CN214751530U

CN214751530U - Aircraft and data interface module thereof

Info

Publication number: CN214751530U
Application number: CN202120739215.0U
Authority: CN
Inventors: 赵德力; 周双久; 李�杰; 张书存; 谢东武; 杨明宇
Original assignee: Guangdong Huitian Aerospace Technology Co Ltd
Current assignee: Guangdong Huitian Aerospace Technology Co Ltd
Priority date: 2021-04-12
Filing date: 2021-04-12
Publication date: 2021-11-16
Anticipated expiration: 2031-04-12

Abstract

The present application relates to an aircraft and a data interface module therefor, the data interface module comprising: the aircraft control system comprises a data output interface used for being connected with a flight control system of the aircraft, a processor used for outputting data to the data output interface, and at least two data interfaces used for being connected with at least two aerial plug of the aircraft. Wherein, the processor is connected with the at least two data interfaces respectively, and the at least two data interfaces include: a first data interface for connection with a first aerial pod of the aircraft, and a second data interface for connection with a second aerial pod of the aircraft; the first data interface and the second data interface are interfaces of the same type, or the first data interface and the second data interface are interfaces of different types. The data processing pressure of the flight control system can be reduced.

Description

Aircraft and data interface module thereof

Technical Field

The application relates to the field of aircraft, in particular to an aircraft and a data interface module thereof.

Background

In the related art, an operation signal of the manned aircraft is directly transmitted to the flight control system through various operation levers, and the flight control system correspondingly controls the aircraft after receiving the operation signal of the various operation levers.

However, the standards of the output interfaces of the various operation levers are not uniform, for example, the direction push rod and the accelerator push rod respectively use different operation interfaces to transmit data, on one hand, the non-uniformity of the operation interfaces limits the extensibility and expandability of an operation system of the aircraft; on the other hand, the flight control system needs to receive different types of operation signals of various operation levers and perform data conversion, which results in a large data processing pressure of the flight control system.

SUMMERY OF THE UTILITY MODEL

In order to solve or partially solve the problems in the related art, the application provides an aircraft and a data interface module thereof, which can reduce the data processing pressure of a flight control system.

A first aspect of the application provides a data interface module for an aircraft, comprising: the data output interface is used for being connected with a flight control system of the aircraft; a processor for outputting data to the data output interface; and at least two data interfaces for interfacing with at least two aerial outlets of the aircraft;

wherein, the processor is connected with the at least two data interfaces respectively, and the at least two data interfaces include: a first data interface for connection with a first aerial pod of the aircraft, and a second data interface for connection with a second aerial pod of the aircraft; the first data interface and the second data interface are interfaces of the same type, or the first data interface and the second data interface are interfaces of different types.

In some embodiments, the at least two data interfaces further comprise: a third data interface for connection with a third aerial plug of the aircraft;

wherein the third data interface is the same data interface as the first data interface.

In some embodiments, the third data interface and the first data interface are USB data interfaces; and the second data interface is a data interface matched with the IO aerial plug.

In some embodiments, at least one of the at least two data interfaces is a USB interface.

In some embodiments, the first data interface is further connected with a fourth hub of the aircraft.

In some embodiments, the data output interface is a data output interface that matches a fifth airline plug of the aircraft; and a serial port to SBUS circuit is arranged between the data output interface and the processor.

In some embodiments, a heat sink and/or a power module connected to the processor is also included.

In some embodiments, further comprising a power module connected to the processor, wherein:

the power supply module is provided with at least one power supply interface for connecting with at least one power supply aerial plug of the aircraft; alternatively, the first and second electrodes may be,

the power supply module is provided with at least two power interfaces for aerial plug connection with at least two power sources of the aircraft.

In some embodiments, the at least two pods are at least two of a pod that interfaces with a throttle operator of the aircraft, a pod that interfaces with a directional operator, a pod that interfaces with a heading operator, and an IO pod.

The second aspect of the present application provides a manned vehicle, which has a flight control system, a plurality of flight control devices, and the data interface module connected between the flight control system and the flight control devices.

