U.S. patent application number 16/801075 was filed with the patent office on 2020-10-29 for photonic lambda switching for satellites.
The applicant listed for this patent is The Boeing Company. Invention is credited to Dennis L. Gould, Bradley A. Scott, James P. Scott, Michael A. Whelan.
Application Number | 20200343991 16/801075 |
Document ID | / |
Family ID | 1000005147466 |
Filed Date | 2020-10-29 |
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United States Patent
Application |
20200343991 |
Kind Code |
A1 |
Scott; James P. ; et
al. |
October 29, 2020 |
PHOTONIC LAMBDA SWITCHING FOR SATELLITES
Abstract
A satellite payload system is presented. The system includes
plurality of optical processing modules, including a plurality of
ring-connected optical processing modules and at least one
inter-satellite optical processing module, and at least one optical
fiber ring communicatively coupled to each of the ring-connected
optical processing modules. At least one of the ring-connected
optical processing modules is configured to provide on-board signal
processing of signals conveyed on the at least one optical fiber
ring. At least one of the ring-connected optical processing modules
is communicatively coupled to a respective inter-satellite optical
processing module. Each inter-satellite optical processing module
is configured to optically communicatively couple to a respective
remote satellite.
Inventors: |
Scott; James P.; (Manhattan
Beach, CA) ; Whelan; Michael A.; (Rancho Palos,
CA) ; Scott; Bradley A.; (Silverado, CA) ;
Gould; Dennis L.; (Whittier, CA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
The Boeing Company |
Chicago |
IL |
US |
|
|
Family ID: |
1000005147466 |
Appl. No.: |
16/801075 |
Filed: |
February 25, 2020 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
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16392105 |
Apr 23, 2019 |
10594430 |
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16801075 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
H04B 10/271 20130101;
H04J 14/022 20130101; H04J 14/0204 20130101; H04B 10/118 20130101;
H04J 14/0205 20130101; H04B 10/25755 20130101 |
International
Class: |
H04J 14/02 20060101
H04J014/02; H04B 10/27 20060101 H04B010/27; H04B 10/118 20060101
H04B010/118; H04B 10/2575 20060101 H04B010/2575 |
Claims
1. A satellite payload system comprising: a plurality of optical
processing modules comprising a plurality of ring-connected optical
processing modules and at least one inter-satellite optical
processing module; and at least one optical fiber ring
communicatively coupled to each of the ring-connected optical
processing modules; wherein at least one of the ring-connected
optical processing modules is configured to provide on-board signal
processing of signals conveyed on the at least one optical fiber
ring; wherein at least two of the ring-connected optical processing
modules are each communicatively coupled to a respective
inter-satellite optical processing module; wherein each
inter-satellite optical processing module is configured to
optically communicatively couple to a respective remote
satellite.
2. The satellite payload system of claim 1, wherein each of the
plurality of optical processing modules comprises: a module input
comprising an optical splitter, a module output comprising an
optical coupler, a dynamic gain equalizer interposed between a
first output of the optical splitter and a first input to the
optical coupler, an output bank of optical filters coupled to a
second output of the optical splitter, and an input bank of optical
filters coupled to a second input of the optical coupler.
3. The satellite payload system of claim 2, wherein the at least
two of the plurality of the ring-connected optical processing
modules that are each communicatively coupled to a respective
inter-satellite optical processing module are each communicatively
coupled to a respective inter-satellite optical processing module
via a respective bank of optical filters, and wherein each
inter-satellite optical processing module is configured to
optically communicatively couple to a respective remote satellite
via at least one of its module input and via its module output.
4. The satellite payload system of claim 2, wherein, for each of
the plurality of optical processing modules, the respective output
bank of optical filters, and the respective input bank of optical
filters are dynamically tunable.
5. The satellite payload system of claim 1, wherein each of the
plurality of optical processing modules have identical
architecture.
6. The satellite payload system of claim 1, wherein the at least
one optical fiber ring comprises dual counter-rotating optical
fiber rings.
7. The satellite payload system of claim 1, wherein the at least
one of the ring-connected optical processing modules is configured
to participate in on-board optical signal processing of photonic
data conveyed on the at least one optical fiber ring.
8. The satellite payload system of claim 1, wherein the at least
one of the ring-connected optical processing modules is configured
to participate in on-board radio-frequency signal processing of
electromagnetic data corresponding to at least one signal conveyed
on the at least one optical fiber ring.
9. The satellite payload system of claim 1, configured to provide
selectable optical routing to a plurality of remote satellites.
10. (canceled)
11. A method performed by a satellite payload system, the satellite
payload system comprising: a plurality of optical processing
modules comprising a plurality of ring-connected optical processing
modules and at least one inter-satellite optical processing module,
wherein at least two of the ring-connected optical processing
modules are each communicatively coupled to a respective
inter-satellite optical processing module; and at least one optical
fiber ring communicatively coupled to each of the ring-connected
optical processing modules; the method comprising: communicatively
coupling optically, by at least one inter-satellite processing
module, to a respective remote satellite; passing, by the at least
one inter-satellite processing module and to at least one of the
ring-connected optical processing modules at least one signal
comprising inter-satellite data; and processing, at least in part
by the at least one of the ring-connected optical processing
modules the inter-satellite data.
