CN107554805B - Flight state monitoring equipment - Google Patents
Flight state monitoring equipment Download PDFInfo
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- CN107554805B CN107554805B CN201710763827.1A CN201710763827A CN107554805B CN 107554805 B CN107554805 B CN 107554805B CN 201710763827 A CN201710763827 A CN 201710763827A CN 107554805 B CN107554805 B CN 107554805B
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Abstract
The invention relates to a flight state monitoring device which comprises a base, a power supply module and a crash protection assembly, wherein the power supply module is connected with the base; the base comprises a sound pick-up, a test button, an erasing button, 3 status indicator lamps, a power status indicator lamp, 2 monitoring equipment support legs, 2 1553 connectors, an Ethernet maintenance connector and a data management module; wherein 3 status indicator lamps are used for instructing flight data record state, flight audio data record state and aircraft video data record state respectively, and 3 status indicator lamps are bright green when supervisory equipment normal operation, and 3 status indicator lamps are bright red when supervisory equipment work is unusual. The invention integrates a sound pick-up, a test button and an erasing button inside, and the functions which need to be finished by two devices originally are finished by one device; the three-axis accelerometer is integrated inside the self-collecting device, so that the self-collecting device can automatically collect three-axis acceleration and complete recording.
Description
Technical Field
The invention belongs to the technical field of avionics, and relates to flight state monitoring equipment, in particular to flight state monitoring equipment.
Background
With the continuous opening of low-altitude fields in various regions of China, the light and small-sized general aircrafts are gradually coming into a big development period. However, due to the immaturity of the domestic low-altitude monitoring and management technology, great pressure is brought to the industrial supervision of civil aviation and the operation control of companies. Therefore, the improvement of the safety guarantee capability of general aviation is very important, and the invention provides the light and small flight state monitoring equipment suitable for the light and general aircraft, which is used for acquiring and recording the relevant information of the general aircraft and constructing a low-altitude monitoring and flight service scheme with low cost and easy deployment for the general aviation through the recorded data.
The invention content is as follows:
the purpose of the invention is as follows: the invention provides a flight state monitoring device, in particular to a light and small flight state monitoring device suitable for a light general aircraft, which is used for acquiring and recording related information of the general aircraft and constructing a low-altitude monitoring and flight service scheme with low cost and easy deployment for the general aviation through recorded data.
The technical scheme is as follows:
the light and small flight state monitoring equipment comprises a base 3, a power supply module 2 and a crash protection component 1, wherein the power supply module 2 is connected with the base 3, and the base 3 is connected with the crash protection component 1;
the base 3 comprises a sound pick-up 31, a test button 32, an erasing button 33, 3 status indicator lamps 34, a power status indicator lamp 35, 2 monitoring equipment legs 36, 2 1553 connectors 37, an Ethernet maintenance connector 38 and a data management module 39; the 3 status indicator lamps 34 are respectively used for indicating a flight data recording status, a flight audio data recording status and an airplane video data recording status, when the monitoring equipment works normally, the 3 status indicator lamps are on green, and when the monitoring equipment works abnormally, the 3 status indicator lamps are on red;
the power module 2 comprises a power box 21, a power box cover plate 22 and a power plate 23; the power supply board 23 is arranged inside the power supply box 21;
the power box cover plate is provided with a micro rectangular connector module, the micro rectangular connector module is used for signal interaction with airborne electronic equipment, the micro rectangular connector module is further connected with an airborne power supply, the micro rectangular connector module comprises a micro rectangular connector 2 plug, and the micro rectangular connector 2 plug and a micro rectangular connector socket form a micro rectangular connector 2313;
the power panel 23 comprises a rectangular connector 2301, a power voting circuit 2302, an AC/DC conversion circuit 2303, a power lightning protection circuit 2312, a spike suppression circuit 2304, an overvoltage protection circuit 2305, a power filter circuit 2306, a DC-DC conversion circuit 2307, a power boost circuit 2308, a power down indication circuit 2309, an energy storage circuit 2310, an external signal lightning protection circuit 2311 and a micro rectangular connector socket.
