Log in

Relevant bibliographies by topics / Hypersonic Inflatable Aerodynamic Decelerators

Contents

Journal articles
Dissertations / Theses
Book chapters
Conference papers

Academic literature on the topic 'Hypersonic Inflatable Aerodynamic Decelerators'

Author: Grafiati

Published: 4 June 2021

Last updated: 14 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Hypersonic Inflatable Aerodynamic Decelerators.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Hypersonic Inflatable Aerodynamic Decelerators"

1

Young, Andrew C., William G. Davids, F. McNeil Cheatwood, and Michael C. Lindell. "Structural analysis of hypersonic inflatable aerodynamic decelerator pressure tub testing." Thin-Walled Structures 131 (October 2018): 869–82. http://dx.doi.org/10.1016/j.tws.2018.07.035.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Guo, Jinghui, Guiping Lin, Xueqin Bu, Shiming Fu, and Yanmeng Chao. "Effect of static shape deformation on aerodynamics and aerothermodynamics of hypersonic inflatable aerodynamic decelerator." Acta Astronautica 136 (July 2017): 421–33. http://dx.doi.org/10.1016/j.actaastro.2017.03.019.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Brune, Andrew J., Serhat Hosder, Karl T. Edquist, and Steven A. Tobin. "Thermal Protection System Response Uncertainty of a Hypersonic Inflatable Aerodynamic Decelerator." Journal of Spacecraft and Rockets 54, no. 1 (2017): 141–54. http://dx.doi.org/10.2514/1.a33732.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Wang, Jingjing, Li Yu, Xue Yang, and Xiaoshun Zhao. "Study on the performance of inflatable decelerator under hypersonic aerodynamic load." IOP Conference Series: Materials Science and Engineering 715 (January 3, 2020): 012073. http://dx.doi.org/10.1088/1757-899x/715/1/012073.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Brune, Andrew J., Thomas K. West, Serhat Hosder, and Karl T. Edquist. "Uncertainty Analysis of Mars Entry Flows over a Hypersonic Inflatable Aerodynamic Decelerator." Journal of Spacecraft and Rockets 52, no. 3 (2015): 776–88. http://dx.doi.org/10.2514/1.a33131.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Hollis, Brian R. "Surface Heating and Boundary-Layer Transition on a Hypersonic Inflatable Aerodynamic Decelerator." Journal of Spacecraft and Rockets 55, no. 4 (2018): 856–76. http://dx.doi.org/10.2514/1.a34046.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Brune, Andrew J., Serhat Hosder, and Karl T. Edquist. "Uncertainty Analysis of Fluid-Structure Interaction of a Deformable Hypersonic Inflatable Aerodynamic Decelerator." Journal of Spacecraft and Rockets 53, no. 4 (2016): 654–68. http://dx.doi.org/10.2514/1.a33532.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Zhao, Yatian, Chao Yan, Hongkang Liu, and Yupei Qin. "Assessment of laminar-turbulent transition models for Hypersonic Inflatable Aerodynamic Decelerator aeroshell in convection heat transfer." International Journal of Heat and Mass Transfer 132 (April 2019): 825–36. http://dx.doi.org/10.1016/j.ijheatmasstransfer.2018.11.025.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Zhao, Yatian, Hongkang Liu, Zaijie Liu, and Chao Yan. "Numerical study of the cone angle effects on transition and convection heat transfer for hypersonic inflatable aerodynamic decelerator aeroshell." International Communications in Heat and Mass Transfer 110 (January 2020): 104406. http://dx.doi.org/10.1016/j.icheatmasstransfer.2019.104406.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

Baginski, Frank, and Kenneth Brakke. "Deployment Analysis of Pneumatic Envelopes Including Ascending Balloons and Inflatable Aerodynamic Decelerators." Journal of Spacecraft and Rockets 49, no. 2 (2012): 413–21. http://dx.doi.org/10.2514/1.a32119.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Dissertations / Theses on the topic "Hypersonic Inflatable Aerodynamic Decelerators"

1

Slagle, Adam Christopher. "Morphing Hypersonic Inflatable Aerodynamic Decelerator (HIAD) Mechanisms and Controls." Diss., Virginia Tech, 2018. http://hdl.handle.net/10919/96194.

