U.S. patent application number 17/074113 was filed with the patent office on 2022-04-21 for integrated aircraft antenna and light assemblies.
This patent application is currently assigned to Rockwell Collins, Inc.. The applicant listed for this patent is Rockwell Collins, Inc.. Invention is credited to Joseph T. Graf, James B. West.
Application Number | 20220119091 17/074113 |
Document ID | / |
Family ID | 1000005240869 |
Filed Date | 2022-04-21 |
United States Patent
Application |
20220119091 |
Kind Code |
A1 |
Graf; Joseph T. ; et
al. |
April 21, 2022 |
INTEGRATED AIRCRAFT ANTENNA AND LIGHT ASSEMBLIES
Abstract
Disclosed are embodiments of exterior aircraft assemblies
integrating compatible elements. In one example, an integrated
aircraft assembly includes an aerodynamic housing attachable to an
aircraft, an antenna system including at least one antenna element
housed within the aerodynamic housing, and a lighting system
including at least one light fixture housed within the aerodynamic
housing. The at least one antenna element and the at least one
light fixture may be co-located within then housing or mounted
separately on the housing.
Inventors: |
Graf; Joseph T.; (Center
Point, IA) ; West; James B.; (Cedar Rapids,
IA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Rockwell Collins, Inc. |
Cedar Rapids |
IA |
US |
|
|
Assignee: |
Rockwell Collins, Inc.
Cedar Rapids
IA
|
Family ID: |
1000005240869 |
Appl. No.: |
17/074113 |
Filed: |
October 19, 2020 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F21V 15/01 20130101;
F21V 23/003 20130101; H01Q 1/282 20130101; F21W 2107/30 20180101;
B64D 2203/00 20130101; F21Y 2115/10 20160801; H01Q 21/061 20130101;
H01Q 1/44 20130101; B64D 47/02 20130101; B64C 1/36 20130101 |
International
Class: |
B64C 1/36 20060101
B64C001/36; B64D 47/02 20060101 B64D047/02; H01Q 1/28 20060101
H01Q001/28; H01Q 1/44 20060101 H01Q001/44; H01Q 21/06 20060101
H01Q021/06; F21V 15/01 20060101 F21V015/01 |
Claims
1. An integrated aircraft assembly, comprising: an aerodynamic
housing attachable to an aircraft, the aerodynamic housing
including a first portion for being received through a structurally
reinforced aperture formed in an airframe of the aircraft and a
second portion for being positioned external to the aircraft; an
antenna system housed within the aerodynamic housing, the antenna
system comprising a substrate and an antenna array, the antenna
array comprising a central element provided on the substrate in a
central position on the substrate and a plurality of parasitic
elements provided on the substrate in a predetermined positional
relationship relative to the central element; and a lighting system
housed within the aerodynamic housing, the lighting system
comprising a plurality of light fixtures interspersed with the
plurality of parasitic elements; wherein the antenna system and the
lighting system function independently.
2. The integrated aircraft assembly according to claim 1, further
comprising a base plate which functions as the substrate of the
antenna assembly and a mounting surface for the plurality of light
fixtures.
3. The integrated aircraft assembly according to claim 2, wherein
the second portion comprises a bezel surrounding and supporting the
base plate and a transparent lens coupled to the bezel, wherein the
antenna array and the plurality of light fixtures are disposed
beneath the transparent lens.
4. The integrated aircraft assembly according to claim 1, further
comprising at least one connector provided at a terminal end of the
first portion for connecting with a power source internal to the
aircraft.
5. The integrated aircraft assembly according to claim 1, wherein
the antenna array is positioned internal to the second portion of
the aerodynamic housing.
6. The integrated aircraft assembly according to claim 1, wherein
the antenna array is positioned external to the second portion of
the aerodynamic housing.
7. The integrated aircraft assembly according to claim 1, wherein
the antenna system is operable for providing at least one of a
communication, navigation, sensing, and flight-critical function,
and wherein the lighting system is operable for providing
illumination for the exterior of the aircraft.
8. The integrated aircraft assembly according to claim 1, wherein
the aerodynamic housing is formed as an exterior aircraft
light.
9. (canceled)
10. (canceled)
11. The integrated assembly according to claim 1, wherein the
antenna array is mounted atop the second portion of the aerodynamic
housing.
12. The integrated assembly according to claim 1, further
comprising at least one control unit communicatively coupled to at
least one of the antenna system and the lighting system and
configured to interface with an aircraft power system.
