CN107554805A - A kind of state of flight monitoring device - Google Patents
A kind of state of flight monitoring device Download PDFInfo
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- CN107554805A CN107554805A CN201710763827.1A CN201710763827A CN107554805A CN 107554805 A CN107554805 A CN 107554805A CN 201710763827 A CN201710763827 A CN 201710763827A CN 107554805 A CN107554805 A CN 107554805A
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Abstract
The present invention relates to a kind of state of flight monitoring device, including base, power module and the protection component that crashes, wherein, the power module connect base, base is connected with the protection component that crashes；Base includes sound pick-up, testing button, erasing button, 3 status indicator lamps, indicator of the power supply status, 2 monitoring device legs, and 2 1553 connectors, Ethernets safeguard connector and data management module；Wherein 3 status indicator lamps, it is respectively used to indicate flight data recording state, flight audio data recording state and aircraft video data recording state, 3 status indicator lamp bright greens when monitoring device is working properly, 3 status indicator lamp shiny reds when monitoring device operation irregularity.The present invention has been internally integrated sound pick-up, testing button and erasing button, and the original function of needing two equipment to complete is completed by an equipment；The present invention has been internally integrated three axis accelerometer, can be from collection 3-axis acceleration, and completes to record.
Description
Technical field
The invention belongs to avionics field, is related to a kind of state of flight monitoring device, particularly a kind of flight shape
State monitoring device.
Background technology
With opening successively for China various regions low latitude field, when small-sized all purpose aircraft is just progressively welcoming a great development
Phase.But because the country is to the immature of low-altitude surveillance and administrative skill, to the supervision of civil aviaton and the operation control of company
Bring enormous pressure.Therefore, it is particularly significant to improve General Aviation safety assurance ability, is applied to the invention provides one kind light
The small-sized state of flight monitoring device of type all purpose aircraft, for acquisition and recording all purpose aircraft relevant information, passes through and is remembered
The data of record, for a kind of low cost of General Aviation structure, the low-altitude surveillance and operational service scheme easily disposed.
The content of the invention：
Goal of the invention：It is a kind of suitable for light-duty all purpose aircraft the invention provides a kind of state of flight monitoring device
Small-sized state of flight monitoring device, it is general by recorded data for acquisition and recording all purpose aircraft relevant information
A kind of low cost of aviation structure, the low-altitude surveillance and operational service scheme easily disposed.
Technical scheme：
A kind of small-sized state of flight monitoring device, including base 3, power module 2 and the protection component 1 that crashes are provided, its
In, the connect base 3 of power module 2, base 3 is connected with the protection component 1 that crashes；
Base 3 includes sound pick-up 31, testing button 32,33,3 status indicator lamps 34 of erasing button, power supply status instruction
35,2, lamp monitoring device leg 36,2 1553 connectors 37, Ethernet safeguard connector 38 and data management module 39；Its
In 3 status indicator lamps 34, be respectively used to indicate flight data recording state, flight audio data recording state and aircraft video
Data-recording status, 3 status indicator lamp bright greens when monitoring device is working properly, when monitoring device operation irregularity 3
Status indicator lamp shiny red；
The power module 2 includes power pack 21, power supply lid plate 22 and power panel 23；Power panel 23 is arranged on power pack
Inside 21；
Micro- rectangular connector module is installed, micro- rectangular connector module is used for and air environment on power supply lid plate
Signal interaction, micro- rectangular connector module are also connected with airborne power supply, and micro- rectangular connector module is inserted including micro- rectangular connector 2
Head, micro- plug of rectangular connector 2 form micro- rectangular connector 2313 with micro- rectangular connector socket；
Power panel 23, which includes rectangular connector 2301, power supply voting circuit 2302, AC/DC change-over circuits 2303, power supply, to be prevented
Thunder and lightning road 2312, peak restrained circuit 2304, overvoltage crowbar 2305, electric source filter circuit 2306, DC-DC conversion circuit
2307th, power boost circuit 2308, power down indicating circuit 2309, accumulator 2310, external signal lightning protection circuit 2311 and micro-
Rectangular connector socket.
