Solar thermal propulsion for an interstellar probe

Lyman, R; Ewing, Mark E.; Krishnan, R. S.; Lester, Dean M.; Propulsion, Thiokol; McNutt, R. L.

doi:10.2514/6.2001-3377

Cited by 10 publications

(5 citation statements)

References 3 publications

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“…Broadly speaking, solar thermal propulsion (STP) is predicated on executing a solar Oberth maneuver and harnessing the incident solar energy during this maneuver to heat the propellant. Initial studies suggested speeds of ∼ 20 AU/yr are conceivable [245], which is comparable to some of the propulsion systems examined hitherto. In the short term, achievable speeds may be restricted to 9 AU/yr [246] owing to thermal issues [247].…”

Section: Solar and Nuclear Thermal Propulsionmentioning

confidence: 55%

Chasing nomadic worlds: A new class of deep space missions

Lingam¹,

Hein²,

Eubanks³

2023

Acta Astronautica

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Section: Solar and Nuclear Thermal Propulsionmentioning

confidence: 55%

Chasing nomadic worlds: A new class of deep space missions

Lingam¹,

Hein²,

Eubanks³

2023

Acta Astronautica

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“…Such large velocities cannot be practically achieved with any chemical rocket or even nuclear thermal propulsion (NTP). Previous studies have focused on ballistic missions using powered near-Sun gravity assists [8][9][10][11][12][13][14] , nuclear electric propulsion (NEP) [15][16][17][18][19][20] , and solar sail propulsion [21][22][23] . The first approach (ballistic) has significant thermal issues and still requires a non-conventional propulsion system near the Sun to reach the desired speeds.…”

Section: Engineering Requirementsmentioning

confidence: 99%

Innovative Interstellar Explorer: Radioisotope Propulsion to the Interstellar Medium

McNutt¹,

Leary²,

Gold³

et al. 2005

41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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An interstellar "precursor" mission has been under discussion in the scientific community for over 25 years. Fundamental scientific questions about the interaction of the Sun with the interstellar medium can only be answered with in situ measurements that such a mission could provide. The Innovative Interstellar Explorer is a funded NASA Vision Mission Study that investigates the use of Radioisotope Electric Propulsion (REP) to enable such a mission. The problem is the development of a probe that can provide the required measurements and can reach a heliocentric distance of at least 200 astronomical units (AU) in a reasonable mission time. The required flyout speed in the direction of the inflowing interstellar medium is provided by a high-energy launch, followed by long-term, low-thrust, continuous acceleration. Trades from also using gravity assists have been studied along with trades between advanced Multi-mission radioisotope thermoelectric generators (MMRTGs) and Stirling radioisotope generators (SRGs), both powered by Pu-238. While subject to mass and power limitations for the instruments on board, such an approach relies on known General Purpose Heat Source (GPHS), Pu-238 technology and current launch vehicles for

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“…Advanced concepts for thermal propulsion, including solar thermal propulsion (STP) and nuclear thermal propulsion (NTP), have gained traction as leading alternatives to chemical propulsion for high‐velocity travel to destinations in our solar system and beyond 1–4 . Both propulsion options function by heating cryogenically stored hydrogen (H 2 ) to high temperatures to be exhausted through a nozzle for propulsion—STP through a close (3–4 solar radii) approach to the sun and NTP using a radioisotope heat source.…”

Section: Introductionmentioning

confidence: 99%

“…Both propulsion options function by heating cryogenically stored hydrogen (H 2 ) to high temperatures to be exhausted through a nozzle for propulsion—STP through a close (3–4 solar radii) approach to the sun and NTP using a radioisotope heat source. STP is being investigated as a means to have a science probe rapidly access the interstellar medium in a reasonable mission lifetime (<20 years), with recent studies indicating velocities three times faster than Voyager 1 are feasible 1–3 . The target application for NTP is human transit to Mars, due to its potential to halve travel time and thus limit the duration that astronauts are exposed to radiation 4 .…”

Section: Introductionmentioning

confidence: 99%

Erosion of refractory carbides in high‐temperature hydrogen from ab initio computations

et al. 2021

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Advanced concepts for in‐space propulsion require coatings that are resistant to erosion in high temperature and pressure hydrogen. The erosion of refractory carbides of interest for this application (ZrC, NbC, HfC, and TaC) is investigated using combined ab initio thermodynamic computations and equilibrium product analyses. The carbides are shown to erode through a combination of four governing reactions, the relative extent of which depend on environmental conditions. The product profiles from these reactions are complex but exhibit lower hydrogen saturation at higher temperatures and lower pressures. A metric is derived to determine the applicability of equilibrium analyses for erosion rates, based on experimental conditions. Heritage mass loss experiments on ZrC in hydrogen satisfy the equilibrium criteria, and, correspondingly, the computed equilibrium erosion rate agrees quantitatively. The results suggest that previously postulated non‐equilibrium effects, namely the prolonged incongruent vaporization originating from high carbon mobility, do not drive erosion over the hours‐long timescales of the experiments. For specific in‐space propulsion designs, comparisons of carbide performance show TaC and HfC outperform other carbides and meet the criteria needed to close designs.

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Solar thermal propulsion for an interstellar probe

Cited by 10 publications

References 3 publications

Chasing nomadic worlds: A new class of deep space missions

Chasing nomadic worlds: A new class of deep space missions

Innovative Interstellar Explorer: Radioisotope Propulsion to the Interstellar Medium

Erosion of refractory carbides in high‐temperature hydrogen from ab initio computations

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