Further, the power panel 23 includes a rectangular connector 2301, a power voting circuit 2302, an AC/DC conversion circuit 2303, a power lightning protection circuit 2312, a spike suppression circuit 2304, an overvoltage protection circuit 2305, a power filter circuit 2306, a DC-DC conversion circuit 2307, a power boost circuit 2308, a power down indication circuit 2309, an energy storage circuit 2310, an external signal lightning protection circuit 2311, and a micro rectangular connector socket.
The micro rectangular connector socket, the power supply voting circuit, the peak suppression circuit 2304, the overvoltage protection circuit 2305, the power supply filter circuit 2306, the DC-DC conversion circuit 2307 and the rectangular connector 2301 are connected in sequence, and transition of a power supply from the micro rectangular connector socket to the rectangular connector is realized;
two paths of connection are formed between the socket of the micro rectangular connector and the power voting circuit, one path is connected with the micro rectangular connector 2313 through the AC/DC conversion circuit 2303, an onboard power supply is converted into 28VDC and then input into the power voting circuit 2302, and the other path is directly connected with the power voting circuit through the micro rectangular connector; voting is carried out on two paths of power supplies, and the power supply voting circuit outputs the power supplies to the peak suppression circuit 2304;
the power supply lightning protection circuit protects the AC/DC conversion circuit and the power supply voting circuit;
the power supply filter circuit is also connected in series with the power supply booster circuit and the energy storage circuit and is connected to the rectangular connector;
the DC-DC conversion circuit is also connected in series with a power failure indication circuit and connected to the rectangular connector;
and a signal lightning protection circuit is connected between the micro rectangular connector and the rectangular connector in parallel.
In particular, the crash protection assembly 1 is connected to a data management module 39 to accomplish data reception and writing, and data protection.
7. The data management module 39 is connected with the sound pickup 31 through the audio signal conditioning module 3907, meanwhile, the audio signal conditioning module 3907 is further connected with the microprocessor connector 2301, receives externally input voice signals, conditions two paths of audio signals and inputs the conditioned audio signals to the audio coding and decoding circuit 3908, the audio coding and decoding circuit 3908 completes coding of the audio signals and outputs the coded audio signals to the FPGA circuit 3902, and the coded audio signals are output to the PowerPC microprocessor circuit 3901 through the FPGA circuit 3902; the video 1 conversion circuit 3903 is connected with the microprocessor connector 2301, receives external PAL video signals, converts the video signals and outputs the video signals to the video coding and decoding chip 3904, and the video coding and decoding circuit 3904 codes the video signals and outputs the video signals to the FPGA circuit 3902 and the PowerPC microprocessor circuit 3901 through the FPGA circuit 3902; the video 2 conversion circuit 3905 is connected with the microprocessor connector 2301, receives external PAL video signals, converts the video signals and outputs the video signals to the video coding and decoding chip 3906, and the video coding and decoding circuit 3906 codes the video signals and outputs the video signals to the FPGA circuit 3902 and the PowerPC microprocessor circuit 3901 through the FPGA circuit 3902; the ARINC-429 interface chip 3909 is connected with the micro-rectangular connector 2301, receives externally input data chain data, UTC time and flight position information, outputs the data chain data, UTC time and flight position information to the FPGA circuit 3902, outputs the data chain data, UTC time and flight position information to the PowerPC microprocessor circuit 3901 through the FPGA circuit, and outputs state information to the micro-rectangular connector 2301 to complete state information output; the ARINC-717 interface circuit 3929 is connected with the micro-rectangular connector 2301, receives externally input ARINC-717 data, outputs the ARINC-717 data to the FPGA circuit 3902, and outputs the ARINC-717 data to the PowerPC microprocessor circuit 3901 through the FPGA circuit; the isolation transformer 3910 is connected with the micro rectangular connector 2301, receives flight data sent by the outside through an Ethernet interface, and outputs the flight data to the PowerPC microprocessor circuit 3901 through an Ethernet physical layer interface chip 3913; the isolation transformer 3911 is connected