CN113985307A - Amphibious aircraft power supply system operating characteristic detection and analysis device - Google Patents
Amphibious aircraft power supply system operating characteristic detection and analysis device Download PDFInfo
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Abstract
The invention relates to the field of power supply systems of amphibious aircraft, in particular to a device for detecting and analyzing the working characteristics of a power supply system of the amphibious aircraft. The system comprises a hardware device and a software system: the hardware device includes: the system comprises voltage sensors (S001-S008) for testing, non-contact current sensors (S009-S016), a signal conditioning unit S1, a signal acquisition unit S2, a signal processing unit S3, a system power supply unit S4, an external unit S5 and a bus controller S6; the invention has a multi-channel high-precision data acquisition device, can synchronously acquire a plurality of groups of variables and realize real-time analysis. The system can monitor the working state of the system in real time and dynamically analyze the working characteristics of the power supply system in the process of aircraft power supply and distribution faults and maintenance. The technical scheme of the invention enables parameters of the power supply system of the amphibious aircraft to be collected in a unified manner, has real-time performance, and can be used for displaying, analyzing, storing and the like data.
Description
Technical Field
The invention relates to the field of power supply systems of amphibious aircraft, in particular to a device for detecting and analyzing the working characteristics of a power supply system of the amphibious aircraft.
Background
The airplane electrical system refers to a general name of an airplane power supply system and electric equipment. The system consists of three subsystems of power supply, power distribution and power utilization. The power supply system is also called as a power supply system and supplies power to various electric equipment on the airplane.
During ground test and starting of an aircraft, the aircraft needs ground to provide power supply support, and the aircraft is generally divided into a starting power supply and a bus power supply. The starting power supply is mainly used for supplying the starting power to the aircraft starter generator, and generally has larger power and more rapid power change. The bus power supply is mainly used for other equipment facilities of the airplane. According to the use characteristics of the airplane, the power supply is divided into an alternating current power supply (115V/400Hz) and a direct current power supply (28V, 72V, 270V and the like), different power supply application occasions are different, and in addition, other forms of conversion power supplies are arranged on the airplane.
In the safe operation of aircraft, the power supply system plays a very important role. Therefore, the performance parameters of the aircraft power supply system are accurately and quickly tested, and the performance of the aircraft power supply system, whether faults exist or not, potential safety hazards exist or not can be analyzed according to data, so that the method has very important significance in the research of the aircraft power supply system. The amphibious aircraft power supply system provided by the invention comprises an alternating current power supply form and a direct current power supply form, and has more power supply functional channels, so that the voltage and current acquisition equipment of a common aviation power supply is difficult to realize unified acquisition and cannot provide analysis reference. In other words, in the conventional data measurement device, several or dozens of different devices are often used to collect and analyze parameters of different systems, and global unified collection and analysis cannot be achieved.
Disclosure of Invention
The invention provides a parameter measurement and analysis device and method for an amphibious aircraft power system. The method is used for measuring output characteristic analysis of a turboprop engine starting generator, assisting in completing characteristic analysis of the relation between a power supply system and a power utilization system in the aircraft ground test process, and providing test data for optimizing the design and improvement of an aircraft power supply system.
The technical scheme of the invention is as follows: an amphibious aircraft power supply system operating characteristic detection and analysis device comprises a hardware device and a software system:
wherein the hardware device includes: the system comprises voltage sensors (S001-S008) for testing, non-contact current sensors (S009-S016), a signal conditioning unit (S1), a signal acquisition unit (S2), a signal processing unit (S3), a system power supply unit (S4), a peripheral unit (S5) and a bus controller (S6); 8 paths of the voltage sensor (S001-S008) and 8 paths of the non-contact current sensor (S009-S016) are connected with the signal conditioning unit S1 through 16 paths of NBC interfaces; the signal conditioning unit S1 is connected to the signal acquisition unit S2, namely the signal conditioning unit S1 normalizes the signal and transmits the signal to the signal acquisition unit S2; the signal acquisition unit S2 is connected to the signal processing unit S3, namely the signal acquisition unit S2 converts the analog signal into a digital signal and transmits the digital signal to the signal processing unit S3, and the signal processing unit S3 processes, analyzes, stores and displays the digital signal; the signal processing unit S3 is connected to the system power supply unit S4 to manage and control the system power supply, the power supply of the whole system is provided by the mains supply conversion direct current (AC/DC) power supply (U14) of the system power supply unit S4, and the backup battery (U15) of the system power supply unit supports the equipment to operate under the condition that no external power supply is supported; the signal processing unit S3 is also connected to the peripheral unit S5 and the bus controller S6;
the software system mainly realizes the analysis and processing of system data: the data processing and analyzing software can perform waveform display and online analysis on the acquired data, judge whether the airplane power supply system has abnormality in the operation process through the data, set a threshold value to alarm the real-time data abnormality and store the data for post analysis.