13. An integrated aircraft assembly, comprising: a housing formed
as an exterior aircraft lighting assembly, the housing including a
first portion for being attached to an aircraft and a second
portion for being positioned external to the aircraft; an antenna
array coupled to the housing; and at least one light fixture
coupled to the housing; wherein a function of the antenna array is
independent of a function of the at least one light fixture; and
wherein the housing is formed as an aerodynamic housing comprising
a base plate, the antenna array comprises a plurality of individual
elements arranged in an annular array around the base plate, and
the at least one light fixture is a light emitting diode (LED
mounted on the base plate.
14. The integrated assembly according to claim 13, wherein the
antenna array and the at least one light fixture are co-located in
the housing.
15. The integrated assembly according to claim 13, wherein the
second portion of the housing comprises the base plate and a lens
coupled to the base plate, the at least one light fixture is
positioned in the second portion under cover of the lens, and the
antenna array is mounted to the base plate.
Description
TECHNICAL FIELD
[0001] The subject matter disclosed herein relates generally to
system co-location and more particularly to integrated aircraft
assemblies including antenna and lighting structures.
BACKGROUND
[0002] There is a critical need to reduce drag and antenna count in
high-performance aircraft such as attack helicopters and fighter
jets. Many of these aircraft require dozens of apertures on the
airframe for mounting communication, sensing and other
flight-critical equipment, as well as for mounting lighting
equipment for flight and safety. Each antenna assembly and
associated structurally reinforced aperture adds weight and drag on
the aircraft which impact mission performance and mission
length.
[0003] Therefore, what is needed are solutions for consolidating
separate aircraft systems to reduce the number of necessary
structures.
SUMMARY
[0004] To achieve the foregoing and other advantages, in a first
embodiment the present disclosure provides an integrated aircraft
assembly including an aerodynamic housing attachable to an aircraft
including a first portion for being received through a structurally
reinforced aperture formed in an airframe of the aircraft and a
second portion for being positioned external to the aircraft, an
antenna system including at least one antenna element housed within
the aerodynamic housing, and a lighting system including at least
one light fixture housed within the aerodynamic housing, wherein
the antenna system and the lighting system function
independently.
[0005] In some embodiments, the integrated aircraft assembly may
further include a base plate which may function as a substrate of
the antenna assembly and a mounting surface for the at least one
light fixture.
[0006] In some embodiments, the second portion of the aerodynamic
housing may include bezel surrounding the base plate and a
transparent lens coupled to the bezel, wherein the at least one
antenna element and the at least one light fixture may be disposed
beneath the transparent cover.
[0007] In some embodiments, the integrated aircraft assembly may
further include at least one connector provided at a terminal end
of the first portion for connecting with a power source internal to
the aircraft.
[0008] In some embodiments, the at least one antenna element may be
positioned internal or external to the second portion of the
aerodynamic housing.
[0009] In some embodiments, the antenna system may be operable for
providing at least one of a communication, navigation, sensing, and
flight-critical function, and the lighting system may be operable
for providing illumination for the exterior of the aircraft.
[0010] In some embodiments, the aerodynamic housing may be formed
as an exterior aircraft light.
[0011] In some embodiments, the antenna system may include a
substrate and an antenna array, and wherein the antenna array may
include a central element provided on the substrate in a central
position on the substrate and a plurality of parasitic elements
provided on the substrate in a predetermined positional
relationship relative to the central element, and wherein the
lighting system may include a plurality of light fixtures
interspersed between the plurality of parasitic elements.
[0012] In some embodiments, the aerodynamic housing may further
include a base plate, the antenna system may include an end fire
radiator element, for instance a plurality of individual Balanced
Antipodal Vivaldi Antenna (BAVA) elements arranged in an annular
array around the base plate, and the at least one light fixture may
be a Light Emitting Diode (LED) mounted on a surface of the base
plate.
[0013] In some embodiments, the at least one antenna element may be
mounted atop the second portion of the aerodynamic housing.
[0014] In some embodiments, the integrated aircraft assembly may
further include at least one control unit communicatively coupled
to at least one of the antenna system and the lighting system and
configured to interface with an aircraft power system.
[0015] According to another inventive aspect, the present
disclosure provides an integrated aircraft assembly including a
housing formed as an exterior aircraft lighting assembly, the
housing including a first portion for being attached to an aircraft
and a second portion for being positioned external to the aircraft,
an antenna array coupled to the housing, and at least one light
fixture coupled to the housing, wherein a function of the antenna
array is independent of a function of the at least one light
fixture.
