Patent Application
20190359096
This application claims the benefit of Indian Patent Application No. 201811019131, filed May 22, 2018, which is incorporated herein by reference in its entirety.
The following description relates to a collapsible structure and, more particularly, to a collapsible structure with varying stiffness-based energy attenuation system.
Currently, certain helicopter seating systems employ fixed profile energy attenuation systems. Energy attenuation capabilities of such fixed profile energy attenuation systems is achieved by wire bending actions to provide for a variation in load with stroke. Wire bending uses forces required to bend a metallic wire, which has a rectangular and varying cross section, and to draw it through offset rollers to provide for the load variation.
Performance characteristics of energy attenuation systems that make use of wire bending tend to vary depending on uncertainties in wire material properties, taper angles and surface finishes. In addition stroke length required to attenuate the energy is relatively high (e.g., approximately 8″ for a 95th Percentile occupant size).
According to an aspect of the disclosure, a collapsible structure is provided and includes a hub, an exterior skin surrounding the hub and a plurality of spokes extending outwardly from the hub to the exterior skin, each spoke being tapered along a length thereof.
In accordance with additional or alternative embodiments, the hub, the exterior skin and the plurality of spokes are symmetric about a central longitudinal axis of the hub.
In accordance with additional or alternative embodiments, each spoke is uniformly distant from neighboring spokes about the hub.
In accordance with additional or alternative embodiments, the exterior skin is polygonal with each vertex being connected to a spoke.
In accordance with additional or alternative embodiments, the hub is an elongate hub with a first end and a second end opposite the first end, the exterior skin is an elongate exterior skin with first and second ends corresponding to the first and second ends of the elongate hub and each spoke is tapered along respective lengths of the elongate hub and the elongate exterior skin.
In accordance with additional or alternative embodiments, the tapering of each spoke is uniform along the respective lengths of the elongate hub and the elongate exterior skin.
In accordance with additional or alternative embodiments, each spoke is thickest at the respective first ends of the elongate hub and the elongate exterior skin and each spoke is thinnest at the respective second ends of the elongate hub and the elongate exterior skin.
In accordance with additional or alternative embodiments, each spoke has a thickness of about 0.1 inches (2.54 mm) at the respective first ends of the elongate hub and the elongate exterior skin and each spoke has a thickness of about 0.06 inches (1.524 mm) at the respective second ends of the elongate hub and the elongate exterior skin.
According to another aspect of the disclosure, an energy attenuation system is provided and includes a housing, a crusher element, rivets disposed to support the crusher element within the housing and at least one collapsible structure. The at least one collapsible structure is disposed to deformably support the crusher element within the housing following failures of the rivets. The at least one collapsible structure is configured to collapse at successive longitudinal portions in response to correspondingly successive compressive forces applied by the crusher element following the failures of the rivets.
According to yet another aspect of the disclosure, an energy attenuation system is provided and includes a housing, a crusher element, rivets disposed to support the crusher element within the housing and at least one collapsible structure. The at least one collapsible structure is disposed to deformably support the crusher element within the housing following failures of the rivets. The at least one collapsible structure includes a hub, an exterior skin surrounding the hub and a plurality of spokes extending outwardly from the hub to the exterior skin, each spoke being tapered along a length thereof.
In accordance with additional or alternative embodiments, the housing includes an aircraft housing, the crusher element includes a seat and failures of the rivets occur in an event a body in the seat experiences an acceleration of about 13-14.5 Gs.
In accordance with additional or alternative embodiments, the at least one collapsible structure is a single use feature.
In accordance with additional or alternative embodiments, the at least one collapsible structure includes multiple collapsible structures at corners of the seat.
In accordance with additional or alternative embodiments, the hub, the exterior skin and the plurality of spokes are symmetric about a central longitudinal axis of the hub.
In accordance with additional or alternative embodiments, each spoke is uniformly distant from neighboring spokes about the hub.
In accordance with additional or alternative embodiments, the exterior skin is polygonal with each vertex being connected to a spoke.
In accordance with additional or alternative embodiments, the hub is an elongate hub with a first end proximate to the housing and a second end opposite the first end and proximate to the crusher element, the exterior skin is an elongate exterior skin with first and second ends corresponding to the first and second ends of the elongate hub and each spoke is tapered along respective lengths of the elongate hub and the elongate exterior skin.