with the micro rectangular connector 2301, receives external software loading information sent through an Ethernet interface, and outputs the software loading information to the PowerPC microprocessor circuit 3901 through an Ethernet physical layer interface chip 3913; the isolation transformer 3912 is connected to the ethernet for the connector 38, receives maintenance information sent by the ground detection equipment, and outputs the maintenance information to the PowerPC microprocessor 3901 through the ethernet physical layer interface chip 3913, and the ethernet physical layer interface chip 3913 is further connected to the clock circuit 3914; the reset circuit 3915 is connected to the micro rectangular connector 2301 and outputs the reset circuit to the PowerPC microprocessor circuit 3901; the switching value acquisition circuit 3926 is respectively connected with the erasing button 33 and the testing button 32, receives the switching values output by the erasing button 33 and the testing button 32, and outputs the switching value signals to the PowerPC microprocessor circuit 3901; the indicator lamp driving circuit 3927 is connected to the PowerPC microprocessor circuit 3901, receives the status signals output by the PowerPC microprocessor circuit 3901, and is connected to the 3 product status indicator lamps 34 and the power status indicator lamp 35, respectively, for controlling the 3 product status indicator lamps and the power status indicator lamp. The PowerPC microprocessor circuit 3901 is also respectively connected with a clock circuit 3917, a program memory 3918, a memory circuit 3920 and a Beijing time acquisition circuit 3922 circuit; the RS-422 interface circuit 3923 and the RS-232 interface circuit 3924 are respectively connected with the micro-rectangular connector 2301 and the PowerPC microprocessor circuit 3901, the MIL-STD-1553 data acquisition circuit 3928 is respectively connected with the 1553 connector 37 and the PowerPC microprocessor circuit 3901, and the triaxial accelerometer 3916 is connected with the PowerPC microprocessor circuit 3901 and outputs acquired transverse, longitudinal and normal triaxial image acceleration signals to the PowerPC microprocessor circuit 3901. The PowerPC microprocessor circuit 3901 is connected with a SATA interface circuit 3921, is connected with a storage board connector 11, and is connected with the crash protection assembly 1 through the storage board connector 11; the power conversion circuit 3925 is connected to the power board 23 through the micro rectangular connector 2301, receives 5VDC output from the power board 23, and converts the VDC into power required by each circuit module in the data management module;
the crash protection component comprises 8 memory chips, wherein flight data (Ethernet interface), data chain data, voice data, cabin sound data, video data 1, video data 2, MIL-STD-1553 data, ARINC-717 and self-collected flight data are respectively stored from the chip 1 to the chip 7;
the recorded data comprises a data packet header and a data packet body;
the data packet header in the data storage format includes a start packet flag, a data type, a channel ID, a data length, a frame number, a data packet flag, a relative time counter, and a packet header checksum.
The data packet body in the data storage format comprises UTC time, Beijing time, fault words, product numbers, airplane numbers and data.
Has the advantages that:
a) the invention integrates a sound pick-up, a test button and an erasing button inside, and the functions which need to be finished by two devices originally are finished by one device;
b) the three-axis accelerometer is integrated inside the self-collecting device, so that the three-axis acceleration can be collected and recorded;
c) the invention has 1-channel ARINC-429 bus to obtain UTC time from an onboard maintenance system, and is also provided with a Beijing time acquisition circuit for acquiring Beijing time, wherein the Beijing time and the UTC time are recorded in each data frame, so that multi-channel data synchronization is convenient to carry out during data recovery;
d) the invention has 3-path high-speed Ethernet interfaces, and 1 path is used for receiving flight data; 1 path for software loading; 1 road is used for ground maintenance;
e) the invention can supply power by 115AC and 28VDC simultaneously, and can also supply power by two power supplies independently; the power supply adaptability of the product is enriched, and the universality of the product is improved, so that the product can be commonly used in more airplanes;
f) the invention adds a lightning protection circuit design to the external alternating current interfaces, and can protect and resist the indirect effect of lightning.
Drawings
FIG. 1 is a block diagram of the components of the present invention.
