U.S. patent application number 16/524324 was filed with the patent office on 2020-01-16 for lighter-than-air platform.
The applicant listed for this patent is Skycom Corporation. Invention is credited to John H. H. BENNETT, Max G. MICHAELIS, IV.
Application Number | 20200021238 16/524324 |
Document ID | / |
Family ID | 59057260 |
Filed Date | 2020-01-16 |
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United States Patent
Application |
20200021238 |
Kind Code |
A1 |
MICHAELIS, IV; Max G. ; et
al. |
January 16, 2020 |
LIGHTER-THAN-AIR PLATFORM
Abstract
Techniques are disclosed relating lighter-than-air aircraft.
Such aircraft may be used for various purposes, such as providing
network connectivity to areas that would otherwise lack such
connectivity. For example, in some embodiments, a lighter-than-air
aircraft according to this disclosure may include various types of
antennas (directional or non-directional) for communicating with
ground-based electronics or with other lighter-than-air
aircraft.
Inventors: |
MICHAELIS, IV; Max G.;
(Kyle, TX) ; BENNETT; John H. H.; (Austin,
TX) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Skycom Corporation |
Austin |
TX |
US |
|
|
Family ID: |
59057260 |
Appl. No.: |
16/524324 |
Filed: |
July 29, 2019 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
14971651 |
Dec 16, 2015 |
10367447 |
|
|
16524324 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
H02S 30/20 20141201;
B64C 2201/122 20130101; B64C 2201/022 20130101; B64C 2201/208
20130101; H02S 10/40 20141201; B64B 1/62 20130101; H02S 20/32
20141201; B64B 1/58 20130101 |
International
Class: |
H02S 20/32 20060101
H02S020/32; B64B 1/58 20060101 B64B001/58; B64B 1/62 20060101
B64B001/62; H02S 30/20 20060101 H02S030/20; H02S 10/40 20060101
H02S010/40 |
Claims
1. An apparatus, comprising: an outer membrane; a flexible bladder
within the outer membrane; a region disposed inside the outer
membrane and outside the flexible bladder; and a pressure
adjustment device configured to adjust a particular pressure within
the apparatus; wherein the apparatus is configured to float at a
selected altitude based on a quantity of lighter-than-air gas in
the flexible bladder; and wherein the pressure adjustment device is
configured to reduce leakage of the lighter-than-air gas from the
flexible bladder by adjusting the particular pressure within the
apparatus such that a pressure inside the flexible bladder is
equalized with a pressure in the region.
2. The apparatus of claim 1, wherein a volume detection device is
configured to measure a volume of the flexible bladder within the
outer membrane, and the pressure adjustment device is configured to
reduce leakage of the lighter-than-air gas from the flexible
bladder by adjusting, based on measurements from the volume
detection device, the particular pressure within the apparatus such
that the volume of the flexible bladder is maintained at a desired
volume less than its maximum volume, thereby equalizing the
pressure inside the flexible bladder with the pressure in the
region.
3. The apparatus of claim 1, wherein the particular pressure is the
pressure inside the flexible bladder.
4. The apparatus of claim 1, wherein the particular pressure is the
pressure in the region.
5. The apparatus of claim 1, wherein the region is filled with a
gas other than the lighter-than-air gas.
6. The apparatus of claim 5, wherein the gas other than the
lighter-than-air gas is air.
7. The apparatus of claim 1, further comprising at least one solar
panel configured to provide electrical power to the apparatus.
8. The apparatus of claim 1, further comprising at least one
propeller configured to maintain the apparatus in a selected
geodetic location.
9. The apparatus of claim 1, wherein the selected altitude is at
least 60,000 feet above sea level.
10. The apparatus of claim 1, wherein the flexible bladder
comprises a plurality of flexible bladders.
11. The apparatus of claim 1, further comprising at least one
antenna configured to provide telecommunications service to land
disposed beneath the apparatus.
12. A method comprising: providing an unmanned, lighter-than-air
aircraft that includes: an outer membrane; a flexible bladder
within the outer membrane; a region disposed inside the outer
membrane and outside the flexible bladder; and a pressure
adjustment device configured to adjust a particular pressure within
the aircraft; causing the aircraft to float at a selected altitude
based on a quantity of lighter-than-air gas in the flexible
bladder; and reducing leakage of the lighter-than-air gas from the
flexible bladder by adjusting the particular pressure within the
aircraft such that a pressure inside the flexible bladder is
equalized with a pressure in the region.
13. The method of claim 12, wherein a volume of the flexible
bladder is measured by a volume detection device within the outer
membrane, and the pressure adjustment device reduces leakage of the
lighter-than-air gas from the flexible bladder by adjusting, based
on measurements from the volume detection device, the particular
pressure within the aircraft such that the volume of the flexible
bladder is maintained at a desired volume less than its maximum
volume, thereby equalizing the pressure inside the flexible bladder
with the pressure in the region.
14. The method of claim 13, wherein the volume detection device
comprises: a lever arm; a tension element configured to press the
lever arm against a surface of the flexible bladder; and a
potentiometer configured, based on a position of the lever arm, to
measure the volume of the flexible bladder.
15. The method of claim 13, wherein the volume detection device
comprises an electromagnetic measurement device configured to: send
electromagnetic radiation to a surface of the flexible bladder; and
based on a delay time associated with a reflection of the
electromagnetic radiation, determine a distance to the flexible
bladder; and based on the determined distance, determine the volume
of the flexible bladder.
16. The method of claim 15, wherein the electromagnetic radiation
is an optical pulse.
17. The method of claim 15, wherein the electromagnetic radiation
is a laser pulse.
18. The method of claim 12, wherein the lighter-than-air gas
comprises hydrogen gas.
19. The method of claim 12, wherein the particular pressure is the
pressure inside the flexible bladder.
20. The method of claim 12, wherein the particular pressure is the
pressure in the region.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This application is a continuation of U.S. patent
application Ser. No. 14/971,651, filed on Dec. 16, 2015, which is
incorporated by reference herein.
BACKGROUND
Technical Field
[0002] This disclosure relates to lighter-than-air platforms. In
particular, this disclosure has applications in the field of
unmanned lighter-than-air platforms that can be used for various
purposes, such as supporting telecommunications equipment,
deploying aerial scientific equipment, etc. In various embodiments,
such lighter-than-air platforms may be realized as drones,
balloons, airships, or any other suitable implementation, and they
may also be referred to as high-altitude lighter-than-air platforms
(HALTAPs). For purposes of this disclosure, the general term
"aircraft" should be understood as encompassing all such
variations.
BRIEF DESCRIPTION OF THE DRAWINGS
[0003] FIG. 1 is a perspective view of an aircraft, according to
some embodiments.
[0004] FIG. 2 is a perspective view of another aircraft, according
to some embodiments.
[0005] FIG. 3 is a cross-sectional view of an aircraft, according
to some embodiments.
[0006] FIG. 4 is a perspective view of a bladder for holding a
lighter-than-air gas and a core portion of a lighter-than-air
aircraft, according to some embodiments.
[0007] FIG. 5 is a perspective view of a deflated and partially
disassembled lighter-than-air aircraft, according to some
embodiments.
[0008] FIG. 6 is a view of a deflated lighter-than-air aircraft
being transported, according to some embodiments.
