CN105070107A - Airborne collision avoidance system, ACAS transmit-receive host digital signal loop self-detection system and method - Google Patents
Airborne collision avoidance system, ACAS transmit-receive host digital signal loop self-detection system and method Download PDFInfo
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Abstract
The invention discloses an airborne collision avoidance system, an ACAS transmit-receive host digital signal loop self-detection system and a method. Without increasing extra hardware equipment, equipment original composition modules of a JSCPU, a coding FPGA, a decoding module, an FZCPU and inherent communication channels thereof are employed to work in a cooperative manner, and software programming is realized. According to the airborne collision avoidance system, the ACAS transmit-receive host digital signal loop self-detection system and the method, digital signal loop self-detection of an ACAS transmit-receive host can be automatically, periodically, and effectively realized, and the self-detection result is reported to a carrier aircraft maintenance system for fault display and record; real-time fault monitoring is performed in the whole work stage of the airborne collision avoidance system, functional module level fault positioning can be accomplished, fault isolation is effectively realized, maintenance and guarantee are facilitated, and the requirements of equipment tests and maintenance are met; host inherent hardware resources are employed in the manner of software programming, test equipment and manual intervention are not needed, the costs of manpower and material resources are effectively lowered, the testability and maintainability of the equipment are improved, and equipment production and maintenance are facilitated.
Description
Technical field
The present invention relates to airborne collision avoidance technical field, particularly relate to a kind of airborne collision avoidance system, ACAS transmitting-receiving main frame numeral hoop road self-checking system and method.
Background technology
Airborne collision avoidance system (i.e. TCAS-TrafficAlertandCollisionAvoidanceSystem) is defined by US Federal Aviation Administration (FAA), is to prevent aerospace plane dangerous close to the requisite equipment with accidents generation.TCAS is mainly used in as aircraft provides air security separation assurance, system adopt the mode of secondary radar detect neighbouring spatial domain close to aircraft, if desired, remind pilot to take workaround to keep suitable safe spacing with other aircraft, reach the object of anticollision.Be facts have proved by flight in recent years, this system is the last line of defense preventing Aircraft Air from bumping against, also be one of the most effective current means, which overcome the limitation of terrestrial air traffic control, the flight safety guarantee ability exceeding ground traffic control and can provide can be provided, close to the danger dealing with aerial burst, avoid midair crash to have huge effect.
It is the key realizing collision prevention function that the ACAS of system receives and dispatches main frame, it is by control antenna beam position, scanning inquiry is carried out to region, 4, aircraft front, rear, left and right, near blank pipe answering machine (S mode/ATCRBS answering machine) is housed aircraft (hereinafter referred to as target machine) will response be made.ACAS receives and dispatches main frame according to the answer signal received, obtain the target information such as height, relative distance, speed, orientation of target machine, and and then calculate its altitude rate, relative distance rate of change, simultaneously in conjunction with positional information and the movable information of the machine, supervision, tracking target machine, set up, upgrade and safeguard targetpath.By monitor and upgrade targetpath and ownship information comprehensive, evaluate the threat level (OT: other aircraft of target machine, PT: close to aircraft, TA: traffic alert, RA: resolution alarm), thus generation Traffic query, or produce analysis consulting according to threaten degree further, prevent from colliding with other aircraft; When both sides are equipped with collision avoidance system, Anticollision information can be exchanged by S mode Data-Link, the object that reaching cooperatively interacts dodges.Otherwise guiding the machine realizes initiatively dodging by airborne collision avoidance system.
But, if ACAS receives and dispatches main frame itself there is fault, decoding target machine information that can not be correct, collision avoidance system work so must be caused abnormal, correct traffic alert (TA) and resolution alarm (RA) can not be provided, thus the object of anti-collision can not be reached.Therefore, need a kind of effective self-sensing method, realize the Autonomous test of each extension set of whole system, module, interface data, when handling failure, indicating fault.