Fig. 2 is a block diagram of the base assembly of the present invention.
FIG. 3 is a schematic view of the power module and crash protection assembly of the present invention.
Fig. 4 is a schematic block diagram of the power module of the present invention.
FIG. 5 is a block diagram of the data management module of the present invention.
The device comprises a base-3, a power supply module-2, a crash protection component-1, a sound pick-up-31, a test button-32, an erasing button-33, a product state indicator lamp-34, a power supply state indicator lamp-35, a supporting angle-36, a 1553 connector-37, an Ethernet maintenance connector-38, a data management module-39, a power supply box-21, a power supply box cover plate-22, a power supply plate-23, a micro rectangular connector module-2201, a storage plate connection-11, a rectangular connector-2301, a power supply voting circuit-2302, an AC/DC conversion circuit-2303, a power supply lightning protection circuit-2312, a peak suppression circuit-2304, an overvoltage protection circuit-2305, a power supply filter circuit-2306, a DC-DC conversion circuit-2307, a power supply boosting circuit-2308, a power failure indication circuit-2309, an energy storage circuit-2310, an external signal lightning protection circuit-2311, a micro rectangular connector-2313, An audio signal conditioning module-3907, an audio coding and decoding circuit-3908, an FPGA circuit-3902, a PowerPC microprocessor circuit-3901, a video 1 conversion circuit-3903, a video coding and decoding chip-3904, a video 2 conversion circuit-3905, a video coding and decoding chip-3906, an ARINC-429 interface chip-3909, an ARINC-717 interface circuit-3929, an isolation transformer-3910, an Ethernet physical layer interface chip-3913, an isolation transformer-3912, an isolation transformer-3911 and a clock circuit-3914; the circuit comprises a reset circuit-3915, a switching value acquisition circuit-3926, an indicator lamp driving circuit-3927, a clock circuit-3917, a program memory-3918, an internal memory circuit-3920 and a Beijing time acquisition circuit-3922; RS-422 interface circuit-3923, RS-232 interface circuit-3924, MIL-STD-1553 data acquisition circuit-3928, triaxial accelerometer-3916, SATA interface circuit-3921 and power conversion circuit-3925.
Detailed Description
The present invention is described in further detail below with reference to the attached drawings.
1. As shown in fig. 1-3, a light and small flight status monitoring device comprises a base 3, a power module 2 and a crash protection component 1, wherein the power module 2 is connected with the base 3, and the base 3 is connected with the crash protection component 1;
the base 3 comprises a sound pick-up 31, a test button 32, an erasing button 33, 3 status indicator lamps 34, a power status indicator lamp 35, 2 monitoring equipment legs 36, 2 1553 connectors 37, an Ethernet maintenance connector 38 and a data management module 39; the 3 status indicator lamps 34 are respectively used for indicating a flight data recording status, a flight audio data recording status and an airplane video data recording status, when the monitoring equipment works normally, the 3 status indicator lamps are on green, and when the monitoring equipment works abnormally, the 3 status indicator lamps are on red;
the power module 2 comprises a power box 21, a power box cover plate 22 and a power plate 23; the power supply board 23 is arranged inside the power supply box 21;
the power box cover plate is provided with a micro rectangular connector module, the micro rectangular connector module is used for signal interaction with airborne electronic equipment, the micro rectangular connector module is further connected with an airborne power supply, the micro rectangular connector module comprises a micro rectangular connector 2 plug, and the micro rectangular connector 2 plug and a micro rectangular connector socket form a micro rectangular connector 2313;
the power panel 23 comprises a rectangular connector 2301, a power voting circuit 2302, an AC/DC conversion circuit 2303, a power lightning protection circuit 2312, a spike suppression circuit 2304, an overvoltage protection circuit 2305, a power filter circuit 2306, a DC-DC conversion circuit 2307, a power boost circuit 2308, a power down indication circuit 2309, an energy storage circuit 2310, an external signal lightning protection circuit 2311 and a micro rectangular connector socket.