According to some embodiments of the application, a data interface module is arranged, and the control data of a plurality of flight control devices of the aircraft are acquired through at least two data interfaces, so that the processor can process the control data of each flight control device into control data with the same data format, and then the control data are transmitted to the flight control system of the aircraft through a data output interface; therefore, the flight control data can be acquired through the unified data interface module, the flight control system can use the data with the same structure for calculation or processing, the flight control system does not need to receive and convert the control data of each flight control device independently, and the data processing pressure of the flight control system is reduced.

Furthermore, the first data interface and the second data interface are interfaces of the same type, so that the data interface module can collect data through the unified data interface, and the data processing pressure of the data interface module is reduced.

In addition, the data interface module is provided with the data interface matched with the IO aviation plug, so that the data interface module is compatible with various control components, and the ductility and expandability of the aircraft are improved.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the application.

Drawings

The foregoing and other objects, features and advantages of the application will be apparent from the following more particular descriptions of exemplary embodiments of the application, as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the application.

FIG. 1 illustrates a block diagram of a data interface module of an aircraft according to an embodiment of the present application;

FIG. 2 illustrates a block diagram of a data interface module of an aircraft according to another embodiment of the present application;

FIG. 3 illustrates a block diagram of a data interface module of an aircraft according to another embodiment of the present application;

FIG. 4 illustrates a block diagram of a data interface module of an aircraft according to another embodiment of the present application;

FIG. 5 illustrates a block diagram of a data interface module of an aircraft according to another embodiment of the present application;

FIG. 6 is a block diagram illustrating a manned aircraft according to one embodiment of the present application.

Reference numerals:

100. 150, 300, 400, 500: a data interface module; 200: a flight control system; 30: a data output interface; 40: a processor; 51: a first data interface; 52: a second data interface; 53: a third data interface; 61: a first air navigation plug; 62: a second aviation plug; 63: a third air inserting; 64: a fourth aviation plug; 65: fifth air inserting; 66: a sixth aviation plug; 67: power supply aviation plug; 70: a serial port to SBUS circuit; 80: a heat sink; 90: a power supply module; 600: a manned aerial vehicle; 610: flight control device.

Detailed Description

Preferred embodiments of the present application will be described in more detail below with reference to the accompanying drawings. While the preferred embodiments of the present application are shown in the drawings, it should be understood that the present application may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. As used in this application and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

It should be understood that although the terms "first," "second," "third," etc. may be used herein to describe various information, these information should not be limited to these terms. These terms are only used to distinguish one type of information from another. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the present application. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "at least one" means one or more than one, and "a plurality" means two or more than two unless specifically limited otherwise.

Unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly and can include, for example, direct connection, indirect connection through an intermediary, communication between two elements, or an interaction between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

In the related technology, the standards of the output interfaces of various operation levers of the manned aircraft are not uniform, for example, a direction push rod and an accelerator push rod respectively use different operation interfaces to transmit data, on one hand, the non-uniformity of the operation interfaces limits the extensibility and expandability of an operation system of the aircraft; on the other hand, the flight control system needs to receive different types of operation signals of various operation levers and perform data conversion, which results in a large data processing pressure of the flight control system. The application provides a manned vehicle and data interface module thereof, and this data interface module has better data receiving and processing ability, can alleviate flight control system's data processing pressure.

The technical solutions of the embodiments of the present application are described in detail below with reference to the accompanying drawings.

Fig. 1 illustrates a block diagram of a data interface module 100 of an aircraft according to an embodiment of the present application.

Referring to fig. 1, the data interface module 100 of the aircraft of the present embodiment includes: a data output interface 30 for connection with a flight control system 200 of an aircraft, a processor 40 for outputting data to the data output interface 30, and at least two data interfaces for connection with at least two aerial plug-ins of the aircraft, the at least two data interfaces comprising: a first data interface 51 for connection with a first aircraft pod 61 and a second data interface 52 for connection with a second aircraft pod 62; wherein the processor 40 is connected with at least two

data interfaces

51, 52 respectively

In some embodiments, the processor 40 is configured to: acquiring the control data transmitted by the at least two

data interfaces

51, 52, processing the data transmitted by the at least two data interfaces into the control data with the same data format according to a preset rule, and outputting the processed control data.

