CN114261522A - Airborne system architecture and aircraft - Google Patents
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Abstract
The invention relates to an airborne system architecture and an aircraft comprising the same, wherein the airborne system architecture has a location functional characteristic, and executes differentiated system functions due to location layout, and mainly comprises a plurality of functional area systems (1), an energy interconnection transmission path (2) and two communication networks (3, 4), wherein the functional area systems (1) are distributed in each area of the aircraft according to needs, main functions in each functional area system (1) are relatively independent and complete, communication is carried out through the 2 communication networks (3, 4), and various energy transmission among areas is carried out through the energy interconnection transmission path (2).
Description
Technical Field
The invention relates to the field of aircrafts, in particular to an airborne system architecture and an aircraft.
Background
In the field of aviation, currently, airborne systems are generally in a function discrete architecture conforming to the ATA2200 standard, each function system is mainly in a centralized architecture, the boundaries of each function system in civil aircrafts are clear, and analysis on the layout of the airborne systems of the existing commercial transport aircraft can find that the distribution of the airborne systems presents certain function location attributes, namely the function systems are concentrated according to regional classification, and different regions have different remarkable function characteristics, which is shown in fig. 1.
In fig. 2, the functional attributes of the areas and the zone locations are properly distributed, and in most civil aircrafts, a great number of controllable facilities are concentrated in the aircraft nose area and have high man-machine interaction attribute, so that the aircraft nose area is positioned as a cabin functional area due to the zone location functional attribute. The wingspan area integrates energy and control mechanisms such as a power device, a generator, a hydraulic pump and a control surface mechanism and the like, and provides power energy and the capability of controlling the airplane, so that the wingspan area is positioned as a power control area due to the regional functional attribute. The tail section area integrates energy sources and control mechanisms such as an auxiliary power device and a control surface mechanism, provides power energy sources for the airplane and has the capability of controlling the airplane, and therefore the tail section area is positioned as a power control area due to the regional functional property. The middle area of the fuselage corresponding to the wingspan area mainly concentrates energy conversion, transfer and transmission facilities and provides an energy transfer function for normal operation of other areas, so that the middle area of the fuselage is positioned as a conversion functional area due to location functional attributes. Other fuselage regions have a high degree of functional commonality, these regions primarily providing the energy and environmental resources required for the passenger and non-passenger cabin regions, such as lighting, power, comfort, cabin environmental awareness, networking, etc., so that other fuselage regions are located as general functional zones due to location-functionalized attributes. In addition, the two parts of man-machine interaction and energy transfer are respectively added to the machine head and the middle area of the machine body on the basis of the functions of other machine body areas, and the difference shows the zone bit functional characteristics of each area.
Based on the characteristics, the aircraft can be divided into a plurality of parts according to the areas, each part is distributed with proper functional attributes based on the layout position, so that each area has certain functional attributes, and all the areas are combined together to form a complete aircraft-mounted system.
According to the functional zoned airborne system architecture provided by the invention, the aircraft is subjected to regional division, and specific function integration and modular design are carried out on a regional system, so that the functional integrity and the obvious characteristics of a certain degree are ensured, a plurality of defects of the existing aircraft design are overcome, the flexible maneuvering characteristics of the regional part are improved through the universalization and modular design, the existing regional system resources are easily utilized to the maximum extent, the mass production, the test, the acceptance and delivery are promoted, the development cost is reduced, the product operation economy is improved, and the development period is shortened.
Disclosure of Invention
The invention provides an airborne system architecture which has a zone functional characteristic, executes differentiated system functions due to zone layout and mainly comprises a plurality of functional area systems (1), an energy interconnection transmission channel (2) and two communication networks (3, 4), wherein the functional area systems (1) are distributed in each area of an aircraft according to needs, main functions in each functional area system (1) are relatively independent and complete, communication is carried out through the 2 communication networks (3, 4), and various energy transmission among the areas is carried out through the energy interconnection transmission channel (2).
The energy interconnection transmission path (2) is used for transmission of power and/or gas sources, the communication networks (3, 4) adopt aviation special buses, the buses CAN be ARINC664, ARINC429, MIL1553B, CAN buses, RS485 buses, TTP buses or other available digital buses, and each regional system (1) provides a redundancy communication function between regional systems through the two communication networks (3, 4).
