Abstract: The present application relates to a system and a method for handling a fault of an aircraft. The system for handing a fault of an aircraft comprises an interface module for receiving the fault message and a troubleshooting decision-making unit for making a troubleshooting decision against the aircraft faults, wherein the troubleshooting decision is made by the troubleshooting decision-making unit based on fault types/safety risks and cost estimation. The examples in the application allow a cost-effective troubleshooting decision.

Abstract: The present application relates to a simulation device of flight management system (FMS), comprising a navigable database and a performance database; a display portion; a horizontal section portion and a vertical section portion, wherein the horizontal section portion and vertical section portion provide horizontal route information and vertical route information of the route designated by a user through the navigable database and performance database; and wherein the display portion is mutually integrated with the horizontal section portion and vertical section portion.

Abstract: A testing equipment of an airplane air conditioning system is disclosed. The test equipment includes a sound receiver and a sound processor. The sound processor processes running noise of airplane air conditioning system sampled by the sound receiver to assess the operative condition of the system. The sound receiver samples environmental noise when the airplane air conditioning system is not running, and the sound processor de-noises the running noise by using the environmental noise.

Abstract: The present invention relates to a system and method for monitoring lubricant of an engine. The system for monitoring lubricant of an engine comprises: a lubricant sensor, which measures lubricant quantity of the engine; a data acquisition unit, which collects the lubricant quantity of the engine from the lubricant sensor at a fixed time interval; and a message generation unit, which generates lubricant quantity monitoring messages according to the lubricant quantity of the engine collected by the data acquisition unit.

Abstract: According to various embodiments, the present invention relates to a platform and method for testing aircraft message trigger logics are disclosed. Apparatus for testing message trigger logics of aircraft comprises: DFDAU (a Digital Flight Data Acquisition Unit), which is adapted to receive message trigger logics to be tested; an input interface, which is adapted to receive data of aircraft condition; and a simulation signal generator, which is adapted to generate simulation signals according to the data of aircraft condition; wherein, the DFDAU is adapted to receive the simulation signals, and generate messages according to the message trigger logics to be tested.

Abstract: The present invention relates to a method and device for monitoring performance of an auxiliary power unit (APU) turbine efficiency of an aircraft. The method comprises: obtaining APU messages at multiple time points within a period; obtaining APU startup parameters including at least a rotation speed at a peak of EGT according to the APU messages; calculating a percentage NPA of the rotation speed when the exhausting gas temperature EGT reaches its peak at the APU startup stage relative to the rotation speed in the APU normal operation; calculating the average of the NPA within the period; and determining which of the stable, decline and failure phases the APU turbine efficiency is in according to the average of the NPA.

Abstract: The present invention relates to a method for detecting performance of the lubricant cooler in aircraft auxiliary power unit APU, comprising: acquiring APU-related messages within a time period; obtaining the operation parameters of the APU lubricant cooler, the operation parameters comprise: lubricant temperature OT and load compressor inlet temperature LCIT; the revised lubricant temperature OT is obtained by the following formula: the revised lubricant temperature=lubricant temperature OTA?the load compressor inlet temperature LCIT; determining the performance of the APU lubricant cooler is in stable phase, decline phase or malfunction phase according to the change trend of the revised lubricant temperature OT with respect to time.

Abstract: The present invention relates to a method for detecting performance of an APU fuel assembly, comprising: obtaining APU messages at multiple time points within a time period; obtaining running parameters of the APU fuel assembly according to the APU messages, the running parameters at least comprising starting time STA; calculating average value AVG and deviation index ? of the starting time STA within said time period; determining whether performance of the APU fuel assembly is in the stable phase, decline phase, or failure phase according to the deviation index ?.

Abstract: The present invention relates to a test apparatus that includes a simulation signal generation portion and a test portion. Embodiments of the simulation signal generation portion include an input interface, a simulation signal generation module, and an output interface. Embodiments of the test portion include wiring extension apparatus, a Digital Flight Data Acquisition Unit and a comparison module.

Abstract: The present invention relates to a method and device for monitoring APU turbine vane fracture and rotor shaft jam. The method for monitoring APU turbine vane fracture and rotor shaft jam comprises: acquiring APU messages at multiple time points within a period; obtaining the operation parameters of the APU according to the APU messages, the operation parameters including at least the start time STA; calculating the average value AVG and the deviation index ? of the start time STA within the period; and determining the circumstance of the turbine vane fracture and rotation shaft jam of APU is in stable phase, decline phase or malfunction phase according to the deviation index ?.

Abstract: The present invention relates to a method for detecting performance of an APU starter, comprising: obtaining APU-related messages at multiple time points within one time period; obtaining running parameters of the APU starter according to the messages, the running parameters comprise starting time STA; calculating average value AVG and deviation index ? of the starting time within said time period; determining whether performance of the APU starter is in a stable phase, decline phase or failure phase according to the deviation index ?.

Abstract: The present invention relates to a system and method for detecting an aircraft jitter. The aircraft jitter detection system comprises: a jitter detection apparatus, which detects accelerations of pitch and yaw of the aircraft; a data acquisition apparatus, which obtains accelerations in two directions detected by the jitter detection apparatus; and a jitter determination apparatus, which extracts frequency spectrum and energy information of the jitter according to the accelerations in two directions obtained by the data acquisition apparatus, and determines whether the aircraft jitters.

Abstract: The present invention relates to a method for detecting addition of engine lubricant, comprising: determining whether the difference value between the lubricant quantity at a first timing and that at a second timing is greater than a first threshold value; delaying a period and determining whether the difference value between the lubricant quantity at a third timing and that at a fourth timing is greater than a second threshold value in response to that the difference value between the lubricant quantity at the first timing and that at the second timing is greater than the first threshold value; and detecting the lubricant increment in response to that the difference value between the lubricant quantity at the third timing and that at the fourth timing is greater than the second threshold value.

Abstract: The present invention relates to a system for monitoring the wing anti-icing valve, comprising: time record device configured to record the time for opening or closing the anti-icing valve; data acquisition device configured to obtain the time for opening or closing the anti-icing valve recorded by the time record device; and message generation device configured to generate the anti-icing valve performance message according to the time for opening or closing the anti-icing valve obtained by the data acquisition device.

Abstract: The present application relates to a simulation device of flight management system (FMS), comprising a navigable database and a performance database; a display portion; a horizontal section portion and a vertical section portion, wherein the horizontal section portion and vertical section portion provide horizontal route information and vertical route information of the route designated by a user through the navigable database and performance database; and wherein the display portion is mutually integrated with the horizontal section portion and vertical section portion.

Abstract: The present invention relates to a system for improving the flight safety, comprising: a prediction component which predicts behaviors of an aircraft; and an indication component which indicates adjustment of an operation of the aircraft to reduce the possibility of occurrence of abnormal flying behaviors.

Abstract: The present invention relates to a platform and method for testing aircraft message trigger logics. Apparatus for testing message trigger logics of aircraft comprises: DFDAU (Digital Flight Data Acquisition Unit), which is adapted to receive message trigger logics to be tested; an input interface, which is adapted to receive data of aircraft condition; and a simulation signal generator, which is adapted to generate simulation signals according to the data of aircraft condition; wherein, the DFDAU is adapted to receive the simulation signals, and generate messages according to the message trigger logics to be tested.

Abstract: The present invention relates to testing equipment of an onboard air conditioning system, comprising: a sound receiver and a sound processor, wherein the sound processor processes the running noise of onboard air conditioning system sampled by the sound receiver to assess the operative condition of the system.