CN207037474U - A kind of system for flight control computer - Google Patents
A kind of system for flight control computer Download PDFInfo
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- CN207037474U CN207037474U CN201720943643.9U CN201720943643U CN207037474U CN 207037474 U CN207037474 U CN 207037474U CN 201720943643 U CN201720943643 U CN 201720943643U CN 207037474 U CN207037474 U CN 207037474U
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- 238000001514 detection method Methods 0.000 claims abstract description 42
- 230000002093 peripheral effect Effects 0.000 claims abstract description 17
- 230000001133 acceleration Effects 0.000 claims description 5
- 230000005611 electricity Effects 0.000 claims description 4
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- 238000013461 design Methods 0.000 abstract description 3
- 241000208340 Araliaceae Species 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
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- 238000005259 measurement Methods 0.000 description 1
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Abstract
The utility model provides a kind of system for flight control computer, air pressure detection module U2 and gyroscope and accelerometer combine detection module U3 are laid out the left field in rectangular slab, and air pressure detection module U2 layouts are in the top of gyroscope and accelerometer combine detection module U3；Master control acquisition module U1 is laid out in circuit board right side area；Master control acquisition module U1 PORT COM is arranged in rectangular slab top edge and/or lower edge in the form of semicircle pad, and the semicircle opening of each semicircle pad is easy to weld peripheral circuit towards the outside of rectangular slab.The utility model is mainly efficient zoned by having been carried out to air pressure detection module U2, gyroscope and accelerometer combine detection module U3 and master control acquisition module U1 layout on circuit board, so that be not in that excessive component intersects between each unit, it is laid out ingenious, so as to obtain the high small area pcb board of compact in design, space availability ratio, while it have also obtained interference free performance, the effect of overall efficiency lifting.
Description
Technical field
It the utility model is related to unmanned air vehicle technique field, more particularly to a kind of system for flight control computer.
Background technology
Unmanned plane is the not manned aircraft manipulated using radio robot and the presetting apparatus provided for oneself, nothing on machine
Driving cabin, but the equipment such as automatic pilot, presetting apparatus are installed, ground staff is by unmanned aerial vehicle controller to it
It is tracked, positions, being remotely controlled, remote measurement and data transfer.
Generally, unmanned plane gathers in the air obtains image or video data, will gather the image obtained or video data enters
After row modulation, unmanned aerial vehicle controller is sent to, corresponding position is carried out to image or video data by unmanned aerial vehicle controller
Reason.
Mapping is performed in UAS, is taken photo by plane etc. in task, to ensure that flight is convenient, the manipulation unmanned plane of safety, just
Need the various flight parameters of grasp unmanned plane motion state, engine behavior information and airborne sensor work shape in real time
State information and being given when jeopardizing safe flight is prompted.
Unmanned plane small volume, each component on circuit in layout requirements it is higher, therefore a component need to be designed
Layout can not be mixed and disorderly on circuit, the intersection reduced as far as possible between each component, reduces the flight control system of pcb board area；Although
System for flight control computer element is few but species is more, and difference in size is big, if not being laid out carefully, can not only make the alternating current of input
Signal interference is big to influence the output of later stage voltage, and the PCB surface product occupied is big, it is also possible to influences whether whole circuit board
Service behaviour.
Utility model content
For the deficiency in the presence of prior art, the utility model provides a kind of system for flight control computer, solves
Components' placement is unreasonable in posture instrument in the prior art, circuit board volume is big, the technical problem of poor performance.
To achieve the above object, the utility model employs following technical scheme：A kind of system for flight control computer, including
Housing and the circuit board being arranged in housing, the circuit board are one piece of rectangular slab, are provided with the rectangular slab：
For gathering the air pressure detection module U2 of air pressure, gyroscope and acceleration for gathering gyro and acceleration information
Meter combine detection module U3 and master control acquisition module U1, the master control acquisition module U1 gather air pressure detection module U2 and top respectively
The information of spiral shell instrument and accelerometer combine detection module U3, and the information received is calculated, then it will be calculated
Information is sent to the master control acquisition module of external equipment by least one PORT COM；
The air pressure detection module U2 and gyroscope and accelerometer combine detection module U3 layouts are in the left side of rectangular slab
Region, and air pressure detection module U2 layouts are in the top of gyroscope and accelerometer combine detection module U3；The master control collection
Module U1 is laid out in circuit board right side area；
The PORT COM of the master control acquisition module U1 be arranged in the form of semicircle pad rectangular slab top edge and/or
Lower edge, the semicircle of each semicircle pad are open towards the outside of rectangular slab.
