Airborne acquisition and control computer redundancy test system

Abstract

The utility model belongs to the technical field of avionics, and particularly relates to an airborne acquisition and control computer redundancy test system. Comprising an airborne acquisition and control computer and ground maintenance equipment display equipment which are connected through an Ethernet download line A (18) or an Ethernet download line B. The airborne acquisition and control computer comprises a power supply module A groove, a power supply module B groove, a fuel oil module A groove and a fuel oil module B groove which are used for inserting corresponding modules. The power supply module A groove supplies power to the fuel oil module A groove and the IO module A groove, and the power supply module B groove supplies power to the fuel oil module B groove and the IO module B groove. And the ground maintenance equipment display equipment is used for displaying the equipment connection state, the current operation board card state, the fuel A board fault information, the fuel B board fault information, the IOA board fault information, the IOB board fault information and the software version information in blocks.

Description

Technical Field

[0001] This utility model belongs to the field of avionics technology, specifically relating to an airborne data acquisition and control computer redundancy testing system. Background Technology

[0002] The airborne data acquisition and control computer is a crucial component of the in-flight refueling fuel measurement and management computer, providing the hardware platform for fuel management. It supplies power to all modules within the system and communicates with the aircraft interface via the HB6096 bus, simultaneously acquiring discrete and analog signals from the aircraft and outputting relevant discrete, analog, and HB6096 signals. It also communicates with the fuel measurement module and power drive module within the in-flight refueling fuel measurement and management computer via an RS422 bus, receiving real-time data on fuel quantity, density, and pressure from the fuselage fuel tanks. The integrity of both the hardware and software is paramount for the product's ability to correctly perform fuel measurement and management and refueling tasks. Common redundancy systems employ dual-backup designs, with each unit acting as a hot backup for the other. Even if one unit fails, the backup unit can still interact with external systems. The redundancy of the airborne data acquisition and control computer is reflected in the fact that all internal hardware boards are designed for backup, and the software on the backup boards is identical. If one set of boards fails, the other set can still interact with external systems.

[0003] When testing common redundancy systems, the integrity of the entire system's hardware and software can be confirmed by performing complete functional performance tests on two backup products within the system. However, for airborne data acquisition and control computers, the integrity of the product's hardware and software cannot be confirmed using conventional testing methods; only whether the product can function normally can be determined.

[0004] If insufficient testing leads to potential product malfunctions upon delivery, the product's backup design will fail during actual use, failing to effectively guarantee the correct and reliable execution of aircraft missions. When redundancy failures are discovered during field use, troubleshooting and resolving the issue often requires adding debugging code or hardware, increasing the cost of onboard equipment and the time cost of field maintenance. Utility Model Content

[0005] The purpose of this utility model is to provide an airborne data acquisition and control computer redundancy testing system. This system provides an effective and reliable redundancy testing method to ensure the integrity of the product's hardware and software, and to ensure that the in-flight refueling fuel measurement and management computer correctly and reliably executes flight missions. It reduces the probability of undetected redundancy function failures before product delivery, ensuring complete and effective redundancy functions before installation; it also reduces the difficulty of locating and troubleshooting product status when field failures occur, lowers product maintenance time and manpower costs, and facilitates fault analysis.

[0006] Technical solution:

[0007] An airborne acquisition and control computer redundancy testing system includes an airborne acquisition and control computer 1 and a ground maintenance equipment display device 10. The control computer 1 and the ground maintenance equipment display device 10 are connected via an Ethernet download cable A18 or an Ethernet download cable B19.

[0008] The airborne data acquisition and control computer 1 includes power module slot A 2, power module slot B 3, fuel module slot A 4, fuel module slot B 5, I / O module slot A 6, and I / O module slot B 7 for inserting corresponding modules. Power module slot A 2, fuel module slot A 4, and I / O module slot A 6 are the A-group boards of the airborne data acquisition and control computer 1; power module slot B 3, fuel module slot B 5, and I / O module slot B 7 are the B-group boards of the airborne data acquisition and control computer 1; power module slot A 2 supplies power to fuel module slot A 4 and I / O module slot A 6, and power module slot B 3 supplies power to fuel module slot B 5 and I / O module slot B 7.