[0009] FIG. 7 is a block diagram of several lighter-than-air
aircraft carrying out different functions, according to some
embodiments.
[0010] FIGS. 8A and 8B are detail views of an inflation-measuring
device, according to some embodiments.
[0011] FIGS. 9A and 9B are detail views of another
inflation-measuring device, according to some embodiments.
[0012] FIG. 10 is a detail view of a payload of a lighter-than-air
aircraft, according to some embodiments.
[0013] FIG. 11 is a detail view of another payload of a
lighter-than-air aircraft, according to some embodiments.
[0014] FIG. 12 is a block diagram of a process flow, according to
some embodiments.
[0015] FIG. 13 is a block diagram of an example computing system,
according to some embodiments.
DETAILED DESCRIPTION
[0016] The present disclosure provides for lighter-than-air
aircraft that can be used for various purposes. In one embodiment,
for example, such aircraft may be equipped with telecommunications
equipment to provide connectivity to areas that would otherwise not
be covered. Many different types of such connectivity are enabled
within this disclosure, such as mobile phone (LTE, CDMA, GSM,
etc.), wireless internet (Wi-Fi, WiMAX, proprietary technology,
etc.), broadcast television, broadcast radio, air traffic control,
and/or other types of connectivity. The backhaul for such
connectivity may be provided via a mesh network made up of a
plurality of such aircraft communicating with one another via
high-gain microwave antennas, laser or other optical connections,
other types of directional antennas, etc. For purposes of this
disclosure, a "mesh" network is defined as including various types
of network topology, including (for example) a simple link or a
series of sequential links. That is, mesh networks need not be
limited to grid-type topologies in which the aircraft have several
neighbors in direct communication. This allows for a viable
alternative to subsea cables, enabling mobile phone service
providers, internet service providers (ISPs), and other providers
to reach markets they would not otherwise be able to reach.
Embodiments of this disclosure may also be used to establish
private networks over long distances.
[0017] In some embodiments, other types of equipment may also be
included, such as radar (which may be used for military or other
purposes, to locate other lighter-than-air aircraft for mesh
networking purposes, to locate other aircraft generally for
navigational or other purposes, to monitor weather, etc.),
scientific instrumentation (e.g., advanced weather monitoring,
climate monitoring, earth observation, space observation with
telescopes or antennas, etc.), cameras (e.g., real-time earth
monitoring, HD, multiple spectrum, military or law enforcement,
surveillance, traffic monitoring, etc.), power beaming equipment,
and any other desired type of aerial equipment. In some
embodiments, a lighter-than-air aircraft according to this
disclosure may be sized to carry payloads of up to 200 pounds. In
other embodiments, payloads of up to 400 pounds or even larger may
be attainable with larger amounts of lifting gas, etc.
[0018] Aircraft according to this disclosure may travel at any
desired altitude, but various considerations (such as typical wind
speeds and regulatory concerns) may make it advantageous to travel
in class E airspace at 60,000 feet above sea level or higher.
[0019] In some embodiments, backhaul connectivity for a group of
aircraft may be established as a mesh network. For example, each
aircraft may employ station-keeping techniques to maintain a
selected geodetic position (e.g., by varying buoyancy for altitude
adjustments and by using one or more propellers for rotational,
latitude and longitude adjustments). If the aircraft are able to
maintain position with sufficient accuracy, then directional
antennas may be employed for communications among the aircraft. In
some embodiments, a given aircraft's directional antenna may be
aligned with other aircraft by rotating the entire aircraft to keep
the directional antenna pointed in a desired direction. In other
embodiments, directional antennas may be rotatable independently
from the aircraft to which they are attached.
[0020] If a ground station such as an ISP has a hardwired link to a
communications network, then one aircraft may be placed nearby to
communicate with the ground station (e.g., via a directional
antenna), and other aircraft may be placed in string or in some
other configuration that allows communications to flow through the
mesh back to the ground station. In some embodiments (e.g., with
sufficiently powerful directional antennas), the curvature of the
earth may be a limiting factor for how far apart aircraft according
to this disclosure may be placed while still remaining in
line-of-sight communication. For example, at a height of 60,000
feet above sea level (and assuming relatively flat terrain between
adjacent aircraft), a spacing of around 600 miles may be
feasible.
[0021] Aircraft according to this disclosure may provide a stable,
reliable, long-life, low-cost platform. Further, the design of such
aircraft makes them amenable to easy, compact transportation. For
example, even though a deployed aircraft may be quite large (e.g.,
a diameter on the order of 200 feet), it may be deflated and
"rolled up" (as described below) to fit into a standard 18-wheeler
truck, shipping container, or rail container.
[0022] Station keeping, navigation, and various other functions of
aircraft according to this disclosure may be computer-controlled in
some embodiments. For example, an onboard computer may be
configured to control the propellers and/or the buoyancy level of
an aircraft. In some embodiments, such an onboard computer may be
hard-coded with instructions as desired. In other embodiments, an
onboard computer may be configured to receive instructions on the
fly (e.g., from another aircraft or from a ground-based operator).
For example, such instructions may in some embodiments be
communicated via the mesh network backhaul.
[0023] Turning now to FIG. 1, an example of lighter-than-air
aircraft 100 is shown. Lighter-than-air aircraft 100 is shown with
an aerodynamic lenticular (lens-shaped) outer membrane 102, and
rigid ring 105 is disposed around the circumference thereof.
Typically, although not necessarily, outer membrane 102 is
airtight.
[0024] The lenticular shape of outer membrane 102 reduces drag
applied by the wind, but various other shapes are also possible
within the scope of this disclosure. As will be discussed in more
detail below, rigid ring 105 may be arranged in several sections
that can be disassembled from one another (for example, to reduce
size during ground shipping of aircraft 100). Several structural
members 104 extend radially from a central core portion (not shown)
to rigid ring 105. One or more flexible bladders (not shown) inside
outer membrane 102 may be filled with a lighter-than-air gas such
as hydrogen or helium, also referred to as a lifting gas. Aircraft
100 also includes several propellers 106, which may be used for
station keeping and/or to move aircraft 100 to a desired location.
Propellers 106 may be mounted rigidly to rigid ring 105, or they be
mounted rotatably to allow them to exert force in different
directions as desired. In some embodiments, propellers 106 may be
mounted in propeller nacelles attached to rigid ring 105. In some
embodiments, four propellers 106 may be positioned at even
intervals around the circumference of rigid ring 105.
[0025] Power for propellers 106 and for other onboard devices may
be provided via one or more solar panels 108. Due to the design of
aircraft 100, it may be advantageous to use flexible solar
panels.
[0026] Outer membrane 102 may in some embodiments be made of a
flexible material such as biaxially-oriented polyethylene
terephthalate (BoPET), commonly referred to as MYLAR.RTM.. In some
embodiments, the flexible bladders inside outer membrane 102 may be
made of the same material. In other embodiments, outer membrane 102
may be made of a rigid material. In some embodiments, structural
members 104 may be used as non-rigid tension elements to maintain
the shape of outer membrane 102 against the pressure of the
lighter-than-air gas in the bladder(s) inside. In other
embodiments, structural members 104 may be rigid.
