CN114488881A - Airplane management system - Google Patents
Airplane management system Download PDFInfo
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- CN114488881A CN114488881A CN202111672996.7A CN202111672996A CN114488881A CN 114488881 A CN114488881 A CN 114488881A CN 202111672996 A CN202111672996 A CN 202111672996A CN 114488881 A CN114488881 A CN 114488881A
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 57
- 230000003993 interaction Effects 0.000 claims abstract description 11
- 238000012544 monitoring process Methods 0.000 claims description 6
- 239000000126 substance Substances 0.000 claims description 5
- 238000013461 design Methods 0.000 abstract description 3
- 238000004891 communication Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005662 electromechanics Effects 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
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Classifications
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/25—Pc structure of the system
- G05B2219/25257—Microcontroller
Abstract
The application belongs to the technical field of design of airplane management systems, and particularly relates to an airplane management system, which comprises: the airplane management computer executes the functions of automatic flight control, comprehensive electromechanical management and comprehensive airplane management control; the fly-by-wire flight control computer executes a fly-by-wire flight control law resolving function; the servo control unit executes a flight control plane servo control function; an undercarriage control unit that performs a braking and turning control function; the airplane management system comprises an airplane management computer, a telex flight control computer and an undercarriage control unit, wherein the airplane management computer, the telex flight control computer and the undercarriage control unit are connected to a primary bus network of the airplane management system to carry out information interaction; the fly-by-wire flight control computer and the servo control unit are accessed to a secondary bus network of the airplane management system to carry out information interaction.
Description
Technical Field
The application belongs to the technical field of design of airplane management systems, and particularly relates to an airplane management system.
Background
Due to the high safety requirement of the airplane, when the airplane management system is designed, in order to avoid the loss of high safety function caused by the failure of a main network or a main control computer of the system, the high safety function is usually taken as a backup in a point-to-point connection mode to improve the safety, under the technical scheme, a large number of required cables are needed, the weight of the system is large, and the comprehensive efficiency is low.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft management system to overcome or mitigate at least one of the technical disadvantages of the known prior art.
The technical scheme of the application is as follows:
an aircraft management system comprising:
the airplane management computer executes the functions of automatic flight control, comprehensive electromechanical management and comprehensive airplane management control;
the fly-by-wire flight control computer executes a fly-by-wire flight control law resolving function;
the servo control unit executes a flight control plane servo control function;
an undercarriage control unit that performs a braking and turning control function;
wherein the content of the first and second substances,
the airplane management computer, the fly-by-wire flight control computer and the undercarriage control unit are connected to a primary bus network of the airplane management system to carry out information interaction;
the telex flight control computer and the servo control unit are accessed to a secondary bus network of the airplane management system to carry out information interaction.
According to an embodiment provided by the application, in the aircraft management system, the aircraft management computer is a master controller of a primary bus network of the aircraft management system, and has control and monitoring functions on the aircraft management computer and the primary bus network of the aircraft management system.
According to the embodiments provided by the present application, in the above-mentioned aircraft management system, the fly-by-wire flight control computer is a master controller of the secondary bus network of the aircraft management system, and has control and monitoring functions for itself and the secondary bus network of the aircraft management system.
According to an embodiment provided by the present application, in the aircraft management system, the fly-by-wire flight control computer outputs an instruction to the servo control unit according to the state of the primary bus network of the aircraft management system and the state of the aircraft management computer, which is specifically as follows:
if the states of the airplane management computer and the primary bus network of the airplane management system are effective, the fly-by-wire flight control computer outputs an instruction to the servo control unit according to the instruction calculated by the airplane management computer;
if the state of the airplane management computer or the primary bus network of the airplane management system is invalid, the fly-by-wire flight control computer outputs an instruction to the servo control unit according to the instruction resolved by the fly-by-wire flight control computer.
According to an embodiment provided by the present application, the aircraft management system further includes:
the cabin data acquisition computer is used for executing data acquisition of the cabin related data sensor and the top control board;
the remote acquisition driving unit executes the data acquisition driving function of the electromechanical system;
the cabin display warning computer executes the display and warning functions of each system information cabin;
the atmospheric data computer is used for executing atmospheric data sensing and resolving functions;
wherein the content of the first and second substances,
the cockpit data acquisition computer, the remote acquisition driving unit, the cockpit display alarm computer and the air data computer are accessed to a primary bus network of the airplane management system to carry out information interaction.
The application has at least the following beneficial technical effects:
the airplane management system integrates the functions of automatic flight control, electromechanical integrated management, airplane integrated control management and the like of a lower safety level into an airplane management computer, can improve the expansion upgrading capability of the system, sets the brake and turning control functions of a higher safety level into independent control units, realizes distributed control by a main flight control function through a secondary bus network, can improve the safety and reliability of the system, reduces the weight, constructs a set of layered integrated system architecture with high safety system independent guarantee reliability and low safety system integrated guarantee performance, and can realize the organic combination of the system integrated performance and the safety and reliability.