12. The method of claim 11, wherein each of the plurality of
optical processing modules comprises: a module input comprising an
optical splitter, a module output comprising an optical coupler, a
dynamic gain equalizer interposed between a first output of the
optical splitter and a first input to the optical coupler, an
output bank of optical filters coupled to a second output of the
optical splitter, and an input bank of optical filters coupled to a
second input of the optical coupler.
13. The method of claim 12, wherein the communicatively coupling
optically comprises communicatively coupling optically via at least
one of a module input and a module output of the at least one
inter-satellite processing module, and wherein the passing
comprises passing via respective banks of optical filters.
14. The method of claim 12, wherein, for each of the plurality of
optical processing modules, the respective output bank of optical
filters and the respective input bank of optical filters are
dynamically tunable.
15. The method of claim 11, wherein each of the plurality of
optical processing modules have identical architecture.
16. The method of claim 11, wherein the at least one optical fiber
ring comprises dual counter-rotating optical fiber rings.
17. The method of claim 11, wherein the processing comprises
optically processing.
18. The method of claim 11, wherein the processing comprises
radio-frequency electromagnetic data processing.
19. The method of claim 11, further comprising repeating the
communicatively coupling optically, the passing, and the
processing, for a plurality of remote satellites.
20. (canceled)
21. The satellite payload system of claim 1, configured to
aggregate a plurality of signals from a plurality of
satellites.
22. The method of claim 11, further comprising aggregating a
plurality of signals from a plurality of satellites.
Description
RELATED APPLICATION
[0001] This application claims priority to, and the benefit of,
U.S. utility patent application Ser. No. 16/392,105 entitled,
"Photonic Lambda Switching for Satellites," and filed on Apr. 23,
2019, the entirety of which is hereby incorporated by
reference.
FIELD
[0002] This disclosure relates to satellite communications.
BACKGROUND
[0003] Known satellite payloads typically operate in the electronic
domain. Further, terrestrial optical systems are typically
custom-built, without using modular design principles.
SUMMARY
[0004] According to various embodiments, a satellite payload system
is disclosed. The satellite payload system includes a plurality of
optical processing modules, each optical processing module
including: a module input including an optical splitter, a module
output including an optical coupler, a dynamic gain equalizer
interposed between a first output of the optical splitter and a
first input to the optical coupler, an output bank of optical
filters coupled to a second output of the optical splitter, and an
input bank of optical filters coupled to a second input of the
optical coupler; where the plurality of optical processing modules
include a plurality of ring-connected optical processing modules
and a plurality of inter-satellite optical processing modules; and
at least one optical fiber ring configured to convey a plurality of
photonic wavelengths, the at least one optical fiber ring
communicatively coupled to each of the ring-connected optical
processing modules via respective module inputs and module outputs
of the ring-connected optical processing modules; where at least
one of the ring-connected optical processing modules is configured
to provide on-board signal processing of wavelengths conveyed on
the at least one optical fiber ring; where a plurality of the
ring-connected optical processing modules are each communicatively
coupled to a respective inter-satellite optical processing module
via respective banks of optical filters; where each inter-satellite
optical processing module is configured to optically
communicatively couple to a respective remote satellite via its
module input and via its module output.
[0005] Various optional features of the above embodiments include
the following. For each of the plurality of optical processing
modules, the respective output bank of optical filters and the
respective input bank of optical filters may be dynamically
tunable. Each of the plurality of optical processing modules may
have identical architecture. The at least one optical fiber ring
may include dual counter-rotating optical fiber rings. The at least
one of the ring-connected optical processing modules may be
configured to provide on-board optical signal processing of
photonic data conveyed on the at least one optical fiber ring. The
at least one of the ring-connected optical processing modules may
be configured to provide on-board radio-frequency signal processing
of electromagnetic data corresponding to wavelengths conveyed on
the at least one optical fiber ring. The satellite payload system
may be configured to provide selectable optical routing to a
plurality of remote satellites. The satellite payload system may be
configured to provide hopped radio-frequency terrestrial
communications. The satellite payload system may be configured to
aggregate a plurality of signals from a plurality of satellites
using time division multiplexing. Each optical processing module
may include radiation-hard optical materials and low outgassing
structural materials.
