CN111932948A - Multi-source acquisition and configuration method for aircraft characteristic information of comprehensive monitoring system - Google Patents
Multi-source acquisition and configuration method for aircraft characteristic information of comprehensive monitoring system Download PDFInfo
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Abstract
The invention discloses a multi-source collecting and configuring method of airplane characteristic information of a comprehensive monitoring system, wherein the comprehensive monitoring system comprises a processor, and ground maintenance equipment, APM equipment and FMS equipment which are connected with the processor, the processor is provided with an internal memory, the APM equipment is provided with a main backup memory and a slave backup memory, and the method comprises the following steps: s1: judging whether the FMS equipment or the ground maintenance equipment transmits the airplane characteristic information or not; s2: if not, reading the aircraft characteristic information from the APM equipment or the processor; s3: if transmission exists, judging whether the airplane is on the ground or in the air; s4: the system is positioned on the ground, receives airplane characteristic information transmitted by FMS equipment or ground maintenance equipment, and updates the airplane characteristic information stored in the main backup memory, the auxiliary backup memory and the internal memory; s5: the configuration is performed using the aircraft characteristic information. The invention can accurately, reliably and safely collect and configure the aircraft characteristic information.
Description
Technical Field
The invention relates to the technical field of aviation safety, in particular to a multi-source acquisition and configuration method for aircraft characteristic information of an integrated monitoring system.
Background
An Integrated Surveillance System (ISS) provides airplane environment Surveillance functions such as severe weather detection (including wind shear detection), air airplane collision prevention, near-ground collision prevention and the like for the airplane, and ensures the full-flight safety of the airplane. The ARINC characteristic 768-2 comprehensive monitoring system specifies the functional configuration and the appearance structure of the system, interface signal definition, electrical characteristics, installation crosslinking and other factors. The ISS includes the following monitoring functions:
airborne Collision Avoidance System (ACAS) (or TCAS)
Air traffic control answering machine (ATCRBS/S mode)
Weather Radar (WXR)/predictive wind shear System (PWS)
Terrain Awareness and Warning System (TAWS)/reactive wind shear system (RWS)
Broadcast auto-correlation monitoring (ADS-B OUT/IN)
The above subfunctions all have their system characteristics specified by the ARINC standard: TCAS (ARINC 735A), transponder (ARINC 718A), weather radar (ARINC 708A), TAWS (ARINC 762), ADS-B OUT (ARINC 718A-3) and ADS-B IN (ARINC 735B).
The ISS is used as complex avionic equipment to realize the perception of comprehensive environments and situations such as air traffic, weather and near-earth collision, carry out danger detection and give out related alarm prompting/avoiding suggestions, and the function of the ISS relates to flight safety. The good operation of each subfunction depends on good information interaction with other systems equipped with the airplane, and also depends on accurate and comprehensive acquisition and use of airplane characteristic information. These aircraft characteristic information are typically programmable data, which ARINC768 further defines as an "installation configuration options file" and an "airline configuration options file" profile as follows:
airplane-assigned 24BIT ICAO Address, unique, for identification of functions like TCAS, ATCRBS/S mode, ADS-B
Whether an aircraft has the climb/increase climb capability required for TCAS decision alerts
Aircraft lift limits for TCAS giving RA decision alerts
Alarm voice volume level configured according to user preferences for voice alarms of TCAS, weather radar, ground proximity alarms
Aircraft radio frequency cable attenuation, calibration for transmission performance, receive performance consistency compensation, etc.
ADS-B required functional information
Other airplane information required for TAWS
TCAS antenna information
Such aircraft characteristic information is generally determined when the aircraft manufacturer delivers the aircraft to the airline, and for a particular aircraft, such information will rarely change during subsequent years of use unless the relevant equipment is upgraded. The functions and performance of the ISS in normal operation require such information, and therefore, whether such aircraft characteristic information can be timely and accurately acquired, identified, updated and maintained is a necessary condition for the ISS to operate well.
In the prior art, the S-mode address is generally configured in a manner of discrete lines, which can meet the use requirements, but the number of the discrete lines is as many as tens, which improves the complexity of the device itself, greatly increases the complexity of the onboard cable, and puts pressure on the reliability and electromagnetic compatibility of the system. Meanwhile, the configuration mode of the hardware connecting line is not beneficial to carrying out state change when necessary.