Further, power panel 23 includes rectangular connector 2301, power supply voting circuit 2302, AC/DC change-over circuits
2303rd, power lightning protection circuit 2312, peak restrained circuit 2304, overvoltage crowbar 2305, electric source filter circuit 2306, DC-
DC translation circuits 2307, power boost circuit 2308, power down indicating circuit 2309, accumulator 2310, external signal thunder-lightning
Road 2311 and micro- rectangular connector socket.
Micro- rectangular connector socket, power supply voting circuit, peak restrained circuit 2304, overvoltage crowbar 2305, power supply
Filter circuit 2306, DC-DC conversion circuit 2307, rectangular connector 2301 couple successively, realize power supply from micro- rectangular connector
Transition of the socket to rectangular connector；
Form two-way between micro- rectangular connector socket and power supply voting circuit to couple, all the way to change by AC/DC
Circuit 2303 is connected with micro- rectangular connector 2313, and power supply voting circuit is inputed to after airborne power supply is converted into 28VDC
2302, another way is that micro- rectangular connector is directly connected to power supply voting circuit；And two-way power supply is put to the vote, power supply voting electricity
Road is exported to peak restrained circuit 2304；
Power lightning protection circuit is protected to AC/DC change-over circuits and power supply voting circuit；
Electric source filter circuit also concatenates power boost circuit and accumulator, and is connected to rectangular connector；
DC-DC conversion circuit also concatenates power down indicating circuit, and is connected to rectangular connector；
Between micro- rectangular connector and rectangular connector and it is connected to signal lighting protection circuit.
Especially, the protection component 1 that crashes is connected with data management module 39, completes data receiver and write-in, and data are prevented
Shield.
7. data management module 39 is connected by audio signal conditioning module 3907 with sound pick-up 31, while audio signal is adjusted
Reason module 3907 is also connected with microprocessor connector 2301, receives the voice signal of outside input, two-way audio signal is entered
Input to audio coding decoding circuit 3908 after row conditioning, audio coding decoding circuit 3908 audio signal is completed export after coding to
FPGA circuitry 3902, and exported by FPGA circuitry 3902 to PowerPC circuit 3901；The change-over circuit of video 1
3903 are connected with microprocessor connector 2301, receive outside pal video signal, complete to export after vision signal conversion to regarding
Frequency codec chip 3904, coding and decoding video circuit 3904 are exported to FPGA circuitry 3902 after vision signal is completed into coding, and
Exported by FPGA circuitry 3902 to PowerPC circuit 3901；The change-over circuit 3905 of video 2 is connected with microprocessor
Device 2301 connects, and receives outside pal video signal, is exported after completing vision signal conversion to coding and decoding video chip 3906,
Coding and decoding video circuit 3906 is exported to FPGA circuitry 3902 after vision signal is completed into coding, and defeated by FPGA circuitry 3902
Go out to PowerPC microcontroller circuits 3901；ARINC-429 interface chips 3909 are connected with micro- rectangular connector 2301, are received
The Data-Link data of outside input, UTC time, flight position information is simultaneously exported to FPGA circuitry 3902, and passes through FPGA circuitry
Export to PowerPC circuit 3901, ARINC-429 interface chips 3909 are gone back output state information and connected to micro- rectangle
Connect device 2301 to connect, the output of completion status information；ARINC-717 interface circuits 3929 are connected with micro- rectangular connector 2301, are connect
The ARINC-717 data of outside input are received, and are exported to FPGA circuitry 3902, and are exported by FPGA circuitry micro- to PowerPC
Processor circuit 3901；Isolating transformer 3910 is connected with micro- rectangular connector 2301, is received outside and is sent out by Ethernet interface
Flying quality is sent, and is exported by ethernet physical layer interface chip 3913 to PowerPC circuit 3901；Isolation becomes
Depressor 3911 is connected with micro- rectangular connector 2301, is received outside and is sent software load information by Ethernet interface, and passes through
Ethernet physical layer interface chip 3913 is exported to PowerPC circuit 3901；Isolating transformer 3912 and Ethernet