Full text

Abstract:

To enable a crewed mission to Mars, precision landing capabilities of Entry, Descent, and Landing (EDL) systems must be improved. The need for larger payloads, higher landing sites, and controllability has motivated the National Aeronautics and Space Administration (NASA) to invest in new technologies to replace traditional rigid aeroshell systems, which are limited in size by the payload envelope of existing launch vehicles. A Hypersonic Inflatable Aerodynamic Decelerator (HIAD) is an emerging technology that provides an increased drag area by inflating the aeroshell to diameters not possible with rigid aeroshells, allowing the vehicle to decelerate higher in the atmosphere, offering access to higher landing sites with more timeline margin. To enable a crewed mission to Mars, future entry vehicles will require precision landing capabilities that go beyond heritage EDL guidance strategies that utilize fuel-intensive and error-prone bank reversals. A novel Direct Force Control (DFC) approach of independently controlling the lift and side force of a vehicle that utilizes a HIAD with an aerodynamic shape morphing capability is proposed. To date, the mechanisms and controls required to morph an inflatable structure to generate lift have not been explored. In this dissertation, novel morphing HIAD concepts are investigated and designed to satisfy mission requirements, aerodynamic tools are built to assess the aerodynamic performance of morphed blunt body shapes, and a structural feasibility study is performed using models correlated to test data to determine the forces required to generate the desired shape change based on a crewed mission to Mars. A novel control methodology is introduced by applying a unique DFC strategy to a morphing HIAD to enhance precision landing capabilities of EDL systems, and the ability of a morphing HIAD to safely land a vehicle on Mars is assessed by performing a closed-loop feedback simulation for a Mars entry trajectory. Finally, a control mechanism is demonstrated on a small-scale inflatable structure. Conclusions and contributions of this research are presented along with a discussion of future research opportunities of morphing HIADs.<br>PHD

APA, Harvard, Vancouver, ISO, and other styles

2

Atkins, Brad Matthew. "Mars Precision Entry Vehicle Guidance Using Internal Moving Mass Actuators." Diss., Virginia Tech, 2014. http://hdl.handle.net/10919/50648.

Full text

Abstract:

Many landing sites of scientific interest on Mars including most of the Southern Hemisphere at elevations above 2km Mars Orbiter Laser Altimeter reference are inaccessible due to current limitations in precision entry guidance and payload deceleration. Precision guidance and large payload deceleration is challenging due to the thin Martian atmosphere, large changes in free stream conditions during entry, and aerothermal and aerodynamic instability concerns associated with control systems with direct external flow field interaction. Such risks have descoped past Mars missions to unguided entry with the exception of Mars Science Laboratory's (MSL) bank angle guidance. Consequently, prior to MSL landing ellipses were on the order of 100's of km. MSL has approached the upper limit of payload deceleration capability for rigid, blunt body sphere cone aeroshells used on all successful Mars entry missions. Hypersonic Inflatable Aerodynamic Decelerators (HIADS) are in development for larger payload deceleration capability through inflated aeroshell diameters greater than rigid aeroshells constrained by the launch rocket diameter, but to date there has been limited dynamics, control, and guidance development for their use on future missions. This dissertation develops internal moving mass actuator (IMMA) control systems for improving Mars precision entry guidance of rigid capsules and demonstrating precision guidance capability for HIADs. IMMAs provide vehicle control moments without direct interaction with the external flow field and can increase payload mass delivered through reducing propellant mass for control and using portions of the payload for the IMMAs. Dynamics models for entry vehicles with rotation and translation IMMAs are developed. IMMA control systems using the models are developed for two NASA vehicle types: a 2.65 m, 602 kg Mars Phoenix-sized entry capsule and an 8.3 m, 5.9 metric ton HIAD approaching payload requirements for robotic precursor missions for future human missions. Linear Quadratic controllers with integral action for guidance command tracking are developed for translation and rotation IMMA configurations. Angle of attack and sideslip guidance laws are developed as an alternative to bank angle guidance for decoupling range and cross-range control for improved precision entry guidance. A new variant of the Apollo Earth return terminal guidance algorithm is implemented to provide the closed-loop angle of attack range control commands. Nonlinear simulations of the entire 8 degree of freedom closed-loop systems demonstrate precision guidance to nominal trajectories and final targets for off-nominal initial entry conditions for flight path angle, range, cross-range, speed and attitude. Mechanical power studies for IMMA motion show rotation IMMA require less total mechanical power than translation actuators, but both systems have low nominal mechanical power requirements (below 100 Watts). Precision guidance for both systems to terminal targets greater than 38 km down-range from an open-loop ballistic entry is shown for low mechanical power, low CM displacement, (< 4.5 in) and at low internal velocities (< 2 in/s) over significant dynamic pressure changes. The collective precision guidance results and low mechanical power requirements show IMMA based entry guidance control systems constitute a promising alternative to thruster based control systems for future Mars landers.<br>Ph. D.

