CN215444230U - Automatic counting device for running time of aircraft engine - Google Patents
Automatic counting device for running time of aircraft engine Download PDFInfo
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- CN215444230U CN215444230U CN202121103041.5U CN202121103041U CN215444230U CN 215444230 U CN215444230 U CN 215444230U CN 202121103041 U CN202121103041 U CN 202121103041U CN 215444230 U CN215444230 U CN 215444230U
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Abstract
一种飞机发动机运转时间自动统计装置，包括用于采集发动机转速的转速传感器，用于将转速传感器采集的转速信号转换为TTL电平信号的转速信号调理电路，将TTL电平信号进行逻辑处理转换为总线形式的频率数字量的可编程逻辑电路，用于传送运转时间数据的总线，用于解析数据的中央处理器，用于存储数据的内部存储器；转速传感器依次通过转速信号调理电路、可编程逻辑电路和中央处理器连接，中央处理器和内部存储器连接，中央处理器还通过总线和外部的飞控计算机连接；转速信号调理电路为依次连接的分压电路、一阶滤波电路、二阶滤波电路和整形电路。本方案提供了一种自动检测转速的装置，自动统计、存储和上传，实现了全方位的自动化。
An automatic statistics device for aircraft engine running time, comprising a rotational speed sensor for collecting the rotational speed of the engine, a rotational speed signal conditioning circuit for converting the rotational speed signal collected by the rotational speed sensor into a TTL level signal, and performing logic processing and conversion on the TTL level signal It is a programmable logic circuit of frequency digital quantity in the form of a bus, a bus for transmitting running time data, a central processing unit for parsing data, and an internal memory for storing data; the speed sensor is in turn through the speed signal conditioning circuit, programmable The logic circuit is connected to the central processing unit, the central processing unit is connected to the internal memory, and the central processing unit is also connected to the external flight control computer through the bus; the speed signal conditioning circuit is a voltage divider circuit, a first-order filter circuit, and a second-order filter connected in sequence. circuits and shaping circuits. This solution provides a device for automatically detecting rotational speed, automatically counting, storing and uploading, and realizing all-round automation.
Description
Technical Field
The utility model relates to the field of rotating speed statistics, in particular to an automatic statistical device for the running time of an aircraft engine.
Background
The service life control of the aircraft engine is extremely important for the reliable use of the engine, and accurate statistics of the running time of the engine is required in the service life control. The traditional engine running time statistical mode is that a detachable process recorder is manually recorded or installed, and relevant time information is read through ground equipment after the process recorder is detached. The former needs manual operation, and the latter needs dismouting many times on the aircraft, and efficiency is all lower.
SUMMERY OF THE UTILITY MODEL
The utility model aims to: the utility model provides an aircraft engine running time automatic statistics device, set up the revolution speed sensor on aircraft engine, after the rotational speed of collection engine, convert into TTL level signal through rotational speed signal conditioning circuit, then send central processing unit to handle and resolve out rotational speed and the running time of engine, then central processing unit stores rotational speed and running time in the memory, sends the data to the flight control computer through the bus and shows simultaneously, provides an automated inspection rotational speed's device, has solved above-mentioned problem.
The technical scheme adopted by the utility model is as follows:
an automatic statistical device for the running time of an aircraft engine comprises a rotating speed sensor for collecting the rotating speed of the engine, a rotating speed signal conditioning circuit for converting a rotating speed signal collected by the rotating speed sensor into a TTL level signal, a programmable logic circuit for performing logic processing on the TTL level signal and converting the TTL level signal into a frequency digital quantity in a bus form, a bus for transmitting running time data, a central processing unit for analyzing the data and an internal memory for storing the data;
the rotating speed sensor is connected with a central processing unit through a rotating speed signal conditioning circuit and a programmable logic circuit in sequence, the central processing unit is connected with an internal memory, and the central processing unit is also connected with an external flight control computer through a bus;
the rotating speed signal conditioning circuit comprises a voltage division circuit, a first-order filter circuit, a second-order filter circuit and a shaping circuit which are connected in sequence.
In order to better realize the scheme, the speed signal conditioning circuit is a voltage dividing resistor R1 and a voltage dividing resistor R2 which are connected to the speed sensor in parallel, respectively, the voltage dividing resistors R1 and R2 are both connected to the non-inverting input terminal of the operational amplifier N1C, the inverting input terminal and the output terminal of the operational amplifier N1C are connected, the output terminal of the operational amplifier N1C is connected to the non-inverting input terminal of the operational amplifier N1D through a resistor R3, the inverting input terminal and the output terminal of the operational amplifier N1D are connected, the output terminal of the operational amplifier N1D is connected to the flip-flop D1A, the output terminal of the operational amplifier N1D is grounded through a resistor R4 which is connected in parallel and a diode V1 which is arranged in an inverting direction, and the output terminal of the flip-flop D1A serves as the output terminal of the speed signal conditioning circuit.
