CN112298584A - Method for synchronizing and fusing rotating speed vibration data of helicopter main reducer - Google Patents
Method for synchronizing and fusing rotating speed vibration data of helicopter main reducer Download PDFInfo
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- CN112298584A CN112298584A CN202011200721.9A CN202011200721A CN112298584A CN 112298584 A CN112298584 A CN 112298584A CN 202011200721 A CN202011200721 A CN 202011200721A CN 112298584 A CN112298584 A CN 112298584A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
Abstract
The invention belongs to the technical field of helicopter vibration monitoring, provides a method for synchronizing and fusing rotating speed vibration data of a helicopter main reducer, solves the problem of low synchronization precision of the existing method, and is used for preprocessing functional data of helicopter main reducer vibration alarm and fault diagnosis. Compared with the traditional method, under the unchangeable condition of existing machine-mounted HUMS product framework, utilize FPGA simultaneous control vibration signal AD to gather, the characteristics of rotational speed collection, capture rotational speed signal rising edge or falling edge inside FPGA, when capturing rising edge or falling edge, the digital signal that will this moment vibration signal AD acquisition result corresponds the bit mark and is "1", it is the interval point number of "1" to correspond the bit through vibration signal, just can acquire actual rotational speed value, and the error is less, this method is synchronous with rotational speed signal and vibration signal in real time, fuse, it is simple easily to realize, do not increase machine-mounted data volume, also do not omit the real-time transform characteristic of rotational speed, be favorable to later stage vibration signal's feature extraction very much.
Description
Technical Field
The invention belongs to the technical field of helicopter vibration monitoring, and particularly relates to a method for synchronizing and fusing rotating speed and vibration data of a helicopter main reducer, which is used for vibration alarm and fault diagnosis of the helicopter main reducer and is convenient for functions of later-stage time domain synchronous averaging, whole-period equal-phase FFT, torsional vibration judgment and the like.
Background
The vibration signal is one of important signals reflecting the working state of the main speed reducer, and contains a large amount of running state information of the system; the rotating speed signal is a key index of the rotating frequency of the internal gear and the bearing of the main reducer. At present, the method for collecting and analyzing vibration signals is an effective method for diagnosing faults of a main speed reducer, and most faults of the main speed reducer are closely related to the vibration signals. Therefore, the vibration monitoring of the main speed reducer is an important content of state monitoring and fault diagnosis. Through a plurality of vibration sensors and speed sensor, various vibration signals and the rotational speed signal of main reducer can be gathered, through the real-time detection to vibration signal's amplitude, vibration intensity, phase place isoparametric, combine the characteristic of rotational speed signal, but real-time supervision main reducer's operation condition avoids the major accident to take place to cause the loss for the enterprise.
The traditional method for synchronizing the vibration signal and the rotating speed signal comprises the following two methods:
1. the method comprises the steps of packaging original data of a vibration signal, an average value of a rotating speed digital signal, a maximum value of the rotating speed digital signal and a minimum value of the rotating speed digital signal in a period of time T, forming a new vibration and rotating speed data packet every other period of time T, and meeting the synchronization requirement of the vibration and rotating speed signals;
2. and synchronously acquiring the vibration signal original data and the rotation speed original data by an AD acquisition device, packaging the vibration signal original data and the rotation speed original data, and forming a new vibration and rotation speed data packet at intervals of time T to meet the synchronous requirements of vibration and rotation speed signals.
The first method cannot completely record the rotation speed signal transformation information, only records the minimum value and the average value, cannot provide accurate information for subsequent equal-phase interpolation fitting when the rotation speed fluctuates, and has low synchronization precision; the second method records a large amount of rotating speed data, particularly for a main speed reducer, when a plurality of rotating speed signals exist, the data amount to be analyzed and recorded is greatly increased, so that the second method is not suitable for airborne electronic products and is commonly used in the analysis and processing process of a ground laboratory.