In accordance with additional or alternative embodiments, the tapering of each spoke is uniform along the respective lengths of the elongate hub and the elongate exterior skin.
In accordance with additional or alternative embodiments, each spoke is thickest at the respective first ends of the elongate hub and the elongate exterior skin and each spoke is thinnest at the respective second ends of the elongate hub and the elongate exterior skin.
In accordance with additional or alternative embodiments, each spoke has a thickness of about 0.1 inches (2.54 mm) at the respective first ends of the elongate hub and the elongate exterior skin and each spoke has a thickness of about 0.06 inches (1.524 mm) at the respective second ends of the elongate hub and the elongate exterior skin.
These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
The subject matter, which is regarded as the disclosure, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features and advantages of the disclosure are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
As will be described below, an energy attenuation system is provided that is operable based on performance of a collapsible structure with varying stiffness and can be used in helicopter seating systems for example. The collapsible structure of the energy attenuation system absorbs input kinetic energy by successive buckling or crushing due to axial compression. The varying stiffness along its length will assist in achieving variable energy absorption for various occupants ranging from those in the 5th percentile occupant size to those in the 95th percentile.
In an operation of the energy attenuation system, once the occupant or the seat the occupant is sitting in reaches an acceleration of about 13-14.5 Gs, rivets that normally hold or prevent crusher movement are sheared and thus allow for the crusher element to start stroking on the collapsible structure whereby the crusher element applies an axial compression load onto the collapsible structure. Impact kinetic energy is thus utilized to deform the collapsible structure as the impact kinetic energy is converted into strain energy. The strain energy of the collapsible structure may be expressed as U=1/2(Vσϵ), where, V=a volume of the collapsible structure, σ=an applied compressive stress, ϵ=strain in the collapsible structure.
With reference to
That is, when the pilot's body accelerates downwardly into the seat 130 of the crusher element 13 with an acceleration that is greater than about 13-14.5 Gs, the rivets 14 fail due to shearing and the crusher element 13 begins to accelerate toward the housing 11. The at least one collapsible structure 20 acts to slow the acceleration of the crusher element 13 or to decelerate the crusher element 13 by deformably collapsing so as to remove or attenuate the energy of the crusher element 13. In accordance with embodiments and, as will be described below, the at least one collapsible structure 20 may be configured to collapse at successive longitudinal portions in response to correspondingly successive compressive forces applied by the crusher element 13 following the failures of the rivets 14.
With reference to
With reference to
As shown in
That is, as shown in
In accordance with still further embodiments, the tapering of each elongate spoke 50 may be is uniform, smooth and/or continuous along the respective lengths of the elongate hub 30 and the elongate exterior skin 40.
The tapering of the elongate spokes 50 will result in varying stiffness along the length of each collapsible structure 20. For example, the top of the collapsible structure 20 (i.e., the first ends 301 and 401) will have a minimum stiffness and the bottom of the collapsible structure 20 (i.e., the second ends 302 and 402) will have a maximum stiffness. This varying stiffness will help in achieving variable energy absorption of various occupants ranging from those in the 5th percentile occupant size to those in the 95th percentile.
With reference to
The energy absorption system 10 described herein can be packaged in various applications, such as helicopter seating systems with the crusher elements 13 being arranged in telescopic tubes of the buckets of the seating systems and the collapsible structure(s) accommodated in fixed bases.
The collapsible structure 20 described herein as having varying stiffness based energy attenuation capabilities for use in an energy absorption system 10 may significantly lower stroke length and weight as compared to existing wire bender designs and can be altered or customized for particular instances. In addition, in an event the collapsible structure 20 is produced using additive manufacturing techniques, performance characteristics thereof could be made predictable and consistent.
While the disclosure is provided in detail in connection with only a limited number of embodiments, it should be readily understood that the disclosure is not limited to such disclosed embodiments. Rather, the disclosure can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the disclosure. Additionally, while various embodiments of the disclosure have been described, it is to be understood that the exemplary embodiment(s) may include only some of the described exemplary aspects. Accordingly, the disclosure is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
| Number | Date | Country | Kind |
|---|---|---|---|
| 20181101931 | May 2018 | IN | national |