[0006] According to various embodiments, a method performed by a
satellite payload system is disclosed. The satellite payload system
includes: a plurality of optical processing modules, each optical
processing module including: a module input including an optical
splitter, a module output including an optical coupler, a dynamic
gain equalizer interposed between a first output of the optical
splitter and a first input to the optical coupler, an output bank
of optical filters coupled to a second output of the optical
splitter, and an input bank of optical filters coupled to a second
input of the optical coupler; where the plurality of optical
processing modules include a plurality of ring-connected optical
processing modules and a plurality of inter-satellite optical
processing modules; and at least one optical fiber ring configured
to convey a plurality of photonic wavelengths, the at least one
optical fiber ring communicatively coupled to each of the
ring-connected optical processing modules via respective module
inputs and module outputs of the ring-connected optical processing
modules; the method including: communicatively coupling optically,
by at least one inter-satellite processing module, to a respective
remote satellite via a module input of the at least one
inter-satellite processing module and via a module output of the at
least one inter-satellite processing module; passing, by the at
least one inter-satellite processing module and to at least one of
the ring-connected optical processing modules via respective banks
of optical filters, wavelengths including inter-satellite data; and
processing, at least in part by the at least one of the
ring-connected optical processing modules, the inter-satellite
data.
[0007] Various optional features of the above embodiments include
the following. For each of the plurality of optical processing
modules, the respective output bank of optical filters and the
respective input bank of optical filters may be dynamically
tunable. Each of the plurality of optical processing modules may
have identical architecture. The at least one optical fiber ring
may include dual counter-rotating optical fiber rings. The
processing may be provided by on-board optical signal processing of
photonic data conveyed on the at least one optical fiber ring. The
processing may be provided by on-board radio-frequency signal
processing of electromagnetic data corresponding to wavelengths
conveyed on the at least one optical fiber ring. The method may
include providing selectable optical routing to a plurality of
remote satellites. The method may include providing hopped
radio-frequency terrestrial communications. The method may include
aggregating a plurality of signals from a plurality of satellites
using time division multiplexing. Each optical processing module
may include radiation-hard optical materials and low outgassing
structural materials.
[0008] According to various embodiments, a satellite payload system
is disclosed. The system includes plurality of optical processing
modules including a plurality of ring-connected optical processing
modules and at least one inter-satellite optical processing module;
and at least one optical fiber ring communicatively coupled to each
of the ring-connected optical processing modules; where at least
one of the ring-connected optical processing modules is configured
to provide on-board signal processing of signals conveyed on the at
least one optical fiber ring; where at least one of the
ring-connected optical processing modules is communicatively
coupled to a respective inter-satellite optical processing module;
where each inter-satellite optical processing module is configured
to optically communicatively couple to a respective remote
satellite.
[0009] Various optional features of the above embodiments include
the following. Each of the plurality of optical processing modules
may include a module input including an optical splitter, a module
output including an optical coupler, a dynamic gain equalizer
interposed between a first output of the optical splitter and a
first input to the optical coupler, an output bank of optical
filters coupled to a second output of the optical splitter, and an
input bank of optical filters coupled to a second input of the
optical coupler. The plurality of the ring-connected optical
processing modules that are each communicatively coupled to a
respective inter-satellite optical processing module may each be
communicatively coupled to a respective inter-satellite optical
processing module via a respective bank of optical filters, and
each inter-satellite optical processing module may be configured to
optically communicatively couple to a respective remote satellite
via at least one of its module input and via its module output. For
each of the plurality of optical processing modules, the respective
output bank of optical filters, and the respective input bank of
optical filters may be dynamically tunable. Each of the plurality
of optical processing modules may have identical architecture. The
at least one optical fiber ring may include dual counter-rotating
optical fiber rings. The at least one of the ring-connected optical
processing modules may be configured to participate in on-board
optical signal processing of photonic data conveyed on the at least
one optical fiber ring. The at least one of the ring-connected
optical processing modules may be configured to participate in
on-board radio-frequency signal processing of electromagnetic data
corresponding to at least one signal conveyed on the at least one
optical fiber ring. The system may be configured to provide
selectable optical routing to a plurality of remote satellites. A
plurality of the ring-connected optical processing modules may each
be communicatively coupled to respective inter-satellite optical
processing modules.
[0010] According to various embodiments, a method performed by a
satellite payload system is disclosed. The satellite payload system
includes a plurality of optical processing modules including a
plurality of ring-connected optical processing modules and at least
one inter-satellite optical processing module; and at least one
optical fiber ring communicatively coupled to each of the
ring-connected optical processing modules. The method includes
communicatively coupling optically, by at least one inter-satellite
processing module, to a respective remote satellite; passing, by
the at least one inter-satellite processing module and to at least
one of the ring-connected optical processing modules at least one
signal including inter-satellite data; and processing, at least in
part by the at least one of the ring-connected optical processing
modules the inter-satellite data.
[0011] Various optional features of the above embodiments include
the following. Each of the plurality of optical processing modules
may include a module input including an optical splitter, a module
output including an optical coupler, a dynamic gain equalizer
interposed between a first output of the optical splitter and a
first input to the optical coupler, an output bank of optical
filters coupled to a second output of the optical splitter, and an
input bank of optical filters coupled to a second input of the
optical coupler. The communicatively coupling optically may include
communicatively coupling optically via at least one of a module
input and a module output of the at least one inter-satellite
processing module, and where the passing may include passing via
respective banks of optical filters. For each of the plurality of
optical processing modules, the respective output bank of optical
filters and the respective input bank of optical filters may be
dynamically tunable. Each of the plurality of optical processing
modules may have identical architecture. The at least one optical
fiber ring may include dual counter-rotating optical fiber rings.