Furthermore, the voltage sensor (S001-S008) is designed as a passive sensor, wherein a fixed capacitor Cin1 and a fixed resistor Rin1 form a resistance-capacitance impedance network, and can detect direct current voltage and alternating current voltage; ccom1 is an adjustable capacitor used for attenuator compensation, and the compensation effect is obtained by adjusting the capacitance value.
Further, the voltage sensors (S001-S008) are divided into 8 groups, namely S001-S008, and can be configured into two forms of direct current acquisition and alternating current acquisition according to requirements; wherein S001-S006 are DC voltage sensors, and S007 and S008 are AC voltage sensors.
Further, the non-contact current sensors (S009 to S016) are classified into dc current sensors and ac current sensors; s009 to S014 are dc current sensors, and S015 and S016 are ac current sensors.
Furthermore, the non-contact direct current sensor (S009-S016) adopts an active sensor and mainly comprises an open type Hall sensor (U01), a signal operational amplifier network (U02) and an impedance network (U03), micro-current signals collected by the Hall sensor (U01) are input into the signal amplifier network (U02), the signal amplifier network (U02) converts the absorbed current into voltage signals to be connected to the impedance network (U03), and the voltage signals are output to other circuit units at the rear end after being converted into voltage. The signal of the direct current can be collected under the condition of not disconnecting the current.
Further, the working part of the non-contact alternating current sensor mainly comprises an open type electromagnetic current transformer (U04) and an impedance network (U05); the iron core of the straight-through current transformer is made into a movable opening and is in a pincer shape.
Further, the signals of the voltage sensor and the non-contact current sensor are processed and then connected with a signal conditioning unit (S1) through a BNC interface.
Furthermore, a matching impedance network (U06) composed of Ro1 and Co1 is arranged at the front end of the signal conditioning unit (S1), active filtering (U07) and active operational amplifier (U08) are adopted at the rear end, and filtering processing and amplitude normalization processing are carried out on the acquired signals; the rear end is connected to a signal acquisition unit (S2) which transmits the normalized signal to the signal acquisition unit, and the signal acquisition unit converts the normalized analog signal into a digital signal by a signal protection unit (U09) and a high-speed ADC acquisition unit (U10).
Further, the signal acquisition unit (S2) is connected with the signal processing unit (S3), and the signal processing unit (S3) is composed of a digital signal processor CPU (U11), a logic control unit (U12) and a storage unit (U13); the signal processing unit (S3) is used for processing the acquired and converted digital signals, analyzing, storing and displaying the data, and controlling the system signals to keep synchronous in the same time coordinate system.
Further, the peripheral unit (S5) includes a display, a mouse, a keyboard, and a USB interface.
Furthermore, the bus control unit (S6) of the invention is connected with an upper computer or forms a network with other equipment through a serial port or a network interface, and transmits data.
The invention has the beneficial effects that: the invention has a multi-channel high-precision data acquisition device, can synchronously acquire a plurality of groups of variables and realize real-time analysis. The system can monitor the working state of the system in real time and dynamically analyze the working characteristics of the power supply system in the process of aircraft power supply and distribution faults and maintenance.
The method is used for measuring output characteristic analysis of a turboprop engine starting generator, assisting in completing characteristic analysis of the relation between a power supply system and a power utilization system in the aircraft ground test process, and providing test data for optimizing the design and improvement of an aircraft power supply system.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description, serve to explain the principles of the invention. And are not to be construed as unduly limiting the invention.
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiment or the prior art will be briefly described below, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
In the drawings:
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a detailed structural schematic of the present invention;
FIG. 3 is a basic schematic diagram of a voltage sensor;
FIG. 4 is a schematic diagram of a DC current sensor;
FIG. 5 is a basic schematic diagram of an AC current sensor;
FIG. 6 is a basic schematic diagram of a signal conditioning unit;
FIG. 7 is a basic schematic diagram of a signal acquisition unit;
FIG. 8 is a basic schematic diagram of a signal processing unit;
FIG. 9 is a flow chart of data processing and analysis software.