[0027] As shown in FIG. 1, various additional elements for aircraft
100 are attached to the bottom. (A more detailed view of these
elements is shown in FIG. 10.) This arrangement, in which the
center of gravity is lowered by such elements, may provide
additional stability compared to other arrangements. One or more
tanks 110 of compressed lifting gas, control circuitry 112, one or
more directional antennas 114, and one or more non-directional
(also referred to as omnidirectional) antennas 116 are shown
attached to the bottom of aircraft 100. Directional antennas 114
may be used for mesh networking among aircraft, for communicating
with ground stations, etc. Non-directional antennas 116 may be used
for providing mobile phone service, Wi-Fi connections, etc.
[0028] Tanks 110 of compressed lifting gas may be used to refill
the bladders inside outer membrane 102 to account for losses due to
diffusion or leaks. Tanks 110 may also be used to add lifting gas
from the bladders to increase the buoyancy of aircraft 100. Gas may
also be released from the bladders to decrease buoyance. In some
embodiments, a compressor may be included so that gas removed from
the bladders may be placed back into tanks 110; in other
embodiments, gas removed from the bladders may be vented to the
atmosphere.
[0029] Control circuitry 112 generally includes any circuitry,
computing devices, or other hardware needed to operate aircraft
100. Control circuitry 112 may also include the telecommunications
circuitry used to communicate via directional antennas 114 and
non-directional antennas 116. As one example, telecommunications
circuitry may include the same type of circuitry that is typically
deployed within a cell tower. In another example, more than one set
of such cell tower circuitry may be included in control circuitry
112 for purposes of providing more than one type of cellular
service (e.g., for different providers). In yet another example, a
customized set of circuitry configured to carry out such functions
may be included in control circuitry 112. For example, some
otherwise-redundant functionality in multiple sets of cell tower
circuitry may be consolidated into a single set of circuitry to
save weight.
[0030] Control circuitry 112 may also include one or more batteries
to be charged by solar panel 108 and to power aircraft 100 at
night. In some embodiments, it may be advantageous to thermally
insulate control circuitry 112, for example because batteries may
not perform well at the cold temperatures that are typical at
60,000 feet and higher. In some embodiments, one or more heaters
may be included in control circuitry 112 for this reason; in other
embodiments, the waste heat from other components of control
circuitry 112 may be sufficient to maintain a desired
temperature.
[0031] Turning now to FIG. 2, another similar embodiment is shown
as aircraft 200. The components of aircraft are generally similar
to those having corresponding reference numerals. That is, outer
membrane 202 corresponds to outer membrane 102 in FIG. 1, etc. (In
FIG. 2 and other figures, for the sake of brevity, corresponding
elements with corresponding reference numerals may not be described
in detail in every figure when it is clear from context what such
reference numerals refer to.)
[0032] In addition to the elements that are similar to aircraft
100, aircraft 200 further includes tail 218. Tail 218 in some
embodiments may be used similarly to a tail fin in a windmill, to
keep aircraft 200 pointing into the wind so that propellers 206 in
certain arrangements may operate more efficiently to keep station.
In other embodiments, tail 218 may be adjustable and usable as a
rudder to steer aircraft 200. Generally speaking, any vertical
member (or any member with a vertical component) may be used for
such purposes. In some embodiments, tail 218 may be formed as an
airfoil; in other embodiments, tail 218 may be formed as a flat
surface.
[0033] Turning now to FIG. 3, a cross-sectional view of aircraft
300 is shown. Inside outer membrane 302, two bladders 326 are now
visible. Bladders 326 may be filled with any suitable
lighter-than-air gas to provide buoyancy to aircraft 300. In
between outer membrane 302 and bladders 326, interstitial space 328
is designated. Interstitial space 328 may be maintained at any
desired pressure and may affect the overall volume (and thus the
overall buoyancy) of the lifting gas. In some embodiments,
interstitial space 328 may be maintained at the same pressure as
bladders 326. In other embodiments, the pressures may be
substantially equal ("substantially equal" being defined, for
purposes of this disclosure, as within 1% of equal). In still other
embodiments, the pressures may be within 5% of equal. In yet other
embodiments, the pressure in interstitial space 328 may be
maintained at whatever pressure is needed to cause bladders 326 to
attain a desired volume. Maintaining interstitial space 328 at a
pressure similar to that of bladders 326 may reduce the rate of
diffusion of lighter-than-air gas out of bladders 326 into
interstitial space 328, and so it may be advantageous to keep the
pressures relatively close.
[0034] Also visible in FIG. 3 is rigid core 320, which is
cylindrically disposed along the central axis of aircraft 300.
Rigid core 320 provides some structural support to aircraft 300,
and it may also house various components. For example, in FIG. 3,
gas distribution valves 322 are shown inside rigid core 320. Gas
distribution valves 322 may be used to control the amount of
lighter-than-air gas in each bladder 326. In some embodiments, the
amount of lighter-than-air gas in each bladder may be adjusted
independently. For example, this may be done in order to achieve a
desired pitch or angle (as a non-horizontal angle may be
advantageous during ascent or descent, as well as other times). In
this embodiment, rigid core 320 further includes compressor 324,
which may be used to adjust the pressure in the interstitial space.
In some embodiments, an additional compressor (not shown) may
remove lighter-than-air gas from bladders 326 and store it in tanks
310.
[0035] Turning now to FIG. 4, an embodiment of bladder 400 is shown
that is similar to one of bladders 326 in FIG. 3. Tanks 410 provide
lighter-than-air gas to bladder 400 via gas distribution valve
422.
[0036] As pictured, bladder 400 subtends one quarter of a full
circular arc, and so in this embodiment, four bladders 400 would be
used in a single aircraft. In various embodiments, one, two, three,
four, five, or any other number of bladders may be used in a
particular aircraft as desired.
[0037] Turning now to FIG. 5, a partially disassembled
lighter-than-air aircraft 500 is shown. The rigid ring mentioned in
the earlier figures has been disassembled into rigid ring segments
505. In one embodiment, rigid ring segments 505 are configured to
attach together end-to-end in a "tent pole" configuration, wherein
the tip of one segment goes inside a hole at the tip of the next
segment. Various other embodiments for a rigid ring that can be
disassembled into rigid ring segments 505 will be apparent to one
of ordinary skill in the art with the benefit of this disclosure,
however. When aircraft 500 is assembled, the assembled rigid ring
segments may be embedded in the outer membrane or attached to the
outer membrane in any suitable manner.
[0038] As shown, outer membrane 502 with deflated bladders inside
(which are not visible in this view) has been wrapped around rigid
core 520. Accordingly, disassembled aircraft 500 has been
drastically reduced in size compared to its deployed
dimensions.
[0039] Turning now to FIG. 6, disassembled aircraft 600 is shown
being transported in a standard 18-wheeler, truck 630. The ability
to deflate the lighter-than-air gas bladders, remove the rigid ring
segments, and wrap the bladders and outer membrane 602 around rigid
core 620 provides for extremely easy transport and deployment of
aircraft 600. Rigid ring segments (not shown) may be stored
alongside aircraft 600 within truck 630 or in any other suitable
manner.
[0040] Once disassembled aircraft 600 has arrived at its deployment
location, it may be assembled and deployed relatively quickly, in
just a few hours. At a high level, the deployment procedure
includes inflating the outer membrane somewhat to give shape to the
aircraft (e.g., the interstitial space may be inflated), attaching
the rigid ring to the outer membrane, attaching any solar panels
and propeller nacelles, and inflating the lighter-than-air gas
bladders inside the outer membrane. The aircraft may then be
pressure-tested and deployed immediately.
