JPS59111010A - Load frequency meter - Google Patents

Abstract

PURPOSE:To facilitate the production of a hard copy while heightening the reliability of a maintenance data by measuring and memorizing continuation time at each level of fatigue accelerating stress employing an IC electronic equipment such as CPU, EAROM, ROM and RAM. CONSTITUTION:An accelerometer I detects acceleration given an aircraft during the flight and an acceleration data processed and discriminated with a CPU 11 is sent to an electrically erasable and writable memory EAROM 12 to be memorized. A time pulse generation module 21 mainly composed of a quartz oscillator outputs a clock signal to the CPU 11 through an interface circuit 10 to provide exact time information and the signal is memorized into the EAROM 12 together with the processed acceleration data. A data collector III inputs various data transmitted in a multiplex fashion to corresponding counting display elements 16 to be displayed while sending them to a printer 17 for printing out to obtain a hard copy.

Description

[Detailed description of the invention] TECHNICAL FIELD This invention relates to cargo management words used in aircraft.

Aircraft are equipped with load frequency meters to estimate the degree of fatigue in the airframe and other components. The load frequency meter is as shown in @1.
Accelerometer 1. Peak acceleration detection circuit (2), count display driver (3), count display (4), operating time counter (
5) AC and DC power supplies (consisting of 6L).The accelerometer weight is installed on the aircraft to measure the vertical acceleration of one aircraft that the aircraft encounters during flight.

Peak acceleration detection circuit (2) Ii jerk measurement Detects the peak value of the obtained acceleration and determines within which range of predetermined acceleration levels it falls. In other words, the acceleration level is -3~Ig, -1
”-Og, 2-3g, 3-4g, 4-5g, 5-5
g, 6 to 7g (7) VC" ii W4 ノV Hellk Setting* Determine which of the levels of the first type the detected acceleration peak value corresponds to. Count display Drime (3) is for driving the divisor display, and in this case, it has seven drivers corresponding to seven different acceleration levels.Of course, there are also seven divisor displays (4), and the peak acceleration detection circuit ( The determination signal from 2) excites the corresponding count display driver and pulses the corresponding division display.

As mentioned above, the load frequency side is activated only when the aircraft is in flight, and it is also important to determine the operating time of this load frequency meter, that is, the cumulative flight time of the aircraft. For this purpose, an AC power source is connected through a switch element (8) which is equipped with an operating time counter (5) and is opened and closed depending on the presence or absence of a load on the aircraft leg.
No. 7IIi is added. In other words, during flight, the switch element (8) is closed, the external AC power source is connected to the AC power source inside the load frequency needle, an AC drive signal is issued, and the operation timetable (5) is activated. . The DC power supply (7) is for supplying stable DC power to each component of the load frequency meter (so-called B power supply), and is the same as the AC power supply (6) mentioned above.
excited by h.

By the way, regarding this more conventional load frequency side, it is possible to measure the degree and frequency of acceleration received during one flight, as well as the flight time, but what is the level of acceleration applied and for how long? was impossible to detect. Of course, in order to obtain data such as acceleration and flight time, the cumulative data 7 displayed on the counter
Manual work of reading and transcribing is required,
This gives rise to the possibility of human error such as misreading of data, resulting in a decrease in the reliability of the obtained data. Furthermore, this counting display was composed of extremely small and highly accurate mechanical parts, and the single display was expensive, leading to an increase in cost.

The present invention provides a completely new load frequency meter that uses all electronic components such as IC elements, instead of the conventional load frequency meter that is composed of mechanical components such as a count display. FIG. 2 shows a block diagram of an embodiment of the present invention. In the same figure, (8) is an accelerometer, and (8) is a switch element for raising the aircraft landing gear signal.

It is equivalent to the conventional one and is indicated by the same numerals as 6D. (9) is an analog-to-digital converter, (1O) is an interface circuit, (11) is a central processing unit, (12) is an electrically erasable memory U EAFtOM, (13)
U read-only memory ROM, (14) temporary storage memory RAM, (15) transmission reception module, (
16) is a division display element, (17) is a printer, (1B
> is DC power supply, (19) is readout switch, (2
0) is a reset switch. Acceleration 1 detects the acceleration that the aircraft receives during flight, and the detected data is converted into a digital quantity via an analog-to-digital converter (9), and sent to the central processing unit cPU via an interface circuit (10). (11).The central processing unit OP U (11) processes the sent acceleration data according to the program stored in the read-only memo IJ (13). It determines whether the acceleration level is at that level, how long it lasts, how many times the application is applied within the corresponding acceleration level, etc.As explained in the conventional example, the acceleration level r41 is -1
A common method is to divide the acceleration from g to log into seven stages. The acceleration history data processed and determined by the central processing unit cPU (11) is sent to and stored in the electrically erasable and writable memory EAROM (12). Temporary memory memo I) RAM (14) is central processing unit OP U (11
) This is to temporarily store the determination results etc. during data processing in K. The DC power supply (1 day) supplies stable DC power to each component of the load frequency LL.

