Abstract: A braking system for an aircraft may comprise: a brake assembly; a hydraulic braking subsystem having a hydraulic brake actuator configured to operate the brake assembly; an electric braking subsystem having an electric brake actuator configured to operate the brake assembly and a load cell configured to measure a force supplied by the electric brake actuator; a hydraulic brake control unit configured to control the hydraulic braking subsystem; and an electric brake control unit configured to control the electric braking subsystem, the electric brake control unit in operable communication with the hydraulic brake control unit, the electric brake control unit configured to calibrate the load cell by a scale factor based on a measured force from the load cell, a measured hydraulic pressure used to exceed the measured force received from the hydraulic brake control unit, and a piston area of the hydraulic brake actuator.

Abstract: It is proposed a pressure vessel comprising a body and a tape-based reinforcement structure arranged onto the body, the tape-based reinforcement structure comprising: a primary tape arranged in a circumferential manner onto the body; a secondary tape arranged in a non-circumferential manner onto the body, at least one portion of the secondary tape being attached to the primary tape.