[0041] The deployment term of an aircraft according to this
disclosure may be quite long, extending without service for years
in some embodiments. Eventually, however, it may become necessary
to recover a deployed aircraft for service, upgrades, and the like.
The recovery of an aircraft at the end of its deployment is similar
to the procedure described above, but in reverse. The aircraft may
be instructed to remove some lighter-than-air gas (or to increase
the pressure in the interstitial space to reduce the volume of the
bladders) to reduce the buoyancy of the aircraft and bring it to
the ground, and then the bladders may be deflated. The solar panels
and propeller nacelles may be removed, the rigid ring may be
removed and disassembled, and the interstitial space may be
deflated. Finally, the outer membrane (e.g., with the bladders
still inside) may be wrapped around the rigid core.
[0042] Turning now to FIG. 7, a plurality of lighter-than-air
aircraft 702, 704, 706, and 708 are shown carrying out various
functions. Aerial backhaul 710, which may be implemented via
directional antennas such as high-gain microwave antennas, connects
each aircraft to the other aircraft in a mesh network.
[0043] Ground station 712 is linked to the greater internet via
ground-based backhaul 716 and receives various types of data via
that connection. For example, TV and radio stations (not shown) may
provide data via ground-based backhaul 716 that is to be broadcast.
Aircraft 702 is connected to ground station 712 via air-to-ground
backhaul 714 and transmits such data to aircraft 704 via aerial
backhaul 710. (The term "air-to-ground backhaul" should be
understood to include data links that flow in either direction or
both directions.) Aircraft 704 is then able to broadcast the data
(e.g., radio broadcast data, TV broadcast data, or other broadcast
data) via one or more omnidirectional antennas. As shown, due to
the terrain between ground station 712 and the broadcast area
underneath aircraft 704, this procedure would be infeasible without
the benefit of this disclosure.
[0044] Additionally, aircraft 704 has a data connection to building
718 (which may be a ground-based ISP, a home, or a business) via
air-to-ground backhaul 720. Building 718 may thus receive internet
backhaul to the greater internet via air-to-ground backhaul 720,
aerial backhaul 710, and finally ground-based backhaul 716. Thus in
some embodiments, aircraft according to this disclosure may be used
as a tier 1 solution that provides backhaul to a traditional
ISP.
[0045] Finally, aircraft 706 is an element of the mesh network and
participates as a link in aerial backhaul 710, but it does not
provide any additional telecommunications services to its coverage
area (which, for a typical LTE antenna, might be an area of
approximately 3420 square miles). However, surplus solar radiation
collected at the solar panels of aircraft 706 may be transmitted
(e.g., via microwave power transmission technology or any other
suitable method) to ground-based power receiver 722. In some
embodiments, aircraft 706 may employ a station-keeping strategy
that keeps its solar panels aimed toward the sun (at least to some
extent) as the sun tracks across the sky. For example, aircraft 706
may be rotated such that an amount of solar radiation incident on
its solar panels is maximized. That is, aircraft 706 may be
configured to maintain a particular position, but to change its
geodetic rotational orientation in response to the position of the
sun. In such an embodiment, it may be desirable to employ
independently rotatable directional antennas (described in more
detail below with reference to FIG. 11) to maintain aerial backhaul
710 while aircraft 706 rotates.
[0046] FIG. 7 provides a few examples of the types of things that
are made possible according to the present disclosure. Various
other uses to which the aircraft of this disclosure may be put will
be apparent to one of ordinary skill in the art with the benefit of
this disclosure.
[0047] Turning now to FIGS. 8A and 8B, close-up views of an
embodiment of a device for measuring the inflation level of a
bladder are shown. Bladder 826 may be installed in any of the
various aircraft of this disclosure.
[0048] As shown, rigid core 820 includes gas distribution valve 822
for filling (or otherwise adjusting the inflation level of) bladder
826. Lever arm 832 is configured to press inward against a surface
of bladder 826 (to which it may or may not be attached). Tension
element 834, such as a spring may be used to provide some force
against the surface of bladder 826. Potentiometer 836 measures the
angular position of lever arm 832.
[0049] In FIG. 8A, bladder 826 is partially deflated, and the
position of lever arm 832 reflects this. In FIG. 8B, bladder 826
has been fully inflated, and the position of lever arm 832 has
adjusted to reflect this new state. The value of potentiometer 836
will also reflect this change, and can be measured in any of
various known ways. Once calibrated, the value of potentiometer 836
can be correlated directly to the inflation level of bladder
826.
[0050] In some embodiments, lever arm 832 may be coupled to rigid
core 820. For example, a pivot of lever arm 832 may be disposed at
a central top portion of the aircraft.
[0051] In some embodiments, one lever arm 832 is used for each
bladder in the aircraft. In other embodiments, arrangements are
contemplated in which multiple lever arms 832 are used for each
bladder.
[0052] Turning now to FIGS. 9A and 9B, close-up views of another
embodiment of a device for measuring the inflation level of a
bladder are shown. This embodiment uses optical measuring, such as
a laser ranging system, to determine the position of a surface of
bladder 926. For example, such a system might measure a delay time
associated with a reflection of an optical pulse to determine a
distance. In other embodiments, a camera-based measuring apparatus
may be used.
[0053] Similarly to in FIGS. 8A and 8B, bladder 926 is attached to
rigid core 920, and its inflation level is controlled via gas
distribution valve 922. Optical measuring device 938 is configured
to measure a distance 940 to a selected location on the surface of
bladder 926.
[0054] As shown in FIG. 9A, bladder 926 is partially deflated, and
distance 940 is measured as being a relatively large value. In FIG.
9B, bladder 926 has been fully inflated, and distance 940 is
measured as being a smaller value. Once calibrated, the value
measured for distance 940 can be correlated directly to the
inflation level of bladder 926.
[0055] Once an inflation level has been measured (e.g., as in FIGS.
8A and 8B, or FIGS. 9A and 9B), various actions may be taken based
on the result. If the inflation level is lower than desired, for
instance, additional lifting gas may be supplied to the bladders.
If the inflation level is higher than desired, some lifting gas may
be removed from the bladders, and either vented to the atmosphere
or re-compressed into a storage tank. Alternatively, pressure may
be increased in the interstitial space to reduce the volume of the
bladders.
[0056] Turning now to FIG. 10, a close-up view of the elements that
may be suspended below aircraft 1000 is shown. Similar to what was
described above with reference to FIG. 1, such elements may include
lighter-than-air gas tanks 1010, control circuitry 1012,
directional antenna 1014, and non-directional antenna 1016.
[0057] These elements (and any other desired elements) may be
suspended from aircraft 1000 via rigid member 1042. Rigid member
1042 may enclose gas tubing (not visible) for allowing
lighter-than-air gas to flow between tanks 1010 and the bladders
via the gas distribution valves in the rigid core. In some
embodiments, rigid member 1042 may itself be a rigid, airtight
pipe, and so a separate gas tubing element may not be necessary.
Rigid member 1042 may be removed from the rigid core (not shown) in
order to ease transportation and/or construction of the rigid ring
while on the ground. Rigid member may also be mounted on a hinge,
shifting the center of gravity, and thereby changing the pitch
(angle) of the aircraft as desired for optimal ascent and
descent.
