Overview of the National Aeronautics and Space Administration Subsonic Rotary Wing Aeronautics Research Program in Rotorcraft Crashworthiness

Jackson, Karen E.; Fuchs, Yvonne T.; Kellas, Sotiris

doi:10.1061/(asce)0893-1321(2009)22:3(229)

Cited by 20 publications

(2 citation statements)

References 6 publications

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“…NASA [28] conducted drop tests on representative fuselage sections with attached energy absorbers at impact speeds between 7.3 to 11.6m/s. This corresponded to a nominal strain rate of between 15 and 23 −1 in these absorbers, which represented the likely strain rates experienced in a survivable crash scenario.…”

Section: Test Methodsmentioning

confidence: 99%

Crush responses of composite cylinder under quasi-static and dynamic loading

Chiu

Falzon

Ruan

et al. 2015

Composite Structures

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General rights Copyright for the publications made accessible via the Queen's University Belfast Research Portal is retained by the author(s) and / or other copyright owners and it is a condition of accessing these publications that users recognise and abide by the legal requirements associated with these rights. AbstractDespite the abundance of studies investigating the performance of composite structures under crush loading, disagreement remains in the literature regarding the effect of increased strain rate on the crush response. This study reports an experimental investigation of the behaviour of a carbon-epoxy composite energy absorber under static and dynamic loading with a strain rate of up to 100 −1 . Good consistency, among samples tested under the same strain rate, was achieved in the identified damage modes and the measured force responses. The energy absorption was found to be independent of strain rate as the total energy absorption appeared to be dominated by fibredominated fracture, which is independent of strain rate within the studied range. The results from this study can inform the design of energy absorbing structures.

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Section: Test Methodsmentioning

confidence: 99%

Crush responses of composite cylinder under quasi-static and dynamic loading

Chiu

Falzon

Ruan

et al. 2015

Composite Structures

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“…Currently available finite element (FE) codes such as LS-DYNA are capable of modeling accurate vehicle structural response during a crash impact (Ref. 6). However, validation of test dummy models in relevant impact scenarios is necessary to confidently employ FE analyses in both the design and safety evaluation phase of rotorcraft.…”

Section: Introductionmentioning

confidence: 99%

Finite Element Model of the THOR-NT Dummy under Vertical Impact Loading for Aerospace Injury Prediction: Model Evaluation and Sensitivity Analysis

Putnam¹,

Untaroiu²,

Littell³

et al. 2015

j am helicopter soc

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Anthropometric test devices, commonly referred to as crash test dummies, are effective tools used to conduct aerospace safety evaluations. In this study, the latest finite element (FE) model of the Test Device for Human Occupant Restraint (THOR) dummy was simulated under vertical impact conditions based on data recorded in a series of drop tests conducted at the NASA Langley Research Center. The purpose of this study was threefold. The first was to improve and then evaluate this FE model for use in a vertical loading environment through kinematic and kinetic response comparisons. The second was to evaluate dummy injury criteria under variable impact conditions. The last was to determine the response sensitivity of the FE model with respect to its preimpact postural position. Results demonstrate that the updated FE model performs well under vertical loading and predicts injury criteria values close to those recorded in testing. In the postural sensitivity study, the head injury criteria response and peak lumbar load show to be primarily sensitive to the preimpact head angle and thorax angle, respectively. The promising results shown by the dummy model recommends its use in impact simulations with vertical deceleration pulses close to those used in this study. In addition, it is believed that assigning accurate viscoelastic material properties to the deformable parts of the model may further increase the model fidelity for a larger range of impacts.

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Large Field Photogrammetry Techniques in Aircraft and Spacecraft Impact Testing

Littell

2011

Dynamic Behavior of Materials, Volume 1

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The Landing and Impact Research Facility (LandIR) at NASA Langley Research Center is a 240 ft. high A-frame structure which is used for full-scale crash testing of aircraft and rotorcraft vehicles. Because the LandIR provides a unique capability to introduce impact velocities in the forward and vertical directions, it is also serving as the facility for landing tests on full-scale and sub-scale Orion spacecraft mass simulators. Recently, a threedimensional photogrammetry system was acquired to assist with the gathering of vehicle flight data before, throughout and after the impact. This data provides the basis for the post-test analysis and data reduction.Experimental setups for pendulum swing tests on vehicles having both forward and vertical velocities can extend to 50 x 50 x 50 foot cubes, while weather, vehicle geometry, and other constraints make each experimental setup unique to each test. This paper will discuss the specific calibration techniques for large fields of views, camera and lens selection, data processing, as well as best practice techniques learned from using the large field of view photogrammetry on a multitude of crash and landing test scenarios unique to the LandIR.

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Overview of the National Aeronautics and Space Administration Subsonic Rotary Wing Aeronautics Research Program in Rotorcraft Crashworthiness

Cited by 20 publications

References 6 publications

Crush responses of composite cylinder under quasi-static and dynamic loading

Crush responses of composite cylinder under quasi-static and dynamic loading

Finite Element Model of the THOR-NT Dummy under Vertical Impact Loading for Aerospace Injury Prediction: Model Evaluation and Sensitivity Analysis

Large Field Photogrammetry Techniques in Aircraft and Spacecraft Impact Testing

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