US 12,456,032 B2
In-flight integrated modular avionics (IMA) reconfiguration
Miguel Angel Sanchez-Puebla Rodriguez, Getafe (ES)
Assigned to Airbus Defence and Space SAU, Getafe (ES)
Filed by Airbus Defence and Space SAU, Getafe (ES)
Filed on Jul. 12, 2022, as Appl. No. 17/863,097.
Claims priority of application No. 21382660 (EP), filed on Jul. 21, 2021.
Prior Publication US 2023/0029440 A1, Jan. 26, 2023
Int. Cl. G06N 3/04 (2023.01); G06F 9/50 (2006.01); G06F 11/30 (2006.01); G06F 11/34 (2006.01)
CPC G06N 3/04 (2013.01) [G06F 9/5077 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A computer-implemented method for in-flight Integrated Modular Avionics (IMA) reconfiguration by means of spatial and temporal partitioning of IMA modules conforming a data processing system, the computer-implemented method comprising the following steps:
(a) reading by a supervisor means of the data processing system data including:
indicative parameters of a plurality of partitions;
health data stored on a common shared configuration table; and
mission type and flight phase that are being performed;
(b) determining by the supervisor means a plurality of criticality parameters of the plurality of partitions of the data processing system, the plurality of criticality parameters including an execution order of the plurality of partitions based on a priority of execution;
(c) determining by the supervisor means a next mode of execution of the plurality of partitions based on previously read data and the plurality of criticality parameters;
(d) writing on a common shared region by the supervisor means the next mode of execution of the plurality of partitions; and
(e) reconfiguring in-fight the IMA modules by activating or deactivating the plurality of partitions of the data processing system based on the next mode of execution of the data processing system,
wherein a criticality parameter for each partition of the data processing system is determined in step (b) by following steps:
calculating a particular fixed polynomial based on a distributed multicore architecture of the data processing system;
executing said particular fixed polynomial by computing at least some of the indicative parameters of a partition, mission type, flight phase and data stored on the common shared configuration table of the data processing system, and
determining the criticality parameter by solving said polynomial.