CN204832499U - Accuse and navigation all -in -one fly - Google Patents
Accuse and navigation all -in -one fly Download PDFInfo
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- CN204832499U CN204832499U CN201520362798.4U CN201520362798U CN204832499U CN 204832499 U CN204832499 U CN 204832499U CN 201520362798 U CN201520362798 U CN 201520362798U CN 204832499 U CN204832499 U CN 204832499U
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Abstract
The utility model discloses an accuse and navigation all -in -one fly belongs to aviation technical field, and it includes: casing, three rudder plates, twin rudders board, power strip, mainboard, navigation board, mother board, MEMS inertia measuring unit, GPSGLONASSBeiDou receiver and atmospheric pressure sensor, the mother board is fixed on the bottom surface of casing inside, three rudder plates, the twin rudders board, the power strip, during the recess in the casing is all fixed through the cold drawing behind the parallel configuration in proper order to mainboard and navigation board, and all be connected through socket and mother board, MEMS inertia measuring unit installs at the boss of casing on the surface, the one side at the navigation board is installed to the GPSGLONASSBeiDou receiver, the opposite side at the navigation board is installed to the atmospheric pressure sensor, install the atmosphere plug at the surface of casing and with atmospheric pressure sensor corresponding position, the inertial navigation system that exists, air data computer, each system of flight control computer is discrete, volume weight is great, the cost is higher problem can be solved to this all -in -one among the current high -speed unmanned air vehicle technique.
Description
Technical field
The utility model belongs to technical field of aerospace, is specifically related to fly control and navigation all-in-one machine.
Background technology
Current UAV Flight Control mostly is flight-control computer, inertial navigation system, air data computer are discrete, and connects work by cable, causes whole avionics system volume weight comparatively large, and is not easy to working service; Therefore need design a kind of for unmanned plane fly control and navigation all-in-one machine.
Utility model content
In view of this, the purpose of this utility model is to provide and flies control and navigation all-in-one machine, can solve the inertial navigation system existed in existing high-speed unmanned aerial vehicle technology, the problem that air data computer, each system of flight-control computer are discrete, volume weight is comparatively large, cost is higher.
The utility model is achieved through the following technical solutions:
Fly control to comprise with navigation all-in-one machine: housing, three rudder plates, Twin Rudders plate, power panel, mainboard, navigation panel, motherboard, MEMS Inertial Measurement Unit, GPS/GLONASS/BeiDou receiver and barometric pressure sensor;
Described housing is rectangular housing, and the bottom surface of enclosure interior is provided with boss, and the two opposite sides of enclosure interior have two or more groove vertically;
Its annexation is as follows: motherboard is fixed on the bottom surface of enclosure interior; Three rudder plates, Twin Rudders plate, power panel, mainboard and navigation panel are all fixed on by cold drawing after laid out in parallel in the groove in housing successively, and are all connected with motherboard by socket, and wherein, navigation panel is positioned at the side of the boss near housing; MEMS Inertial Measurement Unit is arranged in the boss surface of housing, GPS/GLONASS/BeiDou receiver is arranged on the side of navigation panel away from the boss of housing, barometric pressure sensor is arranged on the side of navigation panel near the boss of housing, and MEMS Inertial Measurement Unit, GPS/GLONASS/BeiDou receiver and barometric pressure sensor are all electrically connected with navigation panel; Housing outside surface and the position corresponding with barometric pressure sensor is provided with air plug, one end of air plug is connected with barometric pressure sensor, and the other end of air plug is connected with pitot.
Further, the outside surface of housing is also provided with cylindrical connector, and one end of cylindrical connector and motherboard are electrically connected, and the other end and external unit are electrically connected.
Further, the boss flatness of described housing is for being less than or equal to 0.03.
Further, described GPS/GLONASS/BeiDou receiver is two.
Further, the silicone rubber tube that it is 4mm that the connected mode of the two ends of the air plug on housing and barometric pressure sensor and pitot is by internal diameter is connected.
Principle of work: MEMS Inertial Measurement Unit is measured and gathered the original inertial navigation data of carrier, comprises angular rate data, acceleration information and geomagnetic data, and inertial navigation data is passed to navigation panel;
GPS/GLONASS/BeiDou receiver obtains position and speed data, and position and speed data are passed to navigation panel;
Barometric pressure sensor receives the dynamic and static pressure transmitted from pitot, and is converted into electric signal, by electrical signal transfer to navigation panel;
Navigation panel is carried out integrated navigation to the inertial navigation data of the MEMS Inertial Measurement Unit received and the position of GPS/GLONASS/BeiDou receiver and speed data and is resolved and then obtain integrated navigation data; Meanwhile, the electric signal of navigation panel to the barometric pressure sensor received resolves, and then obtains the atmospheric parameters such as true air speed, indicator air speed, air height; Integrated navigation data and atmospheric parameter are passed to mainboard by navigation panel;
Mainboard utilizes the integrated navigation data that receive and atmospheric parameter to calculate steering wheel by control law to go out rudder amount, carry out flight and control, and then realize the automatic flight of unmanned plane overall process.