Traditional detection method needs to be equipped with special testing staff and utilizes special supporting testing apparatus building platform, and simulation system environment for use is tested accordingly, and cost is high, efficiency is low.Simultaneously because Instrument observation exists personal error, affect test accuracy.When equipment goes wrong in the use procedure of outfield, often can not accomplish fault isolation owing to not possessing corresponding testing conditions, locate the position of breaking down, the mode of complete machine depot repair can only be taked, be unfavorable for localization of fault and the maintenance support of equipment.
Summary of the invention
For solving the problem, the invention provides a kind of ACAS and receiving and dispatching main frame numeral hoop road self-checking system, comprising JSCPU(and monitor CPU), coding FPGA, decoding module, the crashproof CPU of FZCPU(); Described coding FPGA and JSCPU, decoding module, FZCPU all connect, and decoding module is connected with JSCPU, wherein
ACAS receives and dispatches main frame numeral hoop road self-checking system,
JSCPU be used for issuing the self-inspection order of C mode closed loop or S mode closed loop self-inspection order to coding FPGA, receive decoding data, judge self-detection result according to decoding data, send self-detection result to FZCPU;
Coding FPGA generates standard C pattern answer back code, standard S mode answer back code for encoding, and sends control information to decoding module;
Decoding module is used in conjunction with control information, standard C pattern answer back code, standard S mode answer back code being carried out to decoding, and sending decoding data to JSCPU;
FZCPU for receiving the self-detection result of JSCPU, and reports self-detection result.
Further, described decoding module comprises interface FPGA, the C mode signal interpretation circuit be connected with interface FPGA respectively and s mode signal decoding scheme; Wherein, C mode signal interpretation circuit comprises the C mode signal transacting FPGA, the C mode processor that connect in turn, and S mode signal interpretation circuit comprises the S mode signal transacting FPGA, the S mode processor that connect in turn.
Further, the control signal that the FPGA that encodes sends comprises range gate signal, launches frame signals, mode of operation signal.
The invention also discloses a kind of airborne collision avoidance system, comprise ACAS and receive and dispatch main frame, comprise above-mentioned ACAS and receive and dispatch main frame numeral hoop road self-checking system.
Further, described ACAS receives and dispatches main frame and is provided with coding FPGA working station indicator, and when the FPGA that encodes is working properly, coding FPGA working station indicator can be glittering, when FPGA work of encoding is abnormal, coding FPGA working station indicator does not work or Chang Liang.
Further, also comprise carrier aircraft maintenance system, the failure code of self-detection result is reported carrier aircraft maintenance system by FZCPU,
Above-mentioned ACAS receives and dispatches the self checking method of main frame numeral hoop road self-checking system, it is characterized in that, comprising:
C mode process of self-test;
S mode process of self-test;
FZCPU reports the process of self-detection result;
Wherein:
C mode process of self-test comprises the steps:
Step1:JSCPU judges whether timer arrives, if timer arrives, then enters Step2, if do not arrived, then continues to wait for;
Step2:JSCPU issues C mode closed loop self-inspection order to coding FPGA by address, data bus;
Step3: after coding FPGA receives this self-inspection order, coding generation standard C pattern answer back code (wherein can comprise the elevation information of the aircraft appointed), also can generate control signal, described control information comprises range gate signal, launches frame signals, mode of operation signal simultaneously;
Step4: decoding module receives the mode of operation signal of coding FPGA, enter C mode closed loop self-inspection decoding schema, simultaneously Binding distance gate signal, launch frame signals and answer back code signal decoding goes out corresponding decoding information, get out to upload the report data of JSCPU and initiate the interrupt request of transmission decoding data to JSCPU;
After Step5:JSCPU receives this interrupt request, according to the form length appointed in advance, read decoding data by address, data bus from decoding module;
The decoding data form received and the standard C pattern answer back code appointed in advance are made comparisons by Step6:JSCPU, if unanimously, then judge that the self-inspection of C mode closed loop is normal, otherwise judge C mode closed loop self test failure;
S mode process of self-test comprises the steps:
Step1:JSCPU issues S mode closed loop self-inspection order to coding FPGA by address, data bus;
Step2: after coding FPGA receives this self-inspection order, coding generation standard S mode answer back code, (can comprise aircraft relevant height, velocity information and the aircraft address code information appointed) also can generate number control signal simultaneously, and described control signal comprises range gate signal, launches frame signals, mode of operation signal;
Step3: decoding module receives the mode of operation signal of coding FPGA, enter S mode closed loop self-inspection decoding schema, simultaneously Binding distance gate signal, launch frame signals and answer back code signal decoding goes out corresponding decoding information, get out to upload the report data of JSCPU and initiate the interrupt request of transmission decoding data to JSCPU;
After Step4:JSCPU receives this interrupt request, according to the form length appointed in advance, read decoding data by address, data bus from decoding module;
The decoding data form received and the standard S mode answer back code appointed in advance are made comparisons by Step5:JSCPU, if unanimously, then judge that the self-inspection of S mode closed loop is normal; Otherwise judge S mode closed loop self test failure.