Compared to prior art, the utility model has the advantages that：
Mainly by air pressure detection module U2, gyroscope and accelerometer combine detection module U3 and master control on circuit board
Acquisition module U1 layout has carried out efficient zoned so that is not in that excessive component intersects between each unit, layout is skilful
It is wonderful, so as to obtain the high small area pcb board of compact in design, space availability ratio, while it have also obtained interference free performance, complete machine effect
The effect of rate lifting.
Brief description of the drawings
Fig. 1 is the structural representation of the utility model circuit board；
Fig. 2 is the line graph of the utility model chips U1 and the first peripheral circuit；
Fig. 3 is the line graph of the utility model chips U2 and the second peripheral circuit；
Fig. 4 is the line graph of the utility model chips U3 and the 3rd peripheral circuit；
Fig. 5 is the circuit diagram of PORT COM in the utility model.
Embodiment
The utility model is described further below in conjunction with the accompanying drawings.
As shown in Figure 1, shown in Figure 5, a kind of system for flight control computer, including housing and the circuit board that is arranged in housing, it is described
Circuit board is one piece of rectangular slab 1, is provided with the rectangular slab 1：For gathering the air pressure detection module U2 of air pressure, for gathering
The gyroscope and accelerometer combine detection module U3 and master control acquisition module U1 of gyro and acceleration information, the master control collection
Module U1 gathers air pressure detection module U2 and gyroscope and accelerometer combine detection module U3 information respectively, and will receive
Information calculate after the master control that is sent by 14 TTL serial ports and/or SPI serial ports to external equipment of the information that draws gather mould
Block, PORT COM enrich；The air pressure detection module U2 and gyroscope and accelerometer combine detection module U3 layouts are in rectangle
The left field of plate 1, and air pressure detection module U2 layouts are in the top of gyroscope and accelerometer combine detection module U3；It is described
Master control acquisition module U1 is laid out in circuit board right side area；The PORT COM of the master control acquisition module U1 is with semicircle pad 2
Form be arranged in the top edge of rectangular slab 1 and/or lower edge, the semicircle opening of each semicircle pad 2 is towards rectangular slab 1
Outside, it is easy to weld peripheral circuit.
In such scheme, the utility model is mainly by air pressure detection module U2, gyroscope and acceleration on circuit board
Meter combine detection module U3 and master control acquisition module U1 layout has carried out efficient zoned so that was not between each unit
More components intersects, and layout is ingenious, so as to obtain the high small area pcb board of compact in design, space availability ratio, while also obtains
Obtained interference free performance, the effect of overall efficiency lifting.
Such as Fig. 2 simultaneously combines Fig. 1, and the master control acquisition module U1 includes STM32-K6K8 chips and its first peripheral circuit,
First peripheral circuit includes resistance R1, resistance R2, electric capacity C1, the resistance R1 one end and STM32-K6K8 chips
BOOTO pins are electrically connected, other end ground connection；The resistance R2 one termination 3.3V power supplys, the other end respectively with STM32-K6K8 cores
The RESET# pins of piece and electric capacity C1 one end are electrically connected, electric capacity C1 other end ground connection；The resistance R1 is laid on rectangular slab 1
The lower zone of STM32-K6K8 chips, resistance R2 are laid in the upper right comer region of STM32-K6K8 chips on rectangular slab 1；It is described
Electric capacity C1 is laid in the upper left corner area of STM32-K6K8 chips on rectangular slab 1.
Such as Fig. 3 simultaneously combines Fig. 1, Fig. 2, and the air pressure detection module U2 includes BMP180 chips and its second peripheral circuit,
Second peripheral circuit includes SDA pins and the STM32-K6K8 chips of resistance R3, resistance R4, electric capacity C4, BMP180 chip
SDA pins and resistance R3 one end be electrically connected, resistance R3 another termination 3.3V power supplys；The SCL pins of the BMP180 chips
It is electrically connected with the SCL pins of STM32-K6K8 chips and resistance R4 one end, resistance R4 another termination 3.3V power supplys；The electric capacity
C4 one end is connected respectively with the VDD pins and VDDIO pins of BMP180 chips, and the other end is common port；The resistance R3, electricity
Resistance R4 is laid in the left field of air pressure detection module U2 on rectangular slab 1, the electric capacity C4 be laid on rectangular slab 1 gyroscope and
Accelerometer combine detection module U3 lower left corner region.
