Mission Design Overview for the Mars Exploration Rover Mission

Roncoli, Ralph B.; Ludwinski, J.

doi:10.2514/6.2002-4823

Cited by 31 publications

(12 citation statements)

References 2 publications

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“…Unfortunately, due to the fundamentally different configuration of the rover having all the "smarts", as opposed to all the "smarts" on the lander electronics module for Pathfinder, the MER design had significant changes. 12 These changes resulted in additional uncertainty to mitigate in the design of MER.…”

Section: A Mer Missionmentioning

confidence: 99%

Balancing Cost, Risk, and Performance Under Uncertainty in Preliminary Mission Design

Thunnissen

2004

Space 2004 Conference and Exhibit

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A method for propagating and mitigating uncertainty in conceptual-level space mission design is described. The method presented forms a normative method for decision makers seeking to balance cost, risk, and performance in preliminary mission design, with an emphasis on launch vehicle selection. Models representing each of these parameters are created. The variables of the models are then classified. Probabilistic methods, Bayesian techniques, and numerical simulation are used to characterize the resulting parameters. Lastly, results of this analysis are combined with the risk tolerance of the decision maker to guide in balancing these parameters. As an example application, the investigated method is applied to two mission scenarios. The first mission scenario investigates the uncertainty in mission success for the Mars Exploration Rover (MER) mission where the launch vehicle has been selected a priori. The second mission scenario investigates balancing the set of parameters for a generic sun-synchronous low-earth orbit satellite when two possible launch vehicles are available. Use of this approach with the first example yields a surprisingly high level of risk to the mission. Use of the approach for the second example provides quantitative results in estimating the launch cost and risk of the two different options. NomenclatureC cost, fiscal year 2004 dollars in millions (M) (FY2004$M) c exhaust velocity, m/s G(p) geometric distribution with parameter p L(µ,σ) lognormal distribution with parameters µ and σ m mass, kg N(µ,σ) normal distribution with parameters µ and σ P probability of success p variate for a geometric distribution t length of launch operations, days U(min,max) uniform distribution with parameters min and max ∆V change in velocity, m/s κ recurring cost per day of launch operations, fiscal year 2004 dollars in thousands (K) per day (FY2004$K/day) µ mean σ standard deviation subscripts: ach achievable inj injection ld launch date lv launch vehicle other_TCMs other trajectory correction maneuvers prop usable propellant loaded into spacecraft propulsion system prop_ACS usable propellant reserved for attitude control sc_wet spacecraft wet

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Section: A Mer Missionmentioning

confidence: 99%

Balancing Cost, Risk, and Performance Under Uncertainty in Preliminary Mission Design

Thunnissen

2004

Space 2004 Conference and Exhibit

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“…During the interplanetary transfer from Earth to Mars, MER was a spin-stabilized spacecraft with a nominal spin rate of 2 rpm and the cruise stage provided most of the traditional spacecraft subsystem functionality, such as propulsion, power, communications, thermal, and attitude control. 17 Roncoli and Ludwinski 17 discuss the MER mission in detail. The MER cruise stage used two clusters of four 4.5 N Aerojet MR-111C engines (thrusters), one on each side as shown in Fig.…”

Section: A Mars Exploration Rover Spacecraftmentioning

confidence: 99%

Uncertainty Quantification in Conceptual Design via an Advanced Monte Carlo Method

Thunnissen¹,

Swenka

2007

Journal of Aerospace Computing, Information, and Communication

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A method for quantifying uncertainty in conceptual-level design via a computationallyefficient probabilistic method is described. As an example application, the investigated method is applied to estimating the propellant mass required by a spacecraft to perform attitude control. The variables of the design are first classified and assigned appropriate probability density functions. To characterize the attitude control system a slightly-modified version of Subset Simulation, an efficient simulation technique originally developed for reliability analysis of civil engineering structures, is used. The proposal distribution aspect of Subset Simulation is modified vis-à-vis the original technique to account for the general characteristics of the variables involved in conceptual-level design. The results of Subset Simulation are compared with traditional Monte Carlo simulation. The investigated method allows uncertainty in the propellant required to be quantified based on the risk tolerance of the decision maker. For the attitude control example presented, Subset Simulation successfully replicated Monte Carlo simulation results yet required significantly less computational effort, in particular for risk-averse decision makers. Nomenclaturelognormal random variable with parameters μ and σ m number of Subset Simulation levels N number of Subset Simulation samples N c number of Markov chains developed at each simulation level; N c = p 0 N

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“…Thus, the active Heat Rejection System (HRS), which was designed, used, and worked so well on MPF, was selected for MER. The design of the MPF HRS and its adaptation for MER has been documented elsewhere (Birur et al, 1996;Bhandari & Birur, 19982002, and Ganapathi, el al, 2003.…”

mentioning

confidence: 98%

“…90 sols (approximately 93 Earth days) after landing and to demonstrate a total traverse distance of at least 600 m, with a goal of 1000 m (Roncoli & Ludwinski, 2002).…”

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The Hardware Challenges for the Mars Exploration Rover Heat Rejection System

Tsuyuki¹,

Ganapathi²,

Bame³

et al. 2004

AIP Conference Proceedings

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The primary objective of the Mars Exploration Rover (MER) 2003 Project focused on the search for evidence of water on Mars. The launch of two identical flight systems occurred in June and July of 2003. The roving science vehicles are expected to land on the Martian surface in early and late January of 2004, respectively. The flight system design inherited many successfully features and approaches from the Mars Pathfinder Mission. This included the use of a mechanically-pumped fluid loop, known as the Heat Rejection System (HRS), to transport heat from the Rover to radiators on the Cruise Stage during the quiescent trek to Mars. While the heritage of the HRS was evident, application of this system for MER presented unique and difficult challenges with respect to hardware implementation. We will discuss these hardware challenges in each HRS hardware element: the integrated pump assembly, cruise stage HRS, lander HRS, and Rover HRS. These challenges span the entire development cycle including fabrication, assembly, and test. We will conclude by citing the usefulness of this system during launch operations, where in particular, the flight hardware inside the Rover was thermally conditioned by the HRS since there was no other effective means of maintaining its temperature. MISSION OVERVIEW & SPACECRAFT CONFIGURATIONIn August 2000, with less than three years to launch, NASA formally approved a dual rover mission to Mars. The Project was named the Mars Exploration Rover (MER) Project. The primary mission objectives were to determine the aqueous, climatic, and geologic history of a pair of sites on Mars where the conditions may have been favorable to the preservation of evidence of pre-biotic or biotic processes. The primary missions requirements were to deliver two identical rovers to the surface of Mars in order to conduct geologic and atmospheric investigations for at least FIGURE 1. Flight System Configuration Internally Nests Rover.

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Mission Design Overview for the Mars Exploration Rover Mission

Cited by 31 publications

References 2 publications

Balancing Cost, Risk, and Performance Under Uncertainty in Preliminary Mission Design

Balancing Cost, Risk, and Performance Under Uncertainty in Preliminary Mission Design

Uncertainty Quantification in Conceptual Design via an Advanced Monte Carlo Method

The Hardware Challenges for the Mars Exploration Rover Heat Rejection System

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