IRVE-II Post-Flight Trajectory Reconstruction

O’Keefe, Stephen A.; Bose, David M.

doi:10.2514/6.2010-7515

Cited by 27 publications

(10 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…There is limited evidence that a sharp shoulder shape (which prevents significant movement of the vortex shedding location) and a small backshell (which will generate small aerodynamic moments, relative to the forebody, due to small area located relatively close to the center of gravity) should promote vehicle stability even into the subsonic regime. Recent flight tests of the IRVE inflatable decelerators [13] support this viewpoint. More aerodynamic simulation and ballistic range testing are needed to confirm the stability of the blunt open-backed vehicle, but it is currently assumed to be feasible.…”

Section: A Shape and Sizementioning

confidence: 68%

Structures and Mechanisms Design Concepts for Adaptive Deployable Entry Placement Technology

Yount

Arnold

Gage³

et al. 2013

AIAA Aerodynamic Decelerator Systems (ADS) Conference

View full text Add to dashboard Cite

System studies have shown that large deployable aerodynamic decelerators such as the Adaptive Deployable Entry and Placement Technology (ADEPT) concept can revolutionize future robotic and human exploration missions involving atmospheric entry, descent and landing by significantly reducing the maximum heating rate, total heat load, and deceleration loads experienced by the spacecraft during entry [1][2][3]. ADEPT and the Hypersonic Inflatable Aerodynamic Decelerator (HIAD) [4] share the approach of stowing the entry system in the shroud of the launch vehicle and deploying it to a much larger diameter prior to entry.The ADEPT concept provides a low ballistic coefficient for planetary entry by employing an umbrella-like deployable structure consisting of ribs, struts and a fabric cover that form an aerodynamic decelerator capable of undergoing hypersonic flight. The ADEPT "skin" is a 3-D woven carbon cloth that serves as a thermal protection system (TPS) and as a structural surface that transfers aerodynamic forces to the underlying ribs [5]. This paper focuses on design activities associated with integrating ADEPT components (cloth, ribs, struts and mechanisms) into a system that can function across all configurations and environments of a typical mission concept: stowed during launch, in-space deployment, entry, descent, parachute deployment and separation from the landing payload. The baseline structures and mechanisms were selected via trade studies conducted during the summer and fall of 2012. They are now being incorporated into the design of a ground test article (GTA) that will be fabricated in 2013. It will be used to evaluate retention of the stowed configuration in a launch environment, mechanism operation for release, deployment and locking, and static strength of the deployed decelerator. Of particular interest are the carbon cloth interfaces, underlying hot structure, (Advanced CarbonCarbon ribs) and other structural components (nose cap, struts, and main body) designed to withstand the pressure and extremely high heating experienced during planetary entry.[1] Venkatapathy, E., et al., "Adaptive Deployable Entry and Placement Technology (ADEPT): A Feasibility Study for Human Missions to Mars," 21st AIAA

show abstract

Section: A Shape and Sizementioning

confidence: 68%

Structures and Mechanisms Design Concepts for Adaptive Deployable Entry Placement Technology

Yount

Arnold

Gage³

et al. 2013

AIAA Aerodynamic Decelerator Systems (ADS) Conference

View full text Add to dashboard Cite

show abstract

“…(1) (2) In order to reduce any sudden transient in the estimated state or uncertainties where the pressures are introduced into the filter, the measurement is "faded" in and out. This is accomplished by increasing the modeled measurement uncertainty at the end points of the pressure measurement and ramping the uncertainty to its modeled value over a 1.2 second span; this progressively weights the measurement less as it is being removed from the BET.…”

Section: Methodsmentioning

confidence: 99%

“…At a navigated altitude of 88 km, pitch and yaw control were disabled to allow aerodynamic forces to govern angle of attack and sideslip, while roll control continued to hold a planet relative bank angle within ± 5° throughout the experiment. IRVE-3 entered the atmosphere at Mach 10, reaching a peak heat rate of 14 W/cm 2 and peak deceleration of 20 g's. After the experiment concluded at a pre-defined Mach number of 0.7, the center of mass was mechanically translated back and forth to obtain the vehicle's angle of attack response.…”

Section: Mission Descriptionmentioning

confidence: 99%

IRVE-3 Post-Flight Reconstruction

Olds

Beck

Bose

et al. 2013

AIAA Aerodynamic Decelerator Systems (ADS) Conference

View full text Add to dashboard Cite

“…Inflatable, braided fabric tubular members are seeing increased use as structural members in civilian, military and space applications due to their light weight, ability to be packed into a small volume, and rapid deployment . Recently, the United States National Aeronautics and Space Administration (NASA) has investigated the use of inflated torus elements with braided fabric tubular shells in Hypersonic Inflatable Aerodynamic Decelerator (HIAD) applications . HIADs show great promise for use in space mission applications because they permit the landing of large payloads due their substantial frontal area relative to their stowed volume and total weight, and are also ideal for landings in thin atmospheres .…”

Section: Introductionmentioning

confidence: 99%

Experimental Determination of Inflatable, Braided Tube Constitutive Properties

Clapp

Davids

Goupee

et al. 2015

Strain

View full text Add to dashboard Cite

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.

show abstract

IRVE-II Post-Flight Trajectory Reconstruction

Cited by 27 publications

References 1 publication

Structures and Mechanisms Design Concepts for Adaptive Deployable Entry Placement Technology

Structures and Mechanisms Design Concepts for Adaptive Deployable Entry Placement Technology

IRVE-3 Post-Flight Reconstruction

Experimental Determination of Inflatable, Braided Tube Constitutive Properties

Contact Info

Product

Resources

About