The processing may include optically processing. The processing may
include radio-frequency electromagnetic data processing. The method
may include repeating the communicatively coupling optically, the
passing, and the processing, for a plurality of remote satellites.
A plurality of the ring-connected optical processing modules may
each be communicatively coupled to respective inter-satellite
optical processing module.
BRIEF DESCRIPTION OF THE DRAWINGS
[0012] The accompanying drawings, which are incorporated in and
constitute a part of this specification, illustrate the present
teachings and together with the description, serve to explain the
principles of the disclosure.
[0013] FIG. 1 is a schematic diagram of a satellite communication
system that uses photonic lambda switching according to various
embodiments;
[0014] FIG. 2 is a schematic diagram of a satellite payload system
that uses photonic lambda switching according to various
embodiments; and
[0015] FIG. 3 is a flow diagram of a method of satellite photonic
lambda switching according to various embodiments.
[0016] It should be noted that some details of the figures have
been simplified and are drawn to facilitate understanding of the
present teachings, rather than to maintain strict structural
accuracy, detail, and scale.
DETAILED DESCRIPTION
[0017] Reference will now be made in detail to the disclosed
examples, which are illustrated in the accompanying drawings.
Wherever possible, the same reference numbers will be used
throughout the drawings to refer to the same or like parts. In the
following description, reference is made to the accompanying
drawings that form a part thereof, and in which is shown by way of
illustration specific examples. These examples are described in
sufficient detail to enable those skilled in the art to practice
them and it is to be understood that other examples may be utilized
and that changes may be made without departing from the scope of
the disclosure. The following description is, therefore, merely
exemplary.
[0018] Prior art satellite payloads may be analog or (electrical)
digital. By contrast, some embodiments provide all or partial
optical payloads. Such payloads may switch photons from one beam to
another. In particular, some embodiments allow any-to-any optical
beam switching in the payload. Some embodiments can switch between
beams pointing at the Earth or optical crosslinks that connect
between satellites.
[0019] Various embodiments provide satellite signal routing, and/or
switching traffic through a satellite constellation, by processing
radio frequency (RF) carriers or channels containing user traffic
or system control and management traffic, aggregating the traffic
using time-division multiplexing (TDM), and switching the
aggregated TDM traffic to an optical wavelength. Some embodiments
convert the satellite RF signal to light pulses and then back to RF
for the downlink. Some embodiments utilize photonic lambda
switching.
[0020] Some embodiments integrate an optical add/drop multiplexer
(OADM) into a satellite payload to handle inter-satellite switching
and/or routing, the aggregation of RF carriers or channels using
TDM, the mapping of these aggregations onto an optical wavelength,
and the routing of the resulting wavelength to a selected
destination satellite payload. In some embodiments, the OADM may be
reconfigurable OADM (ROADM).
[0021] Some embodiments provide single-hop functionality, as
opposed to double-hop functionality. In general, in double-hop
systems, a user terminal on ground sends data to the satellite. The
satellite may then send the data to an Earth gateway station for
advanced processing. The Earth gateway station then passes the
processed data through fiber on ground to another Earth gateway
system, which sends it back up to a different satellite, which may
pass the data to a final destination terminal on Earth.
[0022] By contrast, some embodiments provide single-hop
functionality. Satellite payloads according to some embodiments
have sufficient on-board processing that the signal does not need
to go back down to a gateway station for processing such as
modulation/encoding/routing/switching. Such processing may instead
be performed on payloads as disclosed herein. Instead of sending
data to an Earth gateway system for advanced processing, some
embodiments utilize inter-satellite links. Thus, data can go from a
ground-based terminal up to a satellite, and not return back to
Earth until it gets to end of the path, at an Earth destination
terminal. Such embodiments solve the problem of efficiently routing
and/or switching traffic through a constellation of
non-geostationary orbit (NGSO) satellites or through a hierarchical
constellation that contains some combination of low Earth orbit
(LEO), medium Earth orbit (MEO), and geostationary orbit (GEO)
satellites.
[0023] The optical or partially-optical payloads of some
embodiments have superior size, weight, and power (SWaP) properties
in comparison to known satellites payloads. In general, optical
hardware is lighter than electronic hardware, so embodiments can do
more processing with the same weight. Embodiments may utilize
erbium doped fiber amplifiers inside optical transceivers, which
can pack more wavelengths into the links. Such embodiments may
provide greater routing capabilities through the optical backbone
in space, in comparison to entirely electronic-based systems.
Further, optical hardware as disclosed herein provides good signal
immunity between different signal paths.
