一种基于异构传感器配置的监控方法、装置及存储介质
By comparing the signal differences between the inertial navigation unit (IRS) and the attitude reference unit (AHRU), and utilizing complementary filtering and logic transformation, the problem of common-mode faults in the triple-redundant input signal architecture of inertial navigation was solved, enabling safe degradation and fault indication of the flight control system, and improving flight safety.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- XIAN FLIGHT SELF CONTROL INST OF AVIC
- Filing Date
- 2023-12-26
- Publication Date
- 2026-07-17
AI Technical Summary
In civil flight control systems, in the triple-redundant input signal architecture of inertial navigation, the inertial navigation unit (IRS) maintains high accuracy in the short term but may experience signal drift, while the attitude reference unit (AHRU) has poor long-term stability, which leads to the correct attitude signal being voted by the wrong sensor signal when there is a common-mode failure, and there is a lack of effective solutions.
By comparing the differences between the angular rate, roll angle, and pitch angle voting values of the IRS and AHRU and the output values of the DMRS, complementary filtering and logic conversion are used to determine whether there is a common-mode fault in the inertial navigation unit IRS, and the flight control system is switched to degraded mode when a fault occurs.
It improves flight safety, prevents catastrophic accidents caused by erroneous inertial navigation signals, ensures that the flight control system automatically degrades in the event of a malfunction, and protects pilot safety.
Smart Images
Figure CN117870657B_ABST