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Aerodynamic Design Analysis And Validation Of A Supersonic Inflatable Decelerator
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Book Synopsis Aerodynamic Design, Analysis, and Validation of a Supersonic Inflatable Decelerator by : Ian Gauld Clark
Download or read book Aerodynamic Design, Analysis, and Validation of a Supersonic Inflatable Decelerator written by Ian Gauld Clark and published by . This book was released on 2009 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of supersonic wind tunnel tests conducted at the NASA Glenn and Langley Research Centers tested both rigid and flexible tension cone models. Testing of rigid force and moment models and pressure models demonstrated the new design to have favorable performance including drag coefficients between 1.4 and 1.5 and static stability at angles of attack from 0o. to 20o. A separate round of tests conducted on flexible tension cone models showed the system to be free of aeroelastic instability. Deployment tests conducted on an inflatable model demonstrated rapid, stable inflation in a supersonic environment. Structural modifications incorporated on the models were seen to reduce inflation pressure requirements by a factor of nearly two. Through this test program, this new tension cone IAD design was shown to be a credible option for a future flight system. Validation of CFD analyses for predicting aerodynamic IAD performance was also completed and the results are presented. Inviscid CFD analyses are seen to provide drag predictions accurate to within 6%. Viscous analyses performed show excellent agreement with measured pressure distributions and flow field characteristics. Comparisons between laminar and turbulent solutions indicate the likelihood of a turbulent boundary layer at high supersonic Mach numbers and large angles of attack.
Book Synopsis Aeroelastic Analysis and Testing of Supersonic Inflatable Aerodynamic Decelerators by : Christopher Lee Tanner
Download or read book Aeroelastic Analysis and Testing of Supersonic Inflatable Aerodynamic Decelerators written by Christopher Lee Tanner and published by . This book was released on 2012 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The current limits of supersonic parachute technology may constrain the ability to safely land future robotic assets on the surface of Mars. This constraint has led to a renewed interest in supersonic inflatable aerodynamic decelerator (IAD) technology, which offers performance advantages over the DGB parachute. Two supersonic IAD designs of interest include the isotensoid and tension cone, named for their respective formative structural theories. Although these concepts have been the subject of various tests and analyses in the 1960s, 1970s, and 2000s, significant work remains to advance supersonic IADs to a technology readiness level that will enable their use on future flight missions. In particular, a review of the literature revealed a deficiency in adequate aerodynamic and aeroelastic data for these two IAD configurations at transonic and subsonic speeds. The first portion of this research amended this deficiency by testing flexible IAD articles at relevant transonic and subsonic conditions. The data obtained from these tests showed that the tension cone has superior drag performance with respect to the isotensoid, but that the isotensoid may demonstrate more favorable aeroelastic qualities than the tension cone. Additionally, despite the best efforts in test article design, there remains ambiguity regarding the accuracy of the observed subscale behavior for flight scale IADs. Due to the expense and complexity of large-scale testing, computational fluid-structure interaction (FSI) analyses will play an increasingly significant role in qualifying flight scale IADs for mission readiness. The second portion of this research involved the verification and validation of finite element analysis (FEA) and computational fluid dynamic (CFD) codes for use within an FSI framework. These verification and validation exercises lend credence to subsequent coupled FSI analyses involving more complex geometries and models. The third portion of this research used this FSI framework to predict the static aeroelastic response of a tension cone IAD in supersonic flow. Computational models were constructed to mimic the wind tunnel test articles and flow conditions. Converged FSI responses computed for the tension cone agreed reasonably well with wind tunnel data when orthotropic material models were used and indicated that current material models may require unrealistic input parameters in order to recover realistic deformations. These FSI analyses are among the first results published that present an extensive comparison between FSI computational models and wind tunnel data for a supersonic IAD.