[0058] Turning now to FIG. 11, another close-up view of elements
that may be suspended below aircraft 1100 is shown. As above, such
elements may include lighter-than-air gas tanks 1110, control
circuitry 1112, and directional antenna 1114. Additionally,
aircraft 1100 includes rotatable joint 1144, which includes slip
ring 1146 for transmission of power and/or signals between control
circuitry 1112 and directional antenna 1114. In some embodiments,
wireless data and/or power transmission techniques may be used
instead of connections based on slip ring 1146.
[0059] As shown, directional antenna 1114 may be rotated separately
from the rest of aircraft 1100 by antenna drive motor 1148. That
is, directional antenna 1114 may be rotated actively and
independently, for example to maintain antenna alignment with some
other aircraft or a ground station as aircraft 1100 itself rotates
(e.g., due to wind, or to track the sun with its solar panels, or
for any other reason). In other embodiments, directional antenna
1114 may be rotated even while aircraft 1100 is not rotating, for
example to change its direction from one aircraft to a different
aircraft.
[0060] In embodiments with more than one directional antenna, a
plurality of rotatable joints and motors may be used to rotate each
directional antenna independently. For example, such an embodiment
may allow aircraft 1100 to track several other aircraft
simultaneously, whether or not aircraft 1100 is itself currently
rotating. In other embodiments with multiple directional antennas,
only one rotatable joint and motor might be used, such that all of
the directional antennas are set at fixed angles relative to one
another. In that case, the entire assembly of directional antennas
may be rotated as a whole, for example to maintain alignment within
a mesh network. Further, in some embodiments, each directional
antenna may be adjusted in the vertical direction as well if
necessary. For example, each directional antenna may be attached to
a gimbal mount or any other type of vertically adjustable
mount.
Example Methods
[0061] Various methods of making and using the aircraft and other
apparatuses disclosed herein are also specifically contemplated
within the scope of this disclosure. Some of such methods will now
be described; others will be apparent to one of ordinary skill in
the art with the benefit of this disclosure. The methods herein may
be used in conjunction with any of the aircraft, apparatuses,
computer systems, or components disclosed herein, among other
devices. In various embodiments, some of the method elements shown
may be performed concurrently, in a different order than shown, or
may even be omitted altogether. Additional method elements may also
be performed as desired.
[0062] Turning now to FIG. 12, a block diagram of one example of
such a method, process flow 1200, is shown. Flow begins at step
1202.
[0063] At step 1202, a lighter-than-air aircraft that includes a
plurality of propellers and a directional antenna is maintained at
a selected aerial geodetic position. For example, the
lighter-than-air aircraft may be maintained at the selected aerial
geodetic position by actuating the propellers, adjusting buoyancy,
etc. Flow proceeds to step 1204.
[0064] At step 1204, the lighter-than-air aircraft is caused to
communicate via the directional antenna with another
lighter-than-air aircraft. As shown, the other lighter-than-air
aircraft also includes a corresponding directional antenna, which
may be used for such communications. Flow ends at step 1204.
Example Computing System
[0065] Various operations described herein may be implemented by a
computing device configured to execute program instructions that
specify the operations. Similarly, various operations may be
performed by circuitry desired or configured to perform the
operations. In some embodiments, a non-transitory computer-readable
medium has program instructions stored thereon that are capable of
causing various operations described herein. As used herein, the
term "processing element" refers to various elements or
combinations of elements configured to execute program
instructions. Processing elements include, for example, circuits
such as an ASIC (Application Specific Integrated Circuit), portions
or circuits of individual processor cores, entire processor cores,
individual processors, programmable hardware devices such as a
field programmable gate array (FPGA), and/or larger portions of
systems that include multiple processors, as well as any
combinations thereof.
[0066] Various embodiments may include storing instructions and/or
data implemented in accordance with the foregoing description in a
tangible computer-readable memory medium. Certain embodiments of
these computer-readable memory media may include instructions
and/or data that are computer executable to perform actions in
accordance with the present disclosure. Generally speaking, such an
article of manufacture may include storage media or memory media
such as magnetic (e.g., disk) or optical media (e.g., CD-ROM and
related technologies, DVD-ROM, etc.). The article of manufacture
may be either volatile or nonvolatile memory. For example, the
article of manufacture may be (without limitation) RAM of various
types, flash memory, ROM of various types, etc. The article of
manufacture may also be a transmission medium.
[0067] Further embodiments may include signals such as electrical,
electromagnetic, or optical signals, conveyed via a communication
medium, link, and/or system (e.g., cable, network, etc.), whether
wired, wireless or both. Such signals may carry instructions and/or
data implemented in accordance with the foregoing description.
[0068] Turning now to FIG. 13, a block diagram of a computing
device (which may also be referred to as a computing system) 1310
is depicted, according to some embodiments. Computing device 1310
may be used to implement various portions of this disclosure.
Computing device 1310 is one example of a device that may be used
as a mobile device, a server computing system, a client computing
system, an embedded computing system, a microcontroller-based
computing system, or any other computing system implementing
portions of this disclosure.
[0069] Computing device 1310 may be any suitable type of device,
including, but not limited to, a personal computer system, desktop
computer, laptop or notebook computer, mobile phone, mainframe
computer system, web server, workstation, or network computer. As
shown, computing device 1310 includes processing unit 1350, storage
subsystem 1312, input/output (I/O) interface 1330 coupled via
interconnect 1360 (e.g., a system bus). I/O interface 1330 may be
coupled to one or more I/O devices 1340. Computing device 1310
further includes network interface 1332, which may be coupled to
network 1320 for communications with, for example, other computing
devices.
[0070] As described above, processing unit 1350 includes one or
more processors. In some embodiments, processing unit 1350 includes
one or more coprocessor units. In some embodiments, multiple
instances of processing unit 1350 may be coupled to interconnect
1360. Processing unit 1350 (or each processor within processing
unit 1350) may contain a cache or other form of on-board memory. In
some embodiments, processing unit 1350 may be implemented as a
general-purpose processing unit, and in other embodiments it may be
implemented as a special purpose processing unit (e.g., an ASIC).
In general, computing device 1310 is not limited to any particular
type of processing unit or processor subsystem.
[0071] As used herein, the terms "processing unit" or "processing
element" refer to circuitry configured to perform operations or to
a memory having program instructions stored therein that are
executable by one or more processors to perform operations.
Accordingly, a processing unit may be implemented as a hardware
circuit implemented in a variety of ways. The hardware circuit may
include, for example, custom very-large-scale integration (VLSI)
circuits or gate arrays, off-the-shelf semiconductors such as logic
chips, transistors, or other discrete components. A processing unit
may also be implemented in programmable hardware devices such as
field programmable gate arrays, programmable array logic,
programmable logic devices, or the like. A processing unit may also
be configured to execute program instructions or computer
instructions from any suitable form of non-transitory
computer-readable media to perform specified operations.
[0072] Storage subsystem 1312 is usable by processing unit 1350
(e.g., to store instructions executable by and data used by
processing unit 1350). Storage subsystem 1312 may be implemented by
any suitable type of physical memory media, including hard disk
storage, floppy disk storage, removable disk storage, flash memory,
random access memory (RAM-SRAM, EDO RAM, SDRAM, DDR SDRAM, RDRAM,
etc.), ROM (PROM, EEPROM, etc.), and so on. Storage subsystem 1312
may consist solely of volatile memory in some embodiments. Storage
subsystem 1312 may store program instructions executable by
computing device 1310 using processing unit 1350, including program
instructions executable to cause computing device 1310 to implement
the various techniques disclosed herein.
