Abstract: Disclosed is a fuel conditioning system (SC) configured to supply an aircraft turbine engine using fuel (Q) from a cryogenic tank (RC), the conditioning system (SC) comprising at least one pumping turbomachine (1), a first heat exchanger (31) configured to heat the fuel (Q) in the fuel circuit (CQ) by circulating an air stream (A), and at least one heating turbomachine (2) configured to supply an air flow (A) to the first heat exchanger (31), the heating turbomachine (2) comprising an air intake compressor (21), a combustion chamber (24) and an air exhaust turbine (22) configured to drive the air intake compressor (21), the combustion chamber (24) being supplied with air taken from the air flow (A) and with the fuel (Q) from the fuel circuit (CQ).

Abstract: A tester for integrated circuits on a silicon wafer includes an input/output connection for testing an integrated circuit. The tester comprises circuitry arranged for transferring a first data frame to the integrated circuit via the input/output connection, the first data frame including a time reference for the data included in the data frame, a field for validating the time reference and a data field including at least one test command and for receiving a second data frame via the input/output connection, the data in the second data frame received having a duration that is a multiple of the time reference.

Abstract: A tester for integrated circuits on a silicon wafer may include an input/output connection for testing an integrated circuit and circuitry causing the tester to perform: transferring a data frame to the integrated circuit via the input/output connection, the data frame including a time reference for the data included in the data frame, a field for validating the time reference and a data field including at least one integrated-circuit test command; and receiving a data frame via the input/output connection, the data in the data frame received having a duration that is a multiple of the time reference.