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781794415997 Total Pages :32 pages Book Rating :4.4/5 (159 download)
Book Synopsis Preliminary Structural Sensitivity Study of Hypersonic Inflatable Aerodynamic Decelerator Using Probabilistic Methods by : National Aeronautics and Space Adm Nasa
Download or read book Preliminary Structural Sensitivity Study of Hypersonic Inflatable Aerodynamic Decelerator Using Probabilistic Methods written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2019-01-22 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Acceptance of new spacecraft structural architectures and concepts requires validated design methods to minimize the expense involved with technology validation via flighttesting. This paper explores the implementation of probabilistic methods in the sensitivity analysis of the structural response of a Hypersonic Inflatable Aerodynamic Decelerator (HIAD). HIAD architectures are attractive for spacecraft deceleration because they are lightweight, store compactly, and utilize the atmosphere to decelerate a spacecraft during re-entry. However, designers are hesitant to include these inflatable approaches for large payloads or spacecraft because of the lack of flight validation. In the example presented here, the structural parameters of an existing HIAD model have been varied to illustrate the design approach utilizing uncertainty-based methods. Surrogate models have been used to reduce computational expense several orders of magnitude. The suitability of the design is based on assessing variation in the resulting cone angle. The acceptable cone angle variation would rely on the aerodynamic requirements. Lyle, Karen H. Langley Research Center NASA/TM-2014-218290, L-20406, NF1676L-18818
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781794430136 Total Pages :34 pages Book Rating :4.4/5 (31 download)
Book Synopsis Comparison of Analysis with Test for Static Loading of Two Hypersonic Inflatable Aerodynamic Decelerator Concepts by : National Aeronautics and Space Adm Nasa
Download or read book Comparison of Analysis with Test for Static Loading of Two Hypersonic Inflatable Aerodynamic Decelerator Concepts written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2019-01-23 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Acceptance of new spacecraft structural architectures and concepts requires validated design methods to minimize the expense involved with technology demonstration via flight-testing. Hypersonic Inflatable Aerodynamic Decelerator (HIAD) architectures are attractive for spacecraft deceleration because they are lightweight, store compactly, and utilize the atmosphere to decelerate a spacecraft during entry. However, designers are hesitant to include these inflatable approaches for large payloads or spacecraft because of the lack of flight validation. This publication summarizes results comparing analytical results with test data for two concepts subjected to representative entry, static loading. The level of agreement and ability to predict the load distribution is considered sufficient to enable analytical predictions to be used in the design process. Lyle, Karen H. Langley Research Center NASA/TM-2015-218778, L-20573, NF1676L-21778
Book Synopsis A System for Aerodynamic Design and Analysis of Supersonic Aircraft. Part 4: Test Cases by : W. D. Middleton
Download or read book A System for Aerodynamic Design and Analysis of Supersonic Aircraft. Part 4: Test Cases written by W. D. Middleton and published by . This book was released on 1980 with total page 238 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A System for Aerodynamic Design and Analysis of Supersonic Aircraft by :
Download or read book A System for Aerodynamic Design and Analysis of Supersonic Aircraft written by and published by . This book was released on 1980 with total page 121 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Longitudinal Aerodynamic Characteristics of Some Supersonic Decelerator Models at Mach Numbers of 2.30 and 4.63 by : Edwin E. Davenport
Download or read book Static Longitudinal Aerodynamic Characteristics of Some Supersonic Decelerator Models at Mach Numbers of 2.30 and 4.63 written by Edwin E. Davenport and published by . This book was released on 1969 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scalability of a Tension Cone Supersonic Inflatable Aerodynamic Decelerator by : Alejandro Pensado
Download or read book Scalability of a Tension Cone Supersonic Inflatable Aerodynamic Decelerator written by Alejandro Pensado and published by . This book was released on 2017 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Human-class missions to Mars will require larger and safer payloads than current technology can achieve. The inflatable aerodynamic decelerator concept has the potential to meet these needs which will enable human-class missions to Mars for a desired 2030s window. This concept, started in the 1960s for the Viking missions, involves a deployable inflatable aeroshell designed for missions with entry, descend and land stages. Research fluctuated in the following decade from minor development in the 1980s to an increased interest in recent years including international entities. The continuing research resulted in two major designs: Supersonic and hypersonic decelerators. The objective of this thesis is to systematically study the scalability of the supersonic inflatable aerodynamic decelerator tension cone and computationally simulate the minimum inflation pressure required for Earth and Mars deployment conditions. The scalability study is based on the 0.6-meter diameter tension cone model studied in the supersonic wind tunnel tests conducted at NASA Glenn Research Center. The scaling parameters chosen to investigate the deployment performance of 14, 17, 20, and 23-meter tension cones are Reynolds number, Froude number, ballistic coefficient, and mass efficiency at a fixed Mach number. Scaling the Reynolds number showed the tension cones operate under laminar flow conditions. Matching the Froude number determined that a larger tension cone is more effective in decelerating the entry vehicle and less effective in a Mars atmosphere compared to an Earth atmosphere. Both the ballistic coefficient and mass efficiency showed that a larger tension cone is less efficient at decelerating because the mass increase of the tension cone overwhelms the effect of increasing the diameter of the tension cone. The velocity to match each scaling parameter was calculated for the 0.6-meter model. These results were compiled into eight potential case studies to investigate the tension cone at these deployment conditions.The objective of the simulations was to determine time history of forces at the scaled conditions, inflation pressure required for deployment, and minimum inflation pressure required to prevent buckling. The computational work focused on the Earth and Mars cases for the 0.6-meter tension cone with the scaled conditions to match the 14-meter tension cone. Matching the Mach number was used as the validation, where the simulation and experimental axial forces agreed with minimal error. In order to determine the inflation pressure required for deployment, the internal pressure of the torus was reduced until the tension shell began to wrinkle. Wrinkles indicate structural failure and eventual torus buckling. The Mach, Reynolds, and Froude number simulations yielded similar results. Fully deployed, the tension cone had small oscillations, wrinkling appeared and became more prominent as the structure began to fail until the torus buckled. The mass efficiency simulation experienced higher axial force, resulting in more violent tension cone oscillations. The torus experienced a bending moment until the structure buckled. This indicates the axial force load limit on the tension cone. The data were compiled shows a linear relationship between minimum torus inflation pressure and axial loading. This allows tension cone mass optimization for future designs.