As shown in fig. 2, the base 3 is composed of a sound pickup 31, a test button 32, an erase button 33, 3 product status indicator lamps 34, a power status indicator lamp 35, 2 supporting angles 36, 2 1553 connectors 37, an ethernet maintenance connector 38 and a data management module 39 installed inside, wherein the 3 product status indicator lamps 34 are respectively used for indicating a flight data recording status, an audio data recording status and a video data recording status, and when the type of data is in normal recording, the status lamps are green and are red when abnormal. The power state indicator lamp is used for indicating whether the product is in a normal power-on state or not, if the product is powered on, the state lamp is lightened, and if the product is not powered on, the state lamp is extinguished;
in particular, the power strip 23 includes a rectangular connector 2301, a power voting circuit 2302, an AC/DC conversion circuit 2303, a power lightning protection circuit 2312, a spike suppression circuit 2304, an overvoltage protection circuit 2305, a power filter circuit 2306, a DC-DC conversion circuit 2307, a power boost circuit 2308, a power down indication circuit 2309, an energy storage circuit 2310, an external signal lightning protection circuit 2311, and a micro rectangular connector receptacle.
The micro rectangular connector socket, the power supply voting circuit, the peak suppression circuit 2304, the overvoltage protection circuit 2305, the power supply filter circuit 2306, the DC-DC conversion circuit 2307 and the rectangular connector 2301 are connected in sequence, and transition of a power supply from the micro rectangular connector socket to the rectangular connector is realized;
two paths of connection are formed between the socket of the micro rectangular connector and the power voting circuit, one path is connected with the micro rectangular connector 2313 through the AC/DC conversion circuit 2303, an onboard power supply is converted into 28VDC and then input into the power voting circuit 2302, and the other path is directly connected with the power voting circuit through the micro rectangular connector; voting is carried out on two paths of power supplies, and the power supply voting circuit outputs the power supplies to the peak suppression circuit 2304;
the power supply lightning protection circuit protects the AC/DC conversion circuit and the power supply voting circuit;
the power supply filter circuit is also connected in series with the power supply booster circuit and the energy storage circuit and is connected to the rectangular connector;
the DC-DC conversion circuit is also connected in series with a power failure indication circuit and connected to the rectangular connector;
and a signal lightning protection circuit is connected between the micro rectangular connector and the rectangular connector in parallel.
As shown in fig. 5, the data management module 39 is connected to the sound pickup 31 through the audio signal conditioning module 3907, and meanwhile, the audio signal conditioning module 3907 is further connected to the microprocessor connector 2301, receives an externally input voice signal, conditions two paths of audio signals and inputs the conditioned audio signals to the audio codec circuit 3908, and the audio codec circuit 3908 encodes the audio signals and outputs the encoded audio signals to the FPGA circuit 3902, and outputs the encoded audio signals to the PowerPC microprocessor circuit 3901 through the FPGA circuit 3902; the video 1 conversion circuit 3903 is connected with the microprocessor connector 2301, receives external PAL video signals, converts the video signals and outputs the video signals to the video coding and decoding chip 3904, and the video coding and decoding circuit 3904 codes the video signals and outputs the video signals to the FPGA circuit 3902 and the PowerPC microprocessor circuit 3901 through the FPGA circuit 3902; the video 2 conversion circuit 3905 is connected with the microprocessor connector 2301, receives external PAL video signals, converts the video signals and outputs the video signals to the video coding and decoding chip 3906, and the video coding and decoding circuit 3906 codes the video signals and outputs the video signals to the FPGA circuit 3902 and the PowerPC microprocessor circuit 3901 through the FPGA circuit 3902; the ARINC-429 interface chip 3909 is connected with the micro-rectangular connector 2301, receives externally input data chain data, UTC time and flight position information, outputs the data chain data, UTC time and flight position information to the FPGA circuit 3902, outputs the data chain data, UTC time and flight position information to the PowerPC microprocessor circuit 3901 through the FPGA circuit, and outputs state information to the micro-rectangular connector 2301 through the ARINC-429 interface chip 3909 to complete state information output; the ARINC-717 interface circuit 3929 is connected with the micro-rectangular connector 2301, receives externally input ARINC-717 data, outputs the ARINC-717 data to the FPGA circuit 3902, and outputs the ARINC-717 data to the PowerPC microprocessor circuit 3901 through the FPGA circuit; the isolation transformer 3910 is connected with the micro