[0024] FIG. 1 is a schematic diagram of a satellite communication
system that uses photonic lambda switching according to various
embodiments. The system as shown includes a constellation of three
satellites 101, 103, 105, which may be in geostationary or
non-geostationary (e.g., LEO or MEO) orbits.
[0025] Each satellite 101, 103, 105 includes a respective payload
101, 104, 106. Payloads 102, 104, 106 provide photonic lambda
switching. In particular, each payload 102, 104, 106 includes an
optical add-drop multiplexor (OADM), which may be a reconfigurable
OADM (ROADM). Each payload 102, 104, 106 includes a TDM
switch/multiplexor (MUX). The TDM switch/MUX may be entirely
optical, or may process in the RF domain. Each payload 101, 104,
106 also includes signal processing circuitry, which may process
signals in the RF domain, or, alternately, entirely in the optical
domain.
[0026] Satellite 101 is shown as having optical inter-satellite
links (OISL) with satellites 103 and 105, respectively. The ISL may
be static, dynamic, or extremely dynamic. A static ISL may be
between satellites within the same orbital plane. Such satellites
may have satellites in front and behind that will constantly be in
view. A dynamic ISL may be between satellites in adjacent orbital
planes. Such satellites may be in view of each-other for, e.g., 15
minutes or so at a time. An extremely dynamic ISL may be between
satellites in adjacent planes in the seam. Such satellites may be
in view of each-other for only a few seconds at a time.
[0027] The ISL may utilize coarse wavelength division multiplexing
(CWDM, e.g., 8 or 16 channels per link) dense WDM (DWDM, e.g., 32,
64 or 128 channels per link) or ultra-dense WDM (UDWDM, e.g., 192
or more channels per link).
[0028] Embodiments may utilize constraint-based wavelength routing.
Such routing may utilize multiple wavelengths between multiple
satellites from one end of the system to the other.
[0029] As depicted in FIG. 1, the satellites may communicate with a
variety of entities on the ground. Satellites 101 and 105 are shown
laying down beams on the Earth. Such communications may be RF
and/or optical. Generally, downlinks to Earth are RF. Further, in
general, optical communication links may be between satellites.
Satellite 101 is shown communicating with cellular and
internet-of-things user terminal 108. However, embodiments are not
so limited. Further ground-based entities that satellite 101 may
communicate with include mobile WiFi access points, aeronautical
and maritime mobile satellite terminals, fixed satellite user
terminals, and other entities.
[0030] Satellite 106 is further shown as communicating with a
global network operations center (global NOC) 110. Such a global
NOC 110 is shown as including a satellite operations center (SOC)
and a cyber-security operations center (CSOC). The CSOC provides
surveillance and monitoring in order to ensure that the system is
secure. The global NOC also includes a network operations center
(NOC), which may include a system resource manager (SRM).
[0031] The SRM may be a distributed entity including a global SRM
that receives operator inputs and constraints, and other external
constraints (e.g., global weather, ephemeris data from external
systems operating in the same frequency bands), and produces global
and regional resource management policies that are disseminated to
distributed SRM clients that reside on each satellite payload,
ground gateway, and user terminal. These disseminated policies are
used by the local payload, gateway, and terminal SRM clients to
create local configuration information related to beam, carrier,
and switching/forwarding functions. The SRM clients may also feed
key performance indicator data back to the global SRM for
continuous optimization of the system resource allocation and
system performance.
[0032] The SRM may support hopped and non-hopped beams. In general,
non-hopped beams utilize static beams, each which has a different
frequency band and is statically assigned to a different cell on
the Earth. The use of different frequency bands provides the
benefit of no interference at the edges of the cells. Static
non-hopped beams are useful as long as the population of users is
static and always demands the same access to the system. But mobile
systems, for example, may have changing demand requirements and
changing access needs per time of day, which means that such
systems may have different demands in different cells at different
points in time.
[0033] Hopped beams utilize beams of different frequency bands in
different places at different times. For hopped beams, different
cells are energized at different points in time. Beam hopping
provides for increased system capacity by giving different users
different access to the system at different times according to a
spatial permutation. Instead of having a multiple fully-energized
beams according to a non-hopped beam system, which may or may not
be used at different times, hopped beam system utilize frequency
division multiplexing (FDM) that gets mapped to the TDM. The TDM is
used to multiplex traffic up onto different optical wavelengths,
and the beam hopping uses FDM that splits the spectrum up into
different channels, then hops among those channels. Thus, beam
hopping allows for servicing dynamic demands in an efficient way.
Hopping can be intelligent, or known pattern, based on what the
customers say they will need.
[0034] The SRM provides for intelligent beam hopping. The system
feeds real-time data from the ground-based terminals into the SRM.
SRM then uses this data to determine how to modify the beam hopping
pattern to increase efficiency of the system over time.
