Rapid automatic test platform and method for airplane excitation power supply

Abstract

The invention provides a rapid automatic test platform and method for an airplane excitation power supply. The platform comprises a control panel, a connector and a digital multimeter, the connector comprises a relay control module, a plurality of relays and a power supply module. The relay control module is connected with the control panel and the control end of each relay, and each relay is arranged between the digital multimeter and different excitation power supplies to be tested; the digital multimeter is used for testing the voltage of the excitation power supply; the power module is used for supplying power to the relay control module and the relay; the control panel is used for storing a mapping relation between the relay and the tested excitation power supply and generating a test case instruction according to the mapping relation; the relay control module receives a test case instruction sent by the control panel, generates a driving instruction, and controls the opening and closing of each relay, thereby achieving the switching of a tested excitation power supply object.

Description

Technical Field

[0001] The invention belongs to the field of aircraft excitation power supply testing, and in particular relates to a rapid automatic testing platform and method for aircraft excitation power supply. Background Art

[0002] The excitation power supply is the reference power supply for various sensors such as cockpit control system sensors, actuation system servo valves, actuator cylinder sensors, and control surface position sensors. Therefore, the excitation power supply is extremely important for aircraft control. The accuracy of the excitation power supply determines the accuracy of the control surface position, control force, fuel flow, and other information sensed by the aircraft sensors.

[0003] Therefore, the quality characteristics of the aircraft excitation power supply need to be tested on the ground. The traditional test method is to lead the excitation power supply to the test panel with a wire, and the operator uses a digital multimeter to test each excitation power supply item by item to see if it meets the requirements. However, since the aircraft design adopts the power system redundancy design concept, taking the aircraft flight control system as an example, the flight control system alone contains 108 excitation power supplies. Using the above traditional test method is time-consuming and has a low degree of automation. Summary of the invention

[0004] Since a large number of excitation power supplies are involved in ground testing, and the current traditional testing methods are time-consuming and have a low degree of automation, the present invention provides a rapid automated testing platform and method for aircraft excitation power supplies, which solves the problem of cumbersome testing of a large number of excitation power supplies.

[0005] A first aspect of the present invention provides a rapid automated test platform for aircraft excitation power supply, comprising: a control panel, a connector, and a digital multimeter;

[0006] The connector includes: a relay control module, multiple relays and a power supply module; the relay control module is connected to the control panel and the control end of each relay.

[0007] Each relay is respectively arranged between the digital multimeter and different excitation power supplies to be tested; the digital multimeter is used to perform voltage test of the excitation power supply;

[0008] The power module is used to supply power to the relay control module and the relay;

[0009] The control panel is used to store the mapping relationship between the relay and the tested excitation power supply, and generate test case instructions according to the mapping relationship;

[0010] The relay control module receives the test case instructions sent by the control panel and generates drive instructions to control the opening and closing of each relay, thereby realizing the switching of the excitation power supply object under test.

[0011] Optionally, the relay control module includes: a processor, a communication interface, and a plurality of relay drive circuits;

[0012] The processor is connected to the control panel via a communication interface and is also connected to the control end of each relay via a plurality of relay drive circuits;

[0013] The communication interface receives the test case instructions issued by the control panel through the LAN bus, and sends them to the processor through the LAN bus;

[0014] The processor is used to parse and verify the test case instructions, control the relay drive circuit through the SPI bus to drive the relay action contained in the test case instructions, and realize the line switching of the tested excitation signal.

[0015] Optionally, the mapping relationship between the relay and the excitation power supply under test indicates the mapping relationship between the MAC address of the I / O port of the processor to which the relay driving circuit of the relay is connected and the excitation power supply under test.

[0016] Optionally, a control panel is used to receive at least one tested excitation power supply input by a user, and generate a test case instruction according to a mapping relationship; the test case instruction carries the MAC address and control instruction of the relay corresponding to each tested excitation power supply input by the user; the control instruction includes opening and closing.

[0017] Optionally, the control panel is used to, upon receiving multiple excitation power supplies to be tested input by the user, sort the excitation power supplies to be tested by category and generate test case instructions.

[0018] Optionally, the categories of the tested excitation power supply include: cockpit position, cabin position, engine position, and movable wing surface position.

