Modular unified avionics system
Inventors
Boblitt, Zachary • Haghani, Noosha • Gheen, Robert • Hernandez-Pellerano, Amri • Lanham, Austin • Kercheval, Bradford • Burns, Michael • Fraction, James • Haddad, Omar • Pagen, Shahana • Laurila, Erik
Assignees
National Aeronautics and Space Administration NASA
Publication Number
US-12326829-B1
Publication Date
2025-06-10
Expiration Date
2042-08-08
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Abstract
An avionics system includes a plurality of card assemblies having a standard height and width, and a depth dependent on dimensions of components mounted on individual ones of the plurality of card assemblies, and a subset of the plurality of card assemblies selected according to their functionality and assembled together along their depth dimensions to form one or more modules having the standard height and width, wherein the one or more modules are distributable among available volumes within a spacecraft.
Core Innovation
The invention is a modular avionics system comprising multiple card assemblies with a standardized height and width, and a depth that varies depending on the components mounted on each card assembly. A subset of these card assemblies is selected based on their functionality and assembled along their depth dimensions to form one or more modules having the standard height and width. These modules are distributable among available volumes within a spacecraft and may be arranged to meet power, weight, volume, data transfer, or thermal requirements.
Each card assembly is mounted in a chassis that provides mechanical fastening to adjacent chassis and includes features such as heatsinks for thermal management and bracing to accommodate structural loads. The chassis design also incorporates lips and grooves to enhance electromagnetic interference (EMI) shielding when modules are assembled. The modular design allows for the flexible selection and configuration of cards to meet mission specific requirements without designing custom motherboards for each configuration.
Claims Coverage
The patent includes numerous claims, with at least one independent claim defining the modular avionics system, focusing on its structural and functional features. The inventive features extracted highlight the key elements claimed in these independent claims.
Modular card assemblies with standardized form factor
The avionics system includes a plurality of card assemblies having a standard height and width, and a depth that depends on the components mounted on each individual card.
Distributable modules assembled along depth dimension
A subset of the card assemblies are selected by functionality and assembled together along their depth dimensions to form modules of standard height and width that can be distributed within the spacecraft's available volumes.
Endcaps and lid assembly for modules
Modules may include endcaps attached at each end along the depth dimension for structural stiffness and EMI shielding. A lid assembly, comprising an enclosure and a lid, may be attached to a module extending along its width and depth.
Chassis features for card assemblies
Each card assembly includes a card mounted in a chassis with mechanisms to fasten to adjacent chassis, heatsinks to conduct heat through the chassis base, bracing to accommodate structural loads, and mating lips and grooves for enhanced EMI shielding.
Processor card with flight software control
The processor card is configured with a main CPU and a second FPGA to store and run flight software and control avionics system operations.
Memory architecture on processor card
The processor card includes programmable read only memory for boot code, magnetoresistive random access memory for application code, static random access memory for temporary volatile storage, and flash memory for non-volatile storage that can be power cycled to clear single event functional interrupts.
Power monitor card controlling power and telemetry
The power monitor card controls power converters and switches on the low voltage power controller card, reads telemetry from the low voltage power controller and output module cards, and provides recovery signals for card resets under the control of a power monitor FPGA.
Power monitor card components and interfaces
It includes a power monitor clock for timing, on-board MRAM for storing initial states and commands, an amplifier coupled to an A/D converter for telemetry conversion, a low voltage power controller card inhibit circuit, and dual I2C bus interfaces for telemetry retrieval.
Housekeeping card monitoring multiple telemetry parameters
The housekeeping card monitors thermal telemetry and single-ended and differential voltages from various cards including communication, processor, power monitor, engine valve drive, data storage, low voltage power controller, output module, and solar array control cards, under the control of a housekeeping FPGA.
The claims collectively cover a modular avionics system with standardized card assemblies assembled into configurable modules tailored for spacecraft integration, featuring mechanical design elements for thermal and EMI management, specialized processing and memory architecture, power monitoring and control, and comprehensive system telemetry monitoring capabilities.
Stated Advantages
Provides a standard set of off-the-shelf avionics functions configurable to meet multiple mission needs, reducing recurring design and qualification costs.
Allows flexible assembly of card assemblies based on functionality to conform to available spacecraft volumes.
Enables distribution of modules to meet power, weight, volume, data transfer, and thermal requirements.
Incorporates mechanical features such as endcaps, lid assemblies, chassis fastening, and EMI shielding lips and grooves to enhance structural integrity and electromagnetic compatibility.
Each card assembly includes passive thermal management through heatsinks and chassis design.
The modular design eliminates the need for custom motherboards for distributed modules, simplifying configuration and integration.
Documented Applications
Use in spacecraft avionics systems providing a Command and Data Handling (C&DH) subsystem.
Applicable to controlling spacecraft communication subsystems including S-Band, X-Band, and Ka-Band transponders.
Monitoring and controlling spacecraft power subsystems including battery charging and solar array power processing.
Controlling thrusters and latch valves in spacecraft propulsion subsystems.
Storing science and experimental data collected by spacecraft instruments.
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