[0073] I/O interface 1330 may represent one or more interfaces and
may be any of various types of interfaces configured to couple to
and communicate with other devices, according to various
embodiments. In some embodiments, I/O interface 1330 is a bridge
chip from a front-side to one or more back-side buses. I/O
interface 1330 may be coupled to one or more I/O devices 1340 via
one or more corresponding buses or other interfaces. Examples of
I/O devices include storage devices (hard disk, optical drive,
removable flash drive, storage array, SAN, or an associated
controller), network interface devices, user interface devices or
other devices (e.g., graphics, sound, etc.).
Example Embodiments
[0074] A numbered list of example embodiments follows. Although
they are written in claim-like language, these embodiments are not
the claims of this application (which follow in a separate
section), but are merely a number of embodiments that are
specifically contemplated and disclosed herein. This list should be
taken as exemplary, not exclusive.
[0075] 1. An apparatus, comprising: an outer membrane formed in a
circular lenticular shape by a plurality of structural members,
wherein the structural members extend radially along the circular
lenticular shape; a flexible bladder within the outer membrane; a
rigid circular ring disposed circumferentially around the circular
lenticular shape; and a plurality of propellers coupled to the
apparatus and operable to maintain the apparatus in a selected
geodetic position; wherein the apparatus is operable to float at a
selected altitude based on a quantity of lighter-than-air gas in
the flexible bladder.
[0076] 2. The apparatus of any other embodiment, further
comprising: a solar panel configured to provide power to the
apparatus.
[0077] 3. The apparatus of any other embodiment, further
comprising: a microwave power transmission antenna configured to
transmit at least a portion of the power provided by the solar
panel to a ground station.
[0078] 4. The apparatus of any other embodiment, wherein the
plurality of propellers are operable to maintain the solar panel in
an orientation toward the sun.
[0079] 5. The apparatus of any other embodiment, wherein the
lighter-than-air gas comprises hydrogen gas.
[0080] 6. The apparatus of any other embodiment, wherein the
plurality of propellers are further operable to maintain the
apparatus in a selected rotational orientation.
[0081] 7. The apparatus of any other embodiment, further comprising
a tank operable to contain a compressed form of the
lighter-than-air gas.
[0082] 8. The apparatus of any other embodiment, further comprising
an inflation-measuring device that includes at least one lever arm
configured to be angularly displaced by the quantity of the
lighter-than-air gas in the flexible bladder.
[0083] 9. The apparatus of any other embodiment, further comprising
a plurality of flexible bladders.
[0084] 10. The apparatus of any other embodiment, wherein a region
of the apparatus disposed between the flexible bladder and the
outer membrane is maintained at a pressure substantially equal to a
pressure within the flexible bladder.
[0085] 11. The apparatus of any other embodiment, further
comprising control circuitry operable to maintain a region of the
apparatus disposed between the flexible bladder and the outer
membrane at a pressure selected to cause the flexible bladder to
have a desired volume.
[0086] 12. The apparatus of any other embodiment, wherein a region
of the apparatus disposed between the flexible bladder and the
outer membrane is maintained at a selected pressure, wherein the
selected pressure is based on a diffusion rate of the
lighter-than-air gas.
[0087] 13. The apparatus of any other embodiment, further
comprising a tail operable to orient the apparatus based on a wind
direction.
[0088] 14. The apparatus of any other embodiment, further
comprising a rudder operable to steer the apparatus.
[0089] 15. The apparatus of any other embodiment, further
comprising a rigid core disposed within a central portion of the
circular lenticular shape.
[0090] 16. The apparatus of any other embodiment, further
comprising at least one non-directional antenna.
[0091] 17. The apparatus of any other embodiment, wherein the at
least one non-directional antenna is an antenna configured to
communicate with mobile phones.
[0092] 18. The apparatus of any other embodiment, wherein the at
least one non-directional antenna is a Long-Term Evolution (LTE)
antenna.
[0093] 19. The apparatus of any other embodiment, wherein the at
least one non-directional antenna is a 3G antenna.
[0094] 20. The apparatus of any other embodiment, wherein the at
least one non-directional antenna is a Wi-Fi antenna.
[0095] 21. The apparatus of any other embodiment, wherein the outer
membrane is flexible.
[0096] 22. The apparatus of any other embodiment, wherein the outer
membrane is made of biaxially-oriented polyethylene terephthalate
(BoPET).
[0097] 23. The apparatus of any other embodiment, further
comprising telecommunications circuitry coupled to the apparatus,
wherein the apparatus is further operable to communicate via the
telecommunications circuitry.
[0098] 24. The apparatus of any other embodiment, wherein the
plurality of structural members are rigid.
[0099] 25. The apparatus of any other embodiment, wherein the
plurality of structural members are non-rigid, tension members.
[0100] 26 An apparatus, comprising: a central core portion; a
flexible membrane wrapped around the central core portion; a
plurality of structural members coupled to the flexible membrane;
and a plurality of ring segments coupled to the flexible membrane;
wherein: the plurality of ring segments are assemblable into a
rigid ring disposed around a perimeter of the flexible membrane;
the plurality of structural members are operable to form the
flexible membrane in a selected shape; and wherein the apparatus is
operable to float at a selected altitude.
[0101] 27. The apparatus of any other embodiment, wherein the
central core portion is cylindrical.
[0102] 28. The apparatus of any other embodiment, wherein the
flexible membrane includes a flexible solar panel coupled
thereto.
[0103] 29. The apparatus of any other embodiment, wherein the
plurality of ring segments are embedded in the flexible
membrane.
[0104] 30. The apparatus of any other embodiment, wherein the
plurality of structural members are non-rigid, tension
elements.
[0105] 31. The apparatus of any other embodiment, wherein the
plurality of structural members are disposed radially in the
selected shape.
[0106] 32. The apparatus of any other embodiment, further
comprising a flexible bladder disposed within the flexible
membrane.
[0107] 33. The apparatus of any other embodiment, wherein the
flexible bladder is inflatable to cause expansion of the flexible
membrane.
[0108] 34. An apparatus, comprising: a lighter-than-air aircraft
that includes: a plurality of propellers configured to maintain the
apparatus at a selected geodetic position; and a directional
antenna; wherein the directional antenna is configured to
communicate with at least one other lighter-than-air aircraft that
includes an other directional antenna.
[0109] 35. The apparatus of any other embodiment, wherein the
plurality of propellers is further configured to maintain the
apparatus at a selected rotational orientation that aims the
directional antenna at the other directional antenna.
[0110] 36. The apparatus of any other embodiment, wherein the
directional antenna is rotatable relative to the apparatus.
[0111] 37. The apparatus of any other embodiment, wherein the
lighter-than-air aircraft is configured to rotate the directional
antenna in an orientation aimed at the other directional
antenna.
[0112] 38. The apparatus of any other embodiment, wherein the
lighter-than-air aircraft includes a balloon.
[0113] 39. The apparatus of any other embodiment, wherein the
lighter-than-air aircraft is a balloon.