Disclosure of Invention
The invention aims to provide a multi-source acquisition and configuration method for aircraft characteristic information of an integrated monitoring system, which can accurately, reliably and safely acquire and configure the aircraft characteristic information.
In order to solve the technical problems, the first technical scheme adopted by the invention is as follows: the method for multi-source collection and configuration of aircraft characteristic information of an integrated monitoring system is provided, the integrated monitoring system comprises a processor, and a ground maintenance device, an APM device and an FMS device which are connected with the processor, wherein the processor is provided with an internal memory, the APM device is provided with a main backup memory and a slave backup memory, and the internal memory, the main backup memory and the slave backup memory are all used for storing aircraft characteristic information, and the method comprises the following steps:
s1: when configuring the airplane characteristic information, judging whether the FMS equipment or the ground maintenance equipment transmits the airplane characteristic information, if the FMS equipment or the ground maintenance equipment does not transmit the airplane characteristic information, performing step S2, otherwise, performing step S3;
s2: reading the aircraft characteristic information from the APM device or the processor, and performing step S5;
s3: judging whether the airplane is on the ground or in the air, if the airplane is on the ground, performing the step S4, otherwise, performing the step S5;
s4: receiving the airplane characteristic information transmitted by the FMS device or the ground maintenance device, updating the airplane characteristic information stored in the main backup memory and the auxiliary backup memory of the APM device and the airplane characteristic information stored in the internal memory of the processor, and performing step S5;
s5: the configuration is performed using the aircraft characteristic information.
Preferably, the step S2 specifically includes:
s21: reading airplane characteristic information from a main backup memory of the APM equipment;
s22: verifying the read aircraft characteristic information, and if the verification fails, performing step S23, and if the verification passes, performing step S5;
s23: reading aircraft characteristic information from a slave backup memory of the APM device;
s24: verifying the read aircraft characteristic information, and if the verification fails, performing step S25, and if the verification passes, performing step S5;
s25: reading aircraft characteristic information from an internal memory of the processor;
s26: and verifying the read aircraft characteristic information, recording fault information when the verification fails, and performing step S5 when the verification passes.
Preferably, after recording the failure information, the step S2 further includes:
s27: the initialized global variables are read as the aircraft characteristic information from the software program run by the processor, and step S5 is performed.
Preferably, the step S24 further includes:
and when the verification is passed, updating the aircraft characteristic information stored in the main backup memory by using the aircraft characteristic information stored in the backup memory.
Preferably, the step 26 further comprises:
and when the verification passes, updating the aircraft characteristic information stored in the main backup memory and the aircraft characteristic information stored in the secondary backup memory by using the aircraft characteristic information stored in the internal memory.
Preferably, the step 27 further comprises:
and updating the aircraft characteristic information stored in the main backup memory, the auxiliary backup memory and the internal memory by using the global variable.
Preferably, the check is a CPC check.
Preferably, the step S3 specifically includes:
and judging whether the airplane is on the ground or in the air according to the air/ground indication signal received by the processor.
Preferably, the processor is connected with the APM device through the SPI synchronous serial port.
Preferably, the FMS devices are two, and the processor is connected with the two FMS devices through an A664 interface and an A429 interface respectively.
Different from the prior art, the invention has the beneficial effects that:
1. the requirement of configuration of aircraft characteristic information of ARINC768-2 is fully met;
2. supporting a plurality of data sources to configure the aircraft characteristic information;
3. the system has a backup and check mechanism, and improves reliability.
Drawings
FIG. 1 is a flow chart of a method for multi-source collection and configuration of aircraft characteristic information for an integrated surveillance system in accordance with an embodiment of the present invention;
FIG. 2 is a functional block diagram of an integrated monitoring system;
fig. 3 is a detailed flowchart of step S2 shown in fig. 1.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 and 2, in the present embodiment, the integrated monitoring system includes a processor 10, and a ground maintenance device 20, an APM device 30, and an FMS device 40 connected thereto, where the processor 10 has an internal memory 11, the APM device 30 has a master backup memory 31 and a slave backup memory 32, and the internal memory 11, the master backup memory 31, and the slave backup memory 32 all store aircraft characteristic information.