[0035] According to various embodiments, the optical ISLs can use
multi-wavelength interconnections (where the SRM determines the
end-to-end path using a routing and wavelength assignment
algorithm) or the optical ISLs can use a single coherent laser,
where all traffic between adjacent satellites is carried using a
single wavelength. The former is optimized for circuit switched
networks, while the latter approach is optimized for packet
switched networks, for example.
[0036] FIG. 2 is a schematic diagram of a satellite payload system
200 that uses photonic lambda switching according to various
embodiments. The satellite payload system 200 may be included in
satellites 101, 103, 105 of FIG. 1, for example. The system 200 is
transparent to the waveforms used (e.g., hopped, non-hopped, TDM,
FDM, CDMA, etc.).
[0037] The satellite payload system 200 may be based around optical
processing modules 202, 204, 206, 208, 210. Multiple such optical
processing modules may be manufactured to have identical
architecture. In this manner, the satellite payload system 200 may
be efficiently designed and manufactured. For example, the optical
processing modules 202, 204, 206, 208, 210 may be built using a
reproducible assembly process. Thus, the optical processing modules
202, 204, 206, 208, 210 may be reusable design components that are
replicated at every add/drop point in the broadcast-and-select
switch design. Such reuse reduces cost and increases manufacturing
and space-qualification efficiencies.
[0038] Example internal architecture of the optical processing
modules 202, 204, 206, 208, 210 is described in reference to
optical processing module 202; however, the description applies to
the remaining optical processing modules 204, 206, 208, 210
according to some embodiments. Optical processing module 202
includes an input 212 and an output 214. The input 212 and output
214 may include physical ports for coupling optical transmission
lines and conveying optical signals to the optical processing
module 202. The input 212 may be coupled to an input of an optical
splitter 216 in the optical processing module 202. The optical
splitter 216 has one input and two outputs. One output of the
optical splitter 216 may be coupled to a dynamic gain equalizer
(DGE) 218.
[0039] The DGE 218 assists in drop/add multiplexing as further
described below. The output of the DGE 218 is coupled to an input
of an optical coupler 220. The optical coupler 220 has two inputs
and one output. The output of the optical coupler 220 is provided
to the output 214 of the optical processing module 202.
[0040] The other output of the optical splitter 216 is coupled to
an bank of output optical filters 222. The output optical filters
222 may be fixed or tunable. Embodiments that utilize tunable
optical filters 222 can dynamically change the routing through the
optical backbone of the satellite constellation. That is,
embodiments that utilize tunable optical filters 222 include ROADM
functionality. The number of optical filters may correspond to the
number of remote satellites with which the satellite communicates.
The output optical filters 222 may include one or more physical
ports for coupling optical transmission lines and conveying optical
signals.
[0041] The other input to the optical coupler 220 is coupled to a
bank of input optical filters 224, which may match the bank of
output optical filters 222. The input optical filters 224 may be
fixed or tunable, providing OADM or ROADM functionality. The input
optical filters 224 may include one or more physical ports for
coupling optical transmission lines and conveying optical
signals.
[0042] Thus, the optical processing module 202 includes an input
212 for receiving optical wavelengths, an output 214 for
transmitting optical wavelengths, a bank of input optical filters
224 for coupling with a corresponding bank of output optical
filters of another optical processing module, and a bank of output
optical filters 222 for coupling to a bank of input optical filters
of another optical processing module.
[0043] The optical and photonic components include features to
facilitate operation in the high-radiation, vacuum, and low-gravity
environments that characterize space. These features include, any,
or any combination, of: the use of radiation-hard optical materials
(e.g., glasses, crystals, liquid crystals, and waveguides), the
replacement of high out-gassing polymers and adhesives with low
outgassing materials (e.g., for structural components), the
elimination of materials that degrade in high radiation
environments with radiation tolerant materials, mitigations to
prevent the formation of conductive whiskers, thermal management to
eliminate dependence on convection for heat transfer, and
implementation of design features to allow operation in a vacuum
environment. Such design features for operation in a vacuum include
venting to facilitate the transition to vacuum and to eliminate
vacuum induced stresses, hermetic sealing to maintain internal
pressure and gas content, and optimized optical designs to allow
operation in both ambient pressure and vacuum environments.
[0044] The satellite payload system 200 further includes dual
counter-rotating optical fiber rings 226. The optical fiber rings
may include a primary optical fiber ring and a secondary optical
fiber ring for redundancy. Both rings have same connections to rest
of the system. The redundant rings may be interconnected such that
if one ring goes down, then the other takes over as the new primary
ring. The optical fiber rings 226 may utilize DWDM or UDWDM. As
described in detail herein, when used in tandem with the optical
modules, the optical fiber rings 226 allow traffic to be switched
from one wavelength on a given external interface to a different
wavelength on a different external interface. That is, the optical
fiber rings 226 at least partially perform optical switching on the
payload by switching wavelengths within them. Note that the
bandwidth of embodiments can be scaled either using more
wavelengths per optical fiber ring or by using additional
interconnected optical fiber rings.