Further, standard S mode answer back code has 112.
Further, the self-inspection frequency of this system is 1s/ time.
Beneficial effect of the present invention is:
The present invention realizes automatically, periodically, effectively realizing the reception loop Autonomous test that ACAS receives and dispatches main frame, and self-detection result reports carrier aircraft maintenance system to carry out malfunction coefficient and record.And carry out real time fail monitoring at the whole working stage of airborne collision avoidance system, functional module level localization of fault can be completed, realize fault isolation effectively, be convenient to maintenance support, meet testing of equipment and maintenance needs.Simultaneously because the present invention utilizes the intrinsic hardware resource of main frame to be realized by the mode of software programming, without the need to testing apparatus and manpower intervention, effectively save human and material resources cost, improve testability and the maintainability of equipment, be convenient to device fabrication and maintenance.
Accompanying drawing explanation
Fig. 1 is that ACAS of the present invention receives and dispatches main frame numeral hoop road self-checking system module map.
Fig. 2 is decoding module schematic diagram of the present invention.
Fig. 3 is that ACAS of the present invention receives and dispatches main frame numeral hoop road self-checking system workflow diagram.
Embodiment
The present invention is under the condition not increasing extra hardware device, and utilize equipment original comprising modules JSCPU, coding FPGA, decoding module, FZCPU and intrinsic communications conduit cooperating thereof, software programming realizes, and its composition frame chart as shown in Figure 1.In the whole course of work of equipment, this self-inspection keeps the frequency cycle of 1s/ time to run, and selftest failure code can be reported carrier aircraft maintenance system by ARINC429 bus by FZCPU, carries out malfunction coefficient and record.
Below modules is described.
JSCPU be used for issuing the self-inspection order of C mode closed loop or S mode closed loop self-inspection order to coding FPGA, receive decoding data, judge self-detection result according to decoding data, send self-detection result to FZCPU;
Coding FPGA generates standard C pattern answer back code, standard S mode answer back code for encoding, and sends control information to decoding module;
Decoding module is used in conjunction with control information, standard C pattern answer back code, standard S mode answer back code being carried out to decoding, and sending decoding data to JSCPU;
FZCPU for receiving the self-detection result of JSCPU, and reports self-detection result.
As shown in Figure 2, it transfers to the different hardware circuit of two-way to realize S mode decoding and C mode decoding respectively to the composition frame chart of decoding module respectively, the C mode signal interpretation circuit that described decoding module comprises interface FPGA, is connected with interface FPGA respectively
,s mode signal interpretation circuit; Wherein, C mode signal interpretation circuit comprises the C mode signal transacting FPGA and C mode processor that connect in turn, and S mode signal interpretation circuit comprises the S mode signal transacting FPGA and S mode processor that connect in turn.