Wherein:
S001-S006 are direct current voltage sensors, S007 and S008 are alternating current voltage sensors, S009-S014 are direct current sensors, and S015 and S016 are alternating current sensors;
s1: signal conditioning unit, S2: signal acquisition unit, S3: signal processing unit, S4: peripheral unit, S5: device power supply system, S6: a bus controller;
u01: open hall sensor, U02: signal operational amplifier network, U03: impedance network, U04: open type electromagnetic current transformer, U05: impedance network, U06 matching impedance network, U07: active filtering, U08: active operational amplifier, U09: the device comprises a signal protection unit, a U10 high-speed ADC acquisition unit, a U11 digital signal processor CPU, a U12 logic control unit, a U13 storage unit, and a U14: mains-converted direct current (AC/DC) supply, U15: and (5) preparing a battery.
Detailed Description
In order to make the technical measures and technical measures of the present invention better understood by those skilled in the art, the present invention is further described in detail with reference to the drawings and examples.
Reference will now be made in detail to the exemplary embodiments of the invention, examples of which are illustrated in the accompanying drawings. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples of apparatus consistent with certain aspects of the invention, as detailed in the appended claims. For example, in the embodiment of the present invention, 16 signals are collected, and the number of the collected paths cannot be used to limit the present invention.
As shown in figure 1, the parameter measurement and analysis device for the power supply system of the amphibious aircraft. The device comprises voltage sensors (S001-S008), non-contact current sensors (S009-S016), a signal conditioning unit (S1), a signal acquisition unit (S2), a signal processing unit (S3), an external unit (S4), a device power supply system (S5) and a bus controller (S6). Wherein 8 paths of the voltage sensor (S001-S008) and 8 paths of the non-contact current sensor (S009-S016) are connected with the signal conditioning unit S1 through 16 paths of NBC interfaces; the signal conditioning unit S1 is connected to the signal acquisition unit S2, namely the signal conditioning unit S1 normalizes the signal and transmits the signal to the signal acquisition unit S2; the signal acquisition unit S2 is connected to the signal processing unit S3, i.e., the signal acquisition unit S2 converts the analog signal into a digital signal and transmits the digital signal to the signal processing unit S3, and the signal processing unit S3 processes, analyzes, stores and displays the digital signal. The signal processing unit S3 is also connected to the system power supply unit S4 to control the system power supply, the power supply system of the whole system is provided by the system power supply unit S4, and the backup battery of the system can support the equipment to operate without the support of an external power supply. The signal processing unit S3 also connects the peripheral unit S5 and the bus controller S6. The signal processing unit S3 controls the peripherals and the bus, and realizes the overall consistent operation of the system.
According to the voltage sensors S001-008 shown in FIGS. 2 and 3, a measurement signal passes through an impedance network formed by connecting Rin1 and Cin1 in parallel and then is connected to a test cable, the other side of the test cable is connected to a BNC connector, and an attenuator compensation capacitor Ccom1 is connected in parallel.
The active direct current sensor S009-S014 shown in the figures 2 and 4 is characterized in that a measuring signal cable passes through an open type Hall sensor U01, an induction signal of the open type Hall sensor U01 is converted into a voltage signal through R1 and is connected to an active signal operational amplifier network U02, the signal is operated through the active signal operational amplifier network U02 and then is connected to a BNC connector on the other side through an impedance network U03 and a testing cable, wherein the impedance network is formed by connecting R2, R3 and C1 in series and parallel. The active direct current sensor is powered by a self-contained power supply, and provides power for the Hall sensor and the operational amplifier network.
By the ac current sensors S015 and S016 shown in fig. 2 and 5, the measurement signal line passes through the open-type electromagnetic current transformer U04, the induction signal of the open-type electromagnetic current transformer U04 is converted into a voltage signal through R4, and then is connected to the impedance network U05 and connected to the BNC connector on the other side through a test cable, wherein the impedance network is composed of R4, R5 and C2 which are connected in series and in parallel.
