CN207054005U - The highly integrated flight control system of small and medium size unmanned aerial vehicles - Google Patents
The highly integrated flight control system of small and medium size unmanned aerial vehicles Download PDFInfo
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- CN207054005U CN207054005U CN201721013636.5U CN201721013636U CN207054005U CN 207054005 U CN207054005 U CN 207054005U CN 201721013636 U CN201721013636 U CN 201721013636U CN 207054005 U CN207054005 U CN 207054005U
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Abstract
The utility model discloses a kind of highly integrated flight control system of small and medium size unmanned aerial vehicles, including：SMA radio frequency connectors, GPS module circuit board, Metal shielding shell, wire pair board connector, fly control main circuit board, digital transmission module circuit board, board to board connector, reversed polarity SMA radio frequency connectors and rectangle air plug connector, wherein, GPS module circuit board, fly control main circuit board and digital transmission module circuit board is integrated in the inside of Metal shielding shell, three passes through wire pair board connector, board to board connector is sequentially connected, GPS module circuit board is interconnected by two SMA radio frequency connectors and outside GPS receiving antenna, fly control main circuit board and communicate interconnection and supply input are carried out with extemal component by rectangle air plug connector, digital transmission module circuit board is interconnected by reversed polarity SMA radio frequency connectors and outside dual-mode antenna.It is of the present utility model to be beneficial in that：(1) each functional module is highly integrated；(2) electromagnetic interference is effectively shielded；(3) power utilization efficiency improves.
Description
Technical field
It the utility model is related to a kind of flight control system of unmanned plane, and in particular to a kind of the highly integrated of small and medium size unmanned aerial vehicles flies
Control system, belong to unmanned air vehicle technique field.
Background technology
At present, the scattered arrangement of each functional module of the flight control system of small and medium size unmanned aerial vehicles, degree of integration is not high, each functional module
Between connected using cable, cause the communications cable between each functional module, power cable is directly exposed in cabin atmosphere, not only cloth
Line is more chaotic, easily causes mutual crosstalk between unlike signal line, power line, and is highly prone to the dry of external electromagnetic environment
Disturb, largely have impact on the reliability and stability of flight control system, while be damaged in applying working condition and factor of natural environment
In the case of maintainable and convertibility it is poor.
In addition, each functional module supply voltage disunity of flight control system, cause that power supply service efficiency is relatively low, and power consumption is larger.
Utility model content
To solve the deficiencies in the prior art, the purpose of this utility model is to provide a kind of the highly integrated of small and medium size unmanned aerial vehicles
Flight control system.
In order to realize above-mentioned target, the utility model adopts the following technical scheme that：
A kind of highly integrated flight control system of small and medium size unmanned aerial vehicles, it is characterised in that including：SMA radio frequency connectors, GPS moulds
Block circuit board, Metal shielding shell, wire pair board connector, fly control main circuit board, digital transmission module circuit board, board to board connector,
Reversed polarity SMA radio frequency connectors and rectangle air plug connector, wherein,
Foregoing GPS module circuit board, winged control main circuit board and digital transmission module circuit board are integrated in the interior of Metal shielding shell
Portion, GPS module circuit board by wire pair board connector with fly control main circuit board be connected, by two SMA radio frequency connectors with outside
The GPS receiving antenna interconnection in portion, fly control main circuit board and be connected by board to board connector with digital transmission module circuit board, pass through rectangle
Air plug connector carries out communicate interconnection and supply input with extemal component, and digital transmission module circuit board is penetrated by reversed polarity SMA
Frequency connector interconnects with outside dual-mode antenna.
The highly integrated flight control system of foregoing small and medium size unmanned aerial vehicles, it is characterised in that aforementioned metal shields the inside of shell
With screen layer dividing plate, foregoing GPS module circuit board, fly control main circuit board and digital transmission module circuit board by screen layer dividing plate independence
Shielding is kept apart, and divides in different spaces.
The highly integrated flight control system of foregoing small and medium size unmanned aerial vehicles, it is characterised in that foregoing GPS module circuit board, fly control
Main circuit board and digital transmission module circuit board are fixed on the inside relevant position of Metal shielding shell by way of screw installation.
It is of the present utility model to be beneficial in that：
(1) each functional module is highly integrated, and the electrical connection between functional module uses board to board connector grafting or extremely short
Cable connection, not only avoid mutual crosstalk between unlike signal line, power line, largely improve flight control system
Reliability and stability, and be also convenient for safeguarding and change；
(2) it is overall to use small size metal shell, it is effectively isolated and shields outside electromagnetic interference, while between each functional module
Also independent isolating shields, and is effectively isolated and shields mutual electromagnetic interference, and largely improve flight control system can
By property and stability；
(3) single power supply can be used to power, each functional module supply voltage is unified, and power utilization efficiency improves, power consumption
Effectively reduce；
(4) external electrical connection uses single connector, effective specification external electric interfaces of flight control system.
Brief description of the drawings
Fig. 1 is each the functional module electric interconnection and topology layout schematic diagram of highly integrated flight control system of the present utility model；
Fig. 2 is that the external electric interfaces schematic diagram of front panel of highly integrated flight control system of the present utility model is (and high in Fig. 1
The left view of integrated flight control system).
The implication of reference in figure：1-SMA radio frequency connectors, 2-GPS module boards, 3- Metal shielding shells, 4-
Wire pair board connector, 5- fly control main circuit board, 6- digital transmission modules circuit board, 7- board to board connectors, 8- reversed polarity SMA radio frequencies and connected
Connect device, 9- rectangle air plug connectors.