The aviation plug is one of connectors, comprises a plug and a socket, is sourced from the military industry, and is named after being used on airplanes, namely the aviation plug. Data interaction between subsystems of an aircraft is typically by means of air-plug and air-plug cables.

In some embodiments, the at least two interposers are at least two of a throttle operator interface interposer, a direction operator interface interposer, a heading operator interface interposer, and an IO interposer of an aircraft, but are not limited to such, and may also be interposers with other flight control devices. The accelerator operating device of the aircraft can be an accelerator push rod, and the rotating speed of the accelerator of the aircraft is controlled by controlling the accelerator push rod; the direction operating device can be a direction push rod, and the aircraft is controlled to fly in the front, back, left and right directions by controlling the direction push rod; the heading operating device can be a yaw rod, and the aircraft is controlled to rotate clockwise or anticlockwise by controlling the yaw rod, namely, the heading of the aircraft is controlled. The IO aviation plug can realize the collection of some other types of flight control data, for example, the IO aviation plug can be connected with an external switch or a button device to realize the collection of switch or button signals.

In some embodiments, at least one of the at least two data interfaces for connecting with at least two aerial outlets of the aircraft is a USB interface. USB is Universal Serial Bus (USB for short) interface, and the USB interface can include various types of USB interfaces such as Type A, Type B, Micro A, Micro B, Mini A, Mini B, Type C, and the USB interface is the unified data interface of standard, has hot plug, transmission distance characteristics far away. It is understood that the data interface is not limited to a USB data interface, for example, in some embodiments, the data interface may also be a Lightning interface, etc.

The aerial plug connected with the USB data interface is a USB aerial plug. One end of the USB aerial plug connected with the control device of the aircraft is matched with the aerial plug cable connected with the flight control device, and the other end of the USB aerial plug connected with the USB data interface is matched with the USB interface of the USB data interface. In practical use, the USB expansion card can be used for expanding the number of interfaces of the USB data interface.

In some embodiments, the first data interface 51 and the second data interface 52 are the same type of interface, for example, may both be USB data interfaces.

In some embodiments, the first data interface 51 and the second data interface 52 are different types of interfaces; for example, one of the first data interface 51 and the second data interface 52 may be a USB data interface, and the other may be a data interface directly connected to the IO aviation plug or connected through a cable, and the data interface may be disposed outside the processor or integrated inside the processor.

The flight control system 200 of the aircraft is used for flight control of the aircraft, and comprises a flight controller, wherein the controller can generate a control command according to control data provided by the data interface module, and the control command is executed by an execution mechanism to realize flight attitude adjustment corresponding to the control data.

Data output interface 30 may be directly connected to flight control system 200 via a cable, or may be connected to flight control system 200 via an air-plug and air-plug cable, or via other types of middleware or intermediate circuitry.

The processor 40 obtains the manipulation data transmitted by the at least two data interfaces, processes the data transmitted by the at least two data interfaces into the manipulation data with the same data format according to a preset rule, and outputs the processed manipulation data to the data output interface 40. The processor 40 may be directly connected to the data output interface 30, or may be connected to the data output interface 30 through an intermediate circuit.

In the embodiment of the application, the data interface module is arranged, and the control data of the flight control devices of the aircraft are acquired through the at least two data interfaces, so that the processor can process the control data of the flight control devices into the control data with the same data format, and then the control data are transmitted to the flight control system of the aircraft through the data output interface. Therefore, the flight control data can be acquired through the unified data interface module, and the flight control system can use the data with the same structure for calculation or processing, so that the flight control system does not need to receive and convert the control data of each flight control device independently, and the data processing pressure of the flight control system is reduced.

Fig. 2 illustrates a block diagram of a data interface module 150 of an aircraft according to another embodiment of the present application.

Referring to fig. 2, the difference between the present embodiment and the embodiment shown in fig. 1 is that at least two data interfaces of the data interface module 150 further include: a third data interface 53 for connection to a third aircraft pod 63.

In some embodiments, the third data interface 53 is the same type of interface as the first data interface 51.

In some embodiments, the first data interface 51 and the second data interface 52 are different types of interfaces.

