Mars Rover Sample Return Orbiter design concepts

Randolph, J. E.

doi:10.2514/6.1989-421

Cited by 6 publications

(8 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…It maps the surface of the planet within 39 degrees of the Martian equator for landing site selection and Rover Traverse Planning [6]. A total often 10 x 10 km sites are mapped for selection of the landing site, and an area of 20 x 20 km at that site is further mapped for Rover Traverse planning.…”

Section: Mrsr Objectives and System Elementsmentioning

confidence: 99%

“…Equation (6) shows that in the limit, as b approaches a, the required preload for the hollow beam is only half as large as that for a solid beam (b=0). This principle had been overlooked in Reference [13], but was recognized by Mr. Hamrick during the present study.…”

Section: (1)mentioning

confidence: 99%

“…Thus, the spring design for the baseline RTG consists of three nested springs, with each spring having a thickness T of 0.221", a free height H + T of 0.451", and a compressed height (H + T -Y e ) of 0.275" during Earth launch and (H + T -Y m ) of 0.375" during Mars operations. 6.2.5 Von-Mises and Shear Stresses in Heat Source: The same solids model shown in Figure 19 was used to compute the von Mises stresses in the modules. The maximum was found to occur in Module 1.…”

Section: (1)mentioning

confidence: 99%

See 2 more Smart Citations

Mars Rover RTG Study

Schock¹

1989

View full text Add to dashboard Cite

The paper describes the design and analysis of Radioisotope Thermoelectric Generators (RTGs) for powering the Mars Rover vehicle, which is a critical element of the unmanned Mars Rover and Sample Return mission (MRSR). The RTG design study was conducted by Fairchild Space Company for the U.S. Department of Energy, in support of the Jet Propulsion Laboratory's MRSR project.The paper briefly describes a reference mission scenario, an illustrative Rover design and activity pattern on Mars, and its power system requirements and environmental constraints, including the RTG cooling requirements during transit to Mars. It identifies the key RTG design problem, i.e. venting the helium generated by the fuel's alpha decay without intrusion of the Martian atmosphere into the RTG, and proposes a design approach for solving that problem. Using that approach, it describes and analyzes a variety of RTG designs, at! based on the proven and safety-qualified General Purpose Heat Source module.The first RTG option described is a very conservative baseline design, employing standard thermoelectric unicouples whose reliability and performance stability has been extensively demonstrated on previous space missions. The heat source of the 250-watt RTG consists of a stack of 18 separate modules that is supported at its ends but not along its length. The paper describes and analyzes the structure that holds the stack together during Earth launch and Mars operations, but allows it to come apart in case of an inadvertent reentry.It then summarizes the baseline RTG's mass breakdown, and presents a detailed description of its thermal, thermoelectric, and electrical analyses. It examines the effect of different operating conditions (beginning versus end of mission, water-cooled versus radiation-cooled, summer day versus winter night) on the RTG's performance. Finally, the paper compares the RTGs' specific powers for different power levels (250W versus 125W), different thermoelectric element designs (standard versus short unicouples, versus multicouples) and different thermoelectric figures of merit (0.00058K"The results presented show the RTG performance achievable with current technology, and the performance improvements that would be achievable with various technology developments. It provides a basis for selecting the optimum strategy for meeting the Mars Rover design goals with minimal programmatic risk and cost.

show abstract

Section: Mrsr Objectives and System Elementsmentioning

confidence: 99%

Section: (1)mentioning

confidence: 99%

Section: (1)mentioning

confidence: 99%

See 1 more Smart Citation

Mars Rover RTG Study

Schock¹

1989

View full text Add to dashboard Cite

show abstract

“…It maps the surface of the planet within 39 degrees of the Martian equator for landing site selection and Rover Traverse Planning [6]. A total of ten 10 x 10 km sites are mapped for selection of the landing site, and an area of 20 x 20 km at that site is more finely mapped for Rover Traverse planning.…”

Section: Mrsr Objectives and System Elementsmentioning

confidence: 99%

Mars Rover RTG Study

Schock¹

1989

View full text Add to dashboard Cite

“…The Communication Orbiter will provide the communication link between the Mars surface elements and Earth [5]. It will be launched in November-December 1998 aboard a Titan IV/IUS, and will be placed in a stationary orbit such that the region between 65.7° south and north of the equator is covered continuously.…”

Section: Mrsr Objectives and System Elementsmentioning

confidence: 99%

Mars Rover RTG Study

Schock¹

1989

View full text Add to dashboard Cite

The paper describes the design and analysis of Radioisotope Thermoelectric Generators (RTGs) for powering the Mars Rover vehicle, which is a critical element of the Mars Rover and Sample Return mission (MRSR).The RTG design study was conducted by Fairchild Space Company for the Department of Energy, in support of the Jet Propulsion Laboratory's MRSR project. The paper briefly describes a reference mission scenario, an illustrative Rover design and activity pattern on Mars, and its power system requirements and environmental constraints, including the RTG cooling requirements during transit to Mars. It identifies the key RTG design problem, i.e. venting the helium generated by the fuel's alpha decay without intrusion of the Martian atmosphere into the RTG, and proposes a design approach for solving that problem. Using that approach, it describes and analyzes a variety of RTG designs, all based on the proven and safetyqualified General Purpose Heat Source Module. The first RTG option described is a very conservative baseline design, employing standard thermoelectric unicouples whose reliability and performance stability has been extensively demonstrated on previous space missions. The heat source of the 250-watt RTG consists of a stack of 18 separate modules that is supported at its ends but not along its length. The paper describes and analyzes the structure that holds the stack together during Earth launch and Mars operations, but allows it to come apart in case of an inadvertent reentry. It then summarizes the baseline RTG's mass breakdown, and presents a detailed description of its thermal, thermoelectric, and electrical analyses. It examines the effect of different operating conditions (BOM/EOM, watercooled/radiation-cooled, summer-day/winter-night) on the RTG's performance. Finally, the paper compares the RTGs' specific powers for different power levels (250W/125W), different thermoelectric element designs (standard unicouples/short unicouples/multicouples), and different thermoelectric figures of merit (0.00058K ). The results presented show the RTG performance achievable with current technology, and the performance improvements that would be achievable with various technology developments. It provides a basis for selecting the optimum strategy for meeting the Mars Rover design goals with minimal programmatic risk and cost.

show abstract

Mars Rover Sample Return Orbiter design concepts

Cited by 6 publications

References 0 publications

Mars Rover RTG Study

Mars Rover RTG Study

Mars Rover RTG Study

Mars Rover RTG Study

Contact Info

Product

Resources

About