[0019] Optionally, the categories of the tested excitation power supply include: fuel system, flight control system and engine parameter acquisition system.

[0020] A second aspect of the present invention provides a method for rapid automated testing of an aircraft excitation power supply, which is performed using a platform as described in any one of the first aspects.

[0021] The present invention provides a rapid automated testing platform and method for aircraft excitation power supplies, which can realize rapid automatic detection of excitation power supplies, shorten the test time from the original 30 minutes to 5 minutes, and improve the test efficiency by 80%. Through application practice, the rapid automated testing of the flight control system excitation power supply has been realized for the first time in China. At the same time, the method has certain versatility and can be used as a reference for the test design of excitation power supplies for other models. The present invention is a rapid automated testing method for aircraft excitation power supplies, which contains a digital multimeter, a connector, and a control panel, and realizes rapid programmed automatic testing of aircraft excitation power supplies. It can not only automatically and programmatically complete the voltage test of a large number of excitation power supplies without human intervention, but also realize the voltage test of a single excitation power supply. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is the design principle block diagram of the excitation power supply test device;

[0023] Figure 2 Relay control module block diagram;

[0024] Figure 3 It is a schematic diagram of the control panel test strategy design;

[0025] Figure 4 It is a schematic diagram of rapid automated testing of the excitation power supply. DETAILED DESCRIPTION

[0026] The present application is further described in detail below with reference to examples and drawings:

[0027] The invention provides a method for rapid automated testing of an aircraft excitation power supply. The wire of the excitation power supply is introduced into the connector through a connector, and the connector realizes the switching of the excitation power supply test object through an internal relay circuit. The digital multimeter is responsible for the voltage test of the excitation power supply. The control panel configures the mapping relationship between the channel number of the relay control module and the excitation signal, develops and customizes, and runs the corresponding test case, and drives the relay inside the connector to perform switching test according to the test case and the order set by the test case.

[0028] The connector is connected to a digital multimeter at one end, and introduces a multi-channel excitation power supply into an internal test circuit through a wire at the other end of the connector. The internal test circuit of the connector includes a relay control module, a relay and a power module. The power module supplies power to the relay control module and the relay. The relay control module receives the test case instruction sent by the control panel to generate a drive instruction, and controls the relay on the test circuit to generate a corresponding switching action, thereby realizing the switching of the excitation power supply object under test.

[0029] The relay control module contains a processor, a communication interface, and a relay drive circuit. The communication interface receives control instructions sent by the control panel through the LAN bus. After analysis and verification by the processor, the relay drive circuit is controlled through the SPI bus to drive the corresponding relay action, thereby realizing the line switching of the measured excitation signal.

[0030] The control panel to which it belongs configures the mapping relationship between the channel number of the relay control module and the excitation signal, allocates different MAC addresses to each relay according to the connection relationship between the relay and the processor I / O port, and forms an interconnection relationship configuration table between the relays with different MAC addresses and each excitation signal to be tested. According to the interconnection relationship configuration table, the MAC address of the relay to be controlled is mapped, and a control instruction is issued to the relay with the MAC address. The processor in the relay control module receives the control instruction issued by the control panel through the network, and parses the control instruction in the network into the action instruction of the relay corresponding to the MAC address.

[0031] The control panel can be customized to develop and edit test cases. According to the number of excitation power supplies to be tested and the classification relationship, a customized test strategy is formulated. The present invention customizes and develops two test strategies.

[0032] The control panel is customized to develop a single-channel excitation test strategy to form a test case. In the human-computer interaction interface, the single-channel excitation power supply to be tested is configured and checked. The control panel issues a test instruction according to the interconnection configuration table. After receiving the instruction, the processor in the relay control module controls the relay action corresponding to the MAC address of the single-channel excitation signal. Connect the cable of the multimeter pen to the excitation signal to be tested. The multimeter can display the test results at this time, and the control panel will pop up a window to prompt personnel to read the test data and records.

