# US 12,181,985 B1 · Small spacecraft processing and bus architecture > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,181,985 B1 - Document ID: US12181985B1 - Status: Granted - Kind: B1 - Application number: 17/159,338 - Filed: 2021-01-27 - Granted: 2024-12-31 - Earliest claimed: 2020-01-27 - Assignees: United States of America as represented by the Administrator of NASA - Applicants: United States of America as represented by the Administrator of NASA - Inventors: Colby Goodloe; Luis Santos Soto; Charles Clagett; David Everett - Web page: https://patentgrep.com/patent/US12181985B1 ## CPC - G06F 11/2028: {eliminating a faulty processor or activating a spare} - B64G 3/00: Observing or tracking cosmonautic vehicles - G06F: ELECTRIC DIGITAL DATA PROCESSING (computer systems based on specific computational models G06N) - B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR ## Abstract A spacecraft computing system, including: a first processor configured to process data from a payload and a first spacecraft system; a second processor configured to process data from a second spacecraft system; an interface connected to the second processor configured to interface with a third spacecraft system, wherein the second processor is configured to monitor the first processor and to initiate the recovery of the first processor when the first processor experiences a fault, wherein the first processor's processing capacity is greater the second processor's processing capacity, and wherein the second processor is more reliable than the first processor. ## Claims ### Claim 1 A spacecraft computing system, comprising: a first processor configured to process data from a payload and a first spacecraft system; a second processor configured to process data from a second spacecraft system; an interface connected to the second processor configured to interface with a third spacecraft system, wherein the second processor is configured to monitor the first processor and to initiate a recovery of the first processor when the first processor experiences a fault, and wherein the first processor's processing capacity is greater the second processor's processing capacity, wherein the first processor implements each of an autonomous maneuver planning and execution function, star tracking, global position system function, and digital radio function; wherein the second processor implements one of orbit control, attitude control system, housekeeping, command decoding, and data packetization; wherein the first processor is configured to process data from at least one of a camera head, star tracker, GPS, navigator front end, or radio receiver and the at least one of a camera head, navigator front end, or radio receiver do not have a processor; wherein the second processor is configured to process data from one of a transceiver, propulsion system, sun sensor, inertial measurement unit, and magnetometer. ### Claim 2 (depends on 1) The spacecraft computing system of claim 1, wherein the second processor implements a management function configured to monitor and manage an operation of the first processor, wherein monitoring the first processor and initiating the recovery of the first processor is performed by a management function implemented by the second processor; wherein the second processor is configured to control power supply electronics on the spacecraft. ### Claim 3 (depends on 2) The spacecraft computing system of claim 2, wherein the power supply electronics do not have a processor. ### Claim 4 (depends on 3) The spacecraft computing system of claim 3, wherein the second processor is configured to control reaction wheels on the spacecraft. ### Claim 5 (depends on 4) The spacecraft computing system of claim 4, wherein the second processor is configured to control a propulsion system on the spacecraft. ### Claim 6 (depends on 5) The spacecraft computing system of claim 5, wherein the second processor is configured to survive a single event effect (SEE) of up to 37 MeV/cm2. ### Claim 7 (depends on 6) The spacecraft computing system of claim 6, wherein the second processor is configured to survive a total ionizing dose (TID) of at least 30 krad. ### Claim 8 (depends on 7) The spacecraft computing system of claim 7, wherein the second processor and interface is configured to survive a total ionizing dose (TID) of at least 100 krad with shielding. ### Claim 9 (depends on 8) The spacecraft computing system of claim 8, further comprising memory connected to the second processor, wherein the memory and the second processor are space grade components. ### Claim 10 (depends on 1) The spacecraft computing system of claim 1, wherein the first processor configured to process data from a payload and a first spacecraft system is configured to process data from a plurality of spacecraft systems. ### Claim 11 (depends on 1) The spacecraft computing system of claim 1, wherein the first processor is configured to process data from each of a camera head, star tracker, GPS, navigator front end, or radio receiver and each of the camera head, navigator front end, or radio receiver do not have a processor. ### Claim 12 A spacecraft computing system, comprising: a first processor configured to process data from at least one payload and a first plurality of spacecraft systems; a second processor configured to process data from a second plurality of spacecraft systems; and an interface connected to the second processor configured to interface with a third spacecraft system, wherein the second processor is configured to monitor the first processor and to initiate a recovery of the first processor when the first processor experiences a fault, wherein the first processor's processing capacity is greater the second processor's processing capacity, wherein the first processor is configured to receive a first plurality of data signals from the at least one payload and the first plurality of spacecraft systems, wherein the first plurality of spacecraft systems comprises at least two of a camera head, a star tracker, a navigation front end, and radio receiver, wherein the first plurality of spacecraft systems do not include an embedded processor for each of the first plurality of spacecraft systems, wherein the second processor is configured to receive a second plurality of data signals from the second plurality of spacecraft systems, wherein the second plurality of spacecraft systems comprises at least two of a transceiver, propulsion system, sun sensor, inertial measurement unit, and magnetometer, wherein the first processor implements each of an autonomous maneuver planning and execution function, star tracking, global position system function, and digital radio function based on the received first plurality of data signals processed by the first processor, and wherein the second processor implements each of orbit control, attitude control system, housekeeping, command decoding, and data packetization based on the received second plurality of data signals processed by the second processor.