[0016] In some embodiments, the antenna array and the at least one
light fixture may be co-located in the housing.
[0017] In some embodiments, the second portion of the housing may
include a base plate and a lens coupled to the base plate, the at
least one light fixture may be positioned in the second portion
under cover of the lens, and the antenna array may be mounted to
the base plate.
[0018] This brief summary is provided solely as an introduction to
subject matter that is fully described in the detailed description
and illustrated in the drawings. This brief summary should not be
considered to describe essential features nor be used to determine
the scope of the claims. Moreover, it is to be understood that both
the foregoing summary and the following detailed description are
exemplary and explanatory only and are not necessarily restrictive
of the subject matter claimed.
BRIEF DESCRIPTION OF THE DRAWINGS
[0019] The detailed description is described with reference to the
accompanying figures. The use of the same reference numbers in
different instances in the description and the figures may indicate
similar or identical items. Various embodiments or examples
("examples") of the present disclosure are disclosed in the
following detailed description and the accompanying drawings. The
drawings are not necessarily to scale. In general, operations of
disclosed processes may be performed in an arbitrary order, unless
otherwise provided in the claims. In the drawings:
[0020] FIG. 1 illustrates an integrated aircraft assembly including
interspersed antenna and lighting elements in accordance with an
exemplary embodiment of the present disclosure;
[0021] FIG. 2 illustrates an integrated aircraft assembly including
an antenna array mounted proximate a lighting element in accordance
with an exemplary embodiment of the present disclosure;
[0022] FIG. 3 illustrates an integrated aircraft assembly including
an annular antenna array surrounding a lighting element in
accordance with an exemplary embodiment of the present
disclosure;
[0023] FIG. 4A is a aide elevation view of an integrated aircraft
assembly formed as an aircraft exterior light in accordance with an
exemplary embodiment of the present disclosure; and
[0024] FIG. 4B is an end view of the integrated aircraft assembly
of FIG. 4A.
DETAILED DESCRIPTION
[0025] Before explaining one or more embodiments of the disclosure
in detail, it is to be understood that the embodiments are not
limited in their application to the details of construction and the
arrangement of the components set forth in the following
description or illustrated in the drawings. In the following
detailed description of embodiments, numerous specific details may
be set forth in order to provide a more thorough understanding of
the disclosure. However, it will be apparent to one of ordinary
skill in the art having the benefit of the instant disclosure that
the embodiments disclosed herein may be practiced without some of
these specific details. In other instances, well-known features may
not be described in detail to avoid unnecessarily complicating the
instant disclosure.
[0026] As used herein a letter following a reference numeral is
intended to reference an embodiment of the feature or element that
may be similar, but not necessarily identical, to a previously
described element or feature bearing the same reference numeral
(e.g., 1, 1a, 1b). Such shorthand notations are used for purposes
of convenience only and should not be construed to limit the
disclosure in any way unless expressly stated to the contrary.
[0027] Further, unless expressly stated to the contrary, "or"
refers to an inclusive or and not to an exclusive or. For example,
a condition A or B is satisfied by any one of the following: A is
true (or present) and B is false (or not present), A is false (or
not present) and B is true (or present), and both A and B are true
(or present).
[0028] In addition, use of "a" or "an" may be employed to describe
elements and components of embodiments disclosed herein. This is
done merely for convenience and "a" and "an" are intended to
include "one" or "at least one," and the singular also includes the
plural unless it is obvious that it is meant otherwise.
[0029] Finally, as used herein any reference to "one embodiment" or
"some embodiments" means that a particular element, feature,
structure, or characteristic described in connection with the
embodiment is included in at least one embodiment disclosed herein.
The appearances of the phrase "in some embodiments" in various
places in the specification are not necessarily all referring to
the same embodiment, and embodiments may include one or more of the
features expressly described or inherently present herein, or any
combination or sub-combination of two or more such features, along
with any other features which may not necessarily be expressly
described or inherently present in the instant disclosure.
[0030] Broadly speaking, the present disclosure provides
embodiments of integrated assemblies including aircraft lighting
and communication/sensing equipment.