Referring to fig. 2 and 6, the signal conditioning unit S1 is shown, and the exemplary embodiment adopted in the present invention has 16 collected signals, where 8 voltage paths and 8 corresponding current paths each correspond to one signal conditioning unit S1, and the signal conditioning units in the present invention should correspond to 16 paths. The signal conditioning unit is structurally described in the embodiment, and different device parameters are adopted for different corresponding acquired signals in the actual implementation process. After the signal passes through the voltage or current sensor, the signal passes through a BNC head to be connected to a matching impedance network U06 of the signal conditioning unit S1, and the impedance relation of the signal can be normally acquired only after being matched with the impedance network of the voltage or current sensor. The active filter network U07 is connected to the matching impedance network U06, the active filter network U07 filters signals, and after interference and clutter signals are filtered, the active filter network U08 is connected to the active operational amplifier network U08 for secondary processing. The amplitude and the size of the processed signal are in a certain proportional relation with the original signal, and the amplitude of the processed signal does not exceed the maximum limit value of the back-end circuit.
Fig. 2 and 7 show that the signal acquisition unit S2 and the signal processed by the signal conditioning unit S1 are connected to the signal protection network U09 of the signal acquisition unit S2, so as to further protect the amplitude of the signal and prevent the operation of the back-end circuit from being damaged. The signal protection network U09 is connected to the high-speed ADC acquisition unit U10, converts analog signals into digital signals, and has acquisition speed meeting system requirements and synchronous acquisition requirements.
Referring to fig. 2 and 8, the signal processing unit S3 is shown, and the signal is converted into a digital signal after passing through the signal acquisition unit S2, and processed by the digital signal processor CPUU11 in the signal processing unit S3. The processed data can be displayed and analyzed through the peripheral unit S5, and can also be stored in and out of the storage unit U13 in the signal processing unit S3. The logic control unit U12 controls synchronous clock and bus communication to realize data synchronism.
According to another aspect of the present invention, there is provided a data acquisition and analysis method for an amphibious aircraft power supply system, wherein the characteristic data of a power supply system of a flight measurement aircraft is acquired and analyzed by using the data acquisition device of the power supply system, and with reference to fig. 9, the data acquisition and analysis method includes the following steps:
step S1: equipment initialization;
step S2: setting equipment parameters;
step S3: starting data acquisition;
step S4: acquiring collected data;
step S5: data processing and analysis can be performed according to the requirement on the measurement type analysis of data access, namely, the data can be analyzed in the time domain, for example, the data is analyzed to obtain effective values, maximum values, average values, peak-to-peak values and the like, and the data can be analyzed in the frequency domain, for example, the data is analyzed to obtain values of harmonic content, crest coefficients, alternating current and direct current distortion and the like.
Step S6: graphical display and presentation of data, where historical data can be queried by review, or stored (automatically or manually);
step S7: and circularly acquiring data to realize real-time updating of the data.
From the above description, it can be seen that the above-described embodiments of the present invention achieve the following technical effects:
the technical scheme of the invention enables parameters of the power supply system of the amphibious aircraft to be collected in a unified manner, has real-time performance, and can be used for displaying, analyzing, storing and the like data.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The device for detecting and analyzing the working characteristics of the power supply system of the amphibious aircraft is characterized by comprising a hardware device and a software system:
the hardware device includes: the system comprises voltage sensors (S001-S008) for testing, non-contact current sensors (S009-S016), a signal conditioning unit S1, a signal acquisition unit S2, a signal processing unit S3, a system power supply unit S4, an external unit S5 and a bus controller S6; 8 paths of the voltage sensor (S001-S008) and 8 paths of the non-contact current sensor (S009-S016) are connected with the signal conditioning unit S1 through 16 paths of NBC interfaces; the signal conditioning unit S1 is connected to the signal acquisition unit S2, namely the signal conditioning unit S1 normalizes the signal and transmits the signal to the signal acquisition unit S2; the signal acquisition unit S2 is connected to the signal processing unit S3, namely the signal acquisition unit S2 converts the analog signal into a digital signal and transmits the digital signal to the signal processing unit S3, and the signal processing unit S3 processes, analyzes, stores and displays the digital signal; the signal processing unit S3 is connected to the system power supply unit S4 to manage and control the system power supply, the power supply of the whole system is provided by the commercial power conversion direct current AC/DC power supply U14 of the system power supply unit S4, and the backup battery U15 supports equipment to operate without an external power supply; the signal processing unit S3 is also connected to the peripheral unit S5 and the bus controller S6;
the software system mainly realizes the analysis and processing of system data: the data processing and analyzing software can perform waveform display and online analysis on the acquired data, judge whether the airplane power supply system has abnormality in the operation process through the data, set a threshold value to alarm the real-time data abnormality and store the data for post analysis.