Disclosure of Invention
The invention aims at the existing two methods: the invention provides a method and a system for synchronizing and fusing rotating speed vibration data of a main reducer, which are suitable for helicopter airborne electronic products, and solves the problems that the existing method cannot synchronize and fuse vibration and rotating speed signals effectively, simply and conveniently.
Utilize FPGA to correspond the position at the ascending edge time mark vibration signal of rotational speed, utilize main reducer vibration signal sampling frequency fixed and frequency high, the characteristics that rotor rotational speed, tail-rotor rotational speed and power turbine rotational speed are low, with vibration and rotational speed signal real-time synchronization, integration, simple easily realize, do not increase machine carries data volume, also do not omit the real-time transform characteristic of rotational speed, the characteristic extraction that is favorable to later stage vibration signal very much.
In order to achieve the purpose, the technical scheme of the invention is as follows:
a method for synchronizing and fusing rotating speed and vibration data of a helicopter main reducer is characterized by comprising the following steps:
step 1, signal acquisition;
collecting n paths of vibration signals and n paths of rotating speed signals; wherein n is a positive integer greater than or equal to 1;
step 2, signal conversion;
respectively converting the n paths of vibration signals into vibration voltage signals; respectively converting the n paths of rotating speed signals into rotating speed square wave signals;
step 3, marking the vibration signal by using the rotating speed signal;
step 3.1, respectively converting n paths of vibration voltage signals into digital signals by using n paths of analog-to-digital conversion units;
3.2, controlling the acquisition starting time, the data reading sequence and the data caching sequence of the n paths of vibration signal analog-to-digital conversion units by the FPGA; synchronously acquiring n paths of vibration digital signals and n paths of rotating speed square wave signals;
3.3, capturing the rising edge or the falling edge of each rotating speed square wave signal by the FPGA, and simultaneously marking all corresponding bits of the n paths of vibration digital signals at the moment as '1'; marking the corresponding bit of the n paths of vibration digital signals at the moment that each rotating speed square wave signal is not on the rising edge or the falling edge as '0';
and 4, acquiring N marked vibration digital signals, and calculating the rotating speed N as Fs/M according to the number M of the marking bit data intervals of any one vibration digital signal, wherein Fs is the sampling frequency of the vibration digital signals. Meanwhile, judging the change condition of the rotating speed; and the multi-channel vibration signals can be aligned according to the mark positions with the same rotating speed, and the synchronization of the multi-channel vibration signals can be realized.
Further, in step 3.2, the FPGA controls n analog-to-digital conversion unit pins CONVST level to be converted simultaneously, so as to realize synchronous acquisition of n vibration digital signals.
Further, Fs is larger than 20KHz, and the rotating speed N is not larger than 400 Hz.
Further, in step 3.3, a 50MHz crystal oscillator signal is used to capture the rising edge or the falling edge of each rotational speed square wave signal.
The invention also provides a system for synchronizing and fusing the rotating speed and vibration data of the main reducer of the helicopter, which is characterized in that: the system comprises n paths of vibration signal conditioning circuits, n paths of rotating speed signal conditioning circuits, an analog-to-digital conversion unit and an FPGA;
the n vibration signal conditioning circuits are respectively used for converting the n vibration signals into vibration voltage signals;
the n paths of rotating speed signal conditioning circuits are respectively used for converting the n paths of rotating speed signals into rotating speed square wave signals;
the analog-to-digital conversion unit comprises n analog-to-digital converters and is used for converting the n paths of vibration voltage signals into digital signals;
the FPGA is used for controlling the acquisition starting time, the data reading sequence and the data cache sequence of the n analog-to-digital converters and synchronously acquiring n paths of vibration digital signals and n paths of rotating speed square wave signals; capturing the rising edge or the falling edge of each rotating speed square wave signal, and simultaneously marking all corresponding bits of the n paths of vibration digital signals at the moment as '1'; and marking the corresponding bit of the n paths of vibration digital signals at the non-rising edge or falling edge time of each rotating speed square wave signal as '0'.