In order to better implement the scheme, a bus sending circuit for converting the signal output by the central processing unit into a bus form is further arranged between the central processing unit and the flight control computer.
In order to better implement the present solution, further, the bus transmission circuit includes a bus protocol chip TL16C754BPN and a driver chip DS26C31 ME/883.
In order to better implement the scheme, further, the central processing unit adopts a TMS320F28335 processor.
To better implement this solution, further, the internal memory uses an EEPROM (X5323 ZAP) type memory.
The automatic counting device for the running time of the aircraft engine comprises a rotating speed sensor, a rotating speed signal conditioning circuit, a programmable logic circuit, a bus, a flight control computer, a central processing unit and an internal memory, wherein the rotating speed sensor is connected with the central processing unit sequentially through the rotating speed signal conditioning circuit, the programmable logic circuit, the central processing unit is connected with the internal memory, and the central processing unit is further connected with the flight control computer through the bus. The system comprises a speed sensor, a speed signal conditioning circuit, a programmable logic circuit, a central processing unit, an internal memory and a flight control computer, wherein the speed sensor is arranged on an engine of an airplane and used for acquiring the speed of the engine of the airplane, the speed signal conditioning circuit divides, filters and shapes the acquired speed signal and then sends the divided, filtered and shaped speed signal to the programmable logic circuit, the programmable logic device converts the engine speed signal FD into a bus-form frequency digital quantity for the central processing unit to acquire after logic processing, the central processing unit processes the digital quantity after acquiring the digital quantity, one path of the processed data is sent to the internal memory by the central processing unit, and the other path of the processed data is sent to the flight control computer through a bus to be displayed.
In summary, due to the adoption of the technical scheme, the utility model has the beneficial effects that:
1. the utility model relates to an automatic statistical device for the running time of an aircraft engine, which is characterized in that a rotating speed sensor is arranged on the aircraft engine, the rotating speed of the engine is acquired and converted into a TTL level signal through a rotating speed signal conditioning circuit, the TTL level signal is sent to a central processing unit for processing and analyzing the rotating speed and the running time of the engine, the central processing unit stores the rotating speed and the running time into a memory and sends data to a flight control computer through a bus for display, and the device for automatically detecting the rotating speed is provided;
2. the utility model relates to an automatic counting device for the running time of an aircraft engine, which is characterized in that a rotating speed sensor is arranged on the aircraft engine, the rotating speed sensor collects the rotating speed of the engine, converts the rotating speed into a TTL level signal through a rotating speed signal conditioning circuit, and then sends the TTL level signal to a central processing unit for processing and analyzing the rotating speed and the running time of the engine, and then the central processing unit stores the rotating speed and the running time into a storage and sends data to a flight control computer through a bus for display.
Drawings
In order to more clearly illustrate the technical solution, the drawings needed to be used in the embodiments are briefly described below, and it should be understood that, for those skilled in the art, other related drawings can be obtained according to the drawings without creative efforts, wherein:
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic diagram of a rotational speed signal conditioning circuit according to the present invention;
FIG. 3 is a schematic diagram of a bus protocol chip circuit connection of the bus transmitter circuit of the present invention;
fig. 4 is a circuit connection diagram of a driving chip of the bus transmission circuit of the present invention.
Detailed Description
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and therefore should not be considered as a limitation to the scope of protection. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The present invention will be described in detail with reference to fig. 1 to 4.
Example 1:
an automatic statistical device for the running time of an aircraft engine is shown in figure 1 and comprises a rotating speed sensor for collecting the rotating speed of the engine, a rotating speed signal conditioning circuit for converting a rotating speed signal collected by the rotating speed sensor into a TTL level signal, a programmable logic circuit for performing logic processing on the TTL level signal and converting the TTL level signal into a frequency digital quantity in a bus form, a bus for transmitting running time data, a central processing unit for analyzing the data and an internal storage for storing the data;
the rotating speed sensor is connected with a central processing unit through a rotating speed signal conditioning circuit and a programmable logic circuit in sequence, the central processing unit is connected with an internal memory, and the central processing unit is also connected with an external flight control computer through a bus;
as shown in fig. 2, the rotation speed signal conditioning circuit is a voltage dividing circuit, a first-order filter circuit, a second-order filter circuit and a shaping circuit, which are connected in sequence.