[0031] Referring to FIG. 1, an integrated aircraft assembly 100 in
accordance with a first exemplary embodiment of the present
disclosure is shown. The integrated assembly 100 includes an
aerodynamic housing 102 configured for mounting to an aircraft. The
housing 102 generally includes a first portion 104 for being
received through a structurally reinforced aperture formed in an
airframe and a second portion 106 for being positioned external to
the aircraft, for instance mounted against or proximate the
aircraft skin or streamlined into the surface of the aircraft. The
first and second portions 104, 106 may be coupled together or may
be integrally formed. One or more connectors 108 may be provided at
a terminal end of the first portion 104 for connecting with one or
more of a power source, light control, radio frequency (RF)
control, RF cabling, etc., internal to the aircraft.
[0032] In some embodiments, the second portion 106 may be
positioned `atop` the first portion 104, and as shown, may envelope
separate systems that may function independently (e.g., mutually
exclusive) or may be operationally coupled. In some embodiments,
the systems may include an antenna system 110 and a lighting system
112. For example, the antenna system 110 may provide one or more of
communication, navigational, sensing, and flight-critical
functions, while the lighting system 112 may provide illumination
for the exterior of the aircraft. In some embodiments, the housing
102 may be implemented in the form of an exterior aircraft light
and the antenna system 110 may be positioned internal or external
to the housing 102. In other embodiments, the housing may be
implemented in the form of an aircraft antenna assembly and the
lighting system 112 may be positioned internal or external to the
housing 102.
[0033] In some embodiments, the housing 102 may be formed as an
exterior aircraft light and the lighting system 112 may be
configured to provide illumination for such operations as
navigation, landing, taxiing, positional indication, collision
avoidance, inspection lighting, etc. Lights may be white or
colored. For example, in an embodiment in which multiple integrated
assemblies 100 are provided as a set of navigation lights, a first
integrated assembly may be configured to produce white light, a
second integrated assembly may be configured to produce green
light, and a third integrated assembly may be configured to produce
red light. In some embodiments, the lights may be configured for
one or more of steady operation, intermittent flashing, and
dimming. In some embodiments, the lighting system 112 may be
implemented as an anticollision light including at least one
rotating beam light and motor for rotating the same, and the
integrated assembly may be installed on the vertical stabilizer. In
some embodiments, the lighting system 112 may be implemented as a
landing and/or taxi light, the integrated assembly may include a
parabolic reflector for directing the beam of light, and the
integrated assembly may be installed on the nose or leading edge of
the wing.
[0034] As shown in FIG. 1, the second portion 106 envelopes the
antenna system 110 and the lighting system 112. The second portion
106 may include a bezel 114 surrounding a base plate 116, wherein
the base plate 116 functions as the substrate for an antenna array
118 and the mounting surface for the one or more individual light
fixtures 120 of the lighting system 112. In some embodiments, the
second portion 106 further includes a transparent, hemispherical
lens 122 coupled to the base plate 116 for covering and protecting
the light and antenna elements, and in some embodiments, focusing
the beam of light.
[0035] Embodiments disclosed herein are not limited to any one
particular antenna type, configuration, or count. For example,
while a monopole based parasitic array is shown, other parasitic
arrays can be utilized such as a parasitic array including
microstrip patch radiating elements. In some embodiments, the
antenna array 118 may be a parasitic array, for instance the C-Band
parasitic array as shown. In an alternative embodiment, the antenna
array may include a Ku-Band array positioned amongst the monopole.
The base plate 116 (e.g., antenna substrate) may be at least
partially formed from printed circuit board material and may
include a `top` surface, a `bottom` surface, and a ground plane
associated with the bottom surface. A central element 124 connects
to the base plate 116. For example, the central element 124 may be
a monopole element or a monopole-type radiating element, for
instance an ultra-wide band (UWB) monopole structure. The central
element 124 may be connected to the base plate 116 and the ground
plane at the generally central location of the base plate 116 as
shown. In some embodiments, the central element 124 may be an
omni-directional element configured to radiate electromagnetic
energy in an omni-directional radiation pattern. In some
embodiments, the central element 124 may be configured for being
connected to a feed line such as an RF feed line, coaxial cable,
printed circuit transmission line (e.g., microstrip, stripline,
etc.), and/or the like.
[0036] The antenna array 118 may further include a plurality of
parasitic elements 126, for example, formed as parasitic pins as
shown. In a non-limiting example, the antenna array 118 may include
six (6) parasitic elements 126 arranged in a ring around and
encircling the central element 124. However, it is understood that
varying numbers of parasitic elements may be implemented in the
antenna array as well as varying positional arrangements. For
example, the antenna array 118 may include one or more additional
rings of parasitic elements positioned in relation to the central
element 124 and/or the first ring. Each of the plurality of
parasitic elements 126 is also connected to the base plate 116 and
may be connected to a load such as a load circuit or a variable
impedance load. In some embodiments, each parasitic element 126 may
have a corresponding load circuit connected (e.g., physically and
electrically) to its base portion and/or the ground plane
associated with the `bottom` surface of the base plate 116.