The invention has the beneficial effects that:
compared with the traditional method, the method has the advantages that the FPGA is utilized to simultaneously control the A/D acquisition and the rotation speed acquisition of the vibration signals under the condition that the structure of the existing airborne HUMS product is unchanged, the rising edge (or the falling edge) of the rotation speed signals is captured in the FPGA, the rising edge (or the falling edge) is captured, the corresponding bit of the digital signals of the A/D acquisition results of the multi-path vibration signals at the moment is marked as '1', the corresponding bit of the digital signals of the A/D acquisition results of the vibration signals at the moment of non-rising edge is marked as '0', the sampling frequency of the vibration signals of the main speed reducer is fixed and the frequency is high (generally 100KHz), and the rotation speed of a rotor, the rotation speed of a tail rotor and the rotation speed of a power turbine are low (400Hz), so that the actual rotation speed value can be obtained through the number of interval points with the corresponding bit of '1' by the vibration signals, the integration is simple and easy to realize, airborne data volume is not increased, real-time rotating speed transformation characteristics are not omitted, and the feature extraction of later-stage vibration signals is facilitated.
Drawings
FIG. 1 is a block diagram of a helicopter main reducer rotational speed vibration data synchronization and fusion system;
FIG. 2 is a schematic diagram of a rising edge of a tachometer signal;
FIG. 3 is a schematic flow chart of the vibration signal of the FPGA internal rotation speed along the time mark.
Detailed Description
The invention is further described with reference to the following figures and specific embodiments:
referring to fig. 1, the system for synchronizing and fusing rotational speed and vibration data of a helicopter main reducer in the present embodiment includes n vibration signal conditioning circuits, n rotational speed signal conditioning circuits, an analog-to-digital conversion unit, and an FPGA; the vibration signal conditioning circuit converts the n paths of vibration signals into vibration voltage signals respectively; the rotating speed signal conditioning circuit respectively converts n rotating speed signals into rotating speed square wave signals; the analog-to-digital conversion unit comprises n analog-to-digital converters and converts n paths of vibration voltage signals into digital signals; the FPGA controls n analog-to-digital converters to acquire starting time, a data reading sequence and a data cache sequence, and synchronously acquires n paths of vibration digital signals and n paths of rotating speed square wave signals; capturing the rising edge or the falling edge of each rotating speed square wave signal, and simultaneously marking all corresponding bits of the n paths of vibration digital signals at the moment as '1'; and marking the corresponding bit of the n paths of vibration digital signals at the non-rising edge or falling edge time of each rotating speed square wave signal as '0'.
Specifically, the synchronization and fusion of the rotating speed and the vibration data are realized through the following processes:
step 1, signal acquisition;
collecting n paths of vibration signals and n paths of rotating speed signals; wherein n is a positive integer greater than or equal to 1;
step 2, signal conversion;
respectively converting the n paths of vibration signals into vibration voltage signals; respectively converting the n paths of rotating speed signals into rotating speed square wave signals;
step 3, marking the vibration signal by using the rotating speed signal;
step 3.1, respectively converting n paths of vibration voltage signals into digital signals by using n paths of analog-to-digital conversion units;
3.2, controlling the acquisition starting time, the data reading sequence and the data caching sequence of the n paths of vibration signal analog-to-digital conversion units by the FPGA; synchronously acquiring n paths of vibration digital signals and n paths of rotating speed square wave signals; the CONVST level of the n analog-to-digital conversion unit pins can be controlled to be converted simultaneously, and synchronous acquisition of n vibration digital signals is achieved.
3.3, as shown in fig. 2 and 3, the FPGA captures the rising edge or the falling edge of each rotating speed square wave signal, and simultaneously, the corresponding bits of the n paths of vibration digital signals at the moment are all marked as "1"; marking the corresponding bit of the n paths of vibration digital signals at the moment that each rotating speed square wave signal is not on the rising edge or the falling edge as '0'; the present embodiment uses a 50MHz crystal oscillator signal to capture the rising or falling edge of each tachometer square wave signal. Other signal capture device implementations may also be used.