Such as Fig. 4 simultaneously combines Fig. 1, Fig. 2, Fig. 3, and gyroscope and accelerometer combine detection the module U3 includes MPU9250
Chip and the 3rd peripheral circuit, the 3rd peripheral circuit include electric capacity C2, C3, the C2 of electric capacity one end and MPU9250
Chip REGOUT pins are electrically connected, and the other end is common port；The C3 of electric capacity one end and MPU9250 chip VDDIO pins electricity
Even, the other end is common port；The electric capacity C2 is laid in the lower left corner region of master control acquisition module U1 on rectangular slab 1, the electricity
The C3 of appearance is laid in the lower right field of master control acquisition module U1 on rectangular slab 1, and the resistance R1 is laid between electric capacity C2, C3
Region；The SDA pins of the MPU9250 chips are electrically connected with the SDA pins of STM32-K6K8 chips, the MPU9250 chips
The SCL pins of SCL pins and STM32-K6K8 chips be electrically connected；The ADO pins of the MPU9250 chips and STM32-K6K8 cores
The ADO pins of piece are electrically connected, and the INT pins of the MPU9250 chips are electrically connected with the INT pins of STM32-K6K8 chips.
As shown in figure 1, diode D1, the diode D1 just extremely common port, negative pole are integrated with the rectangular slab 1
Connect 3.3V power supply；The diode D1 is laid in the fringe region in the left side of rectangular slab 1.
The utility model can export the pitching of installed carrier, roll attitude information in real time, and data output frequencies are variable,
Scope is from 30~200Hz, exportable current altitude；Compact, real-time property is good, flies control system suitable for unmanned plane
System, effective attitude angle output speed is fast, energization.The real-time output body of posture and altitude information is realized using few chip
Product compact (25 × 19mm), easily can be embedded into custom system, output interface is rich by the semicircle pad 2 on module both sides
Richness, there are TTL serial ports and SPI serial ports patterns.
Finally illustrate, above example is only unrestricted to illustrate the technical solution of the utility model, although ginseng
The utility model is described in detail according to preferred embodiment, it will be understood by those within the art that, can be to this
The technical scheme of utility model is modified or equivalent substitution, without departing from the objective and model of technical solutions of the utility model
Enclose, it all should cover among right of the present utility model.
Claims (6)
1. a kind of system for flight control computer, including housing and the circuit board that is arranged in housing, it is characterised in that：The circuit board
For one piece of rectangular slab, it is provided with the rectangular slab：
For gathering the air pressure detection module U2 of air pressure, gyroscope and accelerometer group for gathering gyro and acceleration information
Close detection module U3 and master control acquisition module U1, the master control acquisition module U1 gather air pressure detection module U2 and gyroscope respectively
With accelerometer combine detection module U3 information, and the information received is calculated, the information that then will be calculated
Sent by least one PORT COM to the master control acquisition module of external equipment；
The air pressure detection module U2 and gyroscope and accelerometer combine detection module U3 are laid out the left field in rectangular slab,
And air pressure detection module U2 layouts are in the top of gyroscope and accelerometer combine detection module U3；The master control acquisition module U1
Layout is in circuit board right side area；
The PORT COM of the master control acquisition module U1 is arranged in rectangular slab top edge and/or following in the form of semicircle pad
Edge, the semicircle of each semicircle pad are open towards the outside of rectangular slab.
A kind of 2. system for flight control computer according to claim 1, it is characterised in that：The master control acquisition module U1 includes
STM32-K6K8 chips and its first peripheral circuit, first peripheral circuit includes resistance R1, resistance R2, electric capacity C1, described
Resistance R1 one end and the BOOTO pins of STM32-K6K8 chips are electrically connected, other end ground connection；
A termination 3.3V power supplys of the resistance R2, the other end RESET# pins and electric capacity C1 with STM32-K6K8 chips respectively
One end be electrically connected, electric capacity C1 other end ground connection；
The resistance R1 is laid in the lower zone of STM32-K6K8 chips on rectangular slab, and resistance R2 is laid on rectangular slab
The upper right comer region of STM32-K6K8 chips；
The electric capacity C1 is laid in the upper left corner area of STM32-K6K8 chips on rectangular slab.