The functionalized area system (1) forms a plurality of functionalized area systems (1) due to the difference of functional attributes, and mainly comprises the following characteristics:
-the general function area (10) is composed of an emergency function (11) part, a general function (12) part and a cabin function (13) part;
-the transfer function area (20) is composed of an emergency function (11) part, a general function (12) part, a cabin function (13) and an energy transfer (21) part;
-the cabin functional area (30) is composed of an emergency function (11) part, a general function (12) part, a cabin function (13) and a human-machine interaction (31) part;
-the power steering area (40) is composed of a power integration (41) part and a steering function (42) part;
-wherein the general functional area (10) can be used as a base and in the state of having the characteristics of generalization and modularization, the corresponding energy transfer (21) part and the human-computer interaction (31) part can be added to be upgraded into the conversion functional area (20) and the cockpit functional area (30).
The functional regional system (1) has the regional functional safety of dual-redundancy, and each regional system is the redundant framework of binary channels, mainly has two kinds of modes:
-a dual redundancy (100) of dual functional configurations, i.e. functional configurations, for modules in an area, mainly represented by a barrel-section type transport aircraft architecture (101), a wing-body fusion aircraft architecture (102) and a dish aircraft architecture (103), as well as other types of aircraft architectures;
the other is a whole-area double-channel physical layout, namely a physical layout double-redundancy (200), which is mainly represented by a barrel section type transport aircraft structure (201), a wing body fusion type aircraft structure (202) and a saucer type aircraft structure (203), and other types of aircraft structures.
The onboard system architecture has flexible application characteristics, and can be applied to various aircrafts in various forms, such as a traditional barrel section type transport plane, a wing body fusion type aircraft, a dish type aircraft and other types of aircrafts:
when the method is applied to a traditional cylinder segment type conveyor, functional attribute definition can be carried out on each area system according to the specific condition of the aircraft, so that all areas are combined together to form a fully functional cylinder segment type conveyor;
when the disk-type aircraft is applied to the disk-type aircraft, a 1+ N modular layout can be adopted according to the specific situation of the aircraft, namely, the central area is a circular part (namely 1), the peripheral annular area is formed by combining any identical parts (namely N), and each part is in a complete closed loop with functions and can independently operate;
when the method is applied to the wing-body fusion aircraft, the functional attribute definition can be carried out on each region system according to the specific condition of the aircraft, so that all regions are combined together to form a fully functional wing-body fusion aircraft.
The functions of the area system in the airborne system architecture have diversity, a certain degree of integrity and significant functional features, a plurality of functional systems are integrated in the area, and a certain degree of functional integrity and significant functional features are maintained, wherein the plurality of functional systems include but are not limited to the functional system defined by the ATA2200 specification, and for a certain area system, the configuration of each functional system and the functional integrity in the area is carried out according to the actual situation of the area.
The airborne system architecture has wide application characteristics, and the number of areas is not limited, so that the architecture can be applied to various area division forms, can also be applied to other various aircrafts except the aircrafts of the type, is particularly suitable for modular aircrafts, and can also be applied to medium-sized and large-sized air vehicles such as hovercrafts and the like.
The present invention aims to provide an aircraft comprising an on-board system architecture according to any one of the preceding claims.
Drawings
The invention will be better understood from a reading of the detailed description of the embodiments given as an example and the attached drawings. In the drawings.
Fig. 1 shows a schematic distribution diagram of a functional system on board a commercial transport aircraft.
FIG. 2 is a schematic diagram of a location-functionalized on-board system architecture according to the present invention.
Fig. 3 shows a schematic diagram of the classification of the area systems in the architecture and their functional composition.
Fig. 4 shows a regional system diagram of functional configuration dual redundancy.
FIG. 5 shows a region system diagram of physical layout dual redundancy.
Fig. 6 is a schematic view of a dual-redundancy regional system of a function configuration of a conventional segmental transport machine.
Fig. 7 is a schematic view of a regional system showing the dual redundancy of the physical layout of a conventional tube-section conveyor.
Fig. 8 shows a regional system schematic of the dual redundancy of the wing-body fusion aircraft functional configuration.
Fig. 9 shows a regional system schematic of the dual redundancy of the wing-body fusion aircraft physical layout.
Fig. 10 shows a schematic view of a zone system for dual redundancy of a saucer aircraft functional configuration.
Fig. 11 shows a schematic diagram of a region system for the dual redundancy of the physical layout of a saucer-type aircraft.
The accompanying drawings are included to provide a further understanding of embodiments of the invention. Which illustrate embodiments and serve, in connection with the description, to explain the principles and concepts of the invention. Other embodiments and many of the above advantages can be derived from a review of the figures. The elements of the drawings are not necessarily to scale relative to each other.
