Energy Absorber Design, Fabrication and Testing for a Passive Earth Entry Vehicle

Kellas, Sotiris; Mitcheltree, Robert A.

doi:10.2514/6.2002-1224

Cited by 8 publications

(38 citation statements)

References 4 publications

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“…Not surprisingly, the impact system for the passive vehicle appears to be modestly sensitive to the payload mass. For the passive approach, M-SAPE sizes the impact system as a solid foam energy absorber which is used in conjunction with impacting an infinitely hard surface, an assumption also used for the original MSR EEV [7]. However, unlike MSR, M-SAPE further assumes that the energy absorber is required to attenuate the kinetic energy of the payload only rather than that of the entire vehicle.…”

Section: Mmeev System Analysis For Planetary Entry Descent and Landingmentioning

confidence: 99%

Passive vs. parachute system architecture for robotic sample return vehicles

Maddock

Henning

Samarah

2016

2016 IEEE Aerospace Conference

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Abstract-The Multi-Mission Earth Entry Vehicle (MMEEV)is a flexible vehicle concept based on the Mars Sample Return (MSR) EEV design which can be used in the preliminary sample return mission study phase to parametrically investigate any trade space of interest to determine the best entry vehicle design approach for that particular mission concept. In addition to the trade space dimensions often considered (e.g. entry conditions, payload size and mass, vehicle size, etc.), the MMEEV trade space considers whether it might be more beneficial for the vehicle to utilize a parachute system during descent/landing or to be fully passive (i.e. not use a parachute).In order to evaluate this trade space dimension, a simplified parachute system model has been developed based on inputs such as vehicle size/mass, payload size/mass and landing requirements. This model works in conjunction with analytical approximations of a mission trade space dataset provided by the MMEEV System Analysis for Planetary EDL (M-SAPE) tool to help quantify the differences between an active (with parachute) and a passive (no parachute) vehicle concept.Preliminary results over a range of EEV and mission constraints (including entry conditions, vehicle size, payload mass, and landing requirements) are provided. For most sample return missions, the landing requirement (velocity and/or load) is ultimately determined by science considerations (e.g. sample preservation or containment). Regions of the trade space are identified where a parachute system is clearly more beneficial than the passive approach, and vice versa. Where the choice between the two architectures is less clear, additional considerations must also be taken into account including factors such as overall system reliability; system risk and complexity; and development and testing costs.

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Section: Mmeev System Analysis For Planetary Entry Descent and Landingmentioning

confidence: 99%

Passive vs. parachute system architecture for robotic sample return vehicles

Maddock

Henning

Samarah

2016

2016 IEEE Aerospace Conference

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“…It has been shown [10][11][12] that composite cellular structures can be treated using the same theory [13][14][15][16][17][18] as long as the cell-walls are designed to deform quasi-plastically and energy is absorbed in a similar way to that of metal cellular structures. One obvious difference between the deployable and conventional honeycombs is the flexible hinge.…”

Section: Energy Absorber Design and Optimizationmentioning

confidence: 99%

“…Design tools for the tailoring of composite cellular structures have been utilized by Kellas [10][11][12] who employed theory that was previously developed for isotropic cellular structures by Abramowicz, Wierzbicki and their co-workers [13][14][15][16][17][18]. This type of theoretical treatment requires the crosssection of the cellular structure to be regarded as being composed of an assemblage of basic elements such as "Y", "T" and "+".…”

Section: Energy Absorber Design and Optimizationmentioning

confidence: 99%

Deployable System for Crash—Load Attenuation

Kellas¹,

Jackson²

2010

J. Am. Helicopter Society

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An externally deployable honeycomb structure is investigated with respect to crash energy management for light aircraft. The new concept utilizes an expandable honeycomb-like structure to absorb impact energy by crushing. Distinguished by flexible hinges between cell wall junctions that enable effortless deployment, the new energy absorber offers most of the desirable features of an external airbag system without the limitations of poor shear stability, system complexity, and timing sensitivity. Like conventional honeycomb, once expanded, the energy absorber is transformed into a crush efficient and stable cellular structure. Other advantages, afforded by the flexible hinge feature, include a variety of deployment options such as linear, radial, and/or hybrid deployment methods. Radial deployment is utilized when omnidirectional cushioning is required. Linear deployment offers better efficiency, which is preferred when the impact orientation is known in advance. Several energy absorbers utilizing different deployment modes could also be combined to optimize overall performance and/or improve system reliability as outlined in the paper. Results from a series of component and full scale demonstration tests are presented as well as typical deployment techniques and mechanisms. LS-DYNA analytical simulations of selected tests are also presented.

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“…1 and 3 is the primary mechanism to protect the payload at landing. Kellas and Mitcheltree [15] describe a model of an energyabsorbing sphere that consists of three main components: a rigid inner shell to protect the OS canister, a crushable foam-filled cellular structure, and an outer shell. The cellular structure is made of fiber reinforcement and a matrix material with some variation in the stacking sequence.…”

Section: Impact Dynamicsmentioning

confidence: 99%

“…The theoretical approach of Kellas and Mitcheltree [15] has been implemented for this study. Figure 4 shows sample results from this implementation.…”

Section: Impact Dynamicsmentioning

confidence: 99%

An integrated tool for system analysis of sample return vehicles

Samareh

Maddock

Winski³

2012

2012 IEEE Aerospace Conference

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Abstract-The next important step in space exploration is the return of sample materials from extraterrestrial locations to Earth for analysis. Most mission concepts that return sample material to Earth share one common element: an Earth entry vehicle. The analysis and design of entry vehicles is multidisciplinary in nature, requiring the application of mass sizing, flight mechanics, aerodynamics, aerothermodynamics, thermal analysis, structural analysis, and impact analysis tools.Integration of a multidisciplinary problem is a challenging task; the execution process and data transfer among disciplines should be automated and consistent. This paper describes an integrated analysis tool for the design and sizing of an Earth entry vehicle. The current tool includes the following disciplines: mass sizing, flight mechanics, aerodynamics, aerothermodynamics, and impact analysis tools. Python and Java languages are used for integration. Results are presented and compared with the results from previous studies.

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Energy Absorber Design, Fabrication and Testing for a Passive Earth Entry Vehicle

Cited by 8 publications

References 4 publications

Passive vs. parachute system architecture for robotic sample return vehicles

Passive vs. parachute system architecture for robotic sample return vehicles

Deployable System for Crash—Load Attenuation

An integrated tool for system analysis of sample return vehicles

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