Channelizer supplemented spacecraft telemetry and command functionality
View Patent ↗A spacecraft includes a payload subsystem including a digital channelizer. The digital channelizer provides at least a portion of spacecraft command or telemetry functionality. The spacecraft may optionally also include a telemetry and command (T&C) subsystem, the T&C subsystem including one or more of a command receiver, a command decoder, a telemetry encoder and a telemetry transmitter. The digital channelizer may be communicatively coupled with at least one of the command receiver, the command decoder, the telemetry transmitter and the telemetry encoder.
1. A spacecraft comprising:
a payload subsystem including a digital channelizer; wherein:
the digital channelizer provides a portion of spacecraft command functionality and spacecraft telemetry functionality;
the spacecraft command functionality consists of down converting and demodulating a command carrier signal to a first intermediate frequency (IF) baseband signal, bit-detecting the IF baseband signal and formatting a resulting bit stream into digital command data; the spacecraft telemetry functionality consists of processing or encoding spacecraft telemetry data into a baseband signal, modulating the baseband signal onto a second IF signal and upconverting the modulated baseband signal to a radio frequency (RF) carrier signal; and
the payload subsystem is capable of providing all of the spacecraft command functionality and the spacecraft telemetry functionality.
2. The spacecraft of claim 1 , wherein the payload subsystem provides all of the spacecraft command functionality or the spacecraft telemetry functionality.
3. The spacecraft of claim 2 , wherein the spacecraft excludes a dedicated telemetry and command subsystem.
4. The spacecraft of claim 1 , further comprising:
a telemetry and command (T&C) subsystem, the T&C subsystem including one or more of a command (CMD) receiver, a CMD decoder, a telemetry (TLM) encoder and a TLM transmitter, wherein:
the digital channelizer is communicatively coupled with at least one of the CMD receiver, the CMD decoder, the TLM transmitter and the TLM encoder.
5. The spacecraft of claim 4 , wherein
the digital channelizer is communicatively coupled with two or more of the CMD receiver, the CMD decoder, the TLM transmitter and the TLM encoder by a respective signal path.
6. The spacecraft of claim 5 , wherein at least one of the respective signal paths can be actuated on or off.
7. The spacecraft of claim 5 , further comprising a computer, wherein
the digital channelizer is communicatively coupled with the computer; and
one or both of the digital channelizer and the computer are configured to select one or more of the respective signal paths.
8. The spacecraft of claim 7 , wherein one or both of the digital channelizer and the computer are configured to actuate the respective signal paths on or off.
9. The spacecraft of claim 4 wherein the T&C subsystem includes a ranging capability.
10. The spacecraft of claim 1 , wherein the payload subsystem is configured to provide one or more of a command (CMD) receiver functionality, a CMD decoder functionality, a CMD functionality, a telemetry (TLM) transmitter functionality, a TLM encoder functionality and a TLM functionality.
11. The spacecraft of claim 10 , wherein the payload subsystem is configured to mitigate a deficiency in one or more of the CMD receiver, the CMD decoder, the TLM transmitter, and the TLM encoder.
12. The spacecraft of claim 11 , wherein the deficiency results from a component failure or other reason.
13. The spacecraft of claim 10 , wherein the payload subsystem is configured to mitigate one or more deficiencies in two or more of the CMD receiver, the CMD decoder, the TLM transmitter, and the TLM encoder.
14. The spacecraft of claim 10 , wherein the payload subsystem is configured to mitigate one or more deficiencies of three or more of the CMD receiver, the CMD decoder, the TLM transmitter and the TLM encoder.
15. A method comprising:
operating a spacecraft in a contingency mode, the spacecraft including a telemetry command (T&C) subsystem and a payload subsystem, the T&C subsystem including one or more of a command receiver, a command decoder, a telemetry encoder and a telemetry transmitter, the payload subsystem including a digital channelizer; wherein:
the contingency mode includes a deficiency of at least one of the command receiver, the command decoder, the telemetry transmitter and the telemetry encoder, the deficiency resulting from a component failure or other reason;
operating the spacecraft in the contingency mode includes mitigating the deficiency by providing, with the digital channelizer, one or both of a portion of spacecraft command functionality and a portion of spacecraft telemetry functionality the spacecraft command functionality consisting of down converting and demodulating a command carrier signal to a first intermediate frequency (IF) baseband signal, bit-detecting the IF baseband signal and formatting a resulting bit stream into digital command data and the spacecraft telemetry functionality consisting of processing or encoding spacecraft telemetry data into a baseband signal, modulating the baseband signal onto a second IF signal and upconverting the modulated baseband signal to a radio frequency (RF) carrier signal; and
the payload subsystem is capable of providing all of the spacecraft command functionality and the spacecraft telemetry functionality.
16. The method of claim 15 , wherein the digital channelizer is communicatively coupled with at least one of the command receiver, the command decoder, the telemetry transmitter and the telemetry encoder.
17. The method of claim 15 , wherein:
the payload subsystem is configured to provide one or more of a command (CMD) receiver functionality, a CMD decoder functionality, a CMD functionality, a telemetry (TLM) transmitter functionality, a TLM encoder functionality and a TLM functionality.
18. A non-transitory computer readable medium having software stored thereon, the software including instructions for causing a processor to:
operate a spacecraft in a contingency mode, the spacecraft including a telemetry command (T&C) subsystem and a payload subsystem, the T&C subsystem including one or more of a command receiver, a command decoder, a telemetry encoder and a telemetry transmitter, the payload subsystem including a digital channelizer; wherein:
the contingency mode includes a deficiency of at least one of the command receiver, the command decoder, the telemetry transmitter and the telemetry encoder, the deficiency resulting from a component failure or other reason;
operating the spacecraft in the contingency mode includes mitigating the deficiency by providing, with the digital channelizer, one or both of a spacecraft command functionality and a portion of spacecraft telemetry functionality the spacecraft command functionality consisting of down converting and demodulating a command carrier signal to a first intermediate frequency (IF) baseband signal, bit-detecting the IF baseband signal and formatting a resulting bit stream into digital command data and the spacecraft telemetry functionality consisting of processing or encoding spacecraft telemetry data into a baseband signal, modulating the baseband signal onto a second IF signal and upconverting the modulated baseband signal to a radio frequency (RF) carrier signal; and
the payload subsystem is capable of providing all of the spacecraft command functionality and the spacecraft telemetry functionality.
19. The computer readable medium of claim 18 , wherein the digital channelizer is communicatively coupled with at least one of the command receiver, the command decoder, the telemetry transmitter and the telemetry encoder.
20. The computer readable medium of claim 18 , wherein:
the payload subsystem is configured to provide one or more of a command (CMD) receiver functionality, a CMD decoder functionality, a CMD functionality, a telemetry (TLM) transmitter functionality, a TLM encoder functionality and a TLM functionality.