[0009] Ground maintenance equipment display device 10 is used to display in blocks: equipment connection status 11, current running board status 12, fuel A board fault information 13, fuel B board fault information 14, IOA board fault information 15, IOB board fault information 16, software version information 17.

[0010] Furthermore, the device connection status 11 shows that the airborne acquisition and control computer 1 and the ground maintenance equipment display device 10 are connected via Ethernet download cable A18 or Ethernet download cable B19, indicating whether the hard-wired communication between the two devices is normal.

[0011] Furthermore, the current running board status 12 displays either the A group board or the B group board currently running in the airborne acquisition and control computer 1.

[0012] Furthermore, the fault information 13 of the fuel A board, the fault information 14 of the fuel B board, the fault information 15 of the IOA board, and the fault information 16 of the IOB board respectively display the fault and status information of the fuel module_A slot 4, the fuel module_B slot 5, the IO module_A slot 6, and the IO module_B slot 7 in the airborne acquisition and control computer 1.

[0013] Furthermore, the software version information 17 displays the software status of either Group A or Group B boards. When the airborne acquisition and control computer 1 is connected to the physical ground maintenance equipment to which the ground maintenance equipment display device 10 belongs via Ethernet download cable A18, the software version information 17 displays the software status of Group A boards; when the airborne acquisition and control computer 1 is connected to the physical ground maintenance equipment to which the ground maintenance equipment display device 10 belongs via Ethernet download cable B19, the software version information 17 displays the software status of Group B boards.

[0014] Furthermore, the airborne data acquisition and control computer 1 is installed on the aircraft.

[0015] Beneficial effects:

[0016] This invention can significantly reduce the probability of product redundancy failures not being discovered before delivery and use, ensuring the complete and effective redundancy function of the product before installation and use.

[0017] This invention can significantly reduce the difficulty of locating the product status and troubleshooting when a product fails in the field, reduce the time and manpower costs of product maintenance, and facilitate fault analysis.

[0018] Because the test display interface reports and displays fault and status information for each internal board component, it avoids the situation where, under redundancy design conditions, the entire product's interaction with external systems is normal, but a faulty internal board component goes undetected. Fault words and status information for each board component can be added or removed arbitrarily according to actual needs. Compared to conventional redundancy testing methods, it offers better reliability and completeness. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of an airborne data acquisition and control computer redundancy testing system. Detailed Implementation

[0020] like Figure 1An airborne acquisition and control computer redundancy testing system includes an airborne acquisition and control computer 1 and a ground maintenance equipment display device 10 connected via Ethernet. The control computer 1 and the ground maintenance equipment display device 10 are connected via Ethernet download cable A18 or Ethernet download cable B19. The airborne acquisition and control computer 1 includes power module slot A 2, power module slot B 3, fuel module slot A 4, fuel module slot B 5, I / O module slot A 6, and I / O module slot B 7 for inserting corresponding modules. Power module slot A 2, fuel module slot A 4, and I / O module slot A 6 are for airborne acquisition and control computer redundancy testing. The A group of boards in the acquisition and control computer 1; power module_B slot 3, fuel module_B slot 5, and IO module_B slot 7 are the B group of boards in the airborne acquisition and control computer 1; power module_A slot 2 supplies power to fuel module_A slot 4 and IO module_A slot 6, and power module_B slot 3 supplies power to fuel module_B slot 5 and IO module_B slot 7; the ground maintenance equipment display device 10 is used to display in blocks: equipment connection status 11, current running board status 12, fuel A board fault information 13, fuel B board fault information 14, IOA board fault information 15, IOB board fault information 16, and software version information 17.

[0021] Among them, the boards in the fuel module_A slot 4 and IO module_A slot 6 are disconnected at the same time. The fault information 14 of the fuel B board determines that the board in the fuel module_A slot 4 is missing or faulty and the board in the IO module_A slot 6 is missing or faulty. The fault information 16 of the IOB board determines that the board in the IO module_A slot 6 is missing or faulty.

[0022] Only disconnect the board in slot 4 of the fuel module_A. The fault information 14 of the fuel B board indicates that the board in slot 4 of the fuel module_A is not present.