In order to which connector 38 connects, reception ground checkout equipment, which is sent to, safeguards information, and passes through ethernet physical layer interface chip
3913 export and are also associated with clock circuit to PowerPC microcontroller circuits 3901, ethernet physical layer interface chip 3913
3914；Reset circuit 3915 connects micro- rectangular connector 2301, and is exported to PowerPC circuit 3901 and reset electricity
Road；Switch quantity acquisition circuit 3926 with erasing button 33 and testing button 32, receives erasing button 33 and testing button 32 respectively
The switching value of output, and on-off model is exported to PowerPC circuit 3901；Drive circuit of indicator 3927 with
PowerPC circuit 3901 connects, and receives the status signal of the output of PowerPC circuit 3901, and respectively
It is connected with 3 Product Status indicator lamps 34 and indicator of the power supply status 35, for controlling 3 Product Status indicator lamps and power supply shape
State indicator lamp.PowerPC circuit 3901 has been also respectively connected with clock circuit 3917, program storage 3918, internal memory
Circuit 3920, the circuit of Beijing time Acquisition Circuit 3922；RS-422 interface circuits 3923 and RS-232 interface circuit 3924 are distinguished
It is connected with micro- rectangular connector 2301 and PowerPC microcontroller circuits 3901, MIL-STD-1553 data acquisition circuits 3928
Respectively with 1553 connectors 37 and PowerPC circuit 3901, three axis accelerometer 3916 and PowerPC
Circuit 3901 is connected, and the horizontal of collection, longitudinal direction and the axle of normal direction three are exported as acceleration to PowerPC circuit 3901
Signal.PowerPC circuit 3901 is connected with SATA interface circuit 3921, and is connected with storage connector for substrate 11, leads to
The connection of storage connector for substrate 11 is crossed to be connected with the protection component 1 that crashes；, power converting circuit 3925 passes through micro- rectangular connector
2301 are connected with power panel 23, receive the 5VDC that power panel 23 exports, and be converted to each circuit module institute in data management module
The power supply needed；
Crashing, protection component is interior to include 8 storage chips, and storing flying quality respectively from chip 1 to chip 7, (Ethernet connects
Mouthful), Data-Link data, voice data, cabin sound data, video data 1, video data 2, storage MIL-STD-1553 data,
ARINC-717 and certainly collection flying quality；
It is recorded including data packet head and data inclusion；
Data packet head in data memory format includes starting bag mark, data type, passage ID, data length, frame sequence
Number, packet mark, relative time counter and packet header verification and.
Data inclusion in data memory format includes UTC time, Beijing time, faulty word, production code member, aircraft number
And data.
Beneficial effect：
A) present invention has been internally integrated sound pick-up, testing button and erasing button, needs what two equipment were completed by original
Function is completed by an equipment；
B) present invention has been internally integrated three axis accelerometer, can be from collection 3-axis acceleration, and completes to record；
C) there is the present invention 1 road ARINC-429 bus slave computers to carry maintenance system acquisition UTC time, while oneself is designed with
Beijing time Acquisition Circuit, for gathering Beijing time, all record has Beijing time and UTC time in each data frame, side
Just it is synchronous that multi-channel data is carried out in data convert；
D) present invention has 3 road Fast Ethernet interfaces, and 1 tunnel is used to receive flying quality；1 tunnel loads for software；1 tunnel
For ground maintenance；
E) present invention can be powered simultaneously by 115AC and 28VDC, also can individually be powered work in two kinds of power supplys；
The power adaptation of product is enriched, also improves the versatility of product so that the type product can lead in more aircrafts
With；
F) present invention adds to external communication interface designs with lightning protection circuit, can protect and resist thunder and lightning and imitate indirectly
Should.
Brief description of the drawings
Fig. 1 is the composition frame chart of the present invention.
Fig. 2 is the base composition frame chart of the present invention.
Fig. 3 is power module of the present invention and the protection component composition figure that crashes.
Fig. 4 is power module theory of constitution block diagram of the present invention.
Fig. 5 is data management module theory of constitution block diagram of the present invention.
