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  • Lunar and Planetary Science and Exploration  (2)
  • Structural Mechanics; Spacecraft Design, Testing and Performance  (2)
  • Man/System Technology and Life Support  (1)
  • Spacecraft Design, Testing and Performance; Composite Materials; Fluid Mechanics and Thermodynamics  (1)
  • 2015-2019  (3)
  • 2010-2014  (3)
  • 1
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    Preliminary Development of a Multifunctional Hot Structure Heat Shield (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Development of a Multifunctional Hot Structure Heat Shield concept has initiated with the goal to provide advanced technology with significant benefits compared to the current state of the art heat shield technology. The concept is unique in integrating the function of the thermal protection system with the primary load carrying structural component. An advanced carbon-carbon material system has been evaluated for the load carrying structure, which will be utilized on the outer surface of the heat shield, and thus will operate as a hot structure exposed to the severe aerodynamic heating associated with planetary entry. Flexible, highly efficient blanket insulation has been sized for use underneath the hot structure to maintain desired internal temperatures. The approach was to develop a preliminary design to demonstrate feasibility of the concept. The preliminary results indicate that the concept has the potential to save both mass and volume with significantly less recession compared to traditional heat shield designs, and thus provide potential to enable new planetary missions.
    Keywords: Structural Mechanics; Spacecraft Design, Testing and Performance
    Type: AIAA Paper 2014-0350 , NF1676L-16692 , AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; Jan 13, 2014 - Jan 17, 2014; National Harbor, MD; United States
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  • 2
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    A Multifunctional Hot Structure Heatshield Concept for Planetary Entry (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A multifunctional hot structure heatshield concept is being developed to provide technology enhancements with significant benefits compared to the current state-of-the-art heatshield technology. These benefits can potentially enable future planetary missions. The concept is unique in integrating the function of the thermal protection system with the primary load carrying structural component. An advanced carbon-carbon material system has been evaluated for the load carrying structure, which will be utilized on the outer surface of the heatshield, and thus will operate as a hot structure exposed to the severe aerodynamic heating associated with planetary entry. Flexible, highly efficient blanket insulation is sized for use underneath the hot structure to maintain required operational internal temperatures. The approach followed includes developing preliminary designs to demonstrate feasibility of the concept and benefits over a traditional, baseline design. Where prior work focused on a concept for an Earth entry vehicle, the current efforts presented here are focused on developing a generic heatshield model and performing a trade study for a Mars entry application. This trade study includes both structural and thermal evaluation. The results indicate that a hot structure concept is a feasible alternative to traditional heatshields and may offer advantages that can enable future entry missions.
    Keywords: Structural Mechanics; Spacecraft Design, Testing and Performance
    Type: NF1676L-21700 , AIAA International Space Planes and Hypersonic Systems and Technologies Conference (Hypersonics 2015); Jul 06, 2015 - Jul 09, 2015; Glasgow, Scotland; United Kingdom
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Estimating Mass of Inflatable Aerodynamic Decelerators Using Dimensionless Parameters (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes a technique for estimating mass for inflatable aerodynamic decelerators. The technique uses dimensional analysis to identify a set of dimensionless parameters for inflation pressure, mass of inflation gas, and mass of flexible material. The dimensionless parameters enable scaling of an inflatable concept with geometry parameters (e.g., diameter), environmental conditions (e.g., dynamic pressure), inflation gas properties (e.g., molecular mass), and mass growth allowance. This technique is applicable for attached (e.g., tension cone, hypercone, and stacked toroid) and trailing inflatable aerodynamic decelerators. The technique uses simple engineering approximations that were developed by NASA in the 1960s and 1970s, as well as some recent important developments. The NASA Mars Entry and Descent Landing System Analysis (EDL-SA) project used this technique to estimate the masses of the inflatable concepts that were used in the analysis. The EDL-SA results compared well with two independent sets of high-fidelity finite element analyses.
