A5088990658- Spacecraft Dynamics and Control
- Astro and Planetary Science
- Planetary Science and Exploration
- Space Satellite Systems and Control
- Space Exploration and Technology
- Spacecraft Design and Technology
- Aerospace Engineering and Energy Systems
- Inertial Sensor and Navigation
- Spacecraft and Cryogenic Technologies
- Space Science and Extraterrestrial Life
- Aerospace Engineering and Control Systems
- Gas Dynamics and Kinetic Theory
- Aerospace and Aviation Technology
- Rocket and propulsion systems research
- Surface Modification and Superhydrophobicity
- Icing and De-icing Technologies
- Spaceflight effects on biology
- Heat Transfer and Numerical Methods
- Parallel Computing and Optimization Techniques
- Chemical and Physical Properties in Aqueous Solutions
- Geothermal Energy Systems and Applications
- Chemical Thermodynamics and Molecular Structure
- Thermodynamic and Exergetic Analyses of Power and Cooling Systems
- Statistical and numerical algorithms
- Gender, Health, and Social Inequality
Langley Research Center
2018-2025
Analytical Mechanics Associates (United States)
2015-2019
Pontifícia Universidade Católica do Rio Grande do Sul
2019
Central University of Venezuela
2019
Laboratory for Atmospheric and Space Physics
2018
University of Zulia
2016
North Carolina State University
2013-2014
National Institute of Aerospace
2009
Laboratoire de génie des procédés pour la bioraffinerie, les matériaux bio-sourcés et l’impression fonctionnelle
2000-2005
The 2022 Planetary Science Decadal Survey released by the National Academies of identified exploration Ice Giants, particularly Uranus, as primary next Flagship mission. Uranus Orbit and Probe mission proposal was used baseline while making its recommendation. This which based on a launch date 2031 or 2032, fully-propulsive orbit insertion maneuver at (requiring 60-70% total mass for propellant), reached planet after 13 years interplanetary cruise before 2050 equinox, goal science community....
Abstract The Mars thermosphere (above approximately 120 km) has been probed in situ for one year using accelerometers on board the Atmosphere and Volatile Evolution (MAVEN) spacecraft. This region is affected by radiation energy deposition from Sun momentum lower atmosphere. Densities derived measurements made during nominal science orbits (periapsis > 140 show consistent trends with solar zenith angle Sun‐Mars distance, reflecting direct indirect heating of thermosphere, although...
View Video Presentation: https://doi.org/10.2514/6.2023-0148.vid Development of the Program to Optimize Simulated Trajectories (POST) began in 1970s. Since then, it has become widely utilized across NASA, industry, and academia solve a variety atmospheric ascent entry problems. Its successor, POST2, undergone many upgrades since its release 1990s. Recently, there been an increasing desire take advantage advances parallel computing for both offline online systems. Thus, modifications were...
A significant effort to upgrade the Program Optimize Simulated Trajectories II (POST2), a heritage flight mechanics tool developed at NASA Langley Research Center, is ongoing support current and future missions. To meet mission requirements, it may be necessary for multiple specialized computational tools interact properly assess system. An application programming interface POST2 was allow easier access users enable communication between external applications. demonstration of presented by...
We apply the Fully Numerical Predictor-corrector Aerocapture Guidance to capture a vehicle into orbit for mission at Uranus. Using Genesis flight mechanics simulation, we analyze both undispersed and dispersed trajectories in order tune guidance parameters. then assess performance of using Monte Carlo analyses. Properly accounting oblateness Uranus within proves be critical. identify high-to-low density gradients as cause large target misses. Intentionally targeting steeper flight-path angle...
Recent advances in planetary entry guidance algorithms are motivated by precision landing criteria for human-scale Mars missions and improved in-space computing capabilities. An NPC targeting algorithm, originally developed the Surveyor Program 2001 Missions, has been modified extended to permit a fully generalized, flexible, robust approach spacecraft aerocapture EDL design. This paper describes this generalized (NPCG) how its modifications enable use human missions. System modeling,...
Deployable aeroshells offer the promise of achieving larger aeroshell surface areas for entry vehicles than otherwise attainable without deployment. With area comes ability to decelerate high-mass at relatively low ballistic coefficients. However, an perform even coefficients with deployable aeroshells, a flexible thermal protection system (TPS) is required that capable surviving reasonably high heat flux and durable enough survive rigors construction handling, density packing, deployment,...
Develop two evolutionary rigid vehicle concepts to deliver human-scale payloads (20 metric tons) the surface of Mars: Capsule; Lifting body, mid-range lift-to-drag ratio (Mid L/D). Determine configurations for various mission flight phases. performance: Integrated system mass; Ability meet landing constraints; Payload packaging and access. Provide technology investment recommendations NASA’s Space Technology Mission Directorate.
Flush air data sensing (FADS) systems have been previously used at both Earth and Mars to provide onboard estimates of angle attack, sideslip angle, dynamic pressure. However, these FADS were often not in an in-the-loop sense inform the guidance control systems. A method integrate FADS-derived density wind with a numerical predictor-corrector algorithm is presented. The demonstrated high-fidelity simulation human-scale entry vehicle that utilizes hypersonic inflatable aerodynamic decelerator...
End-to-end mission simulations include multiple phases of flight. For example, an end-to-end Mars simulation may launch from Earth, interplanetary transit to and entry, descent landing. Each phase flight is optimized meet specified constraints often depend on impact subsequent phases. The design optimization tools methodologies used combine different aspects framework their planning are presented. This work focuses a robust implementation Multidisciplinary Design Analysis Optimization (MDAO)...
View Video Presentation: https://doi.org/10.2514/6.2023-0878.vid Aerocapture is a method of spacecraft orbital insertion that has the potential to provide mass savings as compared aerobraking. In particular, aerocapture at Venus desirable due high atmospheric density and for science return. While promising, accurate by means requires an active guidance, navigation, control architecture. This paper documents initial assessment performance two guidance algorithms, generalized numerical...
To support a permanent human settlement on the Lunar surface, improvements to current outpost architecture are investigated. A detailed analysis of architectures utilizing an orbital propellant depot and reusable vehicles is presented. Comparisons focus cost, extensibility, performance, heritage, reliability. An two stage transit vehicle, lander, integrated proposed. 30% reduction in cost for payload delivered lunar surface achieved with proposed when compared ESAS architecture. breakdown...
Abstract In this study, we examine how the Guri catfish Genidens genidens uses estuarine and freshwater habitats along largest South American coastal lagoon, through chemical analysis of otoliths microscopic gonads. Chemical composition (Sr:Ca) otolith edges allowed distinguishing between individuals who used or compartments lagoon. The core-to-edge profiles each individual revealed that population may present two different patterns habitat use ‘type 1’ pattern (89.5%) includes fish appear...