[0037] In some embodiments, each load circuit may be an adjustable
load circuit or a parasitic load circuit. The load circuit may
include a plurality of diodes (e.g., two diodes such as two p-type,
intrinsic, n-type (PIN) diodes, one or more capacitors configured
for being connected to at least one of the PIN diodes, a resistor
configured for being connected to at least one of the one or more
capacitors, and a Direct Current (DC) bias current source
configured for being connected to the resistor. In some
embodiments, the DC bias current source may be configured for
providing DC bias current to the resistor thereby producing a
voltage across the resistor. In further embodiments, the resistor
and capacitor(s) may form a low pass filter for providing the DC
bias current to the diodes. In some embodiments, the load circuit
may be configurable for allowing a variable (e.g., adjustable)
impedance to be applied to the load circuit's corresponding
parasitic element.
[0038] The central element 124 (e.g., monopole element) may be
configured to receive RF energy via the feed line, and based upon
the received RF energy, configured to radiate electromagnetic
energy (e.g., electromagnetic waves) in multiple directions toward
the plurality of parasitic elements 126 to produce a voltage across
the parasitic elements 126. The applied impedance provided to each
parasitic element 126 via its corresponding load circuit can be
selectively varied to cause the antenna array 118 to manipulate the
omni-directional monopole field radiated by the monopole element
and to radiate either multiple directional beams or an omni-beam in
a monopole-like radiation pattern. In some embodiments, the antenna
array 118 is operable at low frequencies down to L-band and high
frequencies up to Ku-band, depending on configuration and
implementation.
[0039] The lighting system 112 generally includes the one or more
light fixtures 120, for instance solid-state Light Emitting Diodes
(LEDs) as shown. LEDs may be preferable over incandescent light
bulbs in aircraft applications due to their good visibility, high
reliability, comparatively small size, lightweight, low power
consumption, quick transition time between intensity changes,
resistance to vibration, etc. As shown, the lighting system 112
includes a plurality of individual LED fixtures 120 (e.g., six (6)
LED fixtures) each mounted on the `top` surface of the base plate
116 and collectively arranged to form a ring of LED fixtures 120
around and encircling the central element 126. As shown, the LED
fixtures 120 are interspersed with the parasitic elements 126, for
example, positioned in the same ring in an alternating fashion such
that each LED fixture 120 is positioned between two spaced-apart
parasitic elements 126 and each parasitic element 126 is positioned
between two spaced-apart LED fixtures 120). LED fixture and
parasitic element type, count and position may be based on desired
beam and wavelength performance, among other parameters. Positional
arrangements other than rings are envisioned, for instance linear
arrays. In some embodiments, the lighting system 112 may include a
focusing element or reflector associated with the LED fixtures 120.
As show, the LED fixtures 120 have the same angle of orientation;
however, it is envisioned and understood that the LED fixtures 120
may have different orientations.
[0040] The antenna system 110 and the lighting system 112 may be
operably and communicatively coupled to one or more control units
configured to interface with the aircraft power system. In some
embodiments, the antenna system 110 and the lighting system 112 may
be electrically coupled to the same control unit and interface with
the same aircraft power system. The control unit may form part of
the integrated assembly 100 or may located internal to the aircraft
as a component of a dedicated aircraft system. In some embodiments,
the control unit is configured to vary the power supplied to the
LED fixtures 120 as a group or individually.
[0041] Referring to FIG. 2, another embodiment of an integrated
assembly is shown generally at 200. Like the first embodiment
discussed above, the integrated assembly 200 generally includes an
aerodynamic housing 202 including a first portion 204 and a second
portion 206 positioned `atop` the first portion, and one or more
electrical connectors 208 provided at the terminal end of the first
portion 204 for being electrically coupled to a power source within
the aircraft. The integrated assembly 200 further includes an
antenna system 210 and a lighting system 212.
[0042] Whereas in the first integrated assembly 100 the antenna
elements are shown positioned internal to the second portion under
the cover of the lens, in the second integrated assembly 200 the
antenna system 210 is shown positioned external of the lens 222,
and more particularly in an annular array coupled to the bezel of
base plate 216. As shown, the antenna system 210 is provided as a
small form factor array of elements 218, for instance Balanced
Antipodal Vivaldi Antenna (BAVA) elements. As shown, the array 218
includes a plurality of individual elements 224 arranged in an
annular array surrounding the perimeter of the base plate 216 and
configured, for example, for accurate Direction Finding (DF) of a
received signal.
