Primary science orbit design for the Mars Reconnaissance Orbiter mission
This paper addresses the constraints, analysis and design evolution of the Mars Reconnaissance Orbiter Primary Science Orbit.
mission↗
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Radio science experiments - The Viking Mars Orbiter and Lander.
The objective of the radio science investigations is to extract the maximum scientific information from the data provided by the radio and radar systems on the Viking Orbiters and Landers. Unique features of the Viking missions include tracking of the landers on the surface of Mars, dual-frequency S- and X-band tracking data from the orbiters, lander-to-orbiter communications system data, and lander radar data, all of which provide sources of information for a number of scientific investigations. Post-flight analyses will provide both new and improved scientific information on physical and surface properties of Mars, on atmospheric and ionospheric properties of Mars, and on solar system properties.
Michael, W. H., Jr.↗
Mars Reconnaissance Orbiter : atmospheric science objectives
Explore the source record for details and available documents.
atmospheric science↗
Mars Reconnaissance Orbiter operations: science planning on NASA's silent workhorse
UNKNOWN
Mihaly, Shannon↗
Mars Reconnaissance Orbiter Navigation Strategy for Mars Science Laboratory Entry, Descent and Landing Telecommunication Relay Support
The Mars Reconnaissance Orbiter (MRO) is an orbiting asset that performs remote sensing observations in order to characterize the surface, subsurface and atmosphere of Mars. To support upcoming NASA Mars Exploration Program Office objectives, MRO will be used as a relay communication link for the Mars Science Laboratory (MSL) mission during the MSL Entry, Descent and Landing sequence. To do so, MRO Navigation must synchronize the MRO Primary Science Orbit (PSO) with a set of target conditions requested by the MSL Navigation Team; this may be accomplished via propulsive maneuvers. This paper describes the MRO Navigation strategy for and operational performance of MSL EDL relay telecommunication support.
Mars Reconnaissance Orbiter (MRO)↗
Orbit Determination and Navigation Software Testing for the Mars Reconnaissance Orbiter
During the extended science phase of the Mars Reconnaissance Orbiter's lifecycle, the operational duties pertaining to navigation primarily involve orbit determination. The orbit determination process utilizes radiometric tracking data and is used for the prediction and reconstruction of MRO's trajectories. Predictions are done twice per week for ephemeris updates on-board the spacecraft and for planning purposes. Orbit Trim Maneuvers (OTM-s) are also designed using the predicted trajectory. Reconstructions, which incorporate a batch estimator, provide precise information about the spacecraft state to be synchronized with scientific measurements. These tasks were conducted regularly to validate the results obtained by the MRO Navigation Team. Additionally, the team is in the process of converting to newer versions of the navigation software and operating system. The capability to model multiple densities in the Martian atmosphere is also being implemented. However, testing outputs among these different configurations was necessary to ensure compliance to a satisfactory degree.
Deep Space Network↗
Mars Reconnaissance Orbiter Navigation Strategy for Mars Science Laboratory Entry, Descent and Landing Telecommunication Relay Support
No abstract available
Entry, Descent and Landing↗
Design Considerations for Aerocapture Delivery of Uranus Orbiter and Probe
This paper presents an aerocapture system design for delivering the Uranus Orbiter and Probe (UOP) subsystems to their science orbit using the Mars Science Laboratory architecture. A packaging and integration scheme are presented for UOP subsystems, with careful consideration of large components required for outer planet science missions (RTG power generation, RF communications). The implication of packaging multiple RTG’s inside an aeroshell during a multiple year cruise phase will be explained, with possible thermal design solutions to mitigate RTG waste heat analyzed. Mass properties and margins for the system are discussed and an overall mass risk assessment is presented for the entry system and total flight system at launch. Alternative vehicle configurations are explored to include multiple probes and enable science objectives during transit to Uranus. Aerocapture mass savings when compared to the baseline UOP design are presented.
Andrew J. Gomez-Delrio↗
Design Considerations for Aerocapture Delivery of Uranus Orbiter and Probe
This paper presents an aerocapture system design for delivering the Uranus Orbiter and Probe (UOP) subsystems to their science orbit using the Mars Science Laboratory architecture. A packaging and integration scheme are presented for UOP subsystems, with careful consideration of large components required for outer planet science missions (RTG power generation, RF communications). The implication of packaging multiple RTG’s inside an aeroshell during a multiple year cruise phase will be explained, with possible thermal design solutions to mitigate RTG waste heat analyzed. Mass properties and margins for the system are discussed and an overall mass risk assessment is presented for the entry system and total flight system at launch. Alternative vehicle configurations are explored to include multiple probes and enable science objectives during transit to Uranus. Aerocapture mass savings when compared to the baseline UOP design are presented.