[0114] 40. The apparatus of any other embodiment, wherein the
lighter-than-air aircraft is an airship.
[0115] 41. The apparatus of any other embodiment, wherein the
lighter-than-air aircraft is a drone.
[0116] 42. The apparatus of any other embodiment, wherein the
directional antenna is an optical antenna.
[0117] 43. The apparatus of any other embodiment, further
comprising a radar unit.
[0118] 44. A method, comprising: maintaining a lighter-than-air
aircraft at a selected aerial geodetic position, wherein the
lighter-than-air aircraft includes: a plurality of propellers; and
a directional antenna; and causing, via the directional antenna,
the lighter-than-air aircraft to communicate with at least one
other lighter-than-air aircraft that includes an other directional
antenna.
[0119] 45. An apparatus, comprising: an outer membrane formed in a
selected shape by a plurality of structural members; a flexible
bladder within the outer membrane; and wherein the apparatus is
operable to float at a selected altitude based on a quantity of
lighter-than-air gas in the flexible bladder; and wherein a
pressure of the lighter-than-air gas in the flexible bladder is
substantially equal to a pressure of a gas in an interstitial space
between the flexible bladder and the outer membrane.
[0120] 46. The apparatus of any other embodiment, wherein the
pressure of the lighter-than-air gas is within 5% of the pressure
of the gas in the interstitial space.
[0121] 47. The apparatus of any other embodiment, wherein the
pressure of the gas in the interstitial space is selected such that
the flexible bladder maintains a desired volume.
[0122] 48. The apparatus of any other embodiment, further
comprising telecommunications circuitry coupled to the
apparatus.
[0123] 49. An apparatus, comprising: an outer membrane formed in a
selected shape by a plurality of structural members; a flexible
bladder within the outer membrane; and at least one lever arm
configured to be angularly displaced by a volume of
lighter-than-air gas in the flexible bladder; wherein the apparatus
is operable to float at a selected altitude based on a quantity of
lighter-than-air gas in the flexible bladder.
[0124] 50. The apparatus of any other embodiment, wherein a pivot
point of the at least one lever arm is disposed at a central top
portion of the apparatus.
[0125] 51. The apparatus of any other embodiment, further
comprising a tensioning member configured to resist the
displacement of the at least one lever arm.
[0126] 52. The apparatus of any other embodiment, further
comprising a tensioning member configured to displace the at least
one lever arm in a direction other than the displacement of the at
least one lever arm by the volume of lighter-than-air gas in the
flexible bladder.
[0127] 53. The apparatus of any other embodiment, wherein the at
least one lever arm comprises a plurality of lever arms.
[0128] 54. The apparatus of any other embodiment, further
comprising a potentiometer operable to measure the angular
displacement of the at least one lever arm.
[0129] 55. The apparatus of any other embodiment, further
comprising control circuitry configured to adjust an inflation
level of the flexible bladder based on the angular
displacement.
[0130] 56. The apparatus of any other embodiment, wherein the at
least one lever arm is attached to the flexible bladder.
[0131] 57. The apparatus of any other embodiment, wherein the at
least one lever arm is not attached to the flexible bladder.
[0132] 58. The apparatus of any other embodiment, further
comprising telecommunications circuitry coupled to the
apparatus.
[0133] 59. An apparatus, comprising: an outer membrane formed in a
selected shape by a plurality of structural members; a flexible
bladder within the outer membrane; and an optical system configured
to determine a volume of lighter-than-air gas in the flexible
bladder; wherein the apparatus is operable to float at a selected
altitude based on a quantity of lighter-than-air gas in the
flexible bladder.
[0134] 60. The apparatus of any other embodiment, wherein the
optical system includes a laser configured to project light onto a
portion of the flexible bladder.
[0135] 61. The apparatus of any other embodiment, further
comprising control circuitry configured to measure a delay time
associated with the light.
[0136] 62. The apparatus of any other embodiment, wherein the
optical system includes a laser exterior to the outer membrane that
is configured to project light onto a portion of the outer
membrane.
[0137] 63. The apparatus of any other embodiment, further
comprising telecommunications circuitry coupled to the
apparatus.
[0138] 64. An apparatus, comprising: an outer membrane formed in a
selected shape by a plurality of structural members; a flexible
bladder within the outer membrane; a monitoring system configured
to determine a volume of lighter-than-air gas in the flexible
bladder; and control circuitry configured to adjust the volume of
lighter-than-air gas in the flexible bladder based on the
determined volume; wherein the apparatus is operable to float at a
selected altitude based on a quantity of lighter-than-air gas in
the flexible bladder.
[0139] 65. The apparatus of any other embodiment, wherein the
monitoring system includes at least one lever arm configured to be
angularly displaced by the volume of lighter-than-air gas in the
flexible bladder.
[0140] 66. The apparatus of any other embodiment, wherein the
monitoring system includes an optical ranging system configured to
measure a position of at least a portion of the flexible
bladder.
[0141] 67. The apparatus of any other embodiment, wherein the
optical ranging system is a laser ranging system.
[0142] 68. The apparatus of any other embodiment, wherein the
optical ranging system is a camera-based ranging system.
[0143] 69. The apparatus of any other embodiment, further
comprising telecommunications circuitry coupled to the
apparatus.
[0144] 70. An apparatus, comprising: an outer membrane formed in a
selected shape by a plurality of structural members; a flexible
bladder within the outer membrane; at least one directional antenna
coupled to the apparatus; and a propeller coupled to the apparatus
and operable to aim the at least one directional antenna in a
selected direction; wherein the apparatus is operable to float at a
selected altitude based on a quantity of lighter-than-air gas in
the flexible bladder.
[0145] 71. The apparatus of any other embodiment, further
comprising a plurality of propellers coupled to the apparatus and
operable to aim the at least one directional antenna in a selected
direction.
[0146] 72. The apparatus of any other embodiment, further
comprising a vertical member operable to rotate the apparatus in
response to airflow.
[0147] 73. The apparatus of any other embodiment, wherein the
vertical member is an airfoil.
[0148] 74. The apparatus of any other embodiment, wherein the
vertical member is a rudder, and wherein the apparatus further
comprises control circuitry configured to change a position of the
rudder.
[0149] 75. The apparatus of any other embodiment, wherein the
vertical member is a tail.
[0150] 76. The apparatus of any other embodiment, further
comprising telecommunications circuitry coupled to the at least one
directional antenna.
[0151] 77. An apparatus, comprising: an outer membrane formed in a
selected shape by a plurality of structural members; a flexible
bladder within the outer membrane; at least one solar panel coupled
to the apparatus; and a propeller coupled to the apparatus and
operable to aim the at least one solar panel in a desired
direction; wherein the apparatus is operable to float at a selected
altitude based on a quantity of lighter-than-air gas in the
flexible bladder.
[0152] 78. The apparatus of any other embodiment, wherein the
desired direction is a direction that maximizes an amount of solar
radiation incident on the at least one solar panel.
[0153] 79. The apparatus of any other embodiment, further
comprising control circuitry configured to alter the desired
direction based on a time of day.
[0154] 80. The apparatus of any other embodiment, further
comprising a plurality of propellers coupled to the apparatus and
operable to aim the at least one solar panel in a selected
direction.
[0155] 81. The apparatus of any other embodiment, further
comprising a vertical member operable to rotate the apparatus in
response to airflow.
