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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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This paper describes the considerations that led to the selection of the three battery systems on MER and the outlines the designs of these batteries.
In mid 2003, NASA will launch identical spacecraft to deliver two large rovers to the Martian surface. As with the successful Mars Pathfinder (MPF) mission, the MER spacecraft will use an airbag landing system to safely deliver its payload.
The Science Activity Planner (SAP), currently under development by our group at the Jet Propulsion Laboratory, will be the primary tool used for science data assessment and science activity planning during the Mars Exploration Rover (MER) mission.
The Mars Exploration Rover (MER) project, will conduct fundamentally new observations of Mars geology, including the first micro-scale study of rock samples, as well as a detailed study of surface environments for the purpose of calibrating and validating orbital remote sensing data.
This paper presents the methodology used in the launch and space vehicle portion of the nuclear risk assessment for the two Mars Exploration Rover (MER) missions, which includes the assessment of accident scenarios and associated probabilities.
The Mars Exploration Rover (MER) mission will send two 185 kg rovers to Mars in 2003 to continue the scientific community's search for evidence of past water on Mars. These twin robotic vehicles will carry harmonic drives and their performance will be characterized at various temperatures, speeds and loads.
This paper presents the experimental results of the Mars Exploration Rover-03 (MER) radar altimeter antennas-airbag interaction.
This paper describes the selection criteria, design and performance of three battery systems on 2003 MER mission.
NASA requires lightweight rechargeable batteries for future missions to Mars and the outer planets that are capable of operating over a wide range of temperatures, with high specific energy and energy densities. Due to their attractive performance characteristics, lithium-ion batteries have been identified as the battery chemistry of choice for a number of future applications, including planetary orbiters, rovers and landers. For example, under the Mars Surveyor Program MSP 01 lithium-ion batteries were developed by Lithion (each being 28 V, 25 Ah, 8-cells. and 9 kg) and fully qualified prior to mission cancellation. In addition to the requirement of being able to supply at least 90 cycles on the surface of Mars, the battery demonstrated operational capability (both charge and discharge) over a large temperature range (-2O'C to +4OoC), with tolerance to non-operational excursions to -30nd 50Currently, JPL is implementing lithium-ion technology on the 2003 Mars Exploration Rover (MER), which will be coupled with a solar array. This mission has similar performance requirements to that of the 2001 Lander in that high energy density and a wide operating temperature range are necessitated. In addition to planetary rover and lander applications, we are also engaged in determining the viability of using lithium-ion technology for orbiter applications that require exceptionally long life (>20,000 cydes at partial depth of discharge). To assess the viabili of lithium-ion cells for these applications, a number of performance characterization tests have been performed (at the cell and battery level) on state-of-art prototype lihium- ion cells, induding: assessing the cycle life performance (at varying DODs), life characteristics at extreme temperatures (< -10nd >+4OoC), rate capability as a function of temperature (-30' to 4OoC), pulse capability, self-discharge and storage characteristics, as well as, mission profile capability. This paper will describe the current and future NASA missions that are considering lithium ion batteries and will contain results of the cell testing conducted to-date to validate the technology for these missions.
The European Center for Medium-Range Weather Forecasts (ECMWF) and Institut Francais Pour la Recherche et 1'Exploitation de la Mer (IFREMER) European Remote-Sensing Satellite (ERS-1), named IFR2, surface wind velocity data products are compared during July 1995 over the Arabian Sea.
The Mars Exploration Rovers (MER)Flight Software (FSW) was designed from the outset to be modified during operations. This paper discusses the content of the uplink products that are sent to the Rover, the planning of the Patch and Load activities, the testing of the products and prcedures, and the actual operations themselves.
The paper describes the innovative numerical algorithms and the command sequence simulation used by the MER mission for planning surface operations.
The Mars Exploration Rover (MER) program successfully landed two rovers, named 'Spirit' and 'Opportunity', on the surface of Mars in January 2004.
The unparalleled success of the Mars Exploration Rovers (MER) powered by GaInP/GaAs/Ge triple-junction solar cells has demonstrated a lifetime for the rovers that exceeded the baseline mission duration by more than a factor of five.
The Mars Exploration Rovers (MER'03), Spirit and Opportunity, represent the state of the art in rover operations on Mars. This paper presents validation experiments of different visual tracking algorithms using the rover's navigation camera.
The Mars Exploration Rovers (MER), were launched in June and July of 2003, repsectively and successfully landed on Mars in early and late January of 2004, repectively. The flight system architecture implemented many successful features of the Mars Pathfinder (MPF) system: A cruise stage that transported an entry vehicle that housed the Lander, which in turn, used airbags to cushion the Rover during the landing event.
Robotic missions to planetary surfaces are becoming more ambitious and of longer duration. The nominal mission timeline for the MER called Spirit currently on the Martian surface is 90 days, with extensions to 180 days depending on rover health. The upcoming 2009 MSL mission is planned to be 300-500 days and will possibly involve traverses on the order of a kilometer or more.
This paper describes the innovative numerical algorithm and the command sequence simulation of the MER mission for surface operations.