[0023] Remove only the board in slot 6 of the IO module_A, and confirm that the board in slot 6 of the IO module_A is missing or faulty through the fault information 13 of the fuel A board; confirm that the board in slot 6 of the IO module_A is missing or faulty through the fault information 16 of the IOB board.

[0024] The airborne data acquisition and control computer 1 is installed on the aircraft.

[0025] Ethernet port 8 is the maintenance interface of the airborne acquisition and control computer 1, and Ethernet port 9 is the maintenance interface of the physical ground maintenance equipment to which the ground maintenance equipment display device 10 belongs. Ethernet port 8 and Ethernet port 9 are connected by Ethernet download cable A18 or Ethernet download cable B19.

[0026] The device connection status 11 can show whether the airborne acquisition and control computer 1 and the ground maintenance equipment display device 10 are connected via Ethernet download cable A18 or Ethernet download cable B19, indicating whether the hard-wired communication between the two devices is normal.

[0027] The current running board status 12 can display either the A group board or the B group board currently running in the airborne acquisition and control computer 1.

[0028] The fuel A board fault information 13, fuel B board fault information 14, IOA board fault information 15, and IOB board fault information 16 can respectively display the fault and status information of fuel module_A slot 4, fuel module_B slot 5, IOA module_A slot 6, and IOA module_B slot 7 in the airborne acquisition and control computer 1.

[0029] The software version information 17 can display the software status of either Group A or Group B boards. When the airborne acquisition and control computer 1 and the physical ground maintenance equipment to which the ground maintenance equipment display device 10 belongs are connected via Ethernet download cable A18, the software version information 17 displays the software status of Group A boards; when the airborne acquisition and control computer 1 and the physical ground maintenance equipment to which the ground maintenance equipment display device 10 belongs are connected via Ethernet download cable B19, the software version information 17 displays the software status of Group B boards.

[0030] The software version information 17 helps confirm the consistency of the software status of the boards that are backups of each other in the product.

[0031] When the power supply to the power module_A slot 2 or power module_B slot 3 is abnormal, the fault information will be displayed via the fuel module_A slot 4 or fuel module_B slot 5 through the fuel A board fault information 13 and fuel B board fault information 14. The power module_A slot 2 and power module_B slot 3 are purely hardware-based.

[0032] When conducting redundancy function testing using the method described above, testers can select device connection status 11, current running board status 12, and software version information 17 on the ground maintenance equipment display device 10. First, they can confirm the hardware connection and communication status between the physical ground maintenance equipment to which the ground maintenance equipment display device 10 belongs and the airborne acquisition and control computer 1. Then, they can check the current running status of the boards within the product and confirm the consistency of the software status among the redundancy boards.

[0033] When conducting fault / status tests using the method described above, testers can select the fuel A board fault information 13, fuel B board fault information 14, IOA board fault information 15, and IOB board fault information 16 on the ground maintenance equipment display device 10 to obtain the real-time fault status of each board in the airborne acquisition and control computer 1, thereby assisting in product fault diagnosis and location analysis.

[0034] The present invention will now be described in further detail with reference to the accompanying drawings, such as... Figure 1 As shown, it consists of an airborne acquisition and control computer 1 and a ground maintenance equipment display device 10. The airborne acquisition and control computer 1 consists of a power module_A slot 2, a power module_B slot 3, a fuel module_A slot 4, a fuel module_B slot 5, an IO module_A slot 6, an IO module_B slot 7, and an Ethernet port 8. The ground maintenance equipment display device 10 consists of a device connection status 11, a current running board status 12, fuel A board fault information 13, fuel B board fault information 14, IOA board fault information 15, IOB board fault information 16, software version information 17, and an Ethernet port 9.

[0035] The power module_A slot 2, fuel module_A slot 4, and IO module_A slot 6 are the A group boards of the airborne acquisition and control computer 1; the power module_B slot 3, fuel module_B slot 5, and IO module_B slot 7 are the B group boards of the airborne acquisition and control computer 1. The two groups of boards can be plugged in and out separately according to the actual test conditions, that is, any one or several boards in the A group can be plugged in and out at the same time, or any one or several boards in the B group can be plugged in and out at the same time.