[0156] 82. The apparatus of any other embodiment, wherein the
vertical member is an airfoil.
[0157] 83. The apparatus of any other embodiment, wherein the
vertical member is a rudder, and wherein the apparatus further
comprises control circuitry configured to change a position of the
rudder.
[0158] 84. The apparatus of any other embodiment, wherein the
vertical member is a tail.
[0159] 85. An apparatus, comprising: an outer membrane formed in a
selected shape by a plurality of structural members; a flexible
bladder within the outer membrane; and telecommunications circuitry
including at least one directional antenna coupled to the
apparatus, wherein the at least one directional antenna is
rotatable relative to the outer membrane; wherein the apparatus is
operable to float at a selected altitude based on a quantity of
lighter-than-air gas in the flexible bladder, and further operable
to communicate via the telecommunications circuitry.
[0160] 86. The apparatus of any other embodiment, further
comprising a plurality of propellers coupled to the apparatus that
are operable to rotate the apparatus to a selected rotational
orientation.
[0161] 87. The apparatus of any other embodiment, wherein the at
least one directional antenna is operable to rotate based on the
rotation of the apparatus.
[0162] 88. The apparatus of any other embodiment, wherein the at
least one directional antenna is operable to maintain a selected
geodetic rotational orientation during rotation of the apparatus by
the plurality of propellers.
[0163] 89. The apparatus of any other embodiment, wherein the at
least one directional antenna includes a plurality of directional
antennas.
[0164] 90. The apparatus of any other embodiment, wherein the
plurality of directional antennas are independently rotatable
relative to one another.
[0165] 91. The apparatus of any other embodiment, wherein the
plurality of directional antennas are maintained at fixed relative
angles to one another.
[0166] 92. The apparatus of any other embodiment, wherein the at
least one directional antenna is coupled to the apparatus via a
slip ring connection configured to transmit power to the at least
one directional antenna.
[0167] 93. The apparatus of any other embodiment, wherein the at
least one directional antenna is coupled to the apparatus via a
slip ring connection configured to transmit data to the at least
one directional antenna.
[0168] 94. The apparatus of any other embodiment, wherein the at
least one directional antenna is operable to receive data from the
apparatus via a local wireless connection.
[0169] 95. The apparatus of any other embodiment, further
comprising a tail operable to orient the apparatus based on a wind
direction.
[0170] 96. The apparatus of any other embodiment, wherein the at
least one directional antenna is operable to maintain a selected
geodetic rotational orientation during rotation of the apparatus by
the tail.
[0171] 97. The apparatus of any other embodiment, further
comprising a solar panel.
[0172] 98. The apparatus of any other embodiment, wherein the
apparatus is configured to rotate based on a sun position.
[0173] 99. The apparatus of any other embodiment, wherein the at
least one directional antenna is operable to maintain a selected
geodetic rotational orientation during rotation of the apparatus
based on the sun position.
[0174] 100. The apparatus of any other embodiment, wherein the at
least one directional antenna is further operable to change a
vertical orientation.
[0175] 101. The apparatus of any other embodiment, wherein the at
least one directional antenna is disposed below the outer
membrane.
[0176] 102. The apparatus of any other embodiment, wherein the
telecommunications circuitry and the at least one directional
antenna are mounted below the outer membrane via a hinged rigid,
and wherein the hinged rigid member is configured to impart a
torque to the outer membrane when actuated
[0177] This specification includes references to "one embodiment,"
"some embodiments," or "an embodiment." The appearances of these
phrases do not necessarily refer to the same embodiment. Particular
features, structures, or characteristics may be combined in any
suitable manner consistent with this disclosure.
[0178] As used herein, the term "based on" is used to describe one
or more factors that affect a determination. This term does not
foreclose the possibility that additional factors may affect the
determination. That is, a determination may be solely based on
specified factors or based on the specified factors as well as
other, unspecified factors. Consider the phrase "determine A based
on B." This phrase specifies that B is a factor is used to
determine A or that affects the determination of A. This phrase
does not foreclose that the determination of A may also be based on
some other factor, such as C. This phrase is also intended to cover
an embodiment in which A is determined based solely on B. As used
herein, the phrase "based on" is synonymous with the phrase "based
at least in part on."
[0179] Within this disclosure, different entities (which may
variously be referred to as "units," "circuits," other components,
etc.) may be described or claimed as "configured" or "operable" to
perform one or more tasks or operations. This formulation--[entity]
configured to [perform one or more tasks]--is used herein to refer
to structure (i.e., something physical, such as an electronic
circuit). More specifically, this formulation is used to indicate
that this structure is arranged to perform the one or more tasks
during operation. A structure can be said to be "configured to"
perform some task even if the structure is not currently being
operated. A "a microwave power transmission antenna configured to
transmit power" is intended to cover, for example, an antenna that
has circuitry that performs this function during operation, even if
the antenna in question is not currently being used (e.g., a power
supply is not connected to it). Thus, an entity described or
recited as "configured to" perform some task refers to something
physical, such as a device, circuit, memory storing program
instructions executable to implement the task, etc. This phrase is
not used herein to refer to something intangible.
[0180] Further, the term "configured to" is not intended to mean
"configurable to." An unprogrammed FPGA, for example, would not be
considered to be "configured to" perform some specific function,
although it may be "configurable to" perform that function, and may
be "configured to" perform that function after programming.
[0181] Reciting in the appended claims that a structure is
"configured to" perform one or more tasks is expressly intended not
to invoke 35 U.S.C. .sctn. 112(f) for that claim element.
Accordingly, none of the claims in this application as-filed are
intended to be interpreted as having means-plus-function elements.
Should Applicant wish to invoke Section 112(f) during prosecution,
it will recite claim elements using the "means for [performing a
function]" construct.
[0182] It is to be understood the present disclosure is not limited
to particular devices or methods, which may, of course, vary. It is
also to be understood that the terminology used herein is for the
purpose of describing particular embodiments only, and is not
intended to be limiting. As used herein, the singular forms "a",
"an", and "the" include singular and plural referents unless the
content clearly dictates otherwise. Furthermore, the word "may" is
used throughout this application in a permissive sense (i.e.,
having the potential to, being able to), not in a mandatory sense
(i.e., must). The term "include," and derivations thereof, mean
"including, but not limited to." The term "coupled" means directly
or indirectly connected.
[0183] Although specific embodiments have been described above,
these embodiments are not intended to limit the scope of the
present disclosure, even where only a single embodiment is
described with respect to a particular feature. Examples of
features provided in the disclosure are intended to be illustrative
rather than restrictive unless stated otherwise. The above
description is intended to cover such alternatives, modifications,
and equivalents as would be apparent to a person skilled in the art
having the benefit of this disclosure. Although various advantages
of this disclosure have been described, any particular embodiment
may incorporate some, all, or even none of such advantages.
[0184] The scope of the present disclosure includes any feature or
combination of features disclosed herein (either explicitly or
implicitly), or any generalization thereof, whether or not it
mitigates any or all of the problems addressed herein. Accordingly,
new claims may be formulated during prosecution of this application
(or an application claiming priority thereto) to any such
combination of features. In particular, with reference to the
appended claims, features from dependent claims may be combined
with those of the independent claims, and features from respective
independent claims may be combined in any appropriate manner and
not merely in the specific combinations enumerated in the appended
claims.
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