In-situ testing system for flight control system loading mechanism

Abstract

The invention relates to an in-situ testing system for a flight control system loading mechanism. The system comprises a portable ruggedized computer and a testing device. The testing device comprises a control lever and a joystick clamp. A force sensor is connected between the control lever and the joystick clamp, an angle sensor is arranged on the joystick clamp, and the force sensor and the angle sensor are electrically connected with a programmable communication interface (PCI) data acquisition card inserted into the fuse ruggedized computer respectively. The in-situ testing system is simple in structure, small in size, convenient to operate and capable of achieving a real-time, fast, correct, reliable and safe test for joystick force and joystick displacement, can generate a joystick force-joystick displacement characteristic ccurve automatically through testing software and achieves performance judgment for the loading mechanism, and the problem that the loading mechanism cannot be detected in in-situ mode due to the fact that an aeronautical maintenance support department is short of detecting devices is solved.

Description

technical field [0001] The invention relates to a test system for an aircraft control system, in particular to an in-situ test system for a load mechanism of an aircraft control system. Background technique [0002] The aircraft control system is used for the pilot to manipulate the aircraft to rotate around the vertical axis, horizontal axis and vertical axis to change or maintain the flight state of the aircraft. It is a very important system of the aircraft. The control system of modern aircraft is basically a non-return control system, and the aerodynamic force acting on the control surface of the aircraft cannot be transmitted back to the control stick. In order to make the pilot have a real feeling of operating the control stick, a load mechanism is set in the control system to generate an appropriate control force and automatically return to the center when the pilot releases the control stick. For example, the flat tail load mechanism is used to form the longitudina...

AI Technical Summary

Problems solved by technology

[0003] At present, aviation maintenance units do not have testing equipment for testing the load mechanism of the aircraft control system, and cannot realize in-situ testing of the load mechanism

Although the out-of-position detection of the load mechanism can be realized, it increases the disassembly and assembly workload of the load mechanism, prolongs the troubleshooting time, reduces the work efficiency, affects the integrity rate of the aircraft, and seriously restricts the development of aviation maintenance and support work.

Images