Due to when carrying out the self-inspection of digital signal loop, the answer back code that decoding module receives is the answer back code information of the TTL form directly sended over by FPGA, therefore when decoding module judges digital signal loop self-inspection state according to mode line information, with regard to direct, the answer back code received is sent in signal transacting FPGA, and need not A/D conversion be carried out.
Self-detection result for receiving the self-detection result of JSCPU, and is reported carrier aircraft maintenance system by FZCPU.
Preferably, in order to ensure the fault Timeliness coverage of native system further, better be applied to airborne collision avoidance system, on the ACAS transmitting-receiving main frame of its airborne collision avoidance system applied, specialized designs has the lighting function for coding FPGA self-inspection, namely a coding FPGA working station indicator is added, when the FPGA that encodes is working properly, coding FPGA working station indicator can be glittering; When FPGA work of encoding is abnormal, coding FPGA working station indicator does not work or Chang Liang.So coding FPGA is when normally working, when JSCPU judge S mode closed loop self-inspection and the self-inspection of C mode closed loop all fault time, can be judged to be that decoding module work is abnormal.When JSCPU judge that the self-inspection of S mode closed loop is normal, C mode closed loop self test failure time can judge that the path of decoding module inter-process C mode self-inspection has fault; When JSCPU judgement S mode closed loop self test failure, the self-inspection of C mode closed loop can be judged to be time normal that the path of decoding module inter-process S mode self-inspection has fault.This design effectively can carry out the fault detect of native system self, has unexpected technique effect.
Below in conjunction with Fig. 3, the course of work that ACAS receives and dispatches main frame numeral hoop road self-checking system is described.
The course of work comprises the process that this self-detection result is reported carrier aircraft maintenance system by C mode process of self-test, S mode process of self-test, FZCPU.
C mode process of self-test comprises the steps:
Step1:JSCPU judges whether timer arrives, if timer arrives, then enters Step2, if do not arrived, then continues to wait for.
The self-inspection frequency that native system is arranged be 1s once, this frequency can not too fast and affect modules other normally work, also can not be too slow and causing trouble can not Timeliness coverage.Concrete frequency also can set according to actual conditions.
Step2:JSCPU issues C mode closed loop self-inspection order to coding FPGA by address, data bus;
Step3: after coding FPGA receives this self-inspection order, coding generation standard C pattern answer back code, (wherein can comprise the elevation information of the aircraft appointed) also can generate associated translation control signal simultaneously, comprises range gate signal, launches frame signals, mode of operation signal.
Step4: decoding module receives the mode of operation signal of coding FPGA, enter C mode closed loop self-inspection decoding schema, simultaneously Binding distance gate signal, launch frame signals and answer back code signal decoding goes out corresponding decoding information, get out to upload the report data of JSCPU and initiate the interrupt request of transmission decoding data to JSCPU.
After Step5:JSCPU receives this interrupt request, according to the form length appointed in advance, read decoding data by address, data bus from decoding module.
The decoding data form received and the aircraft altitude information appointed in advance are made comparisons by Step6:JSCPU, if unanimously, then judge that the self-inspection of C mode closed loop is normal; Otherwise judge C mode closed loop self test failure.The self-inspection of C mode closed loop terminates.
S mode process of self-test comprises the steps:
Step1:JSCPU issues S mode closed loop self-inspection order to coding FPGA by address, data bus.
Step2: after coding FPGA receives this self-inspection order, the standard S mode answer back code of coding long 112 of generation one (wherein can comprise the aircraft relevant height appointed, velocity information and aircraft address code information), also can generate number control signal simultaneously, comprise range gate signal, launch frame signals, mode of operation signal.