Beneficial effect: the utility model adopts MEMS Inertial Measurement Unit, GPS/GLONASS/BeiDou receiver, barometric pressure sensor and flight control modules to carry out integrated navigation and flight controls, traditional inertial navigation system, air data computer, flight-control computer are carried out integrated design, volume is little, lightweight, cost is low.
Accompanying drawing explanation
Fig. 1 is vertical view of the present utility model.
Fig. 2 is three-dimensional plot of the present utility model.
Fig. 3 is three-dimensional plot two of the present utility model.
Wherein, 1-housing, 2-tri-rudder plate, 3-Twin Rudders plate, 4-power panel, 5-mainboard, 6-navigation panel, 7-motherboard, 8-MEMS Inertial Measurement Unit, 9-GPS/GLONASS/BeiDou receiver, 10-barometric pressure sensor.
Embodiment
To develop simultaneously embodiment below in conjunction with accompanying drawing, the utility model is described in detail.
The utility model provides and flies control and navigation all-in-one machine, see accompanying drawing 1-3, comprising: housing 1, circuit board, MEMS Inertial Measurement Unit 8, GPS/GLONASS/BeiDou receiver 9 and barometric pressure sensor 10;
Described housing 1 is rectangular housing, and the bottom surface of housing 1 inside is provided with the higher boss of flatness, and the flatness of boss is for being less than or equal to 0.03, and the two opposite sides of housing 1 inside have two or more groove vertically;
Described circuit board is six pieces, is respectively three rudder plates 2, Twin Rudders plate 3, power panel 4, mainboard 5, navigation panel 6 and motherboard 7;
Its annexation is as follows: described motherboard 7 is fixed by screws on the bottom surface of housing 1 inside; Described three rudder plates 2, Twin Rudders plate 3, power panel 4, mainboard 5 and navigation panel 6 are all fixed in the groove in housing 1 by cold drawing, and are all connected with motherboard 7 by Europlug; Wherein, three rudder plates 2, Twin Rudders plate 3, power panel 4, mainboard 5 and navigation panel 6 laid out in parallel successively; Navigation panel 6 is positioned at the side of the boss near housing 1, and cold drawing is fixed by screws in the groove in housing 1; MEMS Inertial Measurement Unit 8 is arranged in the boss surface of housing 1, and the higher level degree of boss and installation are used for reducing alignment error by face, and the reinforcement of boss is used for local strengthening to ensure the rigidity of installed surface; Two GPS/GLONASS/BeiDou receivers 9 are arranged on the side of navigation panel 6 away from the boss of housing 1, barometric pressure sensor 10 is arranged on the side of navigation panel 6 near the boss of housing 1, and MEMS Inertial Measurement Unit 8, GPS/GLONASS/BeiDou receiver 9 and barometric pressure sensor 10 are all electrically connected with navigation panel 6; Housing 1 outside surface and the position corresponding with barometric pressure sensor 10 is provided with air plug, one end of air plug is that the silicone rubber tube of 4mm is connected with barometric pressure sensor 10 by internal diameter, the other end of air plug is connected with pitot by the silicone rubber tube that internal diameter is 4mm, pitot communicates with outside air, is used for realizing the conduction of dynamic and static pressure; The outside surface of housing 1 is provided with cylindrical connector, and one end and the motherboard 7 of cylindrical connector are electrically connected, and the other end and external unit are electrically connected.
Principle of work: MEMS Inertial Measurement Unit 8 is measured and gathered the original inertial navigation data of carrier, comprises angular rate data, acceleration information and geomagnetic data, and inertial navigation data is passed to navigation panel 6;
GPS/GLONASS/BeiDou receiver 9 obtains position and speed data, and position and speed data are passed to navigation panel 6;
Barometric pressure sensor 10 receives the dynamic and static pressure transmitted from pitot, and is converted into electric signal, by electrical signal transfer to navigation panel 6;
Navigation panel 6 is carried out integrated navigation to the inertial navigation data of the MEMS Inertial Measurement Unit 8 received and the position of GPS/GLONASS/BeiDou receiver 9 and speed data and is resolved and then obtain integrated navigation data; Meanwhile, the electric signal of navigation panel 6 to the barometric pressure sensor 10 received resolves, and then obtains the atmospheric parameters such as true air speed, indicator air speed, air height; Integrated navigation data and atmospheric parameter are passed to mainboard 5 by navigation panel 6;
Mainboard 5 utilizes the integrated navigation data that receive and atmospheric parameter to calculate steering wheel by control law to go out rudder amount, carry out flight and control, and then realize the automatic flight of unmanned plane overall process.