In one specific implementation, the first data interface 51 and the third data interface 53 are both USB interfaces, and the second data interface 52 is an IO air interface. By configuring the first data interface and the third data interface as the same type of interface, the data interface module can acquire data through the unified data interface, and the data processing pressure of the data interface module is reduced. Furthermore, the data interface module is provided with the data interface matched with the IO aerial plug, so that the data interface module is compatible with various control components, and the ductility and expandability of the aircraft are improved.

Fig. 3 illustrates a block diagram of a data interface module 300 of an aircraft according to another embodiment of the present application.

Referring to fig. 3, the present embodiment differs from the embodiment shown in fig. 2 in that the first data interface 51 is also connected to a fourth navigation plug 64 of the aircraft. The fourth aviation plug 64 can be a reserved aviation plug for expansion, and can also be connected with another flight control device different from the flight control devices connected with the first aviation plug to the third aviation plugs 61-63.

It is understood that, in the present embodiment, the first data interface 51 and/or the second data interface 52 of the data interface module 300 may be connected to a plurality of aviation plugs, that is, one data interface can be connected to a plurality of flight control devices. In one embodiment, the first data interface 51 and/or the second data interface 52 may be configured with an interface expansion device (e.g., an interface expansion card) to provide more data interfaces, so that the same data interface can be connected to multiple air sockets.

In some implementations, one or more data interfaces can be reserved so as to be convenient for expanding and connecting other flight control devices and improve the compatibility of the data interface module; in addition, when the aviation plug in use breaks down, the aviation plug can be quickly converted and connected to the reserved data interface, and the transmission safety of the control data of the aircraft is greatly improved.

Fig. 4 illustrates a block diagram of a data interface module 400 of an aircraft according to another embodiment of the present application.

Referring to fig. 4, compared with the embodiment of fig. 3, in this embodiment, the data output interface 30 is connected to the flight control system 200 through a fifth aviation plug 65 of the aircraft, and the data output interface 30 is a data output interface matched with the fifth aviation plug 65; a serial-to-SBUS circuit 70 is included between data output interface 30 and processor 40.

Sbus (serial bus) is a serial bus communication protocol that uses negative logic, i.e., a low level of "1" and a high level of "0". The SBUS serial bus is adapted to interface with flight control system 200. It may be connected to a plurality of devices, each connected to it via a HUB, to obtain respective control information. The processor 40 outputs the processed control data with the same type format to the serial-to-SBUS circuit 70 through the serial output interface, and the serial-to-SBUS circuit 70 converts the serial data output by the processor into a negative-logic serial bus signal and provides the negative-logic serial bus signal to the flight control system 200 through the data output interface 30 and the fifth navigation plug 65.

In this embodiment, the first data interface 51 is used for connecting with the first navigation plug 61 and the fourth navigation plug 64, the second data interface 52 is used for connecting with the second navigation plug 62 and the sixth navigation plug 66, the data output interface 30 is used for connecting with the fifth navigation plug 65, and the third data interface 53 is used for connecting with the third navigation plug 63.

In a specific example, the first data interface and the second data interface are USB data interfaces, the third data interface is an IO air interface, and the data output interface is a SIG air interface; three of the first aerial plug, the second aerial plug, the fourth aerial plug and the sixth aerial plug are respectively an aerial plug butted with an accelerator operating device of an aircraft, an aerial plug butted with a direction operating device and an aerial plug butted with a course operating device, the other aerial plug is a reserved aerial plug for expansion, the third aerial plug is an IO aerial plug, and the fifth aerial plug is an SIG aerial plug.

Fig. 5 shows a block diagram of a data interface module 500 of an aircraft according to another embodiment of the present application.

Referring to fig. 5, compared to the data interface module 100 of fig. 1, the data interface module 500 of the present embodiment further includes a heat sink 80 and a power supply module 90 connected to the processor 40. It will be appreciated that in other embodiments, the interface data module may include one of a heat sink and a power module.

The heat sink 80 includes, but is not limited to, the following kinds of heat sinks 80: a natural cooling radiator, an air cooling radiator, a liquid cooling radiator, a cold plate radiator and a heat pipe radiator, wherein the radiator 80 is used for dissipating heat for the data interface module, particularly the power supply module 90; the power supply module 90 provides power supply for the processor 40 to ensure the normal operation of the processor 40.