Wherein, base -3, power module -2, protection component -1 of crashing, sound pick-up -31, testing button -32, erasing
Button -33, Product Status indicator lamp -34, indicator of the power supply status -35, branch angle -36,1553 connector -37, Ethernet
Safeguard connector -38, data management module -39, power pack -21, power supply lid plate -22, the composition of power panel -23, micro- square
Shape connector modules -2201, memory plane connection -11, rectangular connector -2301, power supply voting circuit -2302, AC/DC
Change-over circuit -2303, power lightning protection circuit -2312, peak restrained circuit -2304, overvoltage crowbar -2305, power supply
Filter circuit -2306, DC-DC conversion circuit -2307, power boost circuit -2308, power down indicating circuit -2309, energy storage
Circuit -2310, external signal lightning protection circuit -2311, micro- rectangular connector -2313, audio signal conditioning module -3907,
Audio coding decoding circuit-3908, FPGA circuitry-3902, PowerPC circuit-3901, the change-over circuit of video 1-
3903rd, coding and decoding video chip -3904, change-over circuit -3905 of video 2, coding and decoding video chip -3906, ARINC-429
Interface chip -3909, ARINC-717 interface circuit -3929, isolating transformer -3910, ethernet physical layer interface core
Piece -3913, isolating transformer -3912, isolating transformer -3911, clock circuit -3914；Reset circuit -3915, open
Pass amount Acquisition Circuit -3926, drive circuit of indicator -3927, clock circuit -3917, program storage -3918, internal memory
Circuit -3920, the circuit of Beijing time Acquisition Circuit -3922；RS-422 interface circuit -3923, RS-232 interface circuit -
3924th, MIL-STD-1553 data acquisition circuit -3928, three axis accelerometer -3916, SATA interface circuit -3921, electricity
Source translation circuit -3925.
Embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
1. a kind of as Figure 1-3, small-sized state of flight monitoring device, including base 3, power module 2 and the guarantor that crashes
Protecting assembly 1, wherein, the connect base 3 of power module 2, base 3 is connected with the protection component 1 that crashes；
Base 3 includes sound pick-up 31, testing button 32,33,3 status indicator lamps 34 of erasing button, power supply status instruction
35,2, lamp monitoring device leg 36,2 1553 connectors 37, Ethernet safeguard connector 38 and data management module 39；Its
In 3 status indicator lamps 34, be respectively used to indicate flight data recording state, flight audio data recording state and aircraft video
Data-recording status, 3 status indicator lamp bright greens when monitoring device is working properly, when monitoring device operation irregularity 3
Status indicator lamp shiny red；
The power module 2 includes power pack 21, power supply lid plate 22 and power panel 23；Power panel 23 is arranged on power pack
Inside 21；
Micro- rectangular connector module is installed, micro- rectangular connector module is used for and air environment on power supply lid plate
Signal interaction, micro- rectangular connector module are also connected with airborne power supply, and micro- rectangular connector module is inserted including micro- rectangular connector 2
Head, micro- plug of rectangular connector 2 form micro- rectangular connector 2313 with micro- rectangular connector socket；
Power panel 23, which includes rectangular connector 2301, power supply voting circuit 2302, AC/DC change-over circuits 2303, power supply, to be prevented
Thunder and lightning road 2312, peak restrained circuit 2304, overvoltage crowbar 2305, electric source filter circuit 2306, DC-DC conversion circuit
2307th, power boost circuit 2308, power down indicating circuit 2309, accumulator 2310, external signal lightning protection circuit 2311 and micro-
Rectangular connector socket.
