Ensuring Temperature Stability of the Unit of Linear Acceleration Meters under Spaceflight Conditions

A non-orthogonally oriented six-component unit of linear acceleration meters (the BILU device) with a digital control system of the measuring channel and the "Manchester"-type code formation module is considered. The device is studied under the conditions of operation as part of the control system of Soyuz-MS and Progress-MS spacecraft. The performance of all BILU modules under spaceflight conditions is evaluated, conclusions about the high overall reliability of the device and maintaining capabilities for its key parameters and technical characteristics during normal flight phases, as well as for the scenario of compartment depressurization, are drawn.