CN214029128U - Multifunctional device for aircraft - Google Patents
Multifunctional device for aircraft Download PDFInfo
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- CN214029128U CN214029128U CN202022737619.4U CN202022737619U CN214029128U CN 214029128 U CN214029128 U CN 214029128U CN 202022737619 U CN202022737619 U CN 202022737619U CN 214029128 U CN214029128 U CN 214029128U
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- 238000004891 communication Methods 0.000 claims abstract description 28
- 238000003780 insertion Methods 0.000 claims description 13
- 230000037431 insertion Effects 0.000 claims description 13
- 239000011159 matrix material Substances 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 4
- 238000005259 measurement Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 230000001413 cellular effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005315 distribution function Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
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Abstract
A multifunctional device for an aircraft is in a prism shape, has three side surfaces with a connecting function, and is internally provided with a battery, an attitude sensor, a temperature control device and the like. The device is used for providing a battery and an attitude sensor with a temperature control effect, and realizes reliable sensor measurement and stable power supply; the connecting device is used for connecting the array type multi-rotor aircraft, and realizes the fixed connection and the mutual communication between the rotor units.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to the field of array type multi-rotor aircrafts.
Background
With the increasingly mature technology of aircrafts, the aircrafts are applied more and more widely, and various problems in our lives can be solved more and more. In the field of array type multi-rotor wings, a flying automobile Volocoter manufactured by Intel, a Yihang 216 manufactured by Yihang intelligent company in China and the like appear, and a patent scheme with the application number of 201822137253X also provides a novel honeycomb array multi-rotor wing scheme. For the cellular array multi-rotor, special communication, sensing and physical connection equipment is needed, and a special power supply is also needed.
Disclosure of Invention
In order to achieve the purpose, the invention provides a multifunctional device for an aircraft, which has the functions of power supply, attitude sensing, rotor connection, data communication and the like, and the invention comprises the following specific contents:
a multifunction device for an aircraft comprising a socket for input of electrical power; a socket comprising 1 to 3 output powers, wherein the output powers are derived from the input powers; the system comprises an attitude sensor and a processor, wherein the processor can read the data of the attitude sensor; the data communication interface device comprises 1 to 6 data communication interface devices which are divided into 1 to 3 groups, and each group has at most two data communication interfaces; the processor may output information including device pose data via the data communication interface.
The additional distribution function also comprises batteries, wherein 1 to 3 groups of the batteries are connected in parallel, and each group is formed by connecting a plurality of batteries in series; the input power may be used to charge a battery, the output power may be from a battery, and the processor may obtain battery charging information or control battery charging.
The added function is that the multifunctional device also comprises a temperature control device, the temperature control device can heat or cool the components in the multifunctional device to keep the temperature within the working range, and the main objects of temperature control comprise a battery and an attitude sensor. The processor may control the temperature control device and may communicate control information via the data communication device.
One option for shell packaging is: the shell is prismatic, the prism shape has three side surfaces with the same length of the top edge, the three side surfaces are in the shape of an outer circular arc, the radii of the three outer circular arcs are the same, and three circle centers form a regular triangle; or the three side surfaces are planar, and the three formed planes form an included angle of 60 degrees with each other; the socket for outputting the electric power is configured to three side surfaces, and at most one socket is arranged on each side surface; the data communication interface device is configured to three sides, each side is provided with at most one group, each group is internally communicated with the communication interface group on the other side, and the processor is communicated with all the data communication interfaces of 1 group.
The added function is that the device also comprises a display device, the display mode is in a dot matrix, character or color form, and the processor controls the display output.
The scheme of the side connecting device is as follows: the three sides are all provided with connecting devices, the connecting devices comprise physical fixed connecting devices, and the physical fixed connecting devices comprise 1 or more plug-in devices, push-pull bayonets and screw holes which are combined randomly.
The more detailed scheme of the physical fixed connecting device is that the physical fixed connecting device comprises 1 or more vertical insertion grooves, wherein the insertion grooves are arranged in the middle of the side surfaces, and the insertion grooves are provided with extensible push-pull clips which are used for being transversely clamped and fixed after being vertically inserted.