As shown in Fig. 2 the base 3 testing button 32, wipes 33,3 Product Status indicator lamps of button by sound pick-up 31
34,36,2, the branch angle of indicator of the power supply status 35,2,1553 connectors 37, Ethernet safeguard connector 38 and installed in inside
Data management module 39 form, wherein 3 Product Status indicator lamps 34, be respectively used to indicate flight data recording state, sound
Frequency data-recording status and video data recording state, when being in normal recordings in the type data, the status lamp BG
Color, shiny red when abnormal.Indicator of the power supply status is used to indicate whether product is in normal power-up state, on fruit product
Electricity, the status lamp are lighted, if not upper electric status lamp extinguishes；
Particularly, power panel 23 include rectangular connector 2301, power supply voting circuit 2302, AC/DC change-over circuits 2303,
Power lightning protection circuit 2312, peak restrained circuit 2304, overvoltage crowbar 2305, electric source filter circuit 2306, DC-DC become
Change circuit 2307, power boost circuit 2308, power down indicating circuit 2309, accumulator 2310, external signal lightning protection circuit
2311 and micro- rectangular connector socket.
Micro- rectangular connector socket, power supply voting circuit, peak restrained circuit 2304, overvoltage crowbar 2305, power supply
Filter circuit 2306, DC-DC conversion circuit 2307, rectangular connector 2301 couple successively, realize power supply from micro- rectangular connector
Transition of the socket to rectangular connector；
Form two-way between micro- rectangular connector socket and power supply voting circuit to couple, all the way to change by AC/DC
Circuit 2303 is connected with micro- rectangular connector 2313, and power supply voting circuit is inputed to after airborne power supply is converted into 28VDC
2302, another way is that micro- rectangular connector is directly connected to power supply voting circuit；And two-way power supply is put to the vote, power supply voting electricity
Road is exported to peak restrained circuit 2304；
Power lightning protection circuit is protected to AC/DC change-over circuits and power supply voting circuit；
Electric source filter circuit also concatenates power boost circuit and accumulator, and is connected to rectangular connector；
DC-DC conversion circuit also concatenates power down indicating circuit, and is connected to rectangular connector；
Between micro- rectangular connector and rectangular connector and it is connected to signal lighting protection circuit.
As shown in figure 5, the data management module 39 is connected by audio signal conditioning module 3907 with sound pick-up 31, together
When audio signal conditioning module 3907 be also connected with microprocessor connector 2301, the voice signal of outside input is received, by two
Road audio signal inputs to audio coding decoding circuit 3908 after being nursed one's health, audio coding decoding circuit 3908 completes audio signal
Export after coding to FPGA circuitry 3902, and exported by FPGA circuitry 3902 to PowerPC circuit 3901；Video
1 change-over circuit 3903 is connected with microprocessor connector 2301, receives outside pal video signal, completes vision signal conversion
After export to coding and decoding video chip 3904, vision signal is completed to export after coding to give FPGA electricity by coding and decoding video circuit 3904
Road 3902, and exported by FPGA circuitry 3902 to PowerPC circuit 3901；The change-over circuit 3905 of video 2 with it is micro-
Processor connector 2301 connects, and receives outside pal video signal, exports after completion vision signal conversion and solved to video volume
Code chip 3906, coding and decoding video circuit 3906 is exported to FPGA circuitry 3902 after vision signal is completed into coding, and is passed through
FPGA circuitry 3902 is exported to PowerPC circuit 3901；ARINC-429 interface chips 3909 and micro- rectangular connector
2301 connections, the Data-Link data of outside input, UTC time being received, flight position information is simultaneously exported to FPGA circuitry 3902, and
Exported by FPGA circuitry and go back output state information to PowerPC circuit 3901, ARINC-429 interface chips 3909
Connected to micro- rectangular connector 2301, the output of completion status information；ARINC-717 interface circuits 3929 and micro- rectangular connector
2301 connections, receive the ARINC-717 data of outside input, and export to FPGA circuitry 3902, and are exported by FPGA circuitry
To PowerPC circuit 3901；Isolating transformer 3910 is connected with micro- rectangular connector 2301, receive it is outside by with
Too network interface sends flying quality, and is exported by ethernet physical layer interface chip 3913 and give PowerPC circuit
3901；Isolating transformer 3911 is connected with micro- rectangular connector 2301, is received outside by Ethernet interface transmission software loading