2. The amphibious aircraft power system working characteristic detection and analysis device as claimed in claim 1, wherein the voltage sensors (S001-S008) are passive sensors, and a fixed capacitor Cin1 and a fixed resistor Rin1 form a resistance-capacitance impedance network, which can detect a direct current voltage and an alternating current voltage; ccom1 is an adjustable capacitor used for attenuator compensation, and the compensation effect is obtained by adjusting the capacitance value.
3. The device for detecting and analyzing the operating characteristics of the power supply system of the amphibious aircraft according to claim 1, wherein the voltage sensors (S001-S008) are divided into 8 groups, namely S001-S008, and can be configured into two forms of direct current collection and alternating current collection according to requirements; wherein S001-S006 are DC voltage sensors, and S007 and S008 are AC voltage sensors.
4. The amphibious aircraft power system operating characteristic detecting and analyzing apparatus as defined in claim 1, wherein the non-contact current sensors (S009-S016) are divided into dc current sensors and ac current sensors; s009 to S014 are dc current sensors, and S015 and S016 are ac current sensors.
5. The device for detecting and analyzing the operating characteristics of the power supply system of the amphibious aircraft as claimed in claim 1, wherein the non-contact type direct current sensor (S009-S016) adopts an active sensor and mainly comprises an open type hall sensor U01, a signal operational amplifier network U02 and an impedance network to form U03, a micro-current signal collected by the hall sensor U01 is input into a signal amplifier network U02, the signal amplifier network U02 converts the absorbed current into a voltage signal and connects the voltage signal to the impedance network U03, and the voltage of the current signal is realized and then the voltage signal is output to other circuit units at the rear end. The signal of the direct current can be collected under the condition of not disconnecting the current.
6. The amphibious aircraft power system operating characteristic detecting and analyzing device as claimed in claim 1, wherein the non-contact type alternating current sensor is mainly composed of an open type electromagnetic current transformer (U04) and an impedance network (U05); the iron core of the straight-through current transformer is made into a movable opening and is in a pincer shape.
7. The device for detecting and analyzing the operating characteristics of the power supply system of an amphibious aircraft according to claim 1, wherein signals of the voltage sensor and the non-contact current sensor are processed and then connected with a signal conditioning unit S1 through a BNC interface.
8. The device for detecting and analyzing the operating characteristics of the power supply system of the amphibious aircraft as claimed in claim 1, wherein a matched impedance network U06 consisting of Ro1 and Co1 is arranged at the front end of the signal conditioning unit S1, and an active filtering U07 and an active operational amplifier U08 are adopted at the rear end to filter and normalize the amplitude of the acquired signals; the rear end is connected to a signal acquisition unit S2, the normalized signal is transmitted to the signal acquisition unit, and the signal acquisition unit converts the normalized analog signal into a digital signal by a signal protection unit U09 and a high-speed ADC acquisition unit U10.
9. The amphibious aircraft power system working characteristic detection and analysis device as claimed in claim 1, wherein the signal acquisition unit S2 is connected to the signal processing unit S3, and the signal processing unit S3 is composed of a digital signal processor CPU, a logic control unit U12 and a storage unit U13; the signal processing unit S3 is used to process the acquired and converted digital signals, analyze, store, display the data, and control the system signals to keep synchronous in the same time coordinate system.
10. The device for detecting and analyzing the operating characteristics of the power supply system of the amphibious aircraft according to claim 1, wherein the bus control unit S6 is connected with an upper computer or forms a network with other equipment through a serial port or a network interface to transmit data.
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|---|---|---|---|---|
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| CN105334471A (en) * | 2015-10-21 | 2016-02-17 | 中国人民解放军海军航空工程学院青岛校区 | Portable airplane power supply quality test system and method |
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| CN113104232A (en) * | 2021-03-25 | 2021-07-13 | 沈阳航空航天大学 | Ground test state monitoring system and monitoring method for airplane power supply system |
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2021
- 2021-10-18 CN CN202111213924.6A patent/CN113985307A/en active Pending
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| CN105068038A (en) * | 2015-08-12 | 2015-11-18 | 国网辽宁省电力有限公司朝阳供电公司 | Operation and maintenancedevice of intelligent ammeter |
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| CN109683588A (en) * | 2018-12-18 | 2019-04-26 | 西北工业大学 | Large Civil Aircraft power supply-distribution system ground experiment integrated verification test platform framework |
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