The increased connecting and fixing function comprises three sides, the positions of the three sides are regular triangles, the three sides are provided with connecting and fixing devices, and the connecting and fixing devices have connecting and fixing effects at least two positions, namely upper, middle and lower positions.
Advantageous effects
The multifunctional device for the aircraft provided by the scheme of the invention provides the battery and the attitude sensor with the temperature control effect, realizes reliable sensor measurement and stable power supply, and realizes fixed connection and mutual communication between rotor wing units in the application of the array type multi-rotor aircraft.
Drawings
Fig. 1 is a schematic illustration of an embodiment of a multifunctional component for an aircraft.
Fig. 2 is a schematic illustration of an embodiment of a multifunctional component for an aircraft.
Fig. 3 is a schematic diagram of the internal connections of the three-sided communication interface.
Fig. 4 is a schematic diagram of an application of the multifunctional device.
Detailed Description
The following description of the present invention, including the embodiments, is provided in the accompanying drawings:
a multifunction device for an aircraft, an embodiment with three insertion grooves on one side:
as shown in figure 1: the multifunctional device has a prismatic shape and is provided with three outer circular arc side surfaces 1 with the same top edge length, the radii of the three outer circular arcs are the same, and three circle centers form a regular triangle; the three sides are all provided with connecting devices which comprise physical fixed connecting devices, the physical fixed connecting devices on each side are three vertical insertion grooves 4, wherein the upper part of the middle insertion groove is provided with a bayonet 5 and a push-pull clip 6 which can be extended out. One of the power output interface and the two data communication interface devices are integrated with the push-pull clip 6.
As shown in fig. 1, the vertical insertion groove is a groove device with a large inside and a small outside, but the upper part and the lower part are consistent, and the proper connection mode is that the device is fixed in the horizontal direction by inserting in the form of an insertion strip from the upper part and the lower part, so that the push-pull clamp is pushed out to be clamped and is clamped in the vertical direction to be completely fixed.
It should be noted that, in fig. 1, the right arc side surface is provided with the push-pull clip 6, and the left arc side surface is provided with the bayonet 5, only for better illustrating the device structure, the actual situation is as shown in the invention, and the three arc side surfaces are provided with the push-pull clip 6 and the bayonet 5 for passing the push-pull clip 6.
The prismatic hollow is internally provided with batteries 2, three groups of the batteries 2 are connected in parallel, and each group is provided with six batteries in series.
The prism shape has upper cover plate 3, has interface 7 of input power on upper cover plate 3, has LED status display lamp 8, and the upper cover plate back has the circuit board, lays controller, attitude sensor, charging circuit and temperature control device on the circuit board, and the circuit is connected with battery and output power interface through power line 9, and is connected with the data communication interface of circular arc side through data line 10. The temperature control device can adopt the forms of semiconductor cooling and heating, forward current refrigeration and reverse current heating.
A multifunctional device for an aircraft, three sides respectively connecting three embodiments of rotor units: as shown in schematic 4: the multifunctional device 14 is connected to three rotor units 15 by side means, respectively. The three outer arc sides of the multifunctional device are respectively tightly attached to the duct walls of the three rotor wing units, and the duct wall of each rotor wing unit at each joint is provided with three rows of vertical insertion strips which are respectively inserted and fixed with the three vertical insertion grooves of the multifunctional device. The bayonet and the push-pull clip of the multifunctional device provide a connection mode of up-and-down fixation. The push-pull clip of the multifunctional device is integrated to provide an electric power interface and a data communication interface for the rotor wing unit.
A multifunction device for an aircraft, an embodiment of a socket on three sides: as shown in fig. 2: three sides of which the positions are distributed in a regular triangle are provided with vertical inserting grooves 11. The embodiment is suitable for a use scene that after the side surface of the multifunctional device is connected with the three rotor wing units, the multifunctional device is connected and fixed on the side edge.