    Keywords: Lunar and Planetary Science and Exploration
    Type: Paper No. IPPW-8-6B , NF1676L-12864 , 8th International Planetary Probe Workshop 2011 (IPPW-8); Jun 06, 2011 - Jun 10, 2011; Portsmouth, VA; United States
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  • 4
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    Human Mars Entry, Descent and Landing Architecture Study: Rigid Decelerators (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Several technology investments are required to develop Mars human scale Entry, Descent, and Landing (EDL) systems. Studies play the critical role of identifying the most feasible technical paths and high payoff investments. The goal of NASA's Entry, Descent and Landing Architecture Study is to inform those technology investments. In Phase 1 of the study, a point design for one lifting-body-like rigid decelerator vehicle, was developed. In Phase 2, a capsule concept was also considered to determine how it accommodated the human mission requirements. This paper summarizes the concept of operations for both rigid vehicles to deliver a 20-metric ton (t) payload to the surface of Mars. Details of the vehicle designs and flight performance are presented along with a packaging, mass sizing, and a launch vehicle fairing assessment. Finally, recommended technology investments based on the analysis of the rigid vehicles are provided.
    Keywords: Lunar and Planetary Science and Exploration
    Type: MSFC-E-DAA-TN60268 , AIAA SPACE Forum; Sep 17, 2018 - Sep 19, 2018; Orlando, FL; United States
    Format: application/pdf
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  • 5
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    Multidisciplinary Tool for Systems Analysis of Planetary Entry, Descent, and Landing (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Systems analysis of a planetary entry (SAPE), descent, and landing (EDL) is a multidisciplinary activity in nature. SAPE improves the performance of the systems analysis team by automating and streamlining the process, and this improvement can reduce the errors that stem from manual data transfer among discipline experts. SAPE is a multidisciplinary tool for systems analysis of planetary EDL for Venus, Earth, Mars, Jupiter, Saturn, Uranus, Neptune, and Titan. It performs EDL systems analysis for any planet, operates cross-platform (i.e., Windows, Mac, and Linux operating systems), uses existing software components and open-source software to avoid software licensing issues, performs low-fidelity systems analysis in one hour on a computer that is comparable to an average laptop, and keeps discipline experts in the analysis loop. SAPE uses Python, a platform-independent, open-source language, for integration and for the user interface. Development has relied heavily on the object-oriented programming capabilities that are available in Python. Modules are provided to interface with commercial and government off-the-shelf software components (e.g., thermal protection systems and finite-element analysis). SAPE currently includes the following analysis modules: geometry, trajectory, aerodynamics, aerothermal, thermal protection system, and interface for structural sizing.
    Keywords: Man/System Technology and Life Support
    Type: LAR-17821-1 , NASA Tech Briefs, September 2011; 44
    Format: application/pdf
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  • 6
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    Optimization of a Hot Structure Aeroshell and Nose Cap for Mars Atmospheric Entry (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The National Aeronautics and Space Administration (NASA) is preparing to send humans beyond Low Earth Orbit and eventually to the surface of Mars. As part of the Evolvable Mars Campaign, different vehicle configurations are being designed and considered for delivering large payloads to the surface of Mars. Weight and packing volume are driving factors in the vehicle design, and the thermal protection system (TPS) for planetary entry is a technology area which can offer potential weight and volume savings. The feasibility and potential benefits of a ceramic matrix composite hot structure concept for different vehicle configurations are explored in this paper, including the nose cap for a Hypersonic Inflatable Aerodynamic Decelerator (HIAD) and an aeroshell for a mid lift-to-drag (Mid L/D) concept. The TPS of a planetary entry vehicle is a critical component required to survive the severe aerodynamic heating environment during atmospheric en- try. The current state-of-the-art is an ablative material to protect the vehicle from the heat load. The ablator is bonded to an underlying structure, which carries the mechanical loads associated with entry. The alternative hot structure design utilizes an advanced carbon-carbon material system on the outer surface of the vehicle, which is exposed to the severe heating and acts as a load carrying structure. The preliminary design using the hot structure concept and the ablative concept is determined for the spherical nose cap of the HIAD entry vehicle and the aeroshell of the Mid L/D entry vehicle. The results of the study indicate that the use of hot structures for both vehicle concepts leads to a feasible design with potential weight and volume savings benefits over current state-of-the-art TPS technology that could enable future missions.
    Keywords: Spacecraft Design, Testing and Performance; Composite Materials; Fluid Mechanics and Thermodynamics
    Type: NF1676L-23840 , Space 2016; Sep 13, 2016 - Sep 16, 2016; Long Beach, CA; United States
    Format: application/pdf
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