Mars sample return, a concept point design by Team-X (JPL's advanced project design team)

Oberto, R.

doi:10.1109/aero.2002.1035567

Cited by 16 publications

(5 citation statements)

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“…One strong deterrents of the EP option was the mission duration on the order of 5 years and limited flight heritage of gridded ion systems. [3] Also in 2001, NASA initiated four industry studies and a fifth JPL Team-X study to explore MSR Architectures. The 2001 Team-X study, was a focused point design of a chemical propulsion MOR option.…”

Section: Previous Architecture Approachesmentioning

confidence: 99%

Mars sample return Orbiter/Earth Return Vehicle technology needs and mission risk assessment

Dankanich

Burke

Hemminger³

2010

2010 IEEE Aerospace Conference

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For many years, NASA and the science community have been asking for a Mars Sample Return (MSR) mission. There have been numerous studies to evaluate MSR mission architectures, technology needs and development plans, and top-level requirements. Because of the challenges, technologically and financially, of the MSR mission, NASA initiated a study top-level look at MSR propulsion technologies through the In-Space Propulsion Technology (ISPT) project office. The impact of propulsion technologies of the MSR Orbiter/Earth Return Vehicle (ERV) are evaluated for performance and overall mission risk. Technology trades included advanced bipropellant engines, electric propulsion, and aerobraking. Results are presented herein. 1 2

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Section: Previous Architecture Approachesmentioning

confidence: 99%

Mars sample return Orbiter/Earth Return Vehicle technology needs and mission risk assessment

Dankanich

Burke

Hemminger³

2010

2010 IEEE Aerospace Conference

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“…Moreover, equation (13 where t 1 is the wait time and t the total time of flight. Secondly, two more constraints are enforced to guarantee that at time t the two spacecrafts move along the same orbit and have the same positions as required by equations (16) and (17):…”

Section: Constraintsmentioning

confidence: 99%

“…On the other hand, the SRO will be equipped with appropriate scientific instruments to perform in-orbit measurements during surface operations of the lander. Due to its interesting properties, a sun-synchronous orbit with = a k m 4222 and = e 0.1362 [16] has been finally selected as an ideal candidate for the SRO parking orbit.…”

Section: Initial Orbitsmentioning

confidence: 99%

Optimal rendezvous trajectory between Sample Return Orbiter and Orbiting Sample Container in a Mars Sample Return mission

Fossà

Bettanini

2020

Acta Astronautica

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A trajectory optimization problem is examined to determine the most fuel-efficient rendezvous trajectory between spacecrafts in different orbits. To explore the whole range of feasible solutions, the wait time and the total time of flight are treated as free parameters while the initial and transfer orbits are not restricted to a particular one. To improve the accuracy of the numerical computation, the Kepler's time of flight equation is posed in terms of universal variables while the Lagrange coefficients are employed to obtain three-dimensional orbit information. The optimal rendezvous trajectory is then obtained enforcing the determined necessary conditions to be satisfied given only the initial state vectors of the involved spacecrafts. Two optimal rendezvous trajectories between a Sample Return Orbiter (SRO) and an Orbiting Sample Container (OS) are computed in the context of a future Mars Sample Return mission to demonstrate the reliability of the proposed solution. Finally, orbital perturbations due to the real shape of planet Mars and the solar radiation pressure are taken into account to determine the additional energy required to compensate these perturbations while performing the rendezvous manoeuvre.

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“…1 Beginning with the resurgence of robotic Mars spacecraft in the mid-to-late 1990's, plans took shape to implement MSR within an ongoing, sustainably funded Mars program. [2][3][4] A new item not common to other space endeavors is the Mars ascent vehicle (MAV), which must lift geology samples to Mars orbit for handoff to an Earth return spacecraft. A variety of liquid propelled and solid propelled MAV concepts was suggested and studied over a period of years, but very little progress has been made toward any implementation.…”

Section: Introductionmentioning

confidence: 99%

Defining the Mars Ascent Problem for Sample Return

Whitehead

2008

AIAA SPACE 2008 Conference &Amp; Exposition

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Lifting geology samples off of Mars is both a daunting technical problem for propulsion experts and a cultural challenge for the entire community that plans and implements planetary science missions. The vast majority of science spacecraft require propulsive maneuvers that are similar to what is done routinely with communication satellites, so most needs have been met by adapting hardware and methods from the satellite industry. While it is even possible to reach Earth from the surface of the moon using such traditional technology, ascending from the surface of Mars is beyond proven capability for either solid or liquid propellant rocket technology. Miniature rocket stages for a Mars ascent vehicle would need to be over 80 percent propellant by mass. It is argued that the planetary community faces a steep learning curve toward nontraditional propulsion expertise, in order to successfully accomplish a Mars sample return mission. A cultural shift may be needed to accommodate more technical risk acceptance during the technology development phase.

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Mars sample return, a concept point design by Team-X (JPL's advanced project design team)

Cited by 16 publications

References 0 publications

Mars sample return Orbiter/Earth Return Vehicle technology needs and mission risk assessment

Mars sample return Orbiter/Earth Return Vehicle technology needs and mission risk assessment

Optimal rendezvous trajectory between Sample Return Orbiter and Orbiting Sample Container in a Mars Sample Return mission

Defining the Mars Ascent Problem for Sample Return

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