This invention relates generally to composite materials, and more particularly, to a multifunctional structural power and lighting system.
A rotorcraft may include one or more rotor systems. One example of a rotorcraft rotor system is a main rotor system. A main rotor system may generate aerodynamic lift to support the weight of the rotorcraft in flight and thrust to counteract aerodynamic drag and move the rotorcraft in forward flight. Another example of a rotorcraft rotor system is a tail rotor system. A tail rotor system may generate thrust in the same direction as the main rotor system's rotation to counter the torque effect created by the main rotor system.
Particular embodiments of the present disclosure may provide one or more technical advantages. A technical advantage of one embodiment may include the capability to provide electrical power to lighting and other devices. A technical advantage of one embodiment may also include the capability to eliminate undesirable weight from a vehicle by replacing some conventional wiring harnesses. A technical advantage of one embodiment may also include the capability to provide redundant electrical power such that the lighting or other electrical device is not subject to a single point of failure.
Certain embodiments of the present disclosure may include some, all, or none of the above advantages. One or more other technical advantages may be readily apparent to those skilled in the art from the figures, descriptions, and claims included herein.
To provide a more complete understanding of the present invention and the features and advantages thereof, reference is made to the following description taken in conjunction with the accompanying drawings, in which:
Rotorcraft 100 represents one example of a vehicle that includes a variety of different electrical devices. Conventional internal and external electrical devices are typically provided with power by wiring harnesses in accordance with traditional circuit designs. However, conventional wiring harnesses are singular in function and add undesirable weight to the vehicle. For example, clamps, fasteners, cable ties, and other items that may be required for installation of a conventional wiring harness, add undesirable weight and consume valuable space in the vehicle. Further, the wiring itself can be an undesirable single point of failure; for example, battle damage from a projectile can sever the wiring, thus breaking the circuit and rendering the electrical device inoperable. Further, conventional electrical devices can generate heat that may require dissipation through a thermal conductor or heat sink, which can further result in undesired weight.
Accordingly, teachings of certain embodiments recognize the capability to provide a structural power system that may eliminate the need for some conventional wiring harnesses. Teachings of certain embodiments recognize that the structural power system may be integrated with structural components of rotorcraft 100, such as a structural aircraft panel.
Teachings of certain embodiments recognize that structural composite 230 may conduct electricity through the in-plane conductive layers 234 while retaining insulative properties in the perpendicular direction. In addition, teachings of certain embodiments recognize that structural composite 230 may conduct heat through the in-plane conductive layers 234 while retaining insulative properties in the perpendicular direction.
Conductive members 236 extend through at least some of the insulative layers 232 to provide an electrical and/or thermal connection between adjacent conductive layers 234. In some embodiments, conductive members 236 may be provided at the exterior edges of structural composite 230 and/or in interior portions of structural composite 230. Teachings of certain embodiments recognize that conductive members 236 may short together multiple conductive layers 234 so as to provide redundant conductive paths. For example, sample structural composites 230 were subject to ballistic testing with a 7.62×39 mm ball-type (aligned) round, a 0.50 cal AP (aligned) round, and a 0.50 cal AP (tumbled) round. In this ballistic testing, the structural composite 230 did not suffer from degradation in electrical behavior due to the ballistic damage (other than loss of insulation material in the area immediately surrounding the projectile impacts).
In one example embodiment, conductive members 236 are formed by first plasma etching away a selective amount of insulative layers 232 near the edges and then spraying a zinc-tin alloy to short the conductive layers 234. Teachings of certain embodiments recognize, however, that conductive layers 234 may be electrically and/or thermally coupled in a variety of ways. Furthermore, as will be explained in greater detail below, selective conductive layers 234 may remain separated in various combinations to enable multiple conductive paths to multiple electrical devices.
In the example of
In some embodiments, insulative layers 232 and/or conductive layers 234 are nanoscale thickness. For example, in some embodiments, conductive layers 234 are less than 500 nanometers thick. In particular embodiments, conductive layers 234 are 150 nanometers thick. In two example configurations, conductive layers 234 are 150 nanometers thick, and insulative layers 232 are 0.8 millimeters or 0.6 millimeters thick. In these example configurations, structural composite 230 may transmit a current of approximately 50 amps in some settings. In another example configuration, structural composite 230 may transmit a current of approximately 25 amps if the insulative layers 232 are 0.5 millimeters thick and the conductive layers 234 are approximately 75 nanometers thick.
In some embodiments, structural composite 230 may exhibit structural properties. For example, in some embodiments, structural composite 230 may exhibit tensile strengths up to 50% greater than that for a pure aluminum panel of the same thickness while at a density that is approximately 18% lighter. If desired, additional insulation protection beyond insulative layers 232 may be provided in a variety ways, such as overcoating, wrapping, or bonding electrically insulative structural or non-structural materials or coatings, e.g. fiberglass/epoxy.
Electrical source 210 is electrically coupled to structural composite 230 via connectors 212 and transmission lines 214. Connectors 212 extend at least partially though structural composite 230 and are in electrical communication with at least some conductive layers 234. Transmission lines 214 provide electrical communication between electrical source 210 and connectors 212.
