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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 973 records · Page 54
All sourcesNASA NTRSDOE OSTI
NASA NTRS2011

Advanced Stirling Duplex Materials Assessment for Potential Venus Mission Heater Head Application

This report will address materials selection for components in a proposed Venus lander system. The lander would use active refrigeration to allow Space Science instrumentation to survive the extreme environment that exists on the surface of Venus. The refrigeration system would be powered by a Stirling engine-based system and is termed the Advanced Stirling Duplex (ASD) concept. Stirling engine power conversion in its simplest definition converts heat from radioactive decay into electricity. Detailed design decisions will require iterations between component geometries, materials selection, system output, and tolerable risk. This study reviews potential component requirements against known materials performance. A lower risk, evolutionary advance in heater head materials could be offered by nickel-base superalloy single crystals, with expected capability of approximately 1100C. However, the high temperature requirements of the Venus mission may force the selection of ceramics or refractory metals, which are more developmental in nature and may not have a well-developed database or a mature supporting technology base such as fabrication and joining methods.

Ritzert, Frank↗
NASA NTRS2012

Mission Sizing and Trade Studies for Low Ballistic Coefficient Entry Systems to Venus

The U.S and the U.S.S.R. have sent seventeen successful atmospheric entry missions to Venus. Past missions to Venus have utilized rigid aeroshell systems for entry. This rigid aeroshell paradigm sets performance limitations since the size of the entry vehicle is constrained by the fairing diameter of the launch vehicle. This has limited ballistic coefficients (beta) to well above 100 kg/m2 for the entry vehicles. In order to maximize the science payload and minimize the Thermal Protection System (TPS) mass, these missions have entered at very steep entry flight path angles (gamma). Due to Venus thick atmosphere and the steep-gamma, high- conditions, these entry vehicles have been exposed to very high heat flux, very high pressures and extreme decelerations (upwards of 100 g's). Deployable aeroshells avoid the launch vehicle fairing diameter constraint by expanding to a larger diameter after the launch. Due to the potentially larger wetted area, deployable aeroshells achieve lower ballistic coefficients (well below 100 kg/m2), and if they are flown at shallower flight path angles, the entry vehicle can access trajectories with far lower decelerations (~50-60 g's), peak heat fluxes (~400 W/cm2) and peak pressures. The structural and TPS mass of the shallow-gamma, low-beta deployables are lower than their steep-gamma, high-beta rigid aeroshell counterparts at larger diameters, contributing to lower areal densities and potentially higher payload mass fractions. For example, at large diameters, deployables may attain aeroshell areal densities of 10 kg/m2 as opposed to 50 kg/m2 for rigid aeroshells. However, the low-beta, shallow-gamma paradigm also raises issues, such as the possibility of skip-out during entry. The shallow-gamma could also increase the landing footprint of the vehicle. Furthermore, the deployable entry systems may be flexible, so there could be fluid-structure interaction, especially in the high altitude, low-density regimes. The need for precision in guidance, navigation and control during entry also has to be better understood. This paper investigates some of the challenges facing the design of a shallow-gamma, low-beta entry system.

Dutta, Soumyo↗
NASA NTRS2012

Sapphire Viewports for a Venus Probe

A document discusses the creation of a viewport suitable for use on the surface of Venus. These viewports are rated for 500 C and 100 atm pressure with appropriate safety factors and reliability required for incorporation into a Venus Lander. Sapphire windows should easily withstand the chemical, pressure, and temperatures of the Venus surface. Novel fixture designs and seals appropriate to the environment are incorporated, as are materials compatible with exploration vessels. A test cell was fabricated, tested, and leak rate measured. The window features polish specification of the sides and corners, soft metal padding of the sapphire, and a metal C-ring seal. The system safety factor is greater than 2, and standard mechanical design theory was used to size the window, flange, and attachment bolts using available material property data. Maintenance involves simple cleaning of the window aperture surfaces. The only weakness of the system is its moderate rather than low leak rate for vacuum applications.

Bates, Stephen↗
NASA NTRS2013

Analysis of Solar Cell Efficiency for Venus Atmosphere and Surface Missions

A simplified model of solar power in the Venus environment is developed, in which the solar intensity, solar spectrum, and temperature as a function of altitude is applied to a model of photovoltaic performance, incorporating the temperature and intensity dependence of the open-circuit voltage and the temperature dependence of the bandgap and spectral response of the cell. We use this model to estimate the performance of solar cells for both the surface of Venus and for atmospheric probes at altitudes from the surface up to 60 km. The model shows that photovoltaic cells will produce power even at the surface of Venus.

