, geomorphology maps and automated rock counts of MRO's High Resolution Imaging Science Experiment (HiRISE) images. The expected landing dispersion which led to the selection of Phoenix's surface target is discussed as well as the actual landing dispersion predicts determined during operations in the weeks, days, and hours before landing. A statistical assessment of these dispersions is performed, comparing the actual landing-safety probabilities to criteria levied by the project. Also discussed are applications for this statistical analysis which were used by the Phoenix project. These include using the statistical analysis used to verify the effectiveness of a pre-planned maneuver menu and calculating the probability of future maneuvers.
Entry, Descent, and Landing Operations Analysis for the Mars Phoenix Lander
The Mars Phoenix lander was launched August 4, 2007 and remained in cruise for ten months before landing in the northern plains of Mars in May 2008. The one-month Entry, Descent, and Landing (EDL) operations phase prior to entry consisted of daily analyses, meetings, and decisions necessary to determine if trajectory correction maneuvers and environmental parameter updates to the spacecraft were required. An overview of the Phoenix EDL trajectory simulation and analysis that was performed during the EDL approach and operations phase is described in detail. The evolution of the Monte Carlo statistics and footprint ellipse during the final approach phase is also provided. The EDL operations effort accurately delivered the Phoenix lander to the desired landing region on May 25, 2008.