Embodiment
Make specific introduce to the utility model below in conjunction with the drawings and specific embodiments.
Referring to Figures 1 and 2, the highly integrated flight control system of small and medium size unmanned aerial vehicles of the present utility model includes：SMA radio frequencies connect
Device 1, GPS module circuit board 2, Metal shielding shell 3, wire pair board connector 4, fly control main circuit board 5, digital transmission module circuit board 6,
Board to board connector 7, reversed polarity SMA radio frequency connectors 8 and rectangle air plug connector 9.
GPS module circuit board 2, winged control main circuit board 5 and digital transmission module circuit board 6 are integrated in the interior of Metal shielding shell 3
Portion, the inside of Metal shielding shell 3 carry screen layer dividing plate, GPS module circuit board 2, fly control main circuit board 5 and digital transmission module electricity
Road plate 6 is kept apart by screen layer dividing plate individual screen, is divided in different spaces, and is fixed on gold by way of screw installation
The inside relevant position of category shielding shell 3.
Annexation between three pieces of circuit boards is as follows：
GPS module circuit board 2 is connected by wire pair board connector 4 with flying control main circuit board 5, is flown control main circuit board 5 and is passed through
Board to board connector 7 is connected with digital transmission module circuit board 6.
Annexation between three pieces of circuit boards and other functional modules is as follows：
GPS module circuit board 2 is interconnected by two SMA radio frequency connectors 1 and outside GPS receiving antenna；
Fly control main circuit board 5 and communicate interconnection and supply input carried out with extemal component by rectangle air plug connector 9,
Not only effective specification flight control system external electric interfaces, and realize the power supply of flight control system single power supply, each functional module
Supply voltage is unified, and power utilization efficiency improves, and power consumption effectively reduces；
Digital transmission module circuit board 6 is interconnected by reversed polarity SMA radio frequency connectors 8 and outside dual-mode antenna.
As can be seen here, the highly integrated flight control system of small and medium size unmanned aerial vehicles of the present utility model, its each functional module highly collect
Into the electrical connection between functional module is connected using board to board connector grafting or extremely short cable, not only avoid different letters
Number crosstalk mutual between line, power line, largely improves the reliability and stability of flight control system, and be also convenient for tieing up
Shield and replacing.
In addition, the highly integrated flight control system of small and medium size unmanned aerial vehicles of the present utility model, it is integrally using outside small size metal
Shell, it is effectively isolated and shields outside electromagnetic interference, while also independent isolating shields (GPS module circuit board between each functional module
2nd, control 6 mutually isolated shielding of main circuit board 5 and digital transmission module circuit board is flown, wire pair board connector 4 and board to board connector 7 divide
In different spaces), be effectively isolated and shield mutual electromagnetic interference, largely improve flight control system reliability and
Stability.
It should be noted that above-described embodiment does not limit the utility model in any form, it is all to use equivalent substitution or wait
The technical scheme that the mode of effect conversion is obtained, all falls within the scope of protection of the utility model.
Claims (3)
1. the highly integrated flight control system of small and medium size unmanned aerial vehicles, it is characterised in that including：SMA radio frequency connectors (1), GPS module electricity
Road plate (2), Metal shielding shell (3), wire pair board connector (4), winged control main circuit board (5), digital transmission module circuit board (6), plate
To connector for substrate (7), reversed polarity SMA radio frequency connectors (8) and rectangle air plug connector (9), wherein,
The GPS module circuit board (2), winged control main circuit board (5) and digital transmission module circuit board (6) are integrated in Metal shielding shell
(3) inside, GPS module circuit board (2) are connected, by two by wire pair board connector (4) with flying control main circuit board (5)
SMA radio frequency connectors (1) interconnect with outside GPS receiving antenna, fly control main circuit board (5) by board to board connector (7) with
Digital transmission module circuit board (6) is connected, by rectangle air plug connector (9) and extemal component communicate and interconnection and powers defeated
Enter, digital transmission module circuit board (6) is interconnected by reversed polarity SMA radio frequency connectors (8) and outside dual-mode antenna.
2. the highly integrated flight control system of small and medium size unmanned aerial vehicles according to claim 1, it is characterised in that the metallic shield
The inside of shell (3) carries screen layer dividing plate, the GPS module circuit board (2), flies control main circuit board (5) and digital transmission module electricity
Road plate (6) is kept apart by screen layer dividing plate individual screen, is divided in different spaces.
3. the highly integrated flight control system of small and medium size unmanned aerial vehicles according to claim 1, it is characterised in that the GPS module
Circuit board (2), winged control main circuit board (5) and digital transmission module circuit board (6) are fixed on metallic shield by way of screw installation
The inside relevant position of shell (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721013636.5U CN207054005U (en) | 2017-08-14 | 2017-08-14 | The highly integrated flight control system of small and medium size unmanned aerial vehicles |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721013636.5U CN207054005U (en) | 2017-08-14 | 2017-08-14 | The highly integrated flight control system of small and medium size unmanned aerial vehicles |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207054005U true CN207054005U (en) | 2018-02-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721013636.5U Active CN207054005U (en) | 2017-08-14 | 2017-08-14 | The highly integrated flight control system of small and medium size unmanned aerial vehicles |
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| CN (1) | CN207054005U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109708536A (en) * | 2018-12-06 | 2019-05-03 | 湖北航天飞行器研究所 | A kind of compact miniaturization integrated form STT missile device |
-
2017
- 2017-08-14 CN CN201721013636.5U patent/CN207054005U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109708536A (en) * | 2018-12-06 | 2019-05-03 | 湖北航天飞行器研究所 | A kind of compact miniaturization integrated form STT missile device |
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