Eric Graat

Initial Results of Rover Localization and Topographic Mapping for the 2003 Mars Exploration Rover Mission

This paper presents the initial results of lander and rover localization and topographic mapping of the MER 2003 mission (by Sol 225 for Spirit and Sol 206 for Opportunity). The Spirit rover has traversed a distance of 3.2 km (actual distance traveled instead of odometry) and Opportunity at 1.2 km. We localized the landers in the Gusev Crater and on the Meridiani Planum using two-way Doppler radio positioning technology and cartographic triangulations through landmarks visible in both orbital and ground images. Additional high-resolution orbital images were taken to verify the determined lander positions. Visual odometry and bundleadjustment technologies were applied to overcome wheel slippages, azimuthal angle drift and other navigation errors (as large as 21 percent). We generated timely topographic products including 68 orthophoto maps and 3D Digital Terrain Models, eight horizontal rover traverse maps, vertical traverse profiles up to Sol 214 for Spirit and Sol 62 for

Mars Exploration Rovers orbit determination filter strategy.

§†† ‡‡ §§ §§ , The successful delivery of the Mars Exploration Rover (MER) landers to well within the boundaries of their surface target areas in January of 2004 was the culmination of years of orbit determination analysis. The process began with a careful consideration of the filter parameters used for pre-launch covariance studies, and continued with the refinement of the filter after launch based on operational experience. At the same time, tools were developed to run a plethora of variations around the nominal filter and analyze the results in ways that had never been previously attempted for an interplanetary mission. In addition to achieving sub-kilometer Mars-relative orbit determination knowledge, the filter strategy and process detected unexpected error sources, while at the same time proving robust by indicating the correct solution. Consequently, MER orbit determination set a new standard for interplanetary navigation. Nomenclature

Mars Exploration Rover cruise orbit determination

The Mars Exploration Rover project consisted of two missions (MER-A: spirit rover and MER-B: opportunity rover) that launched spacecraft on June 10, 2003, and July 8, 2003, respectively. The spacecraft arrived at Mars approximately seven months later on January 4, 2004, and January 24, 2004. These spacecraft needed to be precisely navigated to a Mars atmospheric entry flight path angle of -11.5 deg +/-0.12 deg (3(sigma)) for MER-A and +/-0.14 deg (3(sigma)) for MER-B in order to satisfy the landing site delivery requirements. The orbit determination task of the navigation team needed to accurately determine the trajectory of the spacecraft, predict the trajectory to Mars atmospheric entry, and account for all possible errors sources so that the each spacecraft could be correctly targeted using five trajectory corrections along the way. This paper describes the orbit determination analysis which allowed MER-A to be targeted using only four trajectory correction maneuvers to an entry flight path angle of -11.49 deg +/-O.010 deg (3(sigma)) and MER-B to be targeted using only three trajectory correction maneuvers to an entry flight path angle of -11.47 +/-0.021 deg(3(sigma)).

Mars Exploration Rovers entry, descent, and landing navigation.

During the final approach and Entry, Descent and Landing (EDL) of both Mars Exploration Rovers (MER), one-way Doppler were monitored to detect, in real-time, the following events.

Orbit Determination for the 2007 Mars Phoenix Lander

The Phoenix mission is designed to study the arctic region of Mars. To achieve this goal, the spacecraft must be delivered to a narrow corridor at the top of the Martian atmosphere, which is approximately 20 km wide. This paper will discuss the details of the Phoenix orbit determination process and the effort to reduce errors below the level necessary to achieve successful atmospheric entry at Mars. Emphasis will be placed on properly modeling forces that perturb the spacecraft trajectory and the errors and uncertainties associated with those forces. Orbit determination covariance analysis strongly influenced mission operations scenarios, which were chosen to minimize errors and associated uncertainties.

Navigating Mars Reconnaissance Orbiter: Launch Through Primary Science Orbit

The Mars Reconnaissance Orbiter (MRO) launched on 12 August 2005 from Space Launch Complex 41 at Cape Canaveral Air Force Station. After seven months of cruise, MRO reached Mars and successfully performed the Mars Orbit Insertion (MOI) maneuver. Only two Trajectory Correction Maneuvers were required during interplanetary cruise, this achievement is unprecedented. Shortly after the arrival at Mars, MRO started its most intensive operation, aerobraking, which brought the post-MOI 35-hour orbit to a 2-hour near circular orbit. The final primary science orbit was established at 3:02 pm LMST in a 255km x 320km orbit after five orbit-adjust maneuvers were executed flawlessly during the transition phase. This paper describes the navigation operation from launch through the primary science phase. A robust and precise navigation enabled MRO to accomplish the objectives set by the Mars Exploration Program.

Mars Reconnaissance Orbiter Aerobraking Navigation Operation

After a seven-month interplanetary cruise, the Mars Reconnaissance Orbiter arrived at Mars and executed a 1.0 km/s Mars Orbit Insertion (MOI) maneuver. The post-MOI orbit was highly elliptical with a 35 hour, 428km x 45000km altitude orbit. To establish a useful science orbit, the navigation team used an aerobraking technique to guide the spacecraft into a 2-hour, 255km x 320 km altitude orbit. This paper details the aerobraking navigation operation strategy and flight results. It also describes the aerobraking key requirements and navigation challenges.

Mars Reconnaissance Orbiter navigation during the primary science phase

The Mars Reconnaissance Orbiter began science operations in November 2006, with a suite of seven instruments and investigations, some of which required navigation accuracies much better than previous Mars missions. This paper describes the driving performance requirements levied on Navigation and how well those requirements have been met thus far. Trending analyses that have a direct impact on the Navigation performance, such as atmospheric bias determination, are covered in detail, as well as dynamic models, estimation strategy, tracking data reduction techniques, and residual noise.