The working principle is as follows: the automatic counting device for the running time of the aircraft engine comprises a rotating speed sensor, a rotating speed signal conditioning circuit, a programmable logic circuit, a bus, a flight control computer, a central processing unit and an internal memory, wherein the rotating speed sensor is connected with the central processing unit sequentially through the rotating speed signal conditioning circuit, the programmable logic circuit, the central processing unit is connected with the internal memory, and the central processing unit is further connected with the flight control computer through the bus. The system comprises a speed sensor, a speed signal conditioning circuit, a programmable logic circuit, a central processing unit, an internal memory and a flight control computer, wherein the speed sensor is arranged on an engine of an airplane and used for acquiring the speed of the engine of the airplane, the speed signal conditioning circuit divides, filters and shapes the acquired speed signal and then sends the divided, filtered and shaped speed signal to the programmable logic circuit, the programmable logic device converts the engine speed signal FD into a bus-form frequency digital quantity for the central processing unit to acquire after logic processing, the central processing unit processes the digital quantity after acquiring the digital quantity, one path of the processed data is sent to the internal memory by the central processing unit, and the other path of the processed data is sent to the flight control computer through a bus to be displayed.
In addition, the rotating speed measuring method of the programmable logic circuit is a cycle measuring method: the method is characterized in that a standard high frequency with very high precision is introduced, a rotating speed signal and the standard high frequency are counted simultaneously in the same time, and then the counting ratio of the two frequencies is integrated to calculate the frequency digital quantity of the rotating speed signal.
Example 2:
on the basis of embodiment 1, as shown in fig. 2, the speed signal conditioning circuit is a voltage dividing resistor R1 and a voltage dividing resistor R2 which are connected in parallel to the speed sensor, respectively, the voltage dividing resistors R1 and R2 are both connected to the non-inverting input terminal of an operational amplifier N1C, the inverting input terminal of the operational amplifier N1C is connected to the output terminal, the output terminal of the operational amplifier N1C is connected to the non-inverting input terminal of the operational amplifier N1D through a resistor R3, the inverting input terminal of the operational amplifier N1D is connected to the output terminal, the output terminal of the operational amplifier N1D is connected to a flip-flop D1A, the output terminal of the operational amplifier N1D is grounded through a resistor R4 and an inversely arranged diode V1, and the output terminal of the flip-flop D1A serves as the output terminal of the entire speed signal conditioning circuit.
And a bus sending circuit for converting the signal output by the central processing unit into a bus form is arranged between the central processing unit and the flight control computer. The bus transmission circuit comprises a bus protocol chip TL16C754BPN shown in FIG. 3 and a driver chip DS26C31ME/883 shown in FIG. 4. The internal memory uses an EEPROM (X5323 ZAP) type memory.
The central processing unit adopts a TMS320F28335 processor. The bus width is 32 bits, the main frequency 150M, the instruction period of 6.67nS, the 20-bit data bus, the 32-bit address bus and the I/O interface adopt 3.3V for power supply. After receiving the frequency digital quantity of the rotating speed signal, the central processing unit firstly carries out software filtering, and then the rotating speed of the engine is calculated according to the following formula: engine speed (Rpm) = frequency (Hz) × seconds per minute/speed ratio. And the central processing unit judges whether the rotating speed of the engine is more than 500, and accumulates the total operating time of the engine and the operating time of the engine of the current flight task according to every minute when the rotating speed of the engine is more than 500, and stops accumulating until the rotating speed of the engine is less than or equal to 500. The total running time of the engine is accumulated by reading the total running time of the engine recorded in the internal memory at the last time and accumulating the total running time of the engine on the basis; and the engines of the current flight mission are accumulated from zero. In addition, the central processing unit can also upload the running time parameters of the engine to the flight control computer in real time.
The working principle is as follows: in the speed signal conditioning circuit of the present embodiment, the resistors R1 and R2 perform a voltage division function, and the high level of the speed signal after voltage division is 3.3V. The resistor R3, the capacitor C1 and the operational amplifier N1 form a first-order filter circuit. The resistor R4, the diode V1 and the Schmidt trigger D1 form a shaping circuit, the Schmidt trigger D1 has an obvious effect of shaping waveform distortion of signals, and the diode V1 is a voltage stabilizing diode and is used for clamping transient overvoltage. The rotating speed signal conditioning circuit can improve the acquisition precision of the rotating speed signal.
Other parts of this embodiment are the same as those of embodiment 1, and thus are not described again.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (6)
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| Application Number | Priority Date | Filing Date | Title |
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| CN202121103041.5U CN215444230U (en) | 2021-05-21 | 2021-05-21 | Automatic counting device for running time of aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202121103041.5U CN215444230U (en) | 2021-05-21 | 2021-05-21 | Automatic counting device for running time of aircraft engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113202653A (en) * | 2021-05-21 | 2021-08-03 | 成都凯天电子股份有限公司 | Automatic measuring system for engine running data |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113202653A (en) * | 2021-05-21 | 2021-08-03 | 成都凯天电子股份有限公司 | Automatic measuring system for engine running data |
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