[0033] The control panel to which it belongs customizes the development of automated testing strategies to form test cases. The automated test sorts all the excitation power supplies by category. The tester selects all the excitation power supply items to be tested. The control panel automatically sends the test control instruction of the first-ranked excitation signal to be tested to the relay control module in the connector according to the interconnection configuration table. The relay control module drives the relay corresponding to the MAC address of the first-ranked excitation signal to be tested according to the received instruction. The multimeter can now display the test results, and the control panel pops up a window to prompt the tester to read the test data and records. After the tester clicks "OK", the control panel automatically sends the test control instruction of the second-ranked excitation signal to be tested and the relay drive according to the excitation power supply sorting, and performs the excitation power supply test again. During the entire test process, the items to be tested and the completed test items can be observed in the automated test interface.

[0034] See attached Figure 1The invention of the invention is a method for rapid automated testing of aircraft excitation power supply. The excitation power supply wire is introduced into the connector through the connector, and the connector realizes the switching of the excitation power supply test object through the internal relay circuit. The digital multimeter is responsible for the voltage test of the excitation power supply. The control panel configures the mapping relationship between the channel number of the relay control module and the excitation signal and runs the test case, and drives the relay inside the connector to perform switching test according to the test case setting sequence.

[0035] See attached Figure 2 The relay control module of the present invention includes a processor, a communication interface, and a relay drive circuit. The communication interface receives control instructions issued by the control panel through the LAN bus. After being parsed and verified by the processor, the relay drive circuit is controlled through the SPI bus to drive the corresponding relay action, thereby realizing the line switching of the measured excitation signal.

[0036] Participate in the Figure 3 , 4 The control panel of the present invention can be customized to develop and edit test cases. When receiving multiple tested excitation power supplies input by the user, each tested excitation power supply is sorted by category to generate test case instructions. The excitation power supply has two classification categories, one category is: cockpit position, cabin position, engine position, active wing position, and the other category is: fuel system, flight control system and engine parameter acquisition system.

Claims

1. A rapid automated test platform for aircraft excitation power supply, characterized in that: include: Control panels, connectors, digital multimeters; The connector includes: a relay control module, multiple relays and a power supply module; the relay control module is connected to the control panel and the control end of each relay. Each relay is respectively arranged between the digital multimeter and different excitation power supplies to be tested; the digital multimeter is used to perform voltage test of the excitation power supply; The power module is used to supply power to the relay control module and the relay; The control panel is used to store the mapping relationship between the relay and the tested excitation power supply, and generate test case instructions according to the mapping relationship; The relay control module receives the test case instructions sent by the control panel and generates drive instructions to control the opening and closing of each relay, thereby realizing the switching of the excitation power supply object under test.

2. The aircraft excitation power supply rapid automated testing platform according to claim 1, characterized in that: The relay control module includes: a processor, a communication interface, and multiple relay drive circuits; The processor is connected to the control panel via a communication interface and is also connected to the control end of each relay via a plurality of relay drive circuits; The communication interface receives the test case instructions issued by the control panel through the LAN bus, and sends them to the processor through the LAN bus; The processor is used to parse and verify the test case instructions, control the relay drive circuit through the SPI bus to drive the relay action contained in the test case instructions, and realize the line switching of the tested excitation signal.

3. The aircraft excitation power supply rapid automated testing platform according to claim 2, characterized in that: The mapping relationship between the relay and the excitation power supply under test indicates the mapping relationship between the MAC address of the I / O port of the processor to which the relay driving circuit of the relay is connected and the excitation power supply under test.

4. The aircraft excitation power supply rapid automated testing platform according to claim 3, characterized in that: The control panel is used to receive at least one tested excitation power supply input by the user, and generate a test case instruction according to the mapping relationship; the test case instruction carries the MAC address and control instruction of the relay corresponding to each tested excitation power supply input by the user; the control instruction includes opening and closing.

5. The aircraft excitation power supply rapid automated testing platform according to claim 4, characterized in that: The control panel is used to, when receiving multiple tested excitation power supplies input by the user, sort the tested excitation power supplies by category and generate test case instructions.

6. The aircraft excitation power supply rapid automated testing platform according to claim 5, characterized in that: The classification categories of the tested excitation power supply include: cockpit position, cabin position, engine position, and movable wing surface position.

7. The aircraft excitation power supply rapid automated testing platform according to claim 5, characterized in that: The classification categories of the tested excitation power supplies include: fuel system, flight control system and engine parameter acquisition system.

8. A method for rapid automated testing of aircraft excitation power supply, characterized in that: The method is implemented by using a platform as described in any one of claims 1 to 7.

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