[0036] The power module_A slot 2 supplies power to the fuel module_A slot 4 and the IO module_A slot 6, and the power module_B slot 3 supplies power to the fuel module_B slot 5 and the IO module_B slot 7.

[0037] The airborne data acquisition and control computer 1 is installed on the aircraft, and the ground maintenance equipment display device 10 is the operating interface of the ground maintenance software of its entity, which is installed on a PC.

[0038] Ethernet port 8 is the maintenance interface of the airborne acquisition and control computer 1, and Ethernet port 9 is the maintenance interface of the physical ground maintenance equipment to which the ground maintenance equipment display device 10 belongs. Ethernet port 8 and Ethernet port 9 are connected by Ethernet download cable A18 or Ethernet download cable B19.

[0039] The device connection status 11 can show whether the airborne acquisition and control computer 1 and the ground maintenance equipment display device 10 are connected via Ethernet download cable A18 or Ethernet download cable B19, indicating whether the hard-wired communication between the two devices is normal.

[0040] The current running board status 12 can display either the A group board or the B group board currently running in the airborne acquisition and control computer 1.

[0041] The fuel A board fault information 13, fuel B board fault information 14, IOA board fault information 15, and IOB board fault information 16 can respectively display the fault and status information of fuel module_A slot 4, fuel module_B slot 5, IOA module_A slot 6, and IOA module_B slot 7 in the airborne acquisition and control computer 1.

[0042] The software version information 17 can display the software status of either Group A or Group B boards. When the airborne acquisition and control computer 1 and the physical ground maintenance equipment to which the ground maintenance equipment display device 10 belongs are connected via Ethernet download cable A18, the software version information 17 displays the software status of Group A boards; when the airborne acquisition and control computer 1 and the physical ground maintenance equipment to which the ground maintenance equipment display device 10 belongs are connected via Ethernet download cable B19, the software version information 17 displays the software status of Group B boards.

[0043] When the power supply to the power module_A slot 2 or power module_B slot 3 is abnormal, the fault information will be displayed via the fuel module_A slot 4 or fuel module_B slot 5 through the fuel A board fault information 13 and fuel B board fault information 14. The power module_A slot 2 and power module_B slot 3 are purely hardware-based.

[0044] The general implementation steps of a method for testing the redundancy of an airborne data acquisition and control computer are as follows:

[0045] Step 1: The tester selects either Ethernet download cable A18 or Ethernet download cable B19 to connect the airborne acquisition and control computer 1 to the physical ground maintenance equipment to which the ground maintenance equipment display device 10 belongs.

[0046] Step 2: The tester selects device status connection 11 in the ground maintenance equipment display device 10 to ensure that the hard-wired connection and communication are normal.

[0047] Step 3: The tester selects the current running board status 12 in the ground maintenance equipment display device 10.

[0048] Step 4: If Ethernet download cable A18 is connected at this time, the current running board status 12 will display either the currently running board A or the currently running board B. If a board in group A is faulty, it will switch to the board in group B and display the currently running board B. If a board in group A is working normally, it will display the currently running board A.

[0049] Step 5: If the Ethernet download cable B19 is connected at this time, the currently running B group boards can be displayed through the current running board status 12.

[0050] Step 6: The tester selects the software version information 17 on the ground maintenance equipment display device 10.

[0051] Step 7: If the Ethernet download cable A18 is connected at this time, the software status of the A group boards can be displayed through the software version information 17.

[0052] Step 8: If the Ethernet download cable B19 is connected at this time, the software status of the B group board can be displayed through the software version information 17.

[0053] Step 9: The tester selects the following fault information on the ground maintenance equipment display device 10: Fuel A board fault information 13, Fuel B board fault information 14, IOA board fault information 15, and IOB board fault information 16 to view the fault / status information of any one of the boards.

[0054] When performing board insertion / removal redundancy function testing, follow these steps:

[0055] Step 1: The tester removes any one or more boards from Group A or any one or more boards from Group B of the airborne acquisition and control computer 1.