Step3: decoding module receives the mode of operation signal of coding FPGA, enter S mode closed loop self-inspection decoding schema, simultaneously Binding distance gate signal, launch frame signals and answer back code signal decoding goes out corresponding decoding information, get out to upload the report data of JSCPU and initiate the interrupt request of transmission decoding data to JSCPU;
After Step4:JSCPU receives this interrupt request, according to the form length appointed in advance, read decoding data by address, data bus from decoding module;
The decoding data form received and the standard S mode answer back code appointed in advance are made comparisons by Step5:JSCPU, if unanimously, then judge that the self-inspection of S mode closed loop is normal; Otherwise judge S mode closed loop self test failure.The self-inspection of S mode closed loop terminates;
This self-detection result is passed to FZCPU by data, address bus by the RAM functional module of FPGA inside by Step6:JSCPU;
Should be appreciated that the process of self-test of C mode and the process of self-test of S mode there is no dividing of front and back.
Process of self-test is that this self-detection result of FZCPU reports integrated display system by ARINC429 data bus or other communication modes (as radio communication) be applicable to.
Beneficial effect of the present invention is:
The present invention realizes automatically, periodically, effectively realizing the reception loop Autonomous test that ACAS receives and dispatches main frame, and reported by self-detection result carrier aircraft maintenance system to carry out malfunction coefficient and record.And carry out real time fail monitoring at the whole working stage of airborne collision avoidance system, functional module level localization of fault can be completed, realize fault isolation effectively, be convenient to maintenance support, meet testing of equipment and maintenance needs.Simultaneously because the present invention utilizes the intrinsic hardware resource of main frame to be realized by the mode of software programming, without the need to testing apparatus and manpower intervention, effectively save human and material resources cost, improve testability and the maintainability of equipment, be convenient to device fabrication and maintenance.
Claims (9)
1.ACAS receives and dispatches main frame numeral hoop road self-checking system, it is characterized in that, comprises JSCPU, coding FPGA, decoding module, FZCPU; Described JSCPU, decoding module, FZCPU are connected with coding FPGA respectively, and decoding module is connected with JSCPU, wherein
JSCPU be used for issuing the self-inspection order of C mode closed loop or S mode closed loop self-inspection order to coding FPGA, receive decoding data, judge self-detection result according to decoding data, send self-detection result to FZCPU;
Coding FPGA generates standard C pattern answer back code, standard S mode answer back code for encoding, and sends control information to decoding module;
Decoding module is used in conjunction with control information, standard C pattern answer back code, standard S mode answer back code being carried out to decoding, and sending decoding data to JSCPU;
FZCPU for receiving the self-detection result of JSCPU, and reports self-detection result.
2. ACAS as claimed in claim 1 receives and dispatches main frame numeral hoop road self-checking system, and it is characterized in that, described decoding module comprises interface FPGA, the C mode signal interpretation circuit be connected with interface FPGA respectively and S mode signal interpretation circuit; Wherein, C mode signal interpretation circuit comprises the C mode signal transacting FPGA, the C mode processor that connect in turn, and S mode signal interpretation circuit comprises the S mode signal transacting FPGA, the S mode processor that connect in turn.
3. ACAS as claimed in claim 1 receives and dispatches main frame numeral hoop road self-checking system, and it is characterized in that, the control signal that coding FPGA sends comprises range gate signal, launches frame signals, mode of operation signal.
4. airborne collision avoidance system, comprises ACAS and receives and dispatches main frame, it is characterized in that, the ACAS comprised as described in claim 1 or 2 or 3 receives and dispatches main frame numeral hoop road self-checking system.
5. airborne collision avoidance system as claimed in claim 3, it is characterized in that, described ACAS receives and dispatches main frame and is provided with coding FPGA working station indicator, when the FPGA that encodes is working properly, coding FPGA working station indicator can be glittering, when FPGA work of encoding is abnormal, coding FPGA working station indicator does not work or Chang Liang.
6. the airborne collision avoidance system as described in claim 4 or 5, is characterized in that, also comprises carrier aircraft maintenance system, and the failure code of self-detection result is reported carrier aircraft maintenance system by FZCPU.