A kind of 3. system for flight control computer according to claim 2, it is characterised in that：The air pressure detection module U2 includes
BMP180 chips and its second peripheral circuit, second peripheral circuit include resistance R3, resistance R4, electric capacity C4, BMP180 core
One end of the SDA pins of piece and the SDA pins of STM32-K6K8 chips and resistance R3 is electrically connected, resistance R3 another termination 3.3V electricity
Source；
One end of the SCL pins of the BMP180 chips and the SCL pins of STM32-K6K8 chips and resistance R4 is electrically connected, resistance R4
Another termination 3.3V power supplys；
One end of the electric capacity C4 is connected respectively with the VDD pins of BMP180 chips and VDDIO pins, and the other end is common port；
The resistance R3, resistance R4 are laid in the left field of air pressure detection module U2 on rectangular slab；
The electric capacity C4 is laid in gyroscope and accelerometer combine detection module U3 lower left corner region on rectangular slab.
A kind of 4. system for flight control computer according to claim 2, it is characterised in that：Gyroscope and the accelerometer group
Closing detection module U3 includes MPU9250 chips and the 3rd peripheral circuit, and the 3rd peripheral circuit includes electric capacity C2, C3, described
The C2 of electric capacity one end is electrically connected with MPU9250 chip REGOUT pins, and the other end is common port；The C3 of electric capacity one end with
MPU9250 chip VDDIO pins are electrically connected, and the other end is common port；
The electric capacity C2 is laid in the lower left corner region of master control acquisition module U1 on rectangular slab, and the C3 of the electric capacity is laid in rectangle
Master control acquisition module U1 lower right field on plate, the resistance R1 are laid in the region between electric capacity C2, C3；
The SDA pins of the MPU9250 chips are electrically connected with the SDA pins of STM32-K6K8 chips, the MPU9250 chips
The SCL pins of SCL pins and STM32-K6K8 chips are electrically connected；
The ADO pins of the MPU9250 chips are electrically connected with the ADO pins of STM32-K6K8 chips, the MPU9250 chips
The INT pins of INT pins and STM32-K6K8 chips are electrically connected.
A kind of 5. system for flight control computer according to claim 1, it is characterised in that：The PORT COM is multiple TTL
Serial ports and/or SPI serial ports.
A kind of 6. system for flight control computer according to claim 1, it is characterised in that：Two poles are integrated with the rectangular slab
Pipe D1, the diode D1 just extremely common port, negative pole connect 3.3V power supply；The diode D1 is laid on the left of rectangular slab
Fringe region.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720943643.9U CN207037474U (en) | 2017-07-31 | 2017-07-31 | A kind of system for flight control computer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720943643.9U CN207037474U (en) | 2017-07-31 | 2017-07-31 | A kind of system for flight control computer |
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| Publication Number | Publication Date |
|---|---|
| CN207037474U true CN207037474U (en) | 2018-02-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720943643.9U Active CN207037474U (en) | 2017-07-31 | 2017-07-31 | A kind of system for flight control computer |
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| Country | Link |
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| CN (1) | CN207037474U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110844062A (en) * | 2019-10-15 | 2020-02-28 | 中国民航大学 | Modular multipurpose unmanned aerial vehicle with composite wing layout |
| CN111854739A (en) * | 2020-02-18 | 2020-10-30 | 重庆市皓颖科技发展有限公司 | Small-size high-precision inertial measurement unit |
-
2017
- 2017-07-31 CN CN201720943643.9U patent/CN207037474U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110844062A (en) * | 2019-10-15 | 2020-02-28 | 中国民航大学 | Modular multipurpose unmanned aerial vehicle with composite wing layout |
| CN110844062B (en) * | 2019-10-15 | 2023-01-17 | 中国民航大学 | Modular multipurpose unmanned aerial vehicle with composite wing layout |
| CN111854739A (en) * | 2020-02-18 | 2020-10-30 | 重庆市皓颖科技发展有限公司 | Small-size high-precision inertial measurement unit |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Zhou Shiji Inventor before: Zhou Shiji Inventor before: Gao Huoxia |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231016 Address after: No.23 Xiyong Avenue, Shapingba District, Chongqing 401332 Patentee after: CHINA ELECTRONICS TECHNOLOGY GROUP CORPORATION NO.26 Research Institute Address before: 400060 No. 20-2, building 1, No. 19, Nanhu Branch Road, Chongqing Economic Development Zone Patentee before: CHONGQING HAOYING TECHNOLOGY DEVELOPMENT Co.,Ltd. |