In the present embodiment, the power module 90 is provided with at least two power interfaces for connecting with at least two power jacks 67 of the aircraft, it being understood that the power module 90 may also be provided with only one power interface for connecting with one power jack 67 of the aircraft. The power supply module 90 is configured to selectively enable one of the at least two power interfaces to supply power to the processor 40, and perform switching of the power interface when a preset condition is met. The power supply aviation plug 67 of the aircraft is connected with the power supply module 90 through a power supply interface, and the power supply module 90 provides power supply for the aircraft through the power supply interface.

In this embodiment, at least two power interfaces are provided for the power supply module 90, so that the at least two power interfaces are respectively and correspondingly connected to the at least two power jacks 67, for example, when one power jack 67 fails, the other power jacks 67 connected to the power supply module 90 can be quickly switched to, and thus, the problem that the flight control data cannot be obtained by the flight control system 200 due to power failure or failure of the power supply is avoided, so that the flight fault of the aircraft occurs. At least two power jacks 67 are preferably connected to a plurality of mutually independent power sources of the same or different types.

FIG. 6 illustrates a block diagram of a manned aircraft 600 according to one embodiment of the present application. The manned vehicle may be, for example, an electric manned multi-rotor aircraft, but is not limited thereto.

Referring to fig. 6, the present embodiment shows a manned aircraft 600 having a flight control system 200, a plurality of flight control devices 610, and a data interface module connected between the flight control system 200 and the flight control devices 610, where the data interface module is denoted by 100 in fig. 6, but it is understood that the data interface module in the present embodiment may be any one of the

data interface modules

100, 150, 300, 400, 500 described in the above embodiments.

The aspects of the present application have been described in detail hereinabove with reference to the accompanying drawings. In the above embodiments, the descriptions of the respective embodiments have respective emphasis, and for parts that are not described in detail in a certain embodiment, reference may be made to related descriptions of other embodiments. Those skilled in the art should also appreciate that the acts and modules referred to in the specification are not necessarily required in the present application. In addition, it can be understood that the steps in the method of the embodiment of the present application may be sequentially adjusted, combined, and deleted according to actual needs, and the modules in the device of the embodiment of the present application may be combined, divided, and deleted according to actual needs.

Having described embodiments of the present application, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the spirit of scope of the described embodiments. The terminology used herein is chosen in order to best explain the principles of the embodiments, the practical application, or improvements made to the technology in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.

Claims

1. A data interface module for an aircraft, comprising:

the data output interface is used for being connected with a flight control system of the aircraft;

a processor for outputting data to the data output interface; and the number of the first and second groups,

at least two data interfaces for interfacing with at least two aerial outlets of the aircraft;

2. The data interface module of claim 1, wherein the at least two data interfaces further comprise:

a third data interface for connection with a third aerial plug of the aircraft;

3. The data interface module of claim 2, wherein:

the third data interface and the first data interface are USB data interfaces;

and the second data interface is a data interface matched with the IO aerial plug.

4. The data interface module of claim 1, wherein:

at least one of the at least two data interfaces is a USB interface.

5. The data interface module of claim 1, wherein the first data interface is further connected with a fourth hub of the aircraft.

6. The data interface module of claim 1,

the data output interface is matched with a fifth aviation plug of the aircraft;

and a serial port to SBUS circuit is arranged between the data output interface and the processor.

7. A data interface module according to any one of claims 1 to 6, further comprising a heat sink and/or a power supply module connected to the processor.

8. The data interface module of any of claims 1 to 6, further comprising a power module coupled to the processor, wherein:

9. A data interface module according to any one of claims 1 to 2 or 4 to 6, wherein: the at least two aerial plug are at least two of an aerial plug butted with an accelerator operating device of the aircraft, an aerial plug butted with a direction operating device, an aerial plug butted with a course operating device and an IO aerial plug.

10. A manned vehicle having a flight control system, a plurality of flight control devices, and a data interface module according to any one of claims 1 to 9 connected between the flight control system and the plurality of flight control devices.