![]() With the cable connector of airborne equipment of the flight control system and the aircraft cable separation surface connector, necessary signals are disconnected or introduced to inspect the static performances of the system, subsystems, and their airborne equipment, such as zero position, dead zone, polarity, transmission ratio, stroke, and speed as well as the cross-linking interface between subsystems. The first three functions depend on the fly-by-wire flight control system and the last three functions are relatively independent and are realized through independent subsystems. The flight control system has functions including normal fly-by-wire control, degraded fly-by-wire control, simulated backup operation, mechanical backup operation, automatic control, and lift augmentation control. Chaoyou Zhi, in Test Techniques for Flight Control Systems of Large Transport Aircraft, 2021 7.1.2 Functional and performance test The iterations of design optimization and improvement depend on the accuracy of the requirements proposal, the designers’ understanding of the users’ requirements, the engineering experience of the subsystem and unit designers, and even the assurance of the management and quality system. Possible activities include computational checks, prototype manufacturing, assembly, and subsystem test.Īfter the corresponding verification, commonly comes the unit scheme improvement, subsystem-level scheme optimization, and even system-level scheme change. In the engineering design, processing, manufacturing, assembly, and commissioning of the flight control system and subsystem, various effective verification activities should be carried out to identify problems, to improve the design, and to optimize and iterate the system. Chaoyou Zhi, in Test Techniques for Flight Control Systems of Large Transport Aircraft, 2021 1.6.2.3 Verification test in the design and implementation stageįlight control system, subsystem design, and implementation include a series of verification test activities. After the MBIT is carried out, check if the results of MBIT meet design requirements through automatic flight control system tester. After the AFCC is connected and the PUBIT is completed, set the automatic flight control system in fault state and connect MBIT. ![]() IFBIT: Set the flight profile state of the aircraft in flight simulation system, operate the aircraft to enter test state, connect the autopilot working mode, ensure the automatic flight control system works normally and then set system faults through the automatic flight control system tester, and then read the IFBIT results through the automatic flight control system tester, check if the results of IFBIT meet design requirements. After the PBIT is carried out, check if the results of PBIT meet design requirements through the automatic flight control system tester. PBIT: After the AFCC is connected and the PUBIT is completed, set the automatic flight control system in fault state and connect PBIT. After the PUBIT is carried out, check if the results of the PUBIT meet design requirements through the automatic flight control system tester. PUBIT: Before connecting the AFCC, set the automatic flight control system in fault state and then power on the automatic flight control system. The basic test principle of BIT is described as follows. The automatic flight control system of large aircraft generally has BIT functions, including PUBIT, PBIT, IFBIT and MBIT.
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