Design and Development of Inflatable Aeroshell Structure for IRVE-3

Jurewicz, David; Brown, Glen; Gilles, Brian; Taylor, Anthony P.; Sinclair, Robert; Tutt, Benjamin; Lichodziejewski, David; Kelley, Christopher; Hughes, Stephen J.

doi:10.2514/6.2011-2522

Cited by 15 publications

(7 citation statements)

References 1 publication

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“…For inflatable aeroshell, the structure was placed on a hydraulic ram and surrounded by metal tub. The displacements were measured using string potentiometers and laser scanning [48]. For static load testing of inflatable wing, the deflection is measured for point load at wing tip, distributed loading pattern and wing twist.…”

Section: Experimental Methods 1) Static Loadmentioning

confidence: 99%

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Inflatable structure for aerospace application: Historical perspective and future outlook

Dollah

Saad

CheIdris

2018

J. Fundam and Appl Sci.

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This is an overview topic of inflatable structure for aerospace application. An inflatable structure is a promising choice for a wide r application are inflatable wing, space antenna, solar array, inflatable aeroshell and inflatable aerodynamic decelerators. The advantages of inflatable structure are it offers the potential for compact stowing of lightweight structure. This will efficient packaging, easy to deploy and ultimately lead to reduction in mission cost.Historically, inflatable technology has been introduced as a concept in aerospace application with a patent on flying glider th Over the years, many concepts of inflatable were introduced but only a small number of concepts have progress beyond the stage of design and even fewer manage to be completed and used extensively.

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Section: Experimental Methods 1) Static Loadmentioning

confidence: 99%

“…Several researches on inflatable structure have used LS-DYNA especially the research on IAD. The analysis includes the process of deployment of the inflatable structure [52] or to perform FEA on IAD under static loading condition and to validate the result measured from the experiment [48,[53][54][55].…”

Section: Computational Analysismentioning

confidence: 99%

Inflatable structure for aerospace application: Historical perspective and future outlook

Dollah

Saad

CheIdris

2018

J. Fundam and Appl Sci.

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“…Pressurised gas, which is contained by an internal impermeable membrane, provides the braided tubular members with structural capacity by pre‐tensioning the fabric and behaving as a confined gas . Braided tubular fabric members usually have longitudinal reinforcement in the form of integral cords or secondary longitudinal reinforcing elements . The longitudinal reinforcement provides axial and bending stiffness to the member cross section, and locks the braid angle at the desired value.…”

Section: Introductionmentioning

confidence: 99%

Experimental Determination of Inflatable, Braided Tube Constitutive Properties

Clapp

Davids

Goupee

et al. 2015

Strain

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The primary objective of this study was to conduct constitutive tests of relatively large diameter inflatable, braided fabric tubes at different inflation pressures and braid angles in order to quantify the longitudinal modulus, in-plane shear modulus and effective lamina stiffness properties. The stiffness properties quantified here are of high interest because the same braided fabric tubes have been used in the construction of test articles for a major, multi-year, ground based test campaign led by the United States National Aeronautics and Space Administration. These properties are also input directly into high-fidelity yet computationally intensive 3D shell-based finite-element simulations of the large, inflatable structures. Experimental methods employed during this study included tension-torsion testing, uniaxial tension testing of individual fibre tows, and uniaxial tension testing of gas bladder coupons. Digital image correlation was used to measure all of the geometric information that is necessary to perform netting theory calculations. The test results indicate that fabric in-plane shear modulus is highly dependent on both braid angle and inflation pressure, but that longitudinal stiffness is quite small and relatively unaffected by braid angle and pressure. In addition to advancing the state-of-the art in experimental constitutive property determination of inflatable, braided fabric, this study includes the development of a method to back calculate lamina properties from the experimental results that are suitable for use as input to commonly used finite-element programmes. The digital image correlation data revealed spatial variation of shear strain that was important to consider when computing the gross shear stiffness. Digital image correlation data also captured the braid surface flattening with increasing inflation pressure, which supports the fibre de-crimping theory.

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“…The compression between each torus section creates a flat that increases the ability to react shear forces. Structural models have shown the inflated structure to carry the aerodynamic loading by the shear forces between the tori [13]. …”

Section: Attached Iadsmentioning

confidence: 99%

“…The FTPS is the thermal barrier to reduce the thermal loading on the inflatable structure and provides a smooth surface. The stacked toroid configuration provides a structure that reacts against the aerodynamic forces and decelerates the entry vehicle [6], [13].…”

Section: Attached Iadsmentioning

confidence: 99%

Morphing Hypersonic Inflatable Aerodynamic Decelerator

Green

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The ever growing complexity of missions to planetary bodies has pushed the Viking era rigid aeroshell designs to their operational limits. Plans for future robotic missions to Mars include 1 -2 metric ton payloads, and human missions to Mars push the envelope even further by requiring 40 -80 metric ton payloads. Aeroshell designers have been driven to Hypersonic Inflatable Aerodynamic Decelerator (HIAD) technologies for the promise of entry vehicles that can deliver larger payloads to higher elevations with increased precision and increased aeroshell volume efficiency with their ability to obtain aeroshell diameters not possible with rigid aeroshells. This thesis meets the following goals by evaluating morphed aeroshell shapes applied to two HIAD cases: 1) develop a tool for evaluating morphed aeroshell shapes; 2) determine a morphed aeroshell shape that will generate the greatest change in lift-over-drag, | / |, for a given entry vehicle at a fixed angle of attack, while keeping the stagnation point heat flux below 30 W/cm 2 . 3) Provide a basis for future research of morphing HIAD structures.ii

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Design and Development of Inflatable Aeroshell Structure for IRVE-3

Cited by 15 publications

References 1 publication

Inflatable structure for aerospace application: Historical perspective and future outlook

Inflatable structure for aerospace application: Historical perspective and future outlook

Experimental Determination of Inflatable, Braided Tube Constitutive Properties

Morphing Hypersonic Inflatable Aerodynamic Decelerator

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