Recent Advancements in Modeling and Simulation of Entry Systems at NASA
No abstract available
Barnhardt, Michael↗
Engineering topics
Wright, Michael
Publications and source records attributed to Wright, Michael.
Novel, Low-Cost, Light-Weight High Efficiency (H*10 Capable) Neutron Detector-Dosimeter
The goal of this project was to design, develop and validate a novel, spectroscopy enabled H*(10) neutron dosimetry system based on the tensioned metastable fluid detector (TMFD) sensor technology. The project team consisted of staff from Oak Ridge National Laboratory (ORNL), Purdue University (PU) and Sagamore Adams Laboratories, LLC (SAL). PU-SAL staff were tasked with the design, development, construction and testing of the H*TMFD hardware and software, along with developing the control and data acquisition software for comparison of predictions from H*TMFD against a commonly accepted and widely used industry standard system; for this project, the Li-I detector coupled to bonner spheres (LiI-BSS) system manufactured by Ludlum, Inc. was utilized as the reference (“gold”) standard – similar in terms of neutron spectroscopy enablement to another industry recognized, albeit, significantly higher cost (est. $300K) system referred to as “ROSPEC” (from BTI, Inc., which was not available for this project). ORNL staff were tasked with providing field-relevant guidance, apparatus and facilities for acquiring data against calibrated neutron sources, and comparing results of H*TMFD against LiI-BSS system predictions in a series of blind-tests conducted at ORNL. Over the course of 12 months, the PU-SAL-ORNL staff successfully accomplished the proposed technical and administrative tasks, inclusive of engaging in outreach to potential users of this technology in the DOE-wide infrastructure. The proposed tasks were successfully accomplished in timely manner; the follow-up type tasks pertaining to SBIR type Phases 2-3 were discussed and are initiated, inclusive of filing for intellectual property (IP) disclosures and possible patent filings by PU’s Office of Technology Commercialization (OTC). Two H*TMFD system architectures (see Exhibits 1 & 2 in the report) were developed and constructed for hand-portability by health-physicists (HPs) – the HP-H*TMFD, and the H*TMFD system which consists of a side-by-side mounted array of 4 TMFDs of 3 different sizes in sensitive volume (including one with borated fluid) that now simultaneously enables neutron energy spectroscopy: single bin for < 0.1 MeV, and 152 energy bins in the 0.1-15.2 MeV range; H*(10) dosimetry from ~5 μRem/h towards 10 R/h ranges. Several experiments were conducted using neutron sources in various configurations (shielded and unshielded). In direct comparison against the LiI-BSS industry standard (acquiring data for 26h each source), the H*TMFD system (acquiring data for ~6h for each source) offered H*(10) dose predictions for the most part accurate to within +/-10% for dose rates in the 100-300 μRem/h range. The LiI-BSS was impractical to use under ultra-low (~10 μRem/h) dose rate space, as also another metering device used at ORNL (Ludlum 4241L non-spectroscopy enabled) for which the lower limit is set by the manufacturer at 100 μRem/h. The enablement for efficient use in timely manner at the 10 μRem/h levels is deemed to be a strong enabling factor for H*TMFD for use in the DOE-nuclear laboratory arena. In terms of weight, the HP-H*TMFD weighs under ~5-7 lb.; the H*TMFD system weighs ~35-lb. As such, it is ~1/4 the weight of an LiI-BSS system weighing ~120 lb (LiI detector with 6 bonner spheres) and, ~1/2 the weight of ROSPEC. As a result of this activity, two involved post-doctoral student staff have now transitioned their knowledge and experiences to DOE’s Pacific Northwest National Laboratory (PNNL). A PU graduate student has also benefited from this project work which formed a principal basis for his Ph.D. dissertation work (in progress).