[0043] Further, whereas the first integrated assembly 100 includes
a plurality of LED fixtures provided in a ring encircling the
central element, the second integrated assembly 200 includes one
larger form factor LED fixture 220 mounted on the `top` surface of
the base plate 216. As shown, the LED fixture 220 is mounted at the
general central location of the base plate 216. In all embodiments,
the configuration of the antenna system may be determinative of the
light fixture count and position(s), and vice versa. For example,
whereas the parasitic array depicted in the first integrated
assembly 100 allows for a lighting assembly provided as a ring
array, the position of the central element 124 in the first
integrated assembly 100 conflicts with the LED fixture 220 position
in the second integrated assembly 200. Therefore, some antenna
systems may be compatible with some lighting systems while others
may not, due at least in part to the positional requirements of the
system elements.
[0044] Referring to FIG. 3, another embodiment of an integrated
assembly is shown generally at 300. The integrated assembly 300
includes an aerodynamic housing 302 having an annular flange 304
with apertures for mounting the assembly to an exterior of an
aircraft. The lighting system 312 may be disposed within a central
opening of the housing 302. As shown, the lighting system 312 may
be a self-contained assembly including a light fixture 320
centrally disposed within a transparent lens 322 further containing
a reflector 324 and circuitry associated with the light fixture
320.
[0045] As shown, the antenna system 310 is provided as an annular
array 318 positioned external to the transparent lens 322 and
incorporated into or otherwise mounted to the annular flange 304.
In some embodiments, the annular array 318 may be a BAVA array
including a plurality of individual BAVA elements 324 arranged in
an annular array surrounding the perimeter of the transparent lens
322 and configured, for example, for accurate DF of a received
signal, among or in addition to other functions.
[0046] Referring to FIGS. 4A and 4B, another embodiment of an
integrated assembly is shown generally at 400. As shown, the
aerodynamic housing 402 of the integrated assembly 400 is formed as
a position light configured to be mounted external to an aircraft.
The aerodynamic housing 402 generally includes a first portion 404
for being received in an aperture in an airframe and a second
portion 406 for being mounted external to the aircraft. One or more
connectors 408 may be provided at a terminal end of the first
portion 404 for connecting with a power source internal to the
aircraft. In some embodiments, an externally threaded connector may
be provided at the terminal end of the first portion 404 for being
received in an internally threaded portion in the airframe.
[0047] As shown, the second portion 406 is positioned `atop` the
first portion 404 and contains one or more light fixtures 420 of
the lighting system 412 positioned under the cover of the
transparent lens 422 coupled to the base plate 416. As further
shown, the antenna system 410, for instance a Ku-band parasitic
array, is positioned atop the second portion 406 and provides, for
example, one or more of communication, navigational, sensing, and
flight-critical functions, while the lighting system 412 may
provide illumination for the exterior of the aircraft. In some
embodiments, the integrated assembly 400 may further include a
reflector and heat sink provided in the second portion 406.
[0048] While particular examples of antenna and lighting systems
have been discussed herein with reference to the various
embodiments, it is understood that other systems may be utilized,
for example, antenna assemblies that support a broad range of
frequency bands. In some embodiments, larger antenna assemblies may
be co-located in larger light fixtures (e.g., landing and taxi
lights) to provide frequency coverage down to the L-band. Other
examples of antenna assemblies for integration into lighting
structures include, but are not limited to, circular BAVA arrays
and other Vivaldi/TEM horn array variants, reflector-backed
monopole circular arrays, sectoral horn arrays, squatty biconical
antennas, radial T-line antennas (e.g., CDISK), microwave frequency
pill box antennas, other ground plane driven antennas, etc.
[0049] Although inventive concepts have been described with
reference to the embodiments illustrated in the attached drawing
figures, equivalents may be employed and substitutions made herein
without departing from the scope of the claims. Components
illustrated and described herein are merely examples of a
system/device and components that may be used to implement
embodiments of the inventive concepts and may be replaced with
other devices and components without departing from the scope of
the claims. Furthermore, any dimensions, degrees, and/or numerical
ranges provided herein are to be understood as non-limiting
examples unless otherwise specified in the claims.
* * * * *