rectangular connector 2301, receives flight data sent by the outside through an Ethernet interface, and outputs the flight data to the PowerPC microprocessor circuit 3901 through an Ethernet physical layer interface chip 3913; the isolation transformer 3911 is connected with the micro rectangular connector 2301, receives external software loading information sent through an Ethernet interface, and outputs the software loading information to the PowerPC microprocessor circuit 3901 through an Ethernet physical layer interface chip 3913; the isolation transformer 3911 is connected to the ethernet for the connector 38, receives maintenance information sent by the ground detection equipment, and outputs the maintenance information to the PowerPC microprocessor 3901 through the ethernet physical layer interface chip 3913, and the ethernet physical layer interface chip 3913 is further connected to the clock circuit 3914; the reset circuit 3915 is connected to the micro rectangular connector 2301 and outputs the reset circuit to the PowerPC microprocessor circuit 3901; the switching value acquisition circuit 3926 is respectively connected with the erasing button 33 and the testing button 32, receives the switching values output by the erasing button 33 and the testing button 32, and outputs the switching value signals to the PowerPC microprocessor circuit 3901; the indicator lamp driving circuit 3927 is connected to the PowerPC microprocessor circuit 3901, receives the status signals output by the PowerPC microprocessor circuit 3901, and is connected to the 3 product status indicator lamps 34 and the power status indicator lamp 35, respectively, for controlling the 3 product status indicator lamps and the power status indicator lamp. The PowerPC microprocessor circuit 3901 is also respectively connected with a clock circuit 3917, a program memory 3918, a memory circuit 3920 and a Beijing time acquisition circuit 3922 circuit; the RS-422 interface circuit 3923 and the RS-232 interface circuit 3924 are respectively connected with the micro-rectangular connector 2301 and the PowerPC microprocessor circuit 3901, the MIL-STD-1553 data acquisition circuit 3928 is respectively connected with the 1553 connector 37 and the PowerPC microprocessor circuit 3901, and the triaxial accelerometer 3916 is connected with the PowerPC microprocessor circuit 3901 and outputs acquired transverse, longitudinal and normal triaxial image acceleration signals to the PowerPC microprocessor circuit 3901. The PowerPC microprocessor circuit 3901 is connected with a SATA interface circuit 3921, is connected with a storage board connector 11, and is connected with the crash protection assembly 1 through the storage board connector 11; the power conversion circuit 3925 is connected to the power board 23 through the micro rectangular connector 2301, receives 5VDC output from the power board 23, and converts the VDC into power required by each circuit module in the data management module;
the crash protection component comprises 8 memory chips, wherein flight data (Ethernet interface), data chain data, voice data, cabin sound data, video data 1, video data 2, MIL-STD-1553 data, ARINC-717 and self-collected flight data are respectively stored from the chip 1 to the chip 7.
Claims (3)
1. A flight state monitoring device comprises a base, a power supply module and a crash protection assembly, wherein the power supply module is connected with the base, and the base is connected with the crash protection assembly;
the base comprises a sound pick-up, a test button, an erasing button, 3 status indicator lamps, a power status indicator lamp, 2 monitoring equipment support legs, 2 1553 connectors, an Ethernet maintenance connector and a data management module; the monitoring equipment comprises 3 status indicator lamps, a monitoring system and a monitoring system, wherein the 3 status indicator lamps are respectively used for indicating a flight data recording state, a flight audio data recording state and an airplane video data recording state, when the monitoring equipment works normally, the 3 status indicator lamps are in green, and when the monitoring equipment works abnormally, the 3 status indicator lamps are in red;
the power supply module comprises a power supply box, a power supply box cover plate and a power supply plate; the power panel is arranged inside the power box;
the power box cover plate is provided with a micro rectangular connector module, the micro rectangular connector module is used for signal interaction with airborne electronic equipment, the micro rectangular connector module is also connected with an airborne power supply, the micro rectangular connector module comprises a micro rectangular connector plug, and the micro rectangular connector plug and a micro rectangular connector socket form a micro rectangular connector;
the power panel comprises a rectangular connector, a power voting circuit, an AC/DC conversion circuit, a power lightning protection circuit, a peak suppression circuit, an overvoltage protection circuit, a power filter circuit, a DC-DC conversion circuit, a power booster circuit, a power failure indication circuit, an energy storage circuit, an external signal lightning protection circuit and a micro rectangular connector socket.