The processor 10 is connected to the APM device 30 through the SPI synchronous serial port, and the processor 10 supplies power to the APM device 30. The ARINC768 does not allocate and define the interface signals of the APM device 30, and in this embodiment, the interface signals of the APM device 30 are allocated and defined according to the reserved interfaces on the ISS tail connector specified by the ARINC768, and the specific definition is shown in table 1.
TABLE 1 ISS Tail connector APM Signal definition
The FMS devices 40 are two, and the processor 10 is connected to the two FMS devices 40 through an a664 interface and an a429 interface, respectively. The present embodiment allocates and defines the interface signals of the FMS device 40 according to the reserved interface on the ISS tail connector specified by ARINC768, which is specifically defined in table 2.
TABLE 2 ISS Tail-to-machine fiber and Ethernet Pin definitions
The multi-source acquisition and configuration method provided by the embodiment of the invention comprises the following steps:
s1: when the airplane characteristic information is configured, whether the FMS equipment or the ground maintenance equipment transmits the airplane characteristic information or not is judged, if the FMS equipment or the ground maintenance equipment does not transmit the airplane characteristic information, the step S2 is carried out, and if not, the step S3 is carried out;
s2: reading the aircraft characteristic information from the APM device or the processor, and performing step S5;
s3: judging whether the airplane is on the ground or in the air, if the airplane is on the ground, performing the step S4, otherwise, performing the step S5;
s4: receiving the airplane characteristic information transmitted by the FMS device or the ground maintenance device, updating the airplane characteristic information stored in the main backup memory and the auxiliary backup memory of the APM device and the airplane characteristic information stored in the internal memory of the processor, and performing step S5;
s5: the configuration is performed using the aircraft characteristic information.
In this embodiment, step S3 specifically includes: and judging whether the airplane is on the ground or in the air according to the air/ground indication signal received by the processor. As shown in fig. 2, the processor may receive a null/ground indication signal. This embodiment is defined by ARINC768, the null/ground indication signal is located at the processor ARINC600 connector and the pin assignment is LMP-3G.
Referring to fig. 3, step S2 in the embodiment of the present invention specifically includes:
s21: reading airplane characteristic information from a main backup memory of the APM equipment;
s22: verifying the read aircraft characteristic information, and if the verification fails, performing step S23, and if the verification passes, performing step S5;
s23: reading aircraft characteristic information from a slave backup memory of the APM device;
s24: verifying the read aircraft characteristic information, and if the verification fails, performing step S25, and if the verification passes, performing step S5;
s25: reading aircraft characteristic information from an internal memory of the processor;
s26: and verifying the read aircraft characteristic information, recording fault information when the verification fails, and performing step S5 when the verification passes.
The verification performed in the above steps may be CPC verification, and through the verification, the reliability and the security of the system can be greatly improved.
Further, after recording the failure information, step S2 further includes:
s27: the initialized global variables are read as the aircraft characteristic information from the software program run by the processor, and step S5 is performed.
Wherein, the global variable initialized in the software program run by the processor is the initial flight characteristic information.
As can be seen from the flowchart, in this embodiment, there is a priority order for the reading sources of the aircraft characteristic information, and the order is: the APM device comprises a main backup memory, a slave backup memory, an internal memory and a global variable initialized in a software program operated by the processor. The skilled person will readily conceive of changing the order of priority without departing from the above concept, e.g. the internal memory of the handler has the highest priority, and the corresponding step S25 will be performed first.
In this embodiment, step S24 further includes:
and when the verification is passed, updating the aircraft characteristic information stored in the main backup memory by using the aircraft characteristic information stored in the backup memory.
Step 26 further comprises:
and when the verification passes, updating the aircraft characteristic information stored in the main backup memory and the aircraft characteristic information stored in the secondary backup memory by using the aircraft characteristic information stored in the internal memory.
Step 27 further comprises:
and updating the aircraft characteristic information stored in the main backup memory, the auxiliary backup memory and the internal memory by using the global variable.
Through the mode, the multi-source acquisition and configuration method for the aircraft characteristic information of the comprehensive monitoring system forms a set of complete flow on the acquisition, updating, verification and maintenance of the flight characteristic information, solves the problem of using the aircraft characteristic information in the conventional comprehensive monitoring system, meets the use requirement of equipment, and has the characteristics of high safety, high reliability, convenience and quickness in use, easiness in maintenance and the like.