Electrical output 220 is electrically coupled to structural composite 230 via connectors 222 and transmission lines 224. Connectors 222 extend at least partially though structural composite 230 and are in electrical communication with at least some conductive layers 234. Transmission lines 224 provide electrical communication between electrical output 220 and connectors 222.
Connectors 212 and 222 may be of any suitable shape. In some embodiments, connectors 212 and 222 may be shaped so as to provide sufficient electrical contact to conductive layers 234. In addition, connectors 212 and 222 may be shaped such that they are retained by structural composite 230. In one example embodiment, connectors 212 and 222 may be threadably engaged to insulative layers 232 and/or conductive layers 234. In another example embodiment, connectors 212 and 222 are substantially cylindrical and are disposed within holes in insulative layers 232 and/or conductive layers 234. In yet another example embodiment, connectors 212 and 222 are extended shafts having a plurality of sides (e.g., a five-sided star, a sixteen-sided star, etc.) and may be disposed within holes in insulative layers 232 and/or conductive layers 234 having corresponding shapes. Teachings of certain embodiments recognize that additional surfaces and/or surface area may provide for a stronger contact connection between connectors 212 and 222 and conductive layers 234.
Connectors 212 and 222 may be inserted into structural composite 230 in any suitable manner. In one example, a hole is drilled in structural composite 230. Next, the hole is rinsed in alcohol, and the polymer in the hole is plasma-ashed to reveal more conductive material. The hole is then cleaned with compressed air, and conductive silver nanoflakes are provided in the hole to increase conductivity between connectors 212 and 222 and conductive layers 234. Connectors 212 and 222 are then press-fit in each hole of structural composite 230.
In operation, according to one example embodiment, electrical source 210 provides electrical current through transmission lines 214 and connectors 212 to conductive layers 234. Connectors 222 receive electrical current from conductive layers 234 and transmit the electrical current through transmission lines 224 to electrical output 220.
Teachings of certain embodiments recognize that such a configuration may eliminate a portion of traditional wiring between electrical source 210 and electrical output 220 by incorporating this function into the structure, thereby saving weight associated with conventional wiring, while forming redundant current paths, and reducing costs associated with installation and maintenance of conventional wiring. Further, the reliability and maintainability of the power carrying members are improved because they are embedded in the structure and therefore less susceptible to damage. Further, volume that would otherwise be occupied by conventional wiring harnesses can be utilized for other uses. Further, structural power system 200 is less vulnerable to ballistic damage since conductive layers 234 can continue to conduct electrical power or current even after penetration by a projectile.
The structural power system 200 of
In the lighting system 300a of
The example of
Lighting systems 300 and 400 represent just two example configurations for providing electrical current to LEDs through structural composite 230. Teachings of certain embodiments recognize that other arrangements may be provided.
It should be appreciated that even though lighting system 300 is illustrated as providing exterior lighting, structural lighting system 300 can be implemented for internal lighting as well. Further, it should be appreciated that lighting system 300 can be configured in a wide variety of shapes, sizes, and contours. The lights of structural lighting system 300 can be configured to display and/or communicate a wide variety of lighting features. Exemplary lighting embodiments can be configured for display of requisite exterior aircraft lighting, to identify the aircraft as a certain emergency aircraft, for display of police lighting, or to communicate interior passenger egress, to name a few examples.
Modifications, additions, or omissions may be made to the systems and apparatuses described herein without departing from the scope of the invention. The components of the systems and apparatuses may be integrated or separated. Moreover, the operations of the systems and apparatuses may be performed by more, fewer, or other components. The methods may include more, fewer, or other steps. Additionally, steps may be performed in any suitable order.
Although several embodiments have been illustrated and described in detail, it will be recognized that substitutions and alterations are possible without departing from the spirit and scope of the present invention, as defined by the appended claims.
To aid the Patent Office, and any readers of any patent issued on this application in interpreting the claims appended hereto, applicants wish to note that they do not intend any of the appended claims to invoke paragraph 6 of 35 U.S.C. §112 as it exists on the date of filing hereof unless the words “means for” or “step for” are explicitly used in the particular claim.
Pursuant to 35 U.S.C. §119 (e), this application claims priority to United States Provisional Patent Application Ser. No. 61/783,902, entitled MULTIFUNCTIONAL STRUCTURAL POWER AND LIGHTING SYSTEM, filed Mar. 14, 2013. U.S. Provisional Patent Application Ser. No. 61/783,902 is hereby incorporated by reference. Pursuant to 35 U.S.C. §119 (e), this application claims priority to U.S. Provisional Patent Application Ser. No. 61/623,740, entitled MULTIFUNCTIONAL STRUCTURAL LIGHTING SYSTEM, filed Apr. 13, 2012. U.S. Provisional Patent Application Ser. No. 61/623,740 is hereby incorporated by reference.
Number | Date | Country | |
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61623740 | Apr 2012 | US | |
61783902 | Mar 2013 | US |