How shall we go to Mars? A review of mission scenarios

Walberg, Gerald D.

doi:10.2514/6.1992-481

Cited by 10 publications

(8 citation statements)

References 5 publications

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“…The issue of Earth launch date not being shown can be disregarded since the STOUR simulations search over a span of launch dates beyond the 32 years estimated for the geometry of Earth, Mars, and Venus to repeat in inertial space. With regards to stay times at Mars, several studies that incorporate a stay time at Mars (such as Walberg, 5 Casalino et al, 8 Bailey et al, 14 and Folta et al 15 ) have found solutions with the path EMVE, however such opportunities use a maneuver to capture into orbit at Mars, and are not suitable for an IM-type mission.…”

Section: A Feasibility Of Gravity-assist Pathsmentioning

confidence: 99%

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Fast Mars Free-Returns via Venus Gravity Assist

Hughes

Edelman

Longuski

et al. 2014

AIAA/AAS Astrodynamics Specialist Conference

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Section: A Feasibility Of Gravity-assist Pathsmentioning

confidence: 99%

“…In the last several decades, there have been many trajectory designs for human missions to Mars. [2][3][4][5][6][7][8][9][10][11][12][13][14][15]24 Despite this effort to show the way to Mars, humans have yet to stand on the surface of the red planet, and it remains a long-term goal of the US and several other nations.…”

Section: Introductionmentioning

confidence: 99%

Fast Mars Free-Returns via Venus Gravity Assist

Hughes

Edelman

Longuski

et al. 2014

AIAA/AAS Astrodynamics Specialist Conference

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“…Several studies on Mars trajectories have been carried out [12][13][14][15][16][17]. Planning future missions requires trajectory data years in advance.…”

Section: Mars Exploration Studiesmentioning

confidence: 99%

Interplanetary Trajectory Analysis for 2020-2040 Mars Missions Including Venus Flyby Opportunities

Ishimatsu

2009

AIAA SPACE 2009 Conference &Amp; Exposition

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This thesis develops a tool which is capable of calculating ballistic interplanetary trajectories with planetary flyby options based on the knowledge of astrodynamics and analyzes Mars trajectories in the time frame 2020 to 2040, including transfer trajectories with Venus flybys. Using the trajectory programs developed in this work, we investigate the relation between departure and arrival dates and energy required for the transfer trajectories. The contours of C3 or AVtot for a range of departure dates and times of flight would be useful for the creation of a long-term Earth-Mars and Mars-Earth transportation schedule for mission planning purposes. For planetary flybys, we allow simple powered flybys with the velocity impulse at periapsis to expand the flyby mission windows. Having obtained the results for Earth-Mars and Mars-Earth trajectories by a full-factorial computation, we discuss the nature of the trajectories and the competitiveness of Earth-Venus-Mars flyby trajectory windows with Earth-Mars direct trajectory windows.

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“…to over 3000 metric tons, depending on the launch date, trajectory, and mission profile [8]- [11]. Donahue and Cupples calculate an IMLEO of 668 mt, which would require eight Earth-to-orbit launches on an 80 mt launch vehicle [10].…”

Section: Motivationmentioning

confidence: 99%

Integrated Propulsion and Power Modeling for Bimodal Nuclear Thermal Rockets

Clough¹,

Starkey²,

Lewis³

et al. 2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Design point results show that a 316 MWt reactor produces a thrust and specific impulse of 66.6 kN and 917 s, respectively. The same reactor can be run at 73.8 kWt to produce the necessary 16.7 kW electric power with a Brayton cycle generator. This demonstrates the feasibility of BNTR operation with a NERVAderived reactor but also indicates that the reactor control system must be able to operate with precision across a wide power range, and that the transient analysis of reactor decay heat merits future investigation.Results also identify a significant reactor pressure-drop limitation during propulsion and power-generation operation that is caused by poor tie tube thermal conductivity. This leads to the conclusion that, while BNTR operation is possible with a NERVA-derived reactor, doing so requires careful consideration of the Brayton cycle design point and fuel element survivability.

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How shall we go to Mars? A review of mission scenarios

Cited by 10 publications

References 5 publications

Fast Mars Free-Returns via Venus Gravity Assist

Fast Mars Free-Returns via Venus Gravity Assist

Interplanetary Trajectory Analysis for 2020-2040 Mars Missions Including Venus Flyby Opportunities

Integrated Propulsion and Power Modeling for Bimodal Nuclear Thermal Rockets

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