Landis, Geoffrey A.↗
NASA NTRS2016

COMPASS Final Report: Advanced Long-Life Lander Investigating the Venus Environment (ALIVE)

The COncurrent Multi-disciplinary Preliminary Assessment of Space Systems (COMPASS) Team partnered with the Applied Research Laboratory to perform a NASA Innovative Advanced Concepts (NIAC) Program study to evaluate chemical based power systems for keeping a Venus lander alive(power and cooling) and functional for a period of days. The mission class targeted was either a Discovery ($500M) or New Frontiers ($750M to $780M) class mission. Historic Soviet Venus landers have only lasted on the order of 2 hours in the extreme Venus environment: temperatures of 460 C and pressures of 93 bar. Longer duration missions have been studied using plutonium powered systems to operate and cool landers for up to a year. However, the plutonium load is very large. This NIAC study sought to still provide power and cooling but without the plutonium.

COMPASS↗
NASA NTRS2016

Stopped-Rotor Cyclocopter for Venus Exploration

The cyclocopter system can use two or more rotating blades to create lift, propulsion and control. This system is explored for its use in a mission to Venus. Cyclocopters are not limited to speed and altitude and can provide 360 degrees of vector thrusting which is favorable for good maneuverability. The novel aspect of this study is that no other cyclocopter configuration has been previously proposed for Venus or any (terrestrial or otherwise) exploration application where the cyclocopters rotating blades are stopped, and act as fixed wings. The design considerations for this unique planetary aerial vehicle are discussed in terms of implementing the use of a cyclorotor blade system combined with a fixed wing and stopped rotor mechanism. This proposed concept avoids many of the disadvantages of conventional-rotor stopped-rotor concepts and accounts for the high temperature, pressure and atmospheric density present on Venus while carrying out the mission objectives. The fundamental goal is to find an ideal design that implements the combined use of cyclorotors and fixed wing surfaces. These design concepts will be analyzed with the computational fluid dynamics tool RotCFD for aerodynamic assessment. Aspects of the vehicle design is 3D printed and tested in a small water tunnel or wind tunnel.

Husseyin, Sema↗
NASA NTRS2017

DAVINCI: Deep Atmosphere Venus Investigation of Noble gases, Chemistry, and Imaging

DAVINCI is one of five Discovery-class missions selected by NASA in October 2015 for Phase A studies. Launching in November 2021 and arriving at Venus in June of 2023, DAVINCI would be the first U.S. entry probe to target Venus atmosphere in 45 years. DAVINCI is designed to study the chemical and isotopic composition of a complete cross-section of Venus atmosphere at a level of detail that has not been possible on earlier missions and to image the surface at optical wavelengths and process-relevant scales.

imaging↗
NASA NTRS2017

Structure and Properties of the Foreshock at Venus

The interaction of the solar wind with Venus is dominated by the planet's ionosphere that acts as an obstacle to the flow resulting in an induced magnetosphere and bow shock much smaller than their terrestrial counterparts. This study presents a 3-D electromagnetic hybrid (kinetic ions and fluid electrons) simulation of the solar wind interaction with an unmagnetized obstacle to examine the structure and properties of the Cytherean foreshock during periods of near radial IMF, that is, when it lies upstream of the ionosphere. The interaction between the backstreaming ions and the solar wind results in the generation of two classes of ULF waves: (1) parallel propagating sinusoidal waves with periods approx. 20-30 s and (2) highly oblique fast magnetosonic waves. The joint nonlinear evolution of these waves results in the formation of structures called foreshock cavitons with dimensions comparable to the size of the planet. Foreshock cavitons are also present in the terrestrial foreshock. The excavation of plasma and magnetic field from their cores leads to lower average densities and magnetic field strengths in the foreshock. As in the case of Earth, this excavation results in the formation of a fast magnetosonic pulse/shock at the edge of the foreshock named the foreshock compressional boundary. Also similar to Earth is the formation of spontaneous hot flow anomalies (SHFAs) as foreshock cavitons approach the bow shock. The size and properties of SHFAs at Venus are comparable to those at Earth, and their existence has recently been established at Mars and Venus in a companion paper.