Detailed Description
Fig. 2 shows a zone-functionalized airborne system architecture, which performs differentiated system functions due to zone location layout, and mainly includes a plurality of functional area systems (1), an energy interconnection transmission path (2), and two communication networks (3, 4), wherein the functional area systems (1) are distributed in each area of an aircraft as required, and main functions in each functional area system (1) are kept relatively independent and complete, and communicate through the 2 communication networks (3, 4), and perform inter-area multiple energy transmission through the energy interconnection transmission path (2).
The energy interconnection transmission path (2) is used for transmitting power and/or gas sources, the communication networks (3, 4) adopt aviation special buses, the buses CAN be ARINC664, ARINC429, MIL1553B, CAN buses, RS485 buses, TTP buses or other available digital buses, and each regional system (1) provides a redundancy communication function between regional systems through the two communication networks (3, 4).
The regional system (1) forms a plurality of functional regional systems (1) due to the difference of functional attributes, and mainly comprises the following characteristics:
-the general function area (10) is composed of an emergency function (11) part, a general function (12) part and a cabin function (13) part;
-the transfer function area (20) is composed of an emergency function (11) part, a general function (12) part, a cabin function (13) and an energy transfer (21) part;
-the cabin functional area (30) is composed of an emergency function (11) part, a general function (12) part, a cabin function (13) and a human-machine interaction (31) part;
-the power steering area (40) is composed of a power integration (41) part and a steering function (42) part;
-wherein the general functional area (10) can be used as a base and in the state of having the characteristics of generalization and modularization, the corresponding energy transfer (21) part and the human-computer interaction (31) part can be added to be upgraded into the conversion functional area (20) and the cockpit functional area (30).
An example of the classification and functional composition of a regional system is shown in fig. 3.
The functional regional system (1) has the regional functional safety of dual-redundancy, and each regional system is the redundant framework of binary channels, mainly has two kinds of modes:
-a dual redundancy (100) of dual functional configurations, i.e. functional configurations, for modules in an area, mainly represented by a barrel-section type transport aircraft architecture (101), a wing-body fusion aircraft architecture (102) and a dish aircraft architecture (103), as well as other types of aircraft architectures;
the other is a whole-area double-channel physical layout, namely a physical layout double-redundancy (200), which is mainly represented by a barrel section type transport aircraft structure (201), a wing body fusion type aircraft structure (202) and a saucer type aircraft structure (203), and other types of aircraft structures.
The functions of the area system in the airborne system architecture have diversity, a certain degree of integrity and significant functional features, a plurality of functional systems are integrated in the area, and a certain degree of functional integrity and significant functional features are maintained, wherein the plurality of functional systems include but are not limited to the functional system defined by the ATA2200 specification, and for a certain area system, the configuration of each functional system and the functional integrity in the area is carried out according to the actual situation of the area.
The airborne system architecture has wide application characteristics, and the number of areas is not limited, so that the architecture can be applied to various area division forms, can also be applied to other various aircrafts except the aircrafts of the type, is particularly suitable for modular aircrafts, and can also be applied to medium-sized and large-sized air vehicles such as hovercrafts and the like.
The aircraft assembled based on the onboard system architecture of the present invention is not limited to the above embodiments, and is only illustrated here.
Claims (8)
1. The utility model provides an airborne system architecture, its characterized in that airborne system architecture has the regional functional characteristic, and it carries out differentiation system function because of the location overall arrangement, mainly includes a plurality of functional area system (1), energy interconnection transmission path (2) and two communication network (3, 4), functional area system (1) distributes as required in each region of aircraft, and the main function keeps relatively independent complete in each functional area system (1) to communicate through 2 communication network (3, 4), carry out regional multiple energy transmission through energy interconnection transmission path (2).
2. The on-board system architecture according to claim 1, characterized in that the energy interconnect transmission path (2) is used for transmission of power and/or gas, the communication networks (3, 4) use aircraft-specific buses, which may be ARINC664, ARINC429, MIL1553B, CAN bus, RS485 bus, TTP bus or other available digital buses, and each regional system (1) provides inter-regional redundancy communication functions through two communication networks (3, 4).
3. The zone system (1) according to claim 1, characterized in that a plurality of functionalized zone systems (1) are formed due to the difference of functional attributes, mainly including but not limited to the following features:
-the general function area (10) is composed of an emergency function (11) part, a general function (12) part and a cabin function (13) part;
-the transfer function area (20) is composed of an emergency function (11) part, a general function (12) part, a cabin function (13) and an energy transfer (21) part;
-the cabin functional area (30) is composed of an emergency function (11) part, a general function (12) part, a cabin function (13) and a human-machine interaction (31) part;
-the power steering area (40) is composed of a power integration (41) part and a steering function (42) part;
-wherein the general functional area (10) can be used as a base and in the state of having the characteristics of generalization and modularization, the corresponding energy transfer (21) part and the human-computer interaction (31) part can be added to be upgraded into the conversion functional area (20) and the cockpit functional area (30).