Information, and exported by ethernet physical layer interface chip 3913 to PowerPC circuit 3901；Isolating transformer
3911 with Ethernet in order to which connector 38 is connected, receive ground checkout equipment and be sent to and safeguard information, and pass through Ethernet physics
Layer interface chip 3913 exports to be also associated with to PowerPC circuit 3901, ethernet physical layer interface chip 3913
Clock circuit 3914；Reset circuit 3915 connects micro- rectangular connector 2301, and defeated to PowerPC circuit 3901
Go out reset circuit；Switch quantity acquisition circuit 3926 with erasing button 33 and testing button 32, receives erasing button 33 and surveyed respectively
The switching value that button 32 exports is tried, and on-off model is exported to PowerPC circuit 3901；Indicator lamp driving electricity
Road 3927 is connected with PowerPC circuit 3901, receives the state letter of the output of PowerPC circuit 3901
Number, and be connected respectively with 3 Product Status indicator lamps 34 and indicator of the power supply status 35, for controlling 3 Product Status instructions
Lamp and indicator of the power supply status.PowerPC circuit 3901 has been also respectively connected with clock circuit 3917, program storage
3918, main memory circuit 3920, the circuit of Beijing time Acquisition Circuit 3922；RS-422 interface circuits 3923 and RS-232 interface circuit
3924 are connected to micro- rectangular connector 2301 and PowerPC circuit 3901, MIL-STD-1553 data acquisitions
Circuit 3928 respectively with 1553 connectors 37 and PowerPC circuit 3901, three axis accelerometer 3916 with
PowerPC circuit 3901 is connected, and the horizontal of collection, longitudinal direction and method are exported to PowerPC circuit 3901
To three axles as acceleration signal.PowerPC circuit 3901 is connected with SATA interface circuit 3921, and connects with memory plane
Connect device 11 to connect, be connected by storing the connection of connector for substrate 11 with the protection component 1 that crashes；, power converting circuit 3925 is by micro-
Rectangular connector 2301 is connected with power panel 23, receives the 5VDC that power panel 23 exports, and is converted to each in data management module
Power supply needed for circuit module；
8 storage chips are included in the protection component that crashes, flying quality (ether is stored respectively from chip 1 to chip 7
Network interface), Data-Link data, voice data, cabin sound data, video data 1, video data 2, storage MIL-STD-1553 numbers
According to, ARINC-717 and from collection flying quality.
Claims (3)
1. a kind of state of flight monitoring device, including base, power module and the protection component that crashes, wherein, the power module
Connect base, base are connected with the protection component that crashes；
Base includes sound pick-up, testing button, erasing button, 3 status indicator lamps, indicator of the power supply status, 2 monitoring devices
Leg, 2 1553 connectors, Ethernets safeguard connector and data management module；Wherein 3 status indicator lamps, are respectively used to
Flight data recording state, flight audio data recording state and aircraft video data recording state are indicated, when monitoring device work
3 status indicator lamp bright greens when making normal, 3 status indicator lamp shiny reds when monitoring device operation irregularity；
The power module includes power pack, power supply lid plate and power panel；Power panel is arranged on inside power pack；
Micro- rectangular connector module is installed, micro- rectangular connector module is used for and air environment signal on power supply lid plate
Interaction, micro- rectangular connector module are also connected with airborne power supply, and micro- rectangular connector module includes micro- rectangular connector plug, micro-
Rectangular connector plug forms micro- rectangular connector with micro- rectangular connector socket；
Power panel includes rectangular connector, power supply voting circuit, AC/DC change-over circuits, power lightning protection circuit, peak restrained electricity
Road, overvoltage crowbar, electric source filter circuit, DC-DC conversion circuit, power boost circuit, power down indicating circuit, energy storage electricity
Road, external signal lightning protection circuit and micro- rectangular connector socket.
A kind of 2. state of flight monitoring device as claimed in claim 1, it is characterised in that：
Power panel includes rectangular connector, power supply voting circuit, AC/DC change-over circuits, power lightning protection circuit, peak restrained electricity
Road, overvoltage crowbar, electric source filter circuit, DC-DC conversion circuit, power boost circuit, power down indicating circuit, energy storage electricity
Road, external signal lightning protection circuit and micro- rectangular connector socket.