2. A flight condition monitoring apparatus according to claim 1, wherein:
the micro rectangular connector socket, the power supply voting circuit, the peak suppression circuit, the overvoltage protection circuit, the power supply filter circuit, the DC-DC conversion circuit and the rectangular connector are sequentially connected, so that transition of a power supply from the micro rectangular connector socket to the rectangular connector is realized;
two paths of connection are formed between the socket of the micro rectangular connector and the power supply voting circuit, one path is connected with the micro rectangular connector through an AC/DC conversion circuit, an airborne power supply is converted into 28VDC and then input into the power supply voting circuit, and the other path is directly connected with the power supply voting circuit through the micro rectangular connector; voting two paths of power supplies, and outputting the power supply voting circuit to a peak suppression circuit;
the power supply lightning protection circuit protects the AC/DC conversion circuit and the power supply voting circuit;
the power supply filter circuit is also connected in series with the power supply booster circuit and the energy storage circuit and is connected to the rectangular connector;
the DC-DC conversion circuit is also connected in series with a power failure indication circuit and connected to the rectangular connector;
and a signal lightning protection circuit is connected between the micro rectangular connector and the rectangular connector in parallel.
3. A flight status monitoring apparatus according to claim 1 or 2, wherein: the crash protection component is connected with the data management module to complete data receiving and writing and data protection.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710763827.1A CN107554805B (en) | 2017-08-30 | 2017-08-30 | Flight state monitoring equipment |
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| CN201710763827.1A CN107554805B (en) | 2017-08-30 | 2017-08-30 | Flight state monitoring equipment |
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| CN107554805A CN107554805A (en) | 2018-01-09 |
| CN107554805B true CN107554805B (en) | 2020-06-09 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107807574B (en) * | 2017-11-02 | 2020-06-02 | 中电科技集团重庆声光电有限公司 | Multifunctional interface circuit based on integrated packaging |
| CN109342761B (en) * | 2018-09-11 | 2021-10-12 | 陕西千山航空电子有限责任公司 | Rotor wing rotating speed monitoring processor |
| FR3087909B1 (en) * | 2018-10-25 | 2022-12-16 | Airbus Operations Sas | ACQUISITION SYSTEM FOR AIRCRAFT COMPRISING AN AVIONIC BAY AND AT LEAST ONE RECORDING DEVICE, AND ASSOCIATED AIRCRAFT |
| CN109557339B (en) * | 2018-11-16 | 2021-03-26 | 陕西千山航空电子有限责任公司 | Triaxial accelerometer and impact detection switch |
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| US20160052642A1 (en) * | 2014-08-25 | 2016-02-25 | Honeywell International Inc. | Aircraft electric taxi health management system and method |
| US20180079533A1 (en) * | 2016-09-16 | 2018-03-22 | Williams International Co., L.L.C. | Aircraft engine illumination and diagnostic system |
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| CN204102204U (en) * | 2014-10-28 | 2015-01-14 | 陕西千山航空电子有限责任公司 | A kind of civilian small-sized register |
| CN104331952A (en) * | 2014-10-28 | 2015-02-04 | 陕西千山航空电子有限责任公司 | Wireless cache recorder |
| CN104331951A (en) * | 2014-10-28 | 2015-02-04 | 陕西千山航空电子有限责任公司 | Light-weight and small-size recorder |
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