A multifunction device for an aircraft, the implementation of internally connecting three sets of data communication interfaces is schematically shown in fig. 3: each side surface is provided with a group of data communication interface devices 12, and each group of data communication interface devices is provided with two data communication interfaces 13 which are respectively connected with the other two groups.
Claims (9)
1. A multifunction device for an aircraft, characterized by:
having a prismatic housing;
the prism shape has three side surfaces with the same length of the top edge, the three side surfaces are in the shape of an outer circular arc, the radii of the three outer circular arcs are the same, and three circle centers form a regular triangle; or the three side surfaces are planar, and the three formed planes form an included angle of 60 degrees with each other;
a socket containing input power;
the socket comprises 1 to 3 power output interfaces which are configured on three sides, wherein each side has at most one, and the output power comes from the input power;
the system comprises an attitude sensor and a processor, wherein the processor can read the data of the attitude sensor;
the device comprises 3 groups of data communication interface devices, wherein each group comprises 1 to 2 data communication interfaces, and the processor can output information including device posture data through the data communication interfaces; the data communication interface device is configured to three sides, each side has at most one group, each group is internally communicated with the communication interface group on the other side, and the processor is communicated with all the data communication interfaces of 1 group.
2. A multifunction device for an aircraft according to claim 1, characterized in that:
the battery is connected in parallel by 1 to 3 groups, and each group is formed by connecting a plurality of batteries in series;
the input power can be used for charging the battery, and the output power can be obtained from the battery;
the processor may obtain battery charging information or control battery charging.
3. A multifunction device for an aircraft according to claim 1, characterized in that:
the processor can control the temperature control device and can communicate control information through the data communication device.
4. A multifunction device for an aircraft according to claim 2, characterized in that:
the processor can control the temperature control device and can communicate control information through the data communication device.
5. Multifunction device for aircraft according to claim 4, characterized in that:
the display device is in a dot matrix, character or color form, and the processor controls display output.
6. A multifunctional device for an aircraft according to one of claims 1 to 5, characterized in that:
the three sides are all provided with connecting devices, the connecting devices comprise physical fixed connecting devices, and the physical fixed connecting devices comprise 1 or more plug-in devices, push-pull bayonets and screw holes which are combined randomly.
7. A multifunction device for an aircraft according to claim 6, characterized in that:
the physical fixed connecting device comprises 1 or more vertical insertion grooves, wherein the insertion grooves are arranged in the middle, and the insertion grooves are provided with extensible push-pull clips which are used for being transversely clamped and fixed after being vertically inserted.
8. A multifunction device for an aircraft according to claim 6, characterized in that:
the connecting device comprises three sides, wherein the positions of the three sides are regular triangles, the three sides are provided with connecting and fixing devices, and the connecting and fixing devices have connecting and fixing functions at least two positions of the upper side, the middle side and the lower side.
9. A multifunction device for an aircraft according to claim 7, characterized in that:
the connecting device comprises three sides, wherein the positions of the three sides are regular triangles, the three sides are provided with connecting and fixing devices, and the connecting and fixing devices have connecting and fixing functions at least two positions of the upper side, the middle side and the lower side.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922138255 | 2019-12-03 | ||
| CN2019221382555 | 2019-12-03 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214029128U true CN214029128U (en) | 2021-08-24 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022737619.4U Expired - Fee Related CN214029128U (en) | 2019-12-03 | 2020-11-24 | Multifunctional device for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214029128U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114435609A (en) * | 2021-12-28 | 2022-05-06 | 中国航天空气动力技术研究院 | Airborne equipment temperature control box suitable for near space unmanned aerial vehicle and unmanned aerial vehicle |
-
2020
- 2020-11-24 CN CN202022737619.4U patent/CN214029128U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114435609A (en) * | 2021-12-28 | 2022-05-06 | 中国航天空气动力技术研究院 | Airborne equipment temperature control box suitable for near space unmanned aerial vehicle and unmanned aerial vehicle |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20210824 |
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| CF01 | Termination of patent right due to non-payment of annual fee |