4. The functionalized regional system (1) of claim 1, having dual redundancy regional functional security, each regional system being a dual-channel redundancy architecture, with two main modes:
-a dual redundancy (100) of dual functional configurations, i.e. functional configurations, for modules in an area, mainly represented by a barrel-section type transport aircraft architecture (101), a wing-body fusion aircraft architecture (102) and a dish aircraft architecture (103), as well as other types of aircraft architectures;
the other is a whole-area double-channel physical layout, namely a physical layout double-redundancy (200), which is mainly represented by a barrel section type transport aircraft structure (201), a wing body fusion type aircraft structure (202) and a saucer type aircraft structure (203), and other types of aircraft structures.
5. The architecture of claim 1, wherein the flexible application features of the architecture can be applied in various forms to various aircraft, such as conventional tube-section transport aircraft, fusee aircraft, dish aircraft, and other types of aircraft:
when the airborne system architecture is applied to a traditional tube segment type conveyor, functional attribute definition can be carried out on each area system according to the specific situation of the aircraft, so that all areas are combined together to form a fully functional tube segment type conveyor;
when the airborne system architecture is applied to a saucer-type aircraft, a 1+ N modular layout can be adopted according to the specific situation of the aircraft, namely, a central area is a circular part (namely 1), a peripheral annular area is formed by combining any identical parts (namely N), and each part is in a complete closed loop in function and can independently operate;
when the onboard system architecture is applied to a wing-body fusion aircraft, the functional attribute definition can be performed on each region system according to the specific situation of the aircraft, so that all regions are combined together to form a fully functional wing-body fusion aircraft.
6. The architecture of claim 1, wherein the functions of the regional system have diversity, a certain degree of integrity and significant features, and a plurality of functional systems are integrated in the region and maintain a certain degree of functional integrity and significant features, wherein the plurality of functional systems include but are not limited to the functional systems defined in the ATA2200 specification, and for a certain regional system, the configuration of each functional system and functional integrity in the region is performed according to the actual situation of the region.
7. The architecture of claim 1, characterized by the broad application characteristics, since the number of zones is not limited, the architecture can be applied to various zone division forms, and it can also be applied to other types of aircrafts besides the above type, especially to modular aircrafts, as well as to air vehicles such as medium-sized and large-sized flying cars.
8. The present invention aims to provide an aircraft comprising an on-board system architecture according to any one of the preceding claims.
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107211287A (en) * | 2014-08-29 | 2017-09-26 | 峰鸟航空科技公司 | The system and method that regional air transport network is realized using hybrid electrically aircraft |
| CN110510108A (en) * | 2018-05-22 | 2019-11-29 | 空中客车运营简化股份公司 | Rudder control unit with the single-piece main module that can be moved on bent support frame |
| CN111792048A (en) * | 2020-07-22 | 2020-10-20 | 中国商用飞机有限责任公司 | Control device for aircraft cockpit, escape system and cockpit |
| CN112046773A (en) * | 2020-08-11 | 2020-12-08 | 湖北吉利太力飞车有限公司 | Avionics system of air traffic aircraft based on CAN network |
| CN113247232A (en) * | 2021-05-08 | 2021-08-13 | 陶文英 | Aircraft design method and system with multi-generation layout module structure |
| CN113879530A (en) * | 2021-11-23 | 2022-01-04 | 方钧华 | Aircraft |
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107211287A (en) * | 2014-08-29 | 2017-09-26 | 峰鸟航空科技公司 | The system and method that regional air transport network is realized using hybrid electrically aircraft |
| CN110510108A (en) * | 2018-05-22 | 2019-11-29 | 空中客车运营简化股份公司 | Rudder control unit with the single-piece main module that can be moved on bent support frame |
| CN111792048A (en) * | 2020-07-22 | 2020-10-20 | 中国商用飞机有限责任公司 | Control device for aircraft cockpit, escape system and cockpit |
| CN112046773A (en) * | 2020-08-11 | 2020-12-08 | 湖北吉利太力飞车有限公司 | Avionics system of air traffic aircraft based on CAN network |
| CN113247232A (en) * | 2021-05-08 | 2021-08-13 | 陶文英 | Aircraft design method and system with multi-generation layout module structure |
| CN113879530A (en) * | 2021-11-23 | 2022-01-04 | 方钧华 | Aircraft |
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