And 4, acquiring N marked vibration digital signals, and calculating the rotating speed N as Fs/M according to the number M of the marking bit data intervals of any one vibration digital signal, wherein Fs is the sampling frequency of the vibration digital signals. Meanwhile, judging the change condition of the rotating speed; and the multi-channel vibration signals can be aligned according to the mark positions with the same rotating speed, and the synchronization of the multi-channel vibration signals can be realized.
In the embodiment, one FPGA controls analog-to-digital conversion (controlling acquisition starting time and data reading sequence) and data caching of multiple vibration signals, vibration sampling frequency Fs is greater than 20KHz, multiple rotation speed signal edge capture is controlled, and rotation speed frequency N is not greater than 400 Hz.
The rotational speed vibration data of a certain helicopter main reducing gear is taken as an example for explanation.
A certain helicopter main reducer is provided with 3 paths of rotating speed sensors, namely N1, N2 and N3, and 3 paths of vibration sensors, namely ZD1, ZD2 and ZD 3;
the airborne electronic product collects 3 paths of rotating speed and 3 paths of vibration signals, and a rotating speed signal conditioning circuit is used for converting the rotating speed signals into square wave signals, wherein the rotating speed signal conditioning circuit is a conventional circuit and comprises circuits for filtering, shaping, hysteresis comparison and the like; converting the vibration signal into a voltage signal suitable for A/D acquisition by using a vibration signal conditioning circuit; the vibration signal conditioning circuit is also a conventional circuit and comprises circuits such as filtering, amplifying and the like. And converting the vibration voltage signal into a vibration digital signal by the A/D acquisition.
The airborne electronic product uses FPGA to collect vibration digital signals and rotating speed square wave signals, wherein the sampling frequency Fs of the vibration digital signals is 100KHz, and 50MHz crystal oscillator signals are used for realizing rising edge capture of the rotating speed square wave signals.
3 pieces of 12-bit A/D chips AD7892 are used in common, and the FPGA controls CONVST levels of 3 paths of AD7892 pins to be converted simultaneously to achieve synchronous acquisition of 3 paths of vibration signals; the size of a 3-channel vibration signal storage FIFO in the FPGA is 8 KB; each of N1, N2, and N3 defines 3 vibration signals ZD1, ZD2, ZD3 and each data flag bit is shown in table 1, table 2, and table 3.
Table 1 each data flag bit of vibration signal ZD1
Table 2 each data flag bit of vibration signal ZD2
Table 3 each data flag bit of vibration signal ZD3
The FPGA captures the rising edges of the square wave signals corresponding to N1, N2 and N3, when the rising edge of the rotating speed signal of N1 is detected, the digital signals corresponding to B14 bits of ZD1, ZD2 and ZD3 at the moment are all marked as '1', the B14 bit of the rising edge time marker is not detected as '0', and the marking is carried out continuously in a circulating mode; the method for marking the rising edges of N2 and N3 is the same as that of N1, and finally the vibration data are marked with N1, N2 and N3 corresponding to the rising edge time and the non-rising edge time.
Acquiring data of ZD1, ZD2 and ZD3 marked in FIFO in FPGA by software, calculating a rotating speed N (Fs/M) (100 KHz) according to a vibration data interval point M with a position of '1' in any one of ZD1, ZD2 and ZD3 vibration data B14, and judging the rotating speed change condition according to continuous interval points M1 and M2, wherein if M1 (M2) is … …, namely the interval points are equal, the rotating speed is stable, otherwise, the rotating speed continuously changes and fluctuates; the labeling positions of B12 and B13 are used in the same principle.
