Flap and slat non-instruction motion protection verification system and verification method

A verification system and slat technology, which is applied in the field of aircraft flight control system detection, can solve the problems such as difficulty in simulating the uncommanded movement of flaps and slats for system components, difficulties in verification work, etc., and achieve the effect of comprehensive and reliable functional performance.

Active Publication Date: 2020-04-17
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

At present, most of the functional performance testing of the slat controller, which is the core control component of the aircraft high-lift system, is already mature, but it is difficult to simulate the real non-command movement of the slat for the fault setting of the system components. There are difficulties in the verification of the function of "flaps and slat non-command protection"

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  • Flap and slat non-instruction motion protection verification system and verification method

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Embodiment Construction

[0018] Such as figure 1 As shown, a non-command motion protection verification system for flaps and slats includes flaps and slats control handles, flaps and slats controllers, testers, slats and slats power drive units (slats and slats PDUs), flaps and slats slat PDU), slat rudder surface, flap rudder surface, slat position sensor and flap position sensor, described slat control handle is connected with slat controller, and slat controller is connected with slat controller The tester is connected, and the tester is connected with the slat power drive device and the flap power drive device respectively, and the described slat power drive device and the flap power drive device are respectively connected with the slat rudder surface and the flap rudder surface , the slat control surface is connected with the slat position sensor, the flap control surface is connected with the flap position sensor, and both the slat position sensor and the flap position sensor are connected with ...

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Abstract

The invention discloses a flap and slat non-instruction motion protection verification system and verification method. The device comprises a flap and slat control handle, a flap and slat controller,a tester, a slat power driving device, a flap power driving device, a slat control surface, a flap control surface, a slat position sensor and a flap position sensor, wherein an instruction output bythe flap and slat controller is adjusted through the tester; and the flap and slat driving device drives the control surface to perform non-instruction motion after receiving the adjusted instruction.The test problem of the flap and slat non-instruction motion protection function of the flap and slat controller is solved, the comprehensive and reliable verification of the functional performance of the flap and slat controller is realized, and the reference of a non-instruction motion detection method is provided for other similar products.

Description

technical field [0001] The invention belongs to the technical field of detection of aircraft flight control systems, and in particular relates to a verification system and verification method for non-command movement protection of flaps and slats. Background technique [0002] Aircraft flaps and slats, as the high-lift device of the aircraft, play an important role in the take-off and landing stages of the aircraft. The control system of the flaps and slats is called a high-lift control system, and whether the high-lift control system can work normally will seriously affect the safety of the aircraft. At present, most of the functional performance testing of the slat controller, which is the core control component of the aircraft high-lift system, is already mature, but it is difficult to simulate the real non-command movement of the slat for the fault setting of the system components. There are difficulties in the verification of the function of "flaps and slat non-command...

Claims

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Application Information

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IPC IPC(8): B64C13/00B64D45/00
CPCB64C13/00B64D45/00B64D2045/0085
Inventor 陈素娟董骥
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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