The external AC power source is excited only when the aircraft is in flight via the aircraft's landing gear switch element (8). Interface circuit (10) to provide IW information Central processing unit (11) via f
Outputs the clock signal. This time/base clock signal is used when calculating the duration of each acceleration corresponding to each predetermined acceleration level, excluding the processing of acceleration data in the central processing unit (11), and when adding the acceleration. Of course, this time information is stored in the EAROI.1 (12) together with the acceleration processing data.

In this way, the fatigue data of the acceleration that the aircraft receives during flight is divided into each acceleration level, and the duration, frequency, and total operating time are calculated and stored for each acceleration level data. .

Next, a procedure for reading out the processed data of the acceleration encountered during the above-mentioned flight after the aircraft returns to the ground after the flight is completed will be described. That is, the data collection device III? consists of a count display element (16), a printer (17), a readout switch (1!l)), and a reset switch (20). Central processing unit (11) + ARO1vl (12), R
AM (14).

1' (OM (13), etc., to the acceleration data processing/storage device ■, and each transmission/receiving module T/of the data collection device III and acceleration data processing/storage device ■.
Data transfer commands, data transfer, etc. are exchanged via R(15)k. Note that 1# of the data collection device II is supplied by the acceleration data processing/storage device n. To read data, turn on the data read switch (19) of the data collection device [1n], and then turn on the transmission/reception module (15) on each side of the data collection device nI. A data transfer command is given to the acceleration data processing/storage device (2) via the acceleration data processing/storage device (2). This data transfer command causes the interface circuit (10), central processing unit (11)
(OM (12) Various data stored in Ic are read out and sent to data collection device III. Data collection device ■
inputs the various multiplexed data to the corresponding count display elements (16), displays the data, and also sends it to the printer (17) to print out and obtain a hard copy. In this way, the acceleration data processed and accumulated by the acceleration data processing/storage device H,
For flight time data, connect data collection device 1■
Turn on the readout switch (19) and display the count display element (16).
) and can be operated on a printer (1'7)' to obtain a hard copy. The reset switch (2o) of the data collection device ■■ is used for data processing Φ1. This is for erasing and clearing all the data stored/accumulated in the EAROM (12) of the device (#). By inserting this, all the data in the EAROM (12) will be electrically cleared.

Furthermore, as shown by the broken line in FIG. 2, it is also conceivable to provide a division display similar to that of the conventional device in order to display only important data. This Ii is designed for convenience so that if it is heavy equipment data, the user only needs to look at the display window of the count display without having to operate the data display device III.

As stated above, this invention is based on the OP U JAROM
, FtOM, RAM, etc. 1/'1, also.

It provides a load frequency meter that is equipped with an nI number display element and a printer, and a hard copy is also easily available.
It is possible to measure and store the duration of each level of fatigue acceleration stress that an aircraft encounters during flight, and it is also possible to measure and store the duration of each level of fatigue acceleration stress that an aircraft encounters during flight, and to display various data.
I is a direct electrical signal 9 conducts 7' L1 follows "C1 This digital display element '1 It is easy to operate the printer using the sulfur signal, and the printer can be installed and hard copies can be easily made. You can get the correct IC,
Conventional devices collect data manually by reading and transcribing the counting data displayed on the small display window of the word count display, and there is a possibility of human error such as misreading.
These data are used as maintenance data,
A decrease in reliability was undeniable.In other words, automatic recording by the printer according to the present invention ("L1 without manual intervention,
The problems of the reliability of maintenance data, which the conventional device has, are solved.

In addition, the data processing/storage device IIζ stores, stores, and converts various data that can be erased at any time by command from the data collection device. In addition to official use, it can also be used as a stress frequency meter to accumulate and measure general acceleration stress.

Furthermore, in terms of cost, there is no need to use an expensive count display, and even if it is used, only a very small number may be used for displaying special important data.

Considerable improvements can be made.

[Brief explanation of drawings]

In the drawings, FIG. 1 is a block diagram of a conventional example, and FIG. 2 is a block diagram of an embodiment of the present invention. ■... Accelerometer II - Φ Acceleration data processing/storage device 101 - Interface circuit 11... Central processing unit 12... Electrically erasable/writable memory 13... Read-only memory IIIo writing/data Collection device 16... Count display element 17... - Printer 19... Continuation switch 20... Reset switch Applicant Shinko Electric Co., Ltd. Agent Patent attorney Haruya Saito

Claims (1)

[Claims] 1. An accelerometer that measures the fatigue acceleration stress that an aircraft encounters during flight; in relation to acceleration data from the accelerometer, what range of acceleration levels is there and how long does it last? Acceleration data processing/storage device II consisting of a central processing unit that executes data processing and others, and an electrically erasable and writable memory that stores and accumulates the data processing results.
, a data reading means for transferring the processed data of the electrically erasable and writable memory through the central processing unit, the interface circuit, and the transmission/receiving module; a count display element for displaying the data; and a count display element for displaying the data. A data collection group [III] comprising a printer for obtaining a hard copy of display data, and a reset means for erasing various processing data stored in the electrically erasable and writable memory. .