Drawings
FIG. 1 is a schematic illustration of an aircraft management system provided by an embodiment of the present application;
wherein:
1-an airplane management computer; 2-fly-by-wire flight control computer; 3-a servo control unit; 4-cabin data acquisition computer; 5-a landing gear control unit; 6-remote acquisition driving unit; 7-cabin display alarm computer; 8-an atmospheric data computer; 9-primary bus network of airplane management system; 10-aircraft management system secondary bus network.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; in addition, the drawings are used for illustrative purposes, and the positional relationship is only for illustrative purposes and is not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1.
An aircraft management system comprising:
an airplane management computer 1 for executing automatic flight control, comprehensive electromechanical management and comprehensive airplane management control functions;
the fly-by-wire flight control computer 2 executes a fly-by-wire flight control law resolving function and can acquire signals such as a steering column/a disc/pedals and the like;
a servo control unit 3 for executing a flight control plane servo control function;
a cabin data acquisition computer 4 for executing data acquisition of data sensors and a top control panel of the cabin except for fly-by-wire flight control and landing gear;
the undercarriage control unit 5 executes a braking and turning control function and can acquire undercarriage signals;
a remote acquisition drive unit 6 that performs an electromechanical system data acquisition drive function;
a cabin display alarm computer 7 for executing the display and alarm functions of each system information cabin;
the atmospheric data computer 8 is used for executing atmospheric data sensing and resolving functions;
wherein the content of the first and second substances,
the airplane management computer 1, the fly-by-wire flight control computer 2, the cockpit data acquisition computer 4, the undercarriage control unit 5, the remote acquisition driving unit 6, the cockpit display alarm computer 7 and the air data computer 8 are connected to a primary bus network 9 of the airplane management system to carry out information interaction;
the fly-by-wire flight control computer 2 and the servo control unit 3 are accessed to a secondary bus network 10 of the airplane management system to carry out information interaction;
the primary bus network 9 of the airplane management system executes the communication of systems such as flight control, landing gear, electromechanics and the like, and adopts an advanced bus network with high bandwidth and high real-time performance;
the aircraft management system secondary bus network 10 performs distributed system communications for fly-by-wire flight control, using a mature bus network with low bandwidth and high integrity.
The airplane management computer 1 is used as a main control computer of the primary bus network 9 of the airplane management system, and has the functions of controlling and monitoring the airplane management computer and the primary bus network 9 of the airplane management system so as to improve the safety and reliability of the network main control computer;
the fly-by-wire flight control computer 2 is used as a main control computer of the aircraft management system secondary bus network 10, and has the functions of controlling and monitoring the fly-by-wire flight control computer and the aircraft management system secondary bus network 10 so as to improve the safety and reliability of the network main control computer.
The airplane management computer 1 receives related system sensor data and system state parameters mainly through a primary bus network 9 of the airplane management system, and achieves top-level control management functions of the airplane system, including an automatic flight control function, an electromechanical integrated management function, airplane integrated management control and the like.
The airplane management computer 1 realizes the functions of automatic flight control, electromechanical integrated management and airplane integrated management control, receives data uploaded by the telex flight control computer 2, the cockpit data acquisition computer 4, the undercarriage control unit 5, the remote acquisition driving unit 6 and the atmospheric data computer 8 from a primary bus network 9 of an airplane management system, generates an integrated control management instruction according to the data, and simultaneously sends related information to the cockpit display alarm computer 7 to realize the airplane whole-computer display alarm of each system.
In the airplane management system, except for the servo control unit 3, each computer and control unit of the airplane management system sends data and related state data acquired by an own instruction sensor to a primary bus network 9 of the airplane management system, and the servo control unit 3 realizes information interaction with the fly-by-wire flight control computer 2 only through a secondary bus network 10 of the airplane management system.
The fly-by-wire flight control computer 2 mainly realizes the functions of acquisition and processing of sensors such as a steering column/a disk/a pedal and the like of the fly-by-wire flight control system and related control law resolving, outputs an instruction to the servo control unit 3 according to the state of a primary bus network 9 of the airplane management system and the state of the airplane management computer 1, and realizes the servo control function of the airplane flight control surface, and the servo control function is as follows:
if the states of the airplane management computer 1 and the primary bus network 9 of the airplane management system are effective, the fly-by-wire flight control computer 2 outputs an instruction to the servo control unit 3 according to the instruction solved by the airplane management computer 1;
if the state of the airplane management computer 1 or the primary bus network 9 of the airplane management system is invalid, the fly-by-wire flight control computer 2 outputs an instruction to the servo control unit 3 according to the instruction resolved by the fly-by-wire flight control computer.
The cabin data acquisition unit 4 mainly realizes cabin data acquisition of electromechanical and automatic flight control systems and the like.
The landing gear control unit 5 mainly implements sensor acquisition, processing and related control resolving and servo driving functions of the landing gear control system.
The cockpit display alarm computer 7 receives the state and alarm information of each system sent by the airplane management computer 1 from the primary bus network 9 of the airplane management system, and provides system state display and alarm for pilots.
In the airplane management system, functions of automatic flight control, electromechanical integrated management, airplane integrated control management and the like with lower safety level are integrated into the airplane management computer 1, the expansion upgrading capability of the system can be improved, brake and turning control functions with higher safety level are set as independent control units, the main flight control function realizes distributed control through a secondary bus network, the safety and the reliability of the system can be improved, and the weight is reduced.