46 INSTRUMENTATION RELATED TO NUCLEAR SCIENCE AND ↗
Aerothermodynamics for Dragonfly's Titan Entry
Dragonfly is a proposed spacecraft and mission that would send a mobile robotic rotorcraft lander to Titan, the largest moon of Saturn, in order to study prebiotic chemistry and extraterrestrial habitability at various locations. Titan is unique in having an abundant, complex, and diverse carbon-rich chemistry on the surface of a water-ice-dominated world with an interior water ocean, making it a high priority target for astrobiology and origin of life studies. The mission was initially proposed in April 2017 to NASA's New Frontiers program by the Johns Hopkins Applied Physics Laboratory. In December 2017, it was selected as one of two finalists (out of twelve proposals) to further refine the mission's concept. NASA Ames Research Center and NASA Langley Research Center are partnering as the leads for the Dragonfly's entry system to provide the completed EDL Assembly. The aerothermal analysis for Dragonfly utilizes four simulation tools from NASA Ames Research Center. Traj for calculating the trajectory, DPLR 4.04.0 for calculating the flowfield around the vehicle and convective heating, NEQAIR V15.0 for calculating the radiative heating, and FIAT for calculating the material response and thermal protection system (TPS) sizing for the heatshield. The entry conditions are relatively benign and can readily be accommodated with a tiled PICA heatshield similar to MSL and a number of flight proven materials for the backshell. This work will demonstrate that the aerothermal entry environments can be readily solved using heritage materials and techniques.
New Frontiers↗
Current Investments in the NASA Entry Systems Modeling Project
This talk will provide an overview of investments in the Entry Systems Modeling project, along with some context of where the effort sits in the overall Space Technology EDL Portfolio. Technical highlights, particularly with referent to work on Ablation Modeling, will be given. Future directions will be discussed.
Aerothermodynamics↗
From Tomography to Material Properties of Thermal Protection Systems
A NASA Ames Research Center (ARC) effort, under the Entry Systems Modeling (ESM) project, aims at developing micro-tomography (micro-CT) experiments and simulations for studying materials used in hypersonic entry systems. X-ray micro-tomography allows for non-destructive 3D imaging of a materials micro-structure at the sub-micron scale, providing fiber-scale representations of porous thermal protection systems (TPS) materials. The technique has also allowed for In-situ experiments that can resolve response phenomena under realistic environmental conditions such as high temperature, mechanical loads, and oxidizing atmospheres. Simulation tools have been developed at the NASA Ames Research Center to determine material properties and material response from the high-fidelity tomographic representations of the porous materials with the goal of informing macroscopic TPS response models and guiding future TPS design.
Tomography↗
Technology Investments in the NASA Entry Systems Modeling Project
The Entry Systems Modeling (ESM) technology development project, initiated in 2012 under NASAs Game Changing Development (GCD) Program, is engaged in maturation of fundamental research developing aerosciences, materials, and integrated systems products for entry, descent, and landing(EDL)technologies [1]. To date, the ESM project has published over 200 papers in these areas, comprising the bulk of NASAs research program for EDL modeling. This presentation will provide an overview of the projects successes and challenges, and an assessment of future investments in EDL modeling and simulation relevant to NASAs mission
Barnhardt, Michael↗
X-Ray Micro-Tomography for Advanced Material Technologies: A NASA Perspective
No abstract available
NASA perspective↗
Predictive Modeling for NASA Entry, Descent and Landing Missions
Entry, Descent and Landing (EDL) Modeling and Simulation (MS) is an enabling capability for complex NASA entry missions such as MSL and Orion. MS is used in every mission phase to define mission concepts, select appropriate architectures, design EDL systems, quantify margin and risk, ensure correct system operation, and analyze data returned from the entry. In an environment where it is impossible to fully test EDL concepts on the ground prior to use, accurate MS capability is required to extrapolate ground test results to expected flight performance.
Modeling & Simulation↗
Mars Surface Operations via Low-Latency Telerobotics from Phobos
To help assess the feasibility and timing of Low-Latency Telerobotics (LLT) operations on Mars via a Phobos telecommand base, operations concepts (ops cons) and timelines for several representative sequences for Mars surface operations have been developed. A summary of these LLT sequences and timelines will be presented, along with associated assumptions, operational considerations, and challenges.
telerobotics↗
Low-Latency Teleoperations for Human Exploration and Evolvable Mars Campaign
NASA has been analyzing a number of mission concepts and activities that involve low-latency telerobotic (LLT) operations. One mission concept that will be covered in this presentation is Crew-Assisted Sample Return which involves the crew acquiring samples (1) that have already been delivered to space, and or acquiring samples via LLT from orbit to a planetary surface and then launching the samples to space to be captured in space and then returned to the earth with the crew. Both versions of have key roles for low-latency teleoperations. More broadly, the NASA Evolvable Mars Campaign is exploring a number of other activities that involve LLT, such as: (a) human asteroid missions, (b) PhobosDeimos missions, (c) Mars human landing site reconnaissance and site preparation, and (d) Mars sample handling and analysis. Many of these activities could be conducted from Mars orbit and also with the crew on the Mars surface remotely operating assets elsewhere on the surface, e.g. for exploring Mars special regions and or teleoperating a sample analysis laboratory both of which may help address planetary protection concerns. The operational and technology implications of low-latency teleoperations will be explored, including discussion of relevant items in the NASA Technology Roadmap and also how previously deployed robotic assets from any source could subsequently be used by astronauts via LLT.