In sum, these are only preferred embodiment of the present utility model, be not intended to limit protection domain of the present utility model.All within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (5)
1. fly control and navigation all-in-one machine, it is characterized in that, comprising: housing (1), three rudder plates (2), Twin Rudders plate (3), power panel (4), mainboard (5), navigation panel (6), motherboard (7), MEMS Inertial Measurement Unit (8), GPS/GLONASS/BeiDou receiver (9) and barometric pressure sensor (10);
Described housing (1) is rectangular housing, and the bottom surface of housing (1) inside is provided with boss, and the two opposite sides of housing (1) inside have two or more groove vertically;
Its annexation is as follows: motherboard (7) is fixed on the inner bottom surface of housing (1); Three rudder plates (2), Twin Rudders plate (3), power panel (4), mainboard (5) and navigation panel (6) are all fixed in the groove in housing (1) by cold drawing after laid out in parallel successively, and be all connected with motherboard (7) by socket, wherein, navigation panel (6) is positioned at the side of the boss near housing (1); MEMS Inertial Measurement Unit (8) is arranged in the boss surface of housing (1), GPS/GLONASS/BeiDou receiver (9) is arranged on the side of navigation panel (6) away from the boss of housing (1), barometric pressure sensor (10) is arranged on the side of navigation panel (6) near the boss of housing (1), and MEMS Inertial Measurement Unit (8), GPS/GLONASS/BeiDou receiver (9) and barometric pressure sensor (10) are all electrically connected with navigation panel (6); Housing (1) outside surface and the position corresponding with barometric pressure sensor (10) is provided with air plug, one end of air plug is connected with barometric pressure sensor (10), and the other end of air plug is connected with pitot.
2. fly control and navigation all-in-one machine as claimed in claim 1, it is characterized in that, the outside surface of housing (1) is also provided with cylindrical connector, and one end of cylindrical connector and motherboard (7) are electrically connected, and the other end and external unit are electrically connected.
3. fly control and navigation all-in-one machine as claimed in claim 1, it is characterized in that, the boss flatness of described housing (1) is for being less than or equal to 0.03.
4. fly control and navigation all-in-one machine as claimed in claim 1, it is characterized in that, described GPS/GLONASS/BeiDou receiver (9) is two.
5. fly control and navigation all-in-one machine as claimed in claim 1, it is characterized in that, the silicone rubber tube that it is 4mm that the connected mode of the two ends of the air plug on housing (1) and barometric pressure sensor (10) and pitot is by internal diameter is connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520362798.4U CN204832499U (en) | 2015-05-29 | 2015-05-29 | Accuse and navigation all -in -one fly |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520362798.4U CN204832499U (en) | 2015-05-29 | 2015-05-29 | Accuse and navigation all -in -one fly |
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| Publication Number | Publication Date |
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| CN204832499U true CN204832499U (en) | 2015-12-02 |
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| CN201520362798.4U Active CN204832499U (en) | 2015-05-29 | 2015-05-29 | Accuse and navigation all -in -one fly |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106681193A (en) * | 2017-03-09 | 2017-05-17 | 北京奇正数元科技股份有限公司 | Minitype unmanned plane overall electrical system module |
| CN109490929A (en) * | 2018-12-29 | 2019-03-19 | 北京金朋达航空科技有限公司 | Fly control and navigation all-in-one machine |
| CN109724480A (en) * | 2018-12-29 | 2019-05-07 | 湖北航天技术研究院总体设计所 | A kind of integrated synthesis control device suitable for aircraft |
| WO2020133909A1 (en) * | 2018-12-29 | 2020-07-02 | 北京金朋达航空科技有限公司 | Flight control and navigation integrated machine |
| CN113044229A (en) * | 2021-03-26 | 2021-06-29 | 北京理工大学 | Modular integrated control system on air-drop type aircraft |
-
2015
- 2015-05-29 CN CN201520362798.4U patent/CN204832499U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106681193A (en) * | 2017-03-09 | 2017-05-17 | 北京奇正数元科技股份有限公司 | Minitype unmanned plane overall electrical system module |
| CN109490929A (en) * | 2018-12-29 | 2019-03-19 | 北京金朋达航空科技有限公司 | Fly control and navigation all-in-one machine |
| CN109724480A (en) * | 2018-12-29 | 2019-05-07 | 湖北航天技术研究院总体设计所 | A kind of integrated synthesis control device suitable for aircraft |
| WO2020133909A1 (en) * | 2018-12-29 | 2020-07-02 | 北京金朋达航空科技有限公司 | Flight control and navigation integrated machine |
| CN113044229A (en) * | 2021-03-26 | 2021-06-29 | 北京理工大学 | Modular integrated control system on air-drop type aircraft |
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