The airplane management system disclosed above constructs a set of layered comprehensive system architecture with high safety system independent guarantee reliability and low safety system comprehensive guarantee performance, and achieves the organic combination of system comprehensive performance and safety and reliability.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (5)
1. An aircraft management system, comprising:
the airplane management computer (1) executes the functions of automatic flight control, comprehensive electromechanical management and comprehensive airplane management control;
the fly-by-wire flight control computer (2) executes a fly-by-wire flight control law resolving function;
a servo control unit (3) for executing the flight control plane servo control function;
an undercarriage control unit (5) for performing a braking and turning control function;
wherein the content of the first and second substances,
the airplane management computer (1), the fly-by-wire flight control computer (2) and the undercarriage control unit (5) are accessed to a primary bus network (9) of the airplane management system to carry out information interaction;
the fly-by-wire flight control computer (2) and the servo control unit (3) are accessed to a secondary bus network (10) of the airplane management system to carry out information interaction.
2. An aircraft management system according to claim 1,
the airplane management computer (1) is a main control computer of a primary bus network (9) of the airplane management system, and has the functions of controlling and monitoring the airplane management computer and the primary bus network (9) of the airplane management system.
3. An aircraft management system according to claim 1,
the fly-by-wire flight control computer (2) is a main control computer of the aircraft management system secondary bus network (10) and has the functions of controlling and monitoring the fly-by-wire flight control computer and the aircraft management system secondary bus network (10).
4. An aircraft management system according to claim 1,
the fly-by-wire flight control computer (2) outputs an instruction to the servo control unit (3) according to the state of the primary bus network (9) of the airplane management system and the state of the airplane management computer (1), and the instructions are as follows:
if the states of the airplane management computer (1) and the primary bus network (9) of the airplane management system are effective, the fly-by-wire flight control computer (2) outputs an instruction to the servo control unit (3) according to the instruction solved by the airplane management computer (1);
if the state of the airplane management computer (1) or the primary bus network (9) of the airplane management system is invalid, the fly-by-wire flight control computer (2) outputs an instruction to the servo control unit (3) according to the instruction resolved by the fly-by-wire flight control computer.
5. An aircraft management system according to claim 1,
further comprising:
a cabin data acquisition computer (4) for executing data acquisition of the cabin related data sensor and the top control panel;
a remote acquisition drive unit (6) which performs an electromechanical system data acquisition drive function;
a cabin display alarm computer (7) for executing the display and alarm functions of each system information cabin;
the atmospheric data computer (8) is used for executing atmospheric data sensing and resolving functions;
wherein the content of the first and second substances,
the cockpit data acquisition computer (4), the remote acquisition driving unit (6) and the cockpit display alarm computer (7) are accessed to a primary bus network (9) of the airplane management system to carry out information interaction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111672996.7A CN114488881A (en) | 2021-12-31 | 2021-12-31 | Airplane management system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111672996.7A CN114488881A (en) | 2021-12-31 | 2021-12-31 | Airplane management system |
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| Publication Number | Publication Date |
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| CN114488881A true CN114488881A (en) | 2022-05-13 |
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| CN202111672996.7A Pending CN114488881A (en) | 2021-12-31 | 2021-12-31 | Airplane management system |
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Citations (6)
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| CN103914077A (en) * | 2014-04-03 | 2014-07-09 | 江西洪都航空工业集团有限责任公司 | Manned/unmanned selectable dual-mode flight control system |
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| US20180281948A1 (en) * | 2015-07-24 | 2018-10-04 | Wenying TAO | Method and system for designing cooperatively-driven aircraft system |
| CN112124568A (en) * | 2020-09-28 | 2020-12-25 | 中国商用飞机有限责任公司 | Fly-by-wire flight control system and control method |
| CN113534655A (en) * | 2021-09-07 | 2021-10-22 | 中国商用飞机有限责任公司 | Telex flight backup control system and starting method thereof |
-
2021
- 2021-12-31 CN CN202111672996.7A patent/CN114488881A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103914077A (en) * | 2014-04-03 | 2014-07-09 | 江西洪都航空工业集团有限责任公司 | Manned/unmanned selectable dual-mode flight control system |
| US20180281948A1 (en) * | 2015-07-24 | 2018-10-04 | Wenying TAO | Method and system for designing cooperatively-driven aircraft system |
| CN106774264A (en) * | 2016-12-28 | 2017-05-31 | 中国航空工业集团公司西安飞机设计研究所 | A kind of fly-by-wire flight control system online detection instrument and method |
| CN107608381A (en) * | 2017-09-30 | 2018-01-19 | 江西洪都航空工业集团有限责任公司 | A kind of fly-by-wire flight control system control framework for mixing redundant configurations |
| CN112124568A (en) * | 2020-09-28 | 2020-12-25 | 中国商用飞机有限责任公司 | Fly-by-wire flight control system and control method |
| CN113534655A (en) * | 2021-09-07 | 2021-10-22 | 中国商用飞机有限责任公司 | Telex flight backup control system and starting method thereof |
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