crew autonomy↗
Mars Exploration Rover Heatshield Observation Campaign
For the first time ever, engineers were able to observe a heatshield on the surface of another planet after a successful entry through the atmosphere. A three-week heatshield observation campaign was conducted in December 2004 after the Mars Exploration Rover Opportunity rover exited "Endurance Crater." By utilizing the rover's scientific instruments, data was collected to make a qualitative assessment of the performance of the heatshield. This data was gathered to gain a better understanding of how the heatshield performed during entry through the Martian atmosphere. In addition, this unprecedented look at the heatshield offered engineers the opportunity to assess if any unexpected anomalies occurred. Once a survey of the heatshield debris was completed, multiple targets of interest were chosen for the collection of imaging data. This data was then used to assess the char depth of the thermal protection material, which compared well with computational predictions. Extensive imaging data was collected and showed the main seal in pristine conditions, and no observable indications of structure overheating. Additionally, unexpected vehicle dynamics during the atmospheric entry were explained by the observation of thermal blanket remnants attached to the heatshield.
MER↗
First Stage of a Highly Reliable Reusable Launch System
Electromagnetic launch assist has the potential to provide a highly reliable reusable first stage to a space access system infrastructure at a lower overall cost. This paper explores the benefits of a smaller system that adds the advantages of a high specific impulse air-breathing stage and supersonic launch speeds. The method of virtual specific impulse is introduced as a tool to emphasize the gains afforded by launch assist. Analysis shows launch assist can provide a 278-s virtual specific impulse for a first-stage solid rocket. Additional trajectory analysis demonstrates that a system composed of a launch-assisted first-stage ramjet plus a bipropellant second stage can provide a 48-percent gross lift-off weight reduction versus an all-rocket system. The combination of high-speed linear induction motors and ramjets is identified, as the enabling technologies and benchtop prototypes are investigated. The high-speed response of a standard 60 Hz linear induction motor was tested with a pulse width modulated variable frequency drive to 150 Hz using a 10-lb load, achieving 150 mph. A 300-Hz stator-compensated linear induction motor was constructed and static-tested to 1900 lbf average. A matching ramjet design was developed for use on the 300-Hz linear induction motor.
Kloesel, Kurt J.↗
Lunar Reconnaissance Orbiter FlatSat
This viewgraph presentation reviews the use of FlatSat as a platform for use during flight integration and testing (I&T) of the Lunar Reconnaissance Orbiter (LRO). Included in the presentations are requirements for the facility, a diagram of the LRO FlatSat lab, and discussion of the operational documentation, facility scheduling, and issues and lessons learned.
Wright, Michael↗
Overview of the MEDLI Project
The Mars Science Laboratory Entry, Descent, and Landing Instrumentation (MEDLI) Project's objectives are to measure aerothermal environments, sub-surface heatshield material response, vehicle orientation, and atmospheric density for the atmospheric entry and descent phases of the Mars Science Laboratory (MSL) entry vehicle. The flight science objectives of MEDLI directly address the largest uncertainties in the ability to design and validate a robust Mars entry system, including aerothermal, aerodynamic and atmosphere models, and thermal protection system (TPS) design. The instrumentation suite will be installed in the heatshield of the MSL entry vehicle. The acquired data will support future Mars entry and aerocapture missions by providing measured atmospheric data to validate Mars atmosphere models and clarify the design margins for future Mars missions. MEDLI thermocouple and recession sensor data will significantly improve the understanding of aeroheating and TPS performance uncertainties for future missions. MEDLI pressure data will permit more accurate trajectory reconstruction, as well as separation of aerodynamic and atmospheric uncertainties in the hypersonic and supersonic regimes. This paper provides an overview of the project including the instrumentation design, system architecture, and expected measurement response.