[0045] The optical processing modules 202, 204, 206, 208, 210 may
be classified as ring-connected optical processing modules or
inter-satellite optical processing modules, depending on whether
their respective inputs and outputs are coupled to the optical
fiber rings 226 or are used for inter-satellite links. Thus, the
optical processing modules 204, 208, 210 are ring-connected optical
processing modules, whereas the optical processing modules 202, 206
are inter-satellite optical processing modules.
[0046] The inter-satellite optical processing modules 202, 206 are
coupled to corresponding ring-connected optical processing modules
204, 208, respectively, via their respective optical filter banks.
Thus, the bank of output optical filters 222 of the inter-satellite
optical processing module 202 is communicatively coupled to the
bank of input optical filters 228 of the ring-connected optical
processing module 204. Further, the bank of input optical filters
224 of the inter-satellite optical processing module 202 is
communicatively coupled to the bank of output optical filters 230
of the ring-connected optical processing module 204.
[0047] The ring-connected optical processing module 210 provides
processing of data on the wavelengths picked up from the optical
fiber rings 226. Such processing may be entirely within the optical
domain 232 according to some embodiments. Alternately, according to
some embodiments, the processing is performed in the RF domain 234.
According to such embodiments, the banks of optical filters of the
optical processing module 206 are coupled to RF processing
circuitry. Such RF processing circuitry may include, as shown in
FIG. 2, a TDM switch 236, a TDM modulator/demodulator 238, and
dedicated RF processing circuitry 240.
[0048] The optical processing modules 202, 204, 206, 208, 210 and
optical fiber ring 226 of system 200 may be conceptualized as
including a through path, which includes traffic going to an
adjacent satellite, and a drop path, which includes traffic dropped
for local processing. In particular, the optical splitter 216 of
the optical processing module 202 splits the received ISL signal
into a through path and a drop path. The through path traffic runs
into the 218 DGE, which selects the wavelength(s) that are to be
dropped, and filters them out of the through path. The DGE 218 thus
filters the traffic that is dropped, so that those wavelengths no
longer exist in the through path. All that remains in the through
path that goes to the optical coupler 220 are the signals that were
received that were not dropped for processing. These wavelengths
are sent to the optical coupler 220.
[0049] The drop path from the optical splitter 216 passes waveforms
to the ring-connected optical processing module 204, which passes
such waveforms to the optical fiber rings 226. Such waveforms may
be processed optically by the ring-connected optical processing
module 210 or processed in the RF domain 234 using TDM switch 236,
TDM MUX/DEMUX 238, and RF processor 240. The processed waveforms
are then added to the optical fiber rings 226 via the optical
coupler of the ring-connected optical processing module 210. More
particularly, processed waveforms are picked off of the optical
fiber rings 226 by the ring-connected optical processing module 204
and passed to the inter-satellite optical processing module 202 via
their respective banks of optical filters. At the optical coupler
220, the dropped wavelengths that have been processed on-board,
whether in the RF domain 234 or entirely within the optical domain,
are added to the signal of the through path for transmission to the
adjacent satellite. These signals get transmitted on the ISL. (Note
that some waveforms on the drop path are destined for Earth
terminals on the ground, and those are not re-added to go to the
ISL.) In sum, the DGE 218 filters out all the waveforms on the
optical fiber rings 226 that have been dropped for processing, and
then on the other side of the DGE 218, the optical coupler 220
re-adds the appropriate waveforms that have been processed and
acquired from the optical fiber rings 226, to go out to the ISL via
the output 214. Thus, the DGE 218 performs at least some drop
functionality, and the optical coupler 220 performs at least some
add functionality.
[0050] Some embodiments provide a grooming function where traffic
to/from different RF beams or optical wavelengths can be groomed
onto different optical wavelengths. Such grooming may be performed
optically or partially in the RF domain, as disclosed
presently.
[0051] Some embodiments can change the wavelength of traffic
entirely optically, that is, without entering the RF domain. To do
so, such embodiments may utilize banks of optical filters 222, 224
that are tunable. Such embodiments may use such tunable optical
filter for a switching function. For example, traffic at a first
wavelength may be directed to the drop path via the optical
splitter 216. The traffic may enter the bank of optical filters 222
and be selected by the filter of the corresponding wavelength from
the bank of optical filters 222. The corresponding filter of the
receiving bank of optical filters 228 can tune the corresponding
receiving filter to a second wavelength, different from the first
wavelength. The traffic from the second wavelength may then enter
the optical fiber rings 226 at the second wavelength via the
optical coupler of the ring-connected optical processing module
204.
[0052] Alternately, some embodiments may change wavelengths by
running the signal through an electrical conversion process using
the TDM switch 236. According to such embodiments, as traffic
pulled off at one wavelength, the wavelength is changed in the RF
domain 234, and the changed wavelength is then re-added.
[0053] FIG. 3 is a flow diagram of a method 300 of satellite
photonic lambda switching according to various embodiments. The
method 300 may be performed by a system such as satellite payload
system 200, which may be deployed in a satellite such as satellite
101, 103 or 105.