7. the ACAS as described in any one of claims 1 to 3 receives and dispatches the self checking method of main frame numeral hoop road self-checking system, it is characterized in that, comprises
C pattern process of self-test;
S mode process of self-test;
FZCPU reports the process of self-detection result;
Wherein:
C pattern process of self-test comprises the steps:
Step1:JSCPU judges whether timer arrives, if timer arrives, then enters Step2, if do not arrived, then continues to wait for;
Step2:JSCPU issues C mode closed loop self-inspection order to coding FPGA by address, data bus;
Step3: after coding FPGA receives this self-inspection order, coding generation standard C pattern answer back code, also can generate control signal simultaneously, and described control information comprises range gate signal, launches frame signals, mode of operation signal;
Step4: decoding module receives the mode of operation signal of coding FPGA, enter C mode closed loop self-inspection decoding schema, simultaneously Binding distance gate signal, launch frame signals and answer back code signal decoding goes out corresponding decoding information, get out to upload the report data of JSCPU and initiate the interrupt request of transmission decoding data to JSCPU;
After Step5:JSCPU receives this interrupt request, according to the form length appointed in advance, read decoding data by address, data bus from decoding module;
The decoding data form received and the standard C pattern answer back code appointed in advance are made comparisons by Step6:JSCPU, if unanimously, then judge that the self-inspection of C mode closed loop is normal, otherwise judge C mode closed loop self test failure;
S mode process of self-test comprises the steps:
Step1:JSCPU issues S mode closed loop self-inspection order to coding FPGA by address, data bus;
Step2: after coding FPGA receives this self-inspection order, coding standard S mode answer back code, also can generate number control signal simultaneously, described control signal comprises range gate signal, launches frame signals, mode of operation signal;
Step3: decoding module receives the mode of operation signal of coding FPGA, enter S mode closed loop self-inspection decoding schema, simultaneously Binding distance gate signal, launch frame signals and answer back code signal decoding goes out corresponding decoding information, get out to upload the report data of JSCPU and initiate the interrupt request of transmission decoding data to JSCPU;
After Step4:JSCPU receives this interrupt request, according to the form length appointed in advance, read decoding data by address, data bus from decoding module;
The decoding data form received and the standard S mode answer back code appointed in advance are made comparisons by Step5:JSCPU, if unanimously, then judge that the self-inspection of S mode closed loop is normal; Otherwise judge S mode closed loop self test failure.
8. ACAS as claimed in claim 7 receives and dispatches the self checking method of main frame numeral hoop road self-checking system, and it is characterized in that, self-detection result is reported carrier aircraft maintenance system by ARINC429 bus or communication by FZCPU.
9. ACAS as claimed in claim 7 receives and dispatches the self checking method of main frame numeral hoop road self-checking system, and it is characterized in that, the self-inspection frequency of this system is 1s/ time.
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| CN108111221A (en) * | 2017-12-22 | 2018-06-01 | 四川九洲空管科技有限责任公司 | A kind of fiber link automatic testing method based on certain hip-based platform digital radar |
| CN110780267A (en) * | 2019-10-31 | 2020-02-11 | 四川九洲空管科技有限责任公司 | Self-checking method for receiving and transmitting channel of navigation management inquiry response simulator |
| CN110780267B (en) * | 2019-10-31 | 2021-06-11 | 四川九洲空管科技有限责任公司 | Self-checking method for receiving and transmitting channel of navigation management inquiry response simulator |
| CN111081075A (en) * | 2020-01-19 | 2020-04-28 | 中国民用航空总局第二研究所 | S-mode DAPs data real-time monitoring method and system |
| CN115131994A (en) * | 2022-06-29 | 2022-09-30 | 四川九洲空管科技有限责任公司 | H-ACAS target monitoring capacity and overload capability test method and system |
| CN115131994B (en) * | 2022-06-29 | 2023-08-18 | 四川九洲空管科技有限责任公司 | H-ACAS target monitoring capacity and overload capacity test method and system |
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