[0056] Step 2: If the board removed by the tester involves fuel module_A slot 4 and power module_A slot 2 in group A, then select Ethernet download cable B19 to connect the device.

[0057] Step 3: If the board removed by the tester involves the fuel module_B slot 5 and power module_B slot 3 in group B, then select Ethernet download cable A18 to connect the device.

[0058] Step 4: Except for steps 2 and 3, you can choose either Ethernet download cable A18 or Ethernet download cable B19 to connect the device.

[0059] Step 5: Perform the test according to steps 2 to 9 in the general implementation steps of an airborne data acquisition and control computer redundancy test method.

[0060] In addition to performing functional performance tests on products using conventional redundancy systems, this application can also clearly display the status information of currently running boards and accurately and quickly obtain fault / status information of any group of boards in the product, ensuring the integrity of redundancy function verification and facilitating product designers and testers in locating the redundancy status of the airborne acquisition and control computer and analyzing faults.

[0061] This application can reduce the probability of product redundancy failures not being discovered before product delivery and use, ensuring the complete and effective redundancy functions of the product before installation and use; reduce the difficulty of product status positioning and fault diagnosis when product failures occur in the field, reduce product maintenance time and manpower costs, and facilitate fault analysis.

[0062] It can ensure the integrity of redundancy function verification, ensure the integrity of the product's own hardware and software, facilitate product designers and testers to locate the redundancy status of the airborne acquisition and control computer and analyze faults, and ensure that the in-flight refueling fuel measurement and management computer can correctly and reliably perform flight missions.

Claims

1. A redundancy testing system for an airborne data acquisition and control computer, characterized in that, It includes an airborne data acquisition and control computer (1) and a ground maintenance equipment display device (10). The control computer (1) and the ground maintenance equipment display device (10) are connected via Ethernet download cable A (18) or Ethernet download cable B (19). The airborne acquisition and control computer (1) includes a power module_A slot (2), a power module_B slot (3), a fuel module_A slot (4), a fuel module_B slot (5), an IO module_A slot (6), and an IO module_B slot (7) for inserting corresponding modules. The power module_A slot (2), the fuel module_A slot (4), and the IO module_A slot (6) are used to place the A group boards of the airborne acquisition and control computer (1); the power module_B slot (3), the fuel module_B slot (5), and the IO module_B slot (7) are used to place the B group boards of the airborne acquisition and control computer (1); the power module_A slot (2) supplies power to the fuel module_A slot (4) and the IO module_A slot (6), and the power module_B slot (3) supplies power to the fuel module_B slot (5) and the IO module_B slot (7). The ground maintenance equipment display device (10) is used to display in blocks: equipment connection status (11), current running board status (12), fuel A board fault information (13), fuel B board fault information (14), IOA board fault information (15), IOB board fault information (16), and software version information (17).

2. The system according to claim 1, characterized in that, The device connection status (11) shows that the airborne acquisition and control computer 1 and the ground maintenance equipment display device (10) are connected via Ethernet download cable A (18) or Ethernet download cable B (19) to maintain the connection between the two devices, indicating whether the hard-wired communication between the two devices is normal.

3. The system according to claim 1, characterized in that, The current running board status (12) displays the currently running board A or board B in the airborne acquisition and control computer (1).

4. The system according to claim 1, characterized in that, The fault information of fuel A board (13), fuel B board (14), IOA board (15), and IOB board (16) respectively displays the fault and status information of fuel module_A slot (4), fuel module_B slot (5), IO module_A slot (6), and IO module_B slot (7) in the airborne acquisition and control computer (1).

5. The system according to claim 1, characterized in that, The software version information (17) displays the software status of either Group A or Group B boards. When the airborne acquisition and control computer (1) and the physical ground maintenance equipment to which the ground maintenance equipment display device (10) belongs are connected via Ethernet download cable A (18), the software version information (17) displays the software status of Group A boards. When the airborne acquisition and control computer (1) and the physical ground maintenance equipment to which the ground maintenance equipment display device (10) belongs are connected via Ethernet download cable B (19), the software version information (17) displays the software status of Group B boards.

6. The system according to claim 1, characterized in that, The airborne data acquisition and control computer (1) is installed on the aircraft.

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