Omidi, N.↗
NASA NTRS2019

Co-orbital Asteroids as the Source of Venus's Zodiacal Dust Ring

Photometry from the Helios and STEREO spacecraft revealed regions of enhanced sky surface-brightness suggesting a narrow circumsolar ring of dust associated with Venus's orbit. We model this phenomenon by integrating the orbits of 10,000,000+ dust particles subject to gravitational and non-gravitational forces, considering several different kinds of plausible dust sources. We find that only particles from a hypothetical population of Venus co-orbital asteroids can produce enough signal in a narrow ring to match the observations. Previous works had suggested such objects would be dynamically unstable. However, we re-examined the stability of asteroids in 1:1 resonance with Venus and found that ~8% should survive for the age of the solar system, enough to supply the observed ring.

Pokorný, Petr↗
NASA NTRS2019

Sustaining Mature Entry System Technologies Crucial for Future In-Situ Venus Missions

Severe entry environments at Venus are a key challenge for all missions employing probes, landers, areal platforms, aerocapture and atmospheric skimming. Three specific mature technologies, PICA, HEEET, and ADEPT, are enablers for Venus in-situ missions but are at risk of atrophy or loss if not maintained. All three technologies were NASA-developed in partnership with US industry and rely on both organizations for intellectual property. These technologies are needed only for NASA missions and lack applicability elsewhere. NASA has experienced the loss of prior TPS technologies due to lack of use, including Apollo’s Avcoat (re-created at enormous expense for Orion) and Pioneer-Venus’ heritage carbon phenolic. Given the low flight cadence for planetary entry missions overall and the lack of non-NASA uses for these technologies, there is a real concern for the sustainment of key entry technologies.

Venakatapathy, Ethiraj↗
NASA NTRSDate not supplied

Conceptual Design and Analysis of a Deep Space Habitat with a Venus Flyby

Within the mission trade space for crewed Mars missions, opposition missions are considered as fast transit options to minimize the crewed duration in the deep space radiation environment. However, they tend to have much higher in energy requirements than conjunction class missions, and Venus flybys are often leveraged to lower the total V as much as possible. While the conceptual design of deep space habitats is already a complex problem, the Venus flyby introduces a new environment of operation that adds layers of difficulty. A design point is presented that is capable of performing the crewed Mars mission and ensure the crew is safe flying in proximity to Venus and the Sun. Detailed thermal analysis of the design point is done to show the sensitivity of the thermal control systems to changes in mission parameters.

Akshay Prasad↗
NASA NTRS2017

JPL Navigation Support for the JAXA Akatsuki (Planet-C) Return to Venus

This paper details the orbit determination activities undertaken at JPL in support of the Akatsuki (a.k.a. Planet-C) mission’s return to Venus. The JPL navigation team’s role was to provide independent navigation support as a point of comparison with the JAXA generated orbit determination solutions. Topics covered will include a mission and spacecraft overview; small forces modeling; cruise, approach, and Venus phase orbit determination results; and the international teaming arrangement. A discussion of the preparations for the Venus orbit insertion maneuver, which was successfully executed on December 7, 2015, is also covered in detail in the paper.

Young, Brian↗
NASA NTRS2017

Venus Aerial Platforms and Engineering and Scientific Modeling Needs

NASA’s Planetary Science Division is performing an assessment of the state of technology in aerial platforms for exploration of Venus. A key factor in the design of aerial platforms is knowledge of the Venus environment. Modeling the Venus environment, which is the subject of this workshop, is needed for the design of robust aerial platforms that can carry out their missions successfully. The purpose of this paper is to enumerate the kinds of models that are important for both engineering and scientific aspects of the design of an aerial platform mission. The first meeting of the NASA Aerial Platforms study team took place from May 30 to June 2, 2017 and defined the science that can be performed by aerial platforms. A second study meeting is planned for late November 2017. This paper focuses on the current status.