Gazarik, Michael J.↗
Neptune Polar Orbiter with Probes
The giant planets of the outer solar system divide into two distinct classes: the gas giants Jupiter and Saturn, which consist mainly of hydrogen and helium; and the ice giants Uranus and Neptune, which are believed to contain significant amounts of the heavier elements oxygen, nitrogen, and carbon and sulfur. Detailed comparisons of the internal structures and compositions of the gas giants with those of the ice giants will yield valuable insights into the processes that formed the solar system and, perhaps, other planetary systems. By 2012, Galileo, Cassini and possibly a Jupiter Orbiter mission with microwave radiometers, Juno, in the New Frontiers program, will have yielded significant information on the chemical and physical properties of Jupiter and Saturn. A Neptune Orbiter with Probes (NOP) mission would deliver the corresponding key data for an ice giant planet. Such a mission would ideally study the deep Neptune atmosphere to pressures approaching and possibly exceeding 1000 bars, as well as the rings, Triton, Nereid, and Neptune s other icy satellites. A potential source of power would be nuclear electric propulsion (NEP). Such an ambitious mission requires that a number of technical issues be investigated, however, including: (1) atmospheric entry probe thermal protection system (TPS) design, (2) probe structural design including seals, windows, penetrations and pressure vessel, (3) digital, RF subsystem, and overall communication link design for long term operation in the very extreme environment of Neptune's deep atmosphere, (4) trajectory design allowing probe release on a trajectory to impact Neptune while allowing the spacecraft to achieve a polar orbit of Neptune, (5) and finally the suite of science instruments enabled by the probe technology to explore the depths of the Neptune atmosphere. Another driving factor in the design of the Orbiter and Probes is the necessity to maintain a fully operational flight system during the lengthy transit time from launch through Neptune encounter, and throughout the mission. Following our response to the recent NASA Research Announcement (NRA) for Space Science Vision Missions for mission studies by NASA for implementation in the 2013 or later time frame, our team has been selected to explore the feasibility of such a Neptune mission.
Bienstock, Bernard↗
Recent CFD Simulations of Shuttle Orbiter Contingency Abort Aerodynamics
Modern Computational Fluid Dynamics (CFD) techniques were used to compute aerodynamic forces and moments of the Space Shuttle Orbiter in specific portions of contingency abort trajectory space. The trajectory space covers a Mach number range of 3.5-15, an angle-of-attack range of 20-60 degrees, an altitude range of 100-190 kft, and several different settings of the control surfaces (elevons, body flap, and speed brake). While approximately 40 cases have been computed, only a sampling of the results is presented here. The computed results, in general, are in good agreement with the Orbiter Operational Aerodynamic Data Book (OADB) data (i.e., within the uncertainty bands) for almost all the cases. However, in a limited number of high angle-of-attack cases (at Mach 15), there are significant differences between the computed results, especially the vehicle pitching moment, and the OADB data. A preliminary analysis of the data from the CFD simulations at Mach 15 shows that these differences can be attributed to real-gas/Mach number effects.
Papadopoulos, Periklis↗
CFD Simulations in Support of Shuttle Orbiter Contingency Abort Aerodynamic Database Enhancement
Modern Computational Fluid Dynamics (CFD) techniques were used to compute aerodynamic forces and moments of the Space Shuttle Orbiter in specific portions of contingency abort trajectory space. The trajectory space covers a Mach number range of 3.5-15, an angle-of-attack range of 20deg-60deg, an altitude range of 100-190 kft, and several different settings of the control surfaces (elevons, body flap, and speed brake). Presented here are details of the methodology and comparisons of computed aerodynamic coefficients against the values in the current Orbiter Operational Aerodynamic Data Book (OADB). While approximately 40 cases have been computed, only a sampling of the results is provided here. The computed results, in general, are in good agreement with the OADB data (i.e., within the uncertainty bands) for almost all the cases. However, in a limited number of high angle-of-attack cases (at Mach 15), there are significant differences between the computed results, especially the vehicle pitching moment, and the OADB data. A preliminary analysis of the data from the CFD simulations at Mach 15 shows that these differences can be attributed to real-gas/Mach number effects. The aerodynamic coefficients and detailed surface pressure distributions of the present simulations are being used by the Shuttle Program in the evaluation of the capabilities of the Orbiter in contingency abort scenarios.
Papadopoulos, Periklis E.↗