Micro- rectangular connector socket, power supply voting circuit, peak restrained circuit, overvoltage crowbar, electric source filter circuit, DC-
DC translation circuits, rectangular connector couple successively, realize transition of the power supply from micro- rectangular connector socket to rectangular connector；
Form two-way between micro- rectangular connector socket and power supply voting circuit to couple, all the way to pass through AC/DC change-over circuits
It is connected with micro- rectangular connector, inputs to power supply voting circuit after airborne power supply is converted into 28VDC, another way connects for micro- rectangle
Connect device and be directly connected to power supply voting circuit；And two-way power supply is put to the vote, power supply voting circuit output gives peak restrained circuit；
Power lightning protection circuit is protected to AC/DC change-over circuits and power supply voting circuit；
Electric source filter circuit also concatenates power boost circuit and accumulator, and is connected to rectangular connector；
DC-DC conversion circuit also concatenates power down indicating circuit, and is connected to rectangular connector；
Between micro- rectangular connector and rectangular connector and it is connected to signal lighting protection circuit.
A kind of 3. state of flight monitoring device according to claim 1 or 2, it is characterised in that：Crash protection component and number
Connected according to management module, complete data receiver and write-in, and data protection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710763827.1A CN107554805B (en) | 2017-08-30 | 2017-08-30 | Flight state monitoring equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710763827.1A CN107554805B (en) | 2017-08-30 | 2017-08-30 | Flight state monitoring equipment |
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| CN107554805A true CN107554805A (en) | 2018-01-09 |
| CN107554805B CN107554805B (en) | 2020-06-09 |
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ID=60978199
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|---|---|---|---|
| CN201710763827.1A Active CN107554805B (en) | 2017-08-30 | 2017-08-30 | Flight state monitoring equipment |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107807574A (en) * | 2017-11-02 | 2018-03-16 | 中电科技集团重庆声光电有限公司 | Multifunctional interface circuit based on integrative packaging |
| CN109342761A (en) * | 2018-09-11 | 2019-02-15 | 陕西千山航空电子有限责任公司 | A kind of rotor monitor speed processor |
| CN109557339A (en) * | 2018-11-16 | 2019-04-02 | 陕西千山航空电子有限责任公司 | A kind of three axis accelerometer and impact search switch |
| FR3087909A1 (en) * | 2018-10-25 | 2020-05-01 | Airbus Operations | ACQUISITION SYSTEM FOR AN AIRCRAFT COMPRISING AN AVIONIC BAY AND AT LEAST ONE RECORDING DEVICE, AND ASSOCIATED AIRCRAFT |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
| 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 |
-
2017
- 2017-08-30 CN CN201710763827.1A patent/CN107554805B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160052642A1 (en) * | 2014-08-25 | 2016-02-25 | Honeywell International Inc. | Aircraft electric taxi health management system and method |
| 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 |
| 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 |
| 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 |
| US20180079533A1 (en) * | 2016-09-16 | 2018-03-22 | Williams International Co., L.L.C. | Aircraft engine illumination and diagnostic system |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107807574A (en) * | 2017-11-02 | 2018-03-16 | 中电科技集团重庆声光电有限公司 | Multifunctional interface circuit based on integrative packaging |
| CN109342761A (en) * | 2018-09-11 | 2019-02-15 | 陕西千山航空电子有限责任公司 | A kind of rotor monitor speed processor |
| FR3087909A1 (en) * | 2018-10-25 | 2020-05-01 | Airbus Operations | ACQUISITION SYSTEM FOR AN AIRCRAFT COMPRISING AN AVIONIC BAY AND AT LEAST ONE RECORDING DEVICE, AND ASSOCIATED AIRCRAFT |
| US11954954B2 (en) | 2018-10-25 | 2024-04-09 | Airbus Sas | Acquisition system for aircraft comprising an avionics rack and at least one recording device, and associated aircraft |
| CN109557339A (en) * | 2018-11-16 | 2019-04-02 | 陕西千山航空电子有限责任公司 | A kind of three axis accelerometer and impact search switch |
| 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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| CN107554805B (en) | 2020-06-09 |
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