flight control system

Abstract

The invention relates to a flight control system (1) for operating control surfaces (2) of an aircraft, comprising: a plurality of actuators (3) for redundant actuation of the control surfaces (2) of the aircraft; Actuator-control electronics (4) for calculating and forwarding control signals for the control surface (2) operated by a plurality of actuators (3); arranged for controlling and monitoring the corresponding actuators respectively A plurality of remote electronic units of (3); and a first data bus system (10) for transferring data between the actuator-control electronics (4) and the plurality of remote electronic units (5), wherein the first data The total system (10) comprises: a first data bus (11) for transferring data between the actuator-control electronics (4) and the first of the plurality of remote electronic units (5); A second data bus (12) for transferring data between the controller-control electronics (4) and a second unit of the plurality of remote electronic units (5), wherein the first data bus (11) and the second data bus (12 ) is based on the same bus technology, wherein the first data bus system (10) additionally comprises a backup-data bus (13) for transferring data between the actuator-control electronics (4) and the first remote electronic unit (5) ), wherein the bus technology of the backup data bus (13) is different from that of the first data bus (11) and the second data bus (12). Since the duplex architecture of the main bus provides high system availability and device availability, the backup-data bus is limited to data exchange only between computers which are only required as a minimum configuration for safe flight operation. System components and associated electronics that are not required for minimal configuration (minimum control) are not integrated into the backup network. This reduces complexity, cabling outlay, cable weight and installation costs.

Description

technical field [0001] The invention relates to a flight control system for operating control surfaces of an aircraft. Background technique [0002] The flight control system is used to translate input from the pilot or the flight control computer into corresponding movements of the various control surfaces of the aircraft. The movement of the control surfaces of the aircraft has a direct influence on the flight control during flight of the aircraft, since the flight motion of the aircraft is thus directly achieved. [0003] In the current common fly-by-wire control system, the control commands from the cockpit or the flight control computer are no longer transmitted to the corresponding control surface by means of cables as before, but are transmitted to the aircraft fuselage by digital data transmission. on the control surface, or on the actuator that operates the control surface. In fly-by-wire technology, manual inputs made by the pilot, for example with a joystick, ar...

AI Technical Summary

Problems solved by technology

[0007] The disadvantage of this disclosure is that after a general error leading to the failure of one of the two data networks, an error of the other redundant data network may lead to an operational failure of one or more control surfaces

A further disadvantage is that the implementation of the data network or of the entire bus system with different data network types requires very high development and cost outlays, both in terms of hardware and software, since the connection to the various controllable components of the aircraft must be Two completely independent bus systems for programming and installation

Integration of different data network types is also very challenging

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