[0054] At block 302, the system 200 communicatively couples to a
remote satellite via an inter-satellite link. Such a link may be
provided using, for example, an input and output of an
inter-satellite optical processing module (e.g., optical processing
module 202) of the system 200. The link may be purely optical. The
link may include two components, one for transmission and another
for reception. Standard optical elements may be used to locate,
transmit, and receive optical wavelengths with the remote
satellite.
[0055] At block 304, the system 200 passes received optical
wavelengths from the receiving inter-satellite optical processing
module (e.g., optical processing module 202) to a ring-connected
optical processing module (e.g., optical processing module 204. The
system 200 may pass the wavelengths via their respective banks of
optical filters (e.g., 224, 230).
[0056] At block 306, the system 200 processes the traffic received
over the ISL. The processing may include wavelength changing,
modulation, encoding, routing, and/or switching. The processing may
be performed entirely in the optical domain, or partially in the RF
domain (e.g., 234).
[0057] Once processed, the signal may be re-added to the optical
fiber rings 226, picked up by an optical processing module (e.g.,
206), and sent to a different remote satellite from the satellite
from which it was received prior to processing.
[0058] The present disclosure is not to be limited in terms of the
particular embodiments described in this application, which are
intended as illustrations of various aspects. Many modifications
and variations can be made without departing from its spirit and
scope, as will be apparent to those skilled in the art.
Functionally equivalent methods and apparatuses within the scope of
the disclosure, in addition to those enumerated herein, will be
apparent to those skilled in the art from the foregoing
descriptions. Such modifications and variations are intended to
fall within the scope of the appended claims. The present
disclosure is to be limited only by the terms of the appended
claims, along with the full scope of equivalents to which such
claims are entitled. 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.
[0059] With respect to the use of substantially any plural and/or
singular terms herein, those having skill in the art can translate
from the plural to the singular and/or from the singular to the
plural as is appropriate to the context and/or application. The
various singular/plural permutations may be expressly set forth
herein for sake of clarity.
[0060] It will be understood by those within the art that, in
general, terms used herein, and especially in the appended claims
(e.g., bodies of the appended claims) are generally intended as
"open" terms (e.g., the term "including" should be interpreted as
"including but not limited to," the term "having" should be
interpreted as "having at least," the term "includes" should be
interpreted as "includes but is not limited to," etc.). It will be
further understood by those within the art that if a specific
number of an introduced claim recitation is intended, such an
intent will be explicitly recited in the claim, and in the absence
of such recitation no such intent is present. For example, as an
aid to understanding, the following appended claims may contain
usage of the introductory phrases "at least one" and "one or more"
to introduce claim recitations. However, the use of such phrases
should not be construed to imply that the introduction of a claim
recitation by the indefinite articles "a" or "an" limits any
particular claim containing such introduced claim recitation to
embodiments containing only one such recitation, even when the same
claim includes the introductory phrases "one or more" or "at least
one" and indefinite articles such as "a" or "an" (e.g., "a" and/or
"an" should be interpreted to mean "at least one" or "one or
more"); the same holds true for the use of definite articles used
to introduce claim recitations. In addition, even if a specific
number of an introduced claim recitation is explicitly recited,
those skilled in the art will recognize that such recitation should
be interpreted to mean at least the recited number (e.g., the bare
recitation of "two recitations," without other modifiers, means at
least two recitations, or two or more recitations). Furthermore, in
those instances where a convention analogous to "at least one of A,
B, and C, etc." is used, in general such a construction is intended
in the sense one having skill in the art would understand the
convention (e.g., "a system having at least one of A, B, and C"
would include but not be limited to systems that have A alone, B
alone, C alone, A and B together, A and C together, B and C
together, and/or A, B, and C together, etc.). In those instances
where a convention analogous to "at least one of A, B, or C, etc."
is used, in general such a construction is intended in the sense
one having skill in the art would understand the convention (e.g.,
"a system having at least one of A, B, or C" would include but not
be limited to systems that have A alone, B alone, C alone, A and B
together, A and C together, B and C together, and/or A, B, and C
together, etc.). It will be further understood by those within the
art that virtually any disjunctive word and/or phrase presenting
two or more alternative terms, whether in the description, claims,
or drawings, should be understood to contemplate the possibilities
of including one of the terms, either of the terms, or both terms.
For example, the phrase "A or B" will be understood to include the
possibilities of "A" or "B" or "A and B." In addition, where
features or aspects of the disclosure are described in terms of
Markush groups, those skilled in the art will recognize that the
disclosure is also thereby described in terms of any individual
member or subgroup of members of the Markush group.
[0061] While various aspects and embodiments have been disclosed
herein, other aspects and embodiments will be apparent to those
skilled in the art. The various aspects and embodiments disclosed
herein are for purposes of illustration and are not intended to be
limiting, with the true scope and spirit being indicated by the
following claims.
* * * * *