Thompson, T. W.↗
NASA NTRS2021

The Determination of the Rotational State and Interior Structure of Venus with VERITAS

Understanding the processes that led Venus to its current state and will drive its future evolution is a major objective of the next generation of orbiters. In this work we analyze the retrieval of the spin vector, the tidal response and the moment of inertia of Venus with VERITAS, a NASA Discovery-class mission. By simulating a systematic joint analysis of Doppler tracking data and tie points provided by the onboard synthetic aperture radar we show that VERITAS will provide accuracies (3σ) in the estimates of the tidal Love number k_2 to 4.6×10^(-4), its tidal phase lag to 0.05°, and the moment of inertia factor to 9.8×10^(-4) (0.3% of the expected value). Applying these results to recent models of the Venus interior, we show that VERITAS will provide much improved constraints on the interior structure of the planet.

G Cascioli↗
NASA NTRSDate not supplied

Future Orbiting and In-Situ Exploration of Venus: Mount Etna as Terrestrial Analog

The exploration of Venus will soon experience a new golden era thanks to the recently selected NASA Deep Atmosphere of Venus Investigation of Noble gases, Chemistry and Imaging (DAVINCI) mission, NASA Venus Emissivity, Radio Science, InSAR, Topography & Spectroscopy (VERITAS) mission, and ESA EnVision mission. The DAVINCI mission will focus on the analysis of the the atmospheric vertical structure and composition of Earth’s twin planet and on the geologic structure of a tesserae terrain. The VERITAS mission will investigate the geologic features of its surface as well as geodynamic characteristics of the subsurface, providing high-resolution emissivity data, a global radar map at an approximate resolution of 30 meters/pixel, and estimation of the gravity anomaly of the shallow crust of the planet. The ESA EnVision mission will be complementary to the two NASA missions, providing high resolution 0.8-2.5 micron emissivity data, Synthetic Aperture Radar (SAR) data, and Subsurface Radar Sounder (SRS) data. Beyond those, the proposed Roscosmos-NASA Venera-D mission will also be equipped with an orbiter that will investigate the atmospheric composition and circulation, as well as a lander that will analize the in-situ chemical composition and the surface-atmosphere interactions.

P. D’Incecco↗
NASA NTRSDate not supplied

Investigation of the Reactivity of Calcium Minerals Under Simulated Venus Conditions

The temperature and pressure at the modal radius on Venus is approximately 740K-95.6 bar, while the atmosphere is composed of various volcanic gases such as SO2, OCS, and H2S. Experiments and modeling completed by past researchers have found that these gases can be highly reactive with minerals at Venus conditions. However, the kinetics for many of these reactions have yet to be constrained by experiments. In this project we will research the effects of simulated Venus conditions on the stability of calcium minerals. In particular, we will focus on experiments with exposure to SO2 due to its reactivity with calcium. Additionally, we have selected several minerals that form under different geologic processes to investigate the effects of crystal lattice on kinetics.

S T Port↗
NASA NTRSDate not supplied

Reactivity of Calcium-Bearing Minerals Under Simulated Venus Conditions

•SO2 is reactive with several common elements e.g. calcium [1-4] •Knowledge on chemical reactions has implications for the past and current state of Venus - Venus may have had liquid water on its surface [5], thus hydrous silicates may have formed at that time [6]. - The Venus Emissivity Mapper (on VERITAS and EnVision) will be used to determine bulk composition of the surface by observing transition metal content [8-9] - Calcium diffuses through basalt to react with CO2 and SO2, changing the bulk composition and decreasing the emissivity from orbit [8] - Experiments investigating kinetics will be informative for future emissivity data •Goal: - Constrain reaction rate between several calcium minerals and SO2 - Determine the effect, if any, crystal lattices may have on these rates

S.T. Port↗
NASA NTRSDate not supplied

WEATHERING ON VENUS: CONSTRAINTS FROM MODEL AND EXPERIMENTAL RESULTS

The surface of Venus is in contact with a hot (~470° C), high pressure (92 bars), and caustic (CO2 with S) atmosphere, which should cause progressive alteration of the crust [1, 2]. Alteration should form rock coatings of iron-oxides and sulfates, since water is not stable on the surface to make clay minerals [1, 3]. These coatings could, in theory, be used as a way to age date different lava flows, since the amount of alteration should correlate with the age of the rock exposed to the atmosphere [4, 5]. However, the exact alteration mineralogy and rate are still not well constrained [5]. Further, how the alteration mineralogy affects orbital emissivity measurements of the Venus surface is similarly not well understood [6]. Here we review the recent geochemical modeling [1, 7] and experimental [8-15] studies to constrain the main alteration minerals, potential alteration rates, and open questions about the surface mineralogy of Venus.

J. Filiberto↗