Aerocapture↗
Science Planning for the NASA Mars Reconnaissance Orbiter Mission
The Mars Reconnaissance Orbiter (MRO), launched on August 12, 2005, carries six science instruments, each with unique requirements for repetitive global monitoring, regional or global survey mapping, and/or targeted observations of Mars. Some prefer nadir-only observations, while other instruments require many off-nadir observations (especially for stereo viewing). Because the operations requirements are often incompatible, an interactive science planning process has been developed. This process is more complex than in some recent NASA Mars missions, but less complex (and more repetitive) than processes used by many large planetary missions. It takes full advantage of MRO's novel onboard processing capabilities, and uses simple electronic interactions between geographically distributed teams. This paper describes the process used during MRO's Primary Science Phase (PSP) to plan both interactive and non-interactive observations of Mars, and what has already been learned in the tests and rehearsals preparing for PSP.
planning↗
The Removal of Periodic Gravitational Perturbations from Mars Global Surveyor's Science Phasing Orbits Applied to the Study of the Martian Exosphere
The martian exosphere and upper atmosphere exert measurable drag on the Mars Global Surveyor (MGS) spacecraft. Using the Goddard Space Flight Center's GEODYN orbit determination software, the science phasing orbits (SPO) were analyzed to determine the atmospheric drag and hence, measure the average density near the orbits' perifocus (170-180 km altitude above high northern latitudes). Future work will include the gravity calibration and mapping periods as well. Additional information is contained in the original extended abstract.
Tracadas, P. W.↗
HiRISE: The High Resolution Imaging Science Experiment for Mars Reconnaissance Orbiter
HiRISE, an experiment on the 2005 MRO mission, will provide an unprecedented combination of ground sampling dimension (25-50 cm/pixel), signal-to-noise ratio (greater than 100:1 at all latitudes), swath width (5-10 km), partial 3-color coverage, greater than 2% coverage of Mars at 1 m/pixel or better, and stereo imaging. Additional information is contained in the original extended abstract.
McEwen, A. S.↗
Aerocapture Trajectories for Earth Orbit Technology Demonstration and Orbiter Science Missions at Venus, Mars and Neptune
No abstract provided
Jadusingh, Matt↗
Low-cost, focused-science Mars mission
The Mars Orbiter Water Mission (MOWM) is discussed as an example of a low-cost, low-risk focused-science Mars mission which might be implemented in the near term within recently imposed fiscal constraints. MOWM is designed to act as a follow-on to the Viking results in the areas of comparative climatology and water, carbon dioxide and dust inventories. The STS-compatible space vehicle would be based on proven earth-orbiting satellite hardware, fulfilling requirements for both spinning and despun components, operation with nonoptimum solar cell orientation, PAM-A upper stage compatibility, and data storage for delayed transmission. Study results have shown the technical and economic feasibility of missions based on any of four submitted designs which meet these requirements, and of low-cost, well-focused science objective Mars missions in general.
Stuart, J. R.↗
Navigation Using Deep-Space Optical Communication Systems
This work investigates the deep-space spacecraft navigation performance achievable from tracking data types obtained using optical communication systems. These optical navigation types include ranging between spacecraft and a station on Earth and astrometric measurements of angular position. Two mission scenarios are analyzed: an interplanetary cruise trajectory for a Mars lander (Mars 2020), and a science orbit for a Mars orbiter (MAVEN). Various data types are simulated using comprehensive measurement models, tracking schedules, and geometrical constraints. Sensitivity analyses are performed to assess the effect of various contributors to measurement accuracy and navigation performance. For both of the mission scenarios studied, the optical navigation types yield equivalent or improved performance as compared to traditional radiometric observables, though radiometric data types slightly outperform optical observables during tracking data gaps in the science orbit scenario.
McCandless, Sarah Elizabeth↗
Aerocapture Trajectories for Earth Orbit Technology Demonstration and Orbiter Science Missions at Venus, Earth, Mars, and Neptune
The use of aerocapture to provide the delta-V needed to capture a spacecraft into orbit can provide significant fuel savings compared to a propulsive orbit insertion. The aerocapture guidance method described in this paper uses drag modulation, which deploys a drag skirt in the atmosphere until the amount of delta-V needed to capture into the desired orbit is obtained, at which time the drag skirt is separated from the spacecraft. By modulating the time of drag skirt jettison, the vehicle can target a specific orbit apoapsis in the presence of uncertainties such as entry targeting errors and unknown atmospheric conditions.
Jadusingh, Matt↗
Mars Reconnaissance Orbiter: Ka Band Radio Science Experiments and the Effect of the Troposphere
This viewgraph presentation reviews the possibilities of utilizing the telecommunication links between spacecraft and Earth to examine changes in the phase/frequency, amplitude, and polarization of radio signals to investigate, specifically for the Mars Reconnaissance Orbiter (MRO)mission utilizes X-band coherent (uplink and downlink) carrier Doppler and range for its gravity investigation Gravity team will also take advantage of Ka-band downlink signal Tropospheric calibration data from Advanced Water Vapor Radiometer (AWVR) will be used. The calibration of the received Ka band signal for the effect of the troposphere is discussed.
Ka-band↗