Flight Path Control Strategies for the 2003 Mars Exploration Rover (MER) Mission

Raofi, Behzad; Bhat, R. S.; D’Amario, Louis A.

doi:10.2514/6.2002-4824

Cited by 8 publications

(2 citation statements)

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“…First, the direct entry (DE) has been used for placing landers and rovers on the surface of Mars, such as the Mars Pathfinder (Spencer et. al., 1999) and both Mars Exploration Rovers (Raofi et. al., 2002).…”

Section: Aerobraking Maneuversmentioning

confidence: 98%

Regenerative Aerobraking

Moses¹

2005

AIP Conference Proceedings

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NASA's exploration goals for Mars and Beyond will require new power systems and in situ resource utilization technologies. Regenerative aerobraking may offer a revolutionary approach for in situ power generation and oxygen harvesting during these exploration missions. In theory, power and oxygen can be collected during aerobraking and stored for later use in orbit or on the planet. This technology would capture energy and oxygen from the plasma field that occurs naturally during hypersonic entry using well understood principles of magnetohydrodynamics and oxygen filtration. This innovative approach generates resources upon arrival at the operational site, and thus greatly differs from the traditional approach of taking everything you need with you from Earth. Fundamental analysis, computational fluid dynamics, and some testing of experimental hardware have established the basic feasibility of generating power during a Mars entry. Oxygen filtration at conditions consistent with spacecraft entry parameters at Mars has been studied to a lesser extent. Other uses of the MHD power are presented. This paper illustrates how some features of regenerative aerobraking may be applied to support human and robotic missions at Mars.

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Section: Aerobraking Maneuversmentioning

confidence: 98%

Regenerative Aerobraking

Moses¹

2005

AIP Conference Proceedings

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“…A separate MCS was performed to estimate the total ideal TCM1 ∆V due to all the uncertainties. 20 The PDF for TCM1 ∆V is plotted in Fig. 8.…”

Section: Trajectorymentioning

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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Review and prospect of guidance and control for Mars atmospheric entry

Jiang

2014

Progress in Aerospace Sciences

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Flight Path Control Strategies for the 2003 Mars Exploration Rover (MER) Mission

Cited by 8 publications

References 1 publication

Regenerative Aerobraking

Regenerative Aerobraking

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

Review and prospect of guidance and control for Mars atmospheric entry

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