Book Synopsis A System for Aerodynamic Design and Analysis of Supersonic Aircraft: Test cases by :
Download or read book A System for Aerodynamic Design and Analysis of Supersonic Aircraft: Test cases written by and published by . This book was released on 1980 with total page 234 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A System for Aerodynamic Design and Analysis of Supersonic Aircraft. Pt. 4. Test Cases by : W.D. Middleton
Download or read book A System for Aerodynamic Design and Analysis of Supersonic Aircraft. Pt. 4. Test Cases written by W.D. Middleton and published by . This book was released on 1980 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A System for Aerodynamic Design and Analysis of Supersonic Aircraft by :
Download or read book A System for Aerodynamic Design and Analysis of Supersonic Aircraft written by and published by . This book was released on 1980 with total page 119 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Design and Analysis System for Supersonic Aircraft by : W.D. Middleton
Download or read book Aerodynamic Design and Analysis System for Supersonic Aircraft written by W.D. Middleton and published by . This book was released on 1975 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Structural Merit Function for Aerodynamic Decelerators by : Melvin S. Anderson
Download or read book A Structural Merit Function for Aerodynamic Decelerators written by Melvin S. Anderson and published by . This book was released on 1969 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Structural merit function for aerodynamic decelerators.
Book Synopsis A System for Aerodynamic Design and Analysis of Supersonic Aircraft. Pt. 3. Computer Program Description by : W.D. Middleton
Download or read book A System for Aerodynamic Design and Analysis of Supersonic Aircraft. Pt. 3. Computer Program Description written by W.D. Middleton and published by . This book was released on 1980 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Proceedings of Retardation and Recovery Symposium by :
Download or read book Proceedings of Retardation and Recovery Symposium written by and published by . This book was released on 1963 with total page 488 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report contains the proceedings of the Retardation and Recovery Symposium sponsored by the Aeronautical Systems Division on 13 and 14 November 1962. The Introductory Session was opened with the Keynote Address which reviewed the use and applications of deployable aerodynamic decelerators throughout the past fifty (50) years and noted the areas in which additional work had to be accomplished. The four Technical Sessions deal with the latest significant developments in the retardation and recovery area. The Technical Sessions begin with presentations and discussions of investigations in the hypersonic and supersonic flight regimes followed by a technical analysis of transonic and supersonic flow phenomena. In addition, new aerodynamic decelerator designs and discussion of the wind tunnel tests pertaining to these designs, as well as overall reliability of recovery systems, are presented. The final Technical Session concludes with a discussion of the military, scientific, and general objectives for decelerators intended for future use.
Book Synopsis A System for Aerodynamic Design and Analysis of Supersonic Aircraft. Pt. 1. General Description and Theoretical Development by : W.D. Middleton
Download or read book A System for Aerodynamic Design and Analysis of Supersonic Aircraft. Pt. 1. General Description and Theoretical Development written by W.D. Middleton and published by . This book was released on 1980 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A System for Aerodynamic Design and Analysis of Supersonic Aircraft by : W. D. Middleton
Download or read book A System for Aerodynamic Design and Analysis of Supersonic Aircraft written by W. D. Middleton and published by . This book was released on 1980 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:
