JPH07329893A - Aircraft monitoring device - Google Patents

Abstract

PURPOSE:To provide an aircraft monitoring device capable of estimating an inspection timing from an actual flight load. CONSTITUTION:A load meter 1 mounted on an aircraft, a load frequency computer 2 to compute load frequency during flight by receiving output of the load meter 1, a stress computer 3 to compute stress of a specified part by receiving output of the load frequency computer 2, a breakage computer 4 to compute a degree of breakage of a specified part by receiving the output of the load frequency computer 2 and the breakage computer 4, an inspection timing computer 5 to compute an inspection timing of a specified part by receiving the output of the load frequency computer 2 and the breakage computer 4 and an indicator 6 to indicate an inspection timing of a specified part by receiving the outputs of the inspection timing computer 5 are provided.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aircraft monitor device for maintaining the structural integrity of an aircraft.

[0002]

2. Description of the Related Art Conventionally, in order to maintain the structural integrity of an aircraft, analysis, inspection and repair have been performed in the following procedure. Define areas of importance and potential damage. Determine the basic flight pattern of the aircraft (see Figure 3, (a)). A stress analysis of the structure of each of the above parts is performed. The stress spectrum of each part is obtained (see FIG. 3, (b)). Life analysis (calculation of the time when a crack is generated in a member and the growth rate of the generated crack) is performed for each part from the SN curve (see FIG. 2, (c)). The inspection start timing and the inspection interval are determined from the result of (see FIG. 2, (d)). In accordance with the above, the inspection work will be performed on the actual machine and the required measures will be taken. Is being carried out.

[0003]

In the above conventional aircraft structural soundness assurance method, the basic flight pattern is defined by defining the operation mode of a general aircraft. The statistical idea that the life of the airframe structure is determined by this basic flight pattern is applied. In the actual operation of the airframe, the load on the airframe is different for each flight due to the flight time, the flight speed, the airframe motion, the weight of the airframe, and the like.

In the conventional method, the flight status of each aircraft is individually grasped for each flight, and the life analysis is not performed from the result.

In order to ensure soundness by statistical processing using the basic flight pattern, inspection on the safety side is generally instructed, which leads to an increase in maintenance cost of the aircraft and a decrease in operating efficiency.

[0006]

The present invention takes the following means in order to solve the above problems.

That is, as an aircraft monitor device, a load cell mounted on the aircraft, a load frequency calculator for calculating the load frequency during flight by receiving the output of the load cell, and a predetermined output for receiving the output of the load frequency calculator Of the stress calculator for calculating the stress of the portion, the load frequency calculator and the damage degree calculator for calculating the damage degree of the predetermined portion by receiving the output of the stress calculator, and the load frequency calculator and the damage degree calculator An inspection time calculator for receiving the output and calculating the inspection time of the predetermined portion, and a display for receiving the output of the inspection time calculator and displaying the inspection time of the predetermined portion are provided.

[0008]

In the above means, the load cell outputs the load during flight. The load frequency calculator receives the output of the load cell and calculates and outputs the load frequency during flight. The stress calculator receives the output of the load frequency calculator and calculates the stress for a predetermined portion of the machine body, that is, a structure important point. The damage degree calculator receives the output of the stress calculator and the output of the load frequency calculator,
The degree of damage to the predetermined part is calculated. The inspection timing calculator receives the outputs of the damage degree calculator and the load frequency calculator, and calculates the remaining flight time until it is estimated that the predetermined part will be damaged,
Output the inspection time. The display receives the output of the inspection time calculator and displays the inspection time of each predetermined part.

In this way, the required inspection time of the important portion is estimated and output based on the actual load. Therefore, the operator can know the time when the important parts need to be inspected for each flight, so that unnecessary inspections can be prevented and the operation efficiency of the aircraft can be improved.

[0010]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention described above will be described with reference to FIGS. In FIG. 1, a load cell 1 is mounted on an aircraft. The output is sent to the load frequency calculator 2. The output of the load frequency calculator 2 is sent to the stress calculator 3, the damage degree calculator 4, and the inspection time calculator 5. The output of the stress calculator 3 is sent to the inspection timing calculator 5 via the damage degree calculator 4. The output of the inspection time calculator 5 is sent to the display.

In the above, the load cell 1 of the airframe measures and outputs the load during flight (see FIG. 2). The load frequency calculator 2 processes the load data from the load cell 1 to calculate the load frequency per 1 FLT Hr of the current (in flight) FLT (see FIGS. 2 and 3). The stress calculator 3 receives the output of the load frequency calculator 2, and the load response curve that has already been calculated or analyzed by a test or the like for a predetermined structural important point (a point that affects the soundness of the aircraft) (Fig. (2, FIG. 3) is used to calculate the stress of each part. Damage degree calculator 4
Receives the output of the stress calculator 3 and the output of the load frequency calculator 2, and inputs the material S / N curve (FIG. 2,
) Is used to calculate the degree of damage at each site.
The inspection time calculator 5 receives the outputs of the damage degree calculator 4 and the load frequency calculator 2 and calculates the remaining flight time until it is estimated that damage will occur in each part, and outputs the inspection time (FIG. 2). , Fig. 3,). The display 6 receives the output of the inspection time calculator 5 and displays the inspection time of each part (FIGS. 2, 3,).

In this way, the flight load that differs depending on the operating conditions (flight speed, airframe motion, airframe weight, etc.) of each airframe is calculated for each flight, the damage state of the airframe structure is estimated, and it is necessary for each part of the airframe. The appropriate inspection time is displayed. Therefore, unnecessary inspections can be prevented, appropriate preventive maintenance can be performed, and the operating efficiency of the aircraft can be improved.

Further, if this adoption is taken into consideration from the design stage, it is possible to manage the individual fatigue of the airframe during actual operation, and the weight of the structure can be reduced.

[0014]

As described above, according to the present invention, the required inspection time of a predetermined important point is estimated and output based on the actual load during flight. Therefore, the operator can know the time when the important parts need to be inspected for each flight, so that unnecessary inspections can be prevented and the operation efficiency of the aircraft can be improved.

[Brief description of drawings]

FIG. 1 is a configuration block diagram of an embodiment of the present invention.

FIG. 2 is an operation explanatory view of the same embodiment.

FIG. 3 is an operation explanatory view of the same embodiment.

FIG. 4 is an explanatory diagram of a conventional example.

[Explanation of symbols]

 1 load meter 2 load frequency calculator 3 stress calculator 4 damage degree calculator 5 inspection timing calculator 6 indicator

Claims (1)

[Claims] 1. A load cell mounted on an aircraft, a load frequency calculator that calculates the load frequency during flight by receiving the output of the load meter, and calculates the stress of a predetermined part by receiving the output of the load frequency calculator. And a damage degree calculator for calculating the degree of damage of the predetermined portion by receiving the outputs of the load frequency calculator and the stress calculator, and the predetermined degree of receiving the outputs of the load frequency calculator and the damage degree calculator. An aircraft monitor device comprising: an inspection time calculator for calculating an inspection time of a part; and a display device for receiving the output of the inspection time calculator and displaying the inspection time of the predetermined part.