APA, Harvard, Vancouver, ISO, and other styles

3

Tanner, Christopher Lee. "Aeroelastic analysis and testing of supersonic inflatable aerodynamic decelerators." Diss., Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/47534.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

Book chapters on the topic "Hypersonic Inflatable Aerodynamic Decelerators"

1

Abraham, Nijo, Ralph Buehrle, Justin Templeton, Mike Lindell, and Sean Hancock. "Modal Test of Six-Meter Hypersonic Inflatable Aerodynamic Decelerator." In Special Topics in Structural Dynamics, Volume 6. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-04729-4_34.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Hypersonic Inflatable Aerodynamic Decelerators"

1

Green, Justin S., Barry Dunn, and Robert Lindberg. "Morphing Hypersonic Inflatable Aerodynamic Decelerator." In AIAA Aerodynamic Decelerator Systems (ADS) Conference. American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-1256.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Brune, Andrew J., Thomas West, Serhat Hosder, and Karl T. Edquist. "Uncertainty Analysis of Mars Entry Flows over Hypersonic Inflatable Aerodynamic Decelerators." In 11th AIAA/ASME Joint Thermophysics and Heat Transfer Conference. American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2672.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Beck, Robin A., Susan White, James Arnold, et al. "Overview of Initial Development of Flexible Ablators for Hypersonic Inflatable Aerodynamic Decelerators." In 21st AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar. American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2511.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Kushner, Laura K., Justin Littell, and Alan Cassell. "Photogrammetry of a Hypersonic Inflatable Aerodynamic Decelerator." In AIAA Aerodynamic Decelerator Systems (ADS) Conference. American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-1284.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Santos, Mario, Serhat Hosder, and Thomas K. West. "Multi-Fidelity Turbulent Heating Prediction of Hypersonic Inflatable Aerodynamic Decelerators with Surface Scalloping." In AIAA AVIATION 2020 FORUM. American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-2724.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Polsgrove, Tara P., Herbert D. Thomas, Alicia Dwyer Cianciolo, Tim Collins, and Jamshid Samareh. "Mission and design sensitivities for human Mars landers using Hypersonic Inflatable Aerodynamic Decelerators." In 2017 IEEE Aerospace Conference. IEEE, 2017. http://dx.doi.org/10.1109/aero.2017.7943887.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Hughes, Stephen, F. Cheatwood, Robert Dillman, et al. "Hypersonic Inflatable Aerodynamic Decelerator (HIAD)Technology Development Overview." In 21st AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar. American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2524.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Bose, David M., Jeremy Shidner, Richard Winski, Carlie Zumwalt, F. M. Cheatwood, and Stephen J. Hughes. "The Hypersonic Inflatable Aerodynamic Decelerator (HIAD) Mission Applications Study." In AIAA Aerodynamic Decelerator Systems (ADS) Conference. American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-1389.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Sheta, Essam F., Vinod Venugopalan, and Maxim de Jong. "Development and Performance Assessment of Hypersonic Inflatable Aerodynamic Decelerator." In 23rd AIAA Aerodynamic Decelerator Systems Technology Conference. American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-2166.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

Cassell, Alan, Gregory Swanson, R. Johnson, Stephen Hughes, and F. Cheatwood. "Overview of Hypersonic Inflatable Aerodynamic Decelerator Large Article Ground Test Campaign." In 21st AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar. American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2569.

Full text

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!