Software polls to obtain data of ZD1, ZD2 and ZD3 marked in FIFO in FPGA, and ZD1, ZD2 and ZD3 are initially aligned according to the marking bit of B14 as '1', so that vibration signal synchronization can be realized, and the marking bits of B12 and B13 have the same use principle.
The method synchronizes and fuses the rotating speed signal and the vibration signal in real time, is simple and easy to realize, does not increase the airborne data volume, does not omit the real-time rotating speed transformation characteristics, and is very favorable for the characteristic extraction of the vibration signal in the later period.
Claims (5)
1. A method for synchronizing and fusing rotating speed vibration data of a helicopter main reducer is characterized by comprising the following steps:
step 1, signal acquisition;
collecting n paths of vibration signals and n paths of rotating speed signals; wherein n is a positive integer greater than or equal to 1;
step 2, signal conversion;
respectively converting the n paths of vibration signals into vibration voltage signals; respectively converting the n paths of rotating speed signals into rotating speed square wave signals;
step 3, marking the vibration signal by using the rotating speed signal;
step 3.1, respectively converting n paths of vibration voltage signals into digital signals by using n paths of analog-to-digital conversion units;
3.2, controlling the acquisition starting time, the data reading sequence and the data caching sequence of the n paths of vibration signal analog-to-digital conversion units by the FPGA; synchronously acquiring n paths of vibration digital signals and n paths of rotating speed square wave signals;
3.3, capturing the rising edge or the falling edge of each rotating speed square wave signal by the FPGA, and simultaneously marking all corresponding bits of the n paths of vibration digital signals at the moment as '1'; marking the corresponding bit of the n paths of vibration digital signals at the moment that each rotating speed square wave signal is not on the rising edge or the falling edge as '0';
and 4, acquiring N marked vibration digital signals, and calculating the rotating speed N as Fs/M according to the number M of the marking bit data intervals of any one vibration digital signal, wherein Fs is the sampling frequency of the vibration digital signals.
2. The helicopter main reducer rotational speed vibration data synchronization and fusion method according to claim 1, characterized in that: in step 3.2, the FPGA controls N analog-to-digital conversion unit pins CONVST level to be converted simultaneously, and synchronous acquisition of n vibration digital signals is achieved.
3. The helicopter main reducer rotational speed vibration data synchronization and fusion method according to claim 1 or 2, characterized in that: fs is more than 20KHz, and the rotating speed N is not more than 400 Hz.
4. The helicopter main reducer rotational speed vibration data synchronization and fusion method according to claim 3, characterized in that: and 3.3, capturing the rising edge or the falling edge of each rotating speed square wave signal by using a 50MHz crystal oscillator signal.
5. The utility model provides a helicopter main reducer rotational speed vibration data is synchronous and fuse system which characterized in that: the system comprises n paths of vibration signal conditioning circuits, n paths of rotating speed signal conditioning circuits, an analog-to-digital conversion unit and an FPGA;
the n vibration signal conditioning circuits are respectively used for converting the n vibration signals into vibration voltage signals;
the n paths of rotating speed signal conditioning circuits are respectively used for converting the n paths of rotating speed signals into rotating speed square wave signals;
the analog-to-digital conversion unit comprises n analog-to-digital converters and is used for converting the n paths of vibration voltage signals into digital signals;
the FPGA is used for controlling the acquisition starting time, the data reading sequence and the data cache sequence of the n analog-to-digital converters and synchronously acquiring n paths of vibration digital signals and n paths of rotating speed square wave signals; capturing the rising edge or the falling edge of each rotating speed square wave signal, and simultaneously marking all corresponding bits of the n paths of vibration digital signals at the moment as '1'; and marking the corresponding bit of the n paths of vibration digital signals at the non-rising edge or falling edge time of each rotating speed square wave signal as '0'.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113395070A (en) * | 2021-04-12 | 2021-09-14 | 上海昱章电气成套设备有限公司 | Analog signal processing method and device and computer equipment |
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