In the embodiments provided in the present application, it should be understood that the disclosed apparatus and method can be implemented in other ways. The apparatus embodiments described above are merely illustrative, and for example, the flowchart and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of apparatus, methods and computer program products according to various embodiments of the present application. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
In addition, functional modules in the embodiments of the present application may be integrated together to form an independent part, or each module may exist separately, or two or more modules may be integrated to form an independent part.
The functions, if implemented in the form of software functional modules and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present application or portions thereof that substantially contribute to the prior art may be embodied in the form of a software product stored in a storage medium and including instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present application. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
The above description is only an example of the present application and is not intended to limit the scope of the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present application, and shall be covered by the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
Claims (10)
1. A multi-source collection and configuration method for aircraft characteristic information of an integrated monitoring system, wherein the integrated monitoring system comprises a processor, and a ground maintenance device, an APM device and an FMS device which are connected with the processor, the processor is provided with an internal memory, the APM device is provided with a main backup memory and a slave backup memory, and the internal memory, the main backup memory and the slave backup memory are all used for storing aircraft characteristic information, and the method is characterized by comprising the following steps:
s1: when configuring the airplane characteristic information, judging whether the FMS equipment or the ground maintenance equipment transmits the airplane characteristic information, if the FMS equipment or the ground maintenance equipment does not transmit the airplane characteristic information, performing step S2, otherwise, performing step S3;
s2: reading the aircraft characteristic information from the APM device or the processor, and performing step S5;
s3: judging whether the airplane is on the ground or in the air, if the airplane is on the ground, performing the step S4, otherwise, performing the step S5;
s4: receiving the airplane characteristic information transmitted by the FMS device or the ground maintenance device, updating the airplane characteristic information stored in the main backup memory and the auxiliary backup memory of the APM device and the airplane characteristic information stored in the internal memory of the processor, and performing step S5;
s5: the configuration is performed using the aircraft characteristic information.
2. The multi-source collection and configuration method according to claim 1, wherein the step S2 specifically includes:
s21: reading airplane characteristic information from a main backup memory of the APM equipment;
s22: verifying the read aircraft characteristic information, and if the verification fails, performing step S23, and if the verification passes, performing step S5;
s23: reading aircraft characteristic information from a slave backup memory of the APM device;
s24: verifying the read aircraft characteristic information, and if the verification fails, performing step S25, and if the verification passes, performing step S5;
s25: reading aircraft characteristic information from an internal memory of the processor;
s26: and verifying the read aircraft characteristic information, recording fault information when the verification fails, and performing step S5 when the verification passes.
3. The multi-source collecting and configuring method according to claim 2, wherein after recording the fault information, the step S2 further comprises:
s27: the initialized global variables are read as the aircraft characteristic information from the software program run by the processor, and step S5 is performed.
4. The multi-source collection and configuration method according to claim 3, wherein the step S24 further comprises:
and when the verification is passed, updating the aircraft characteristic information stored in the main backup memory by using the aircraft characteristic information stored in the backup memory.
5. The multi-source acquisition and configuration method of claim 4, wherein the step 26 further comprises:
and when the verification passes, updating the aircraft characteristic information stored in the main backup memory and the aircraft characteristic information stored in the secondary backup memory by using the aircraft characteristic information stored in the internal memory.
6. The multi-source collection and configuration method of claim 5, wherein the step 27 further comprises:
and updating the aircraft characteristic information stored in the main backup memory, the auxiliary backup memory and the internal memory by using the global variable.
7. The multi-source acquisition and configuration method of claim 3 wherein the check is a CPC check.
8. The multi-source acquisition and configuration method according to claim 1, wherein the step S3 specifically comprises:
and judging whether the airplane is on the ground or in the air according to the air/ground indication signal received by the processor.
9. The multi-source acquisition and configuration method of claim 1, wherein the processor is connected to the APM device via an SPI synchronous serial port.
10. The multi-source acquisition and configuration method according to claim 6, wherein there are two FMS devices, and the processor is connected to the two FMS devices through an A664 interface and an A429 interface, respectively.
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