CN103592908A - Air vehicle integrated testing system based on 1553B bus - Google Patents

Abstract

An aircraft integrated test system based on the 1553B bus, including a power distribution conversion module, a DC power supply, a DC power supply controller, an AC power supply, an AC power supply controller, a measurement and control computer, a bus controller, a test interface adapter, a bus protocol conversion module, AD acquisition module, digital multimeter, test control module, signal conditioning module and data interpretation module. The present invention fully integrates relevant equipment in the traditional aircraft test scheme to form a highly integrated general test platform, assisted by advanced software technology, and realizes the integration, miniaturization and portability of the aircraft ground test.

Description

An Aircraft Integrated Test System Based on 1553B Bus

technical field

The invention relates to an aircraft integrated test system based on a 1553B bus, which is suitable for verifying the parameter characteristics of the avionics system during the ground test of the aerospace/aviation aircraft before leaving the factory.

Background technique

At present, the traditional distributed test technology is widely used in the ground test system of the domestic aviation/space vehicle before leaving the factory, which is used for the internal function and performance test of different systems.

Aviation/aerospace vehicle distributed test technology refers to the difference between different subsystems, such as the power supply and power distribution subsystem, navigation guidance and control subsystem, measurement and control communication subsystem, data and health management subsystem under the same avionics system. It has a set of independent ground test equipment, which independently completes the functions of power supply, power distribution, signal excitation, state parameter control, and measurement of various systems on the aircraft. This test method, in the initial stage of the development of the defense industry, had certain advantages in the development and management of the system according to the actual needs of the ground test system at that time. At present, with the continuous improvement of test requirements for aircraft avionics systems, the defects of distributed test schemes, duplication of test equipment functions, and poor comprehensive utilization have become more and more obvious. Inconsistent standards lead to poor compatibility and low reliability of the entire system, and the maintenance of test equipment requires a lot of manpower and material resources, resulting in a lot of waste of resources. Secondly, due to the large number of equipment in the test site of each subsystem, the layout of cables in the site is often chaotic, the command of personnel is not in place, the test process and status are not clear, it is very easy to cause misoperation by test personnel, the number of test repetitions is large, and it is difficult to find errors, etc. question.

With the increase of aircraft development tasks, the accumulation of a large amount of experience of designers, the vigorous development of network technology, the continuous innovation of bus test technology, and the urgent need for new test technology, the traditional distributed ground test technology can no longer adapt to the current aviation environment. /Test requirements for aerospace vehicles.

Contents of the invention

The technical solution problem of the present invention is: overcome the deficiency of traditional distributed test technology, provide a kind of aircraft integrated test system based on 1553B bus, realize the integration, miniaturization, portability of aviation/aerospace aircraft test before leaving the factory.

Technical solution of the present invention is:

An aircraft integrated test system based on 1553B bus, including: power distribution conversion module, DC power supply, DC power supply controller, AC power supply, AC power supply controller, measurement and control computer, bus controller, test interface adapter, bus protocol conversion module , AD acquisition module, digital multimeter, test control module, signal conditioning module and data interpretation module;

The external power supply supplies power to the DC power supply and the AC power supply through the power distribution conversion module. The DC power supply controller controls the DC power supply to provide DC power to the test interface adapter. The AC power supply controller controls the AC power supply to provide AC power to the test interface adapter. The measurement and control computer sends test instructions to the bus. controller, the bus controller converts the test instructions into 1553B bus data packets and sends them to the test control module through the 1553B bus, and the test control module generates corresponding test excitation signals according to the test instructions in the data packets, and passes the bus protocol conversion module Perform bus protocol conversion, and then send the test excitation signal to the aircraft through the test interface adapter to control the aircraft to perform corresponding actions. The analog signal generated when the aircraft operates is sent to the signal conditioning module through the test interface adapter for signal conditioning. After conditioning, the signal is sent to Input the AD acquisition module for analog-to-digital conversion, and also send it to the digital multimeter. The AD acquisition module sends the generated digital signal to the data interpretation module for data interpretation, and then sends it to the measurement and control computer through the 1553B bus and the bus controller in turn. ;The digital multimeter sends the measurement results directly to the measurement and control computer through the 1553B bus and the bus controller;

The bus data signal generated when the aircraft operates is sent to the bus protocol conversion module through the test interface adapter for bus protocol conversion, and then sent to the measurement and control computer through the 1553B bus and the bus controller in turn.

The data interpretation is specifically: if the converted digital signal is within the preset range, then the converted digital signal is sent to the measurement and control computer through the 1553B bus and the bus controller in turn; if the converted digital signal exceeds the preset range, then An abnormal data prompt signal is generated, and the abnormal data prompt signal and the converted digital signal are sent to the measurement and control computer through the 1553B bus and the bus controller.

The digital multimeter includes a digital ammeter and a digital voltmeter, which are used to test the voltage value and current value of the analog signal, and the precision is higher than six and a half digits.

The beneficial effect of the present invention compared with prior art is:

(1) The present invention can realize the high integration of the ground test system. The measurement and control computer is connected to the 1553B data bus as a BC terminal, directly obtains the test information uploaded and uploaded by the aircraft and sends different test instructions according to the test process. At the same time, it can also Through the test interface adapter, various traditional test equipment can be connected externally to expand its own test function.

(2) The test information interaction is strictly controlled according to the 1553B bus protocol, which can prevent misoperation; the test judgment speed block can directly observe the test results on the display screen of the measurement and control computer, and the test results can be directly printed by the built-in printer, or The data is directly stored in the hard disk of the measurement and control computer to complete the one-stop ground test.

(3) The present invention can adopt the test resource sharing system to effectively reduce the number of test equipment, so that the cables on the test site can be centralized and restrained, so that the test site is clear and easy to manage, and it also prevents the repeated use of test equipment and reduces Test costs, reducing the number of operators.

Description of drawings

Fig. 1 is a system block diagram of the present invention;

Detailed ways

Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

As shown in Figure 1, the present invention provides a kind of aircraft integrated test system based on 1553B bus, including: power distribution conversion module, DC power supply, DC power supply controller, AC power supply, AC power supply controller, measurement and control computer, bus control device, test interface adapter, bus protocol conversion module, AD acquisition module, digital multimeter, test control module, signal conditioning module and data interpretation module;

The external power supply supplies power to the DC power supply and the AC power supply through the power distribution conversion module. The DC power supply controller controls the DC power supply to provide DC power to the test interface adapter. The AC power supply controller controls the AC power supply to provide AC power to the test interface adapter. The measurement and control computer sends test instructions to the bus. controller, the bus controller converts the test instructions into 1553B bus data packets and sends them to the test control module through the 1553B bus, and the test control module generates corresponding test excitation signals according to the test instructions in the data packets, and passes the bus protocol conversion module Perform bus protocol conversion, and then send the test excitation signal to the aircraft through the test interface adapter to control the aircraft to perform corresponding actions. The analog signal generated when the aircraft operates is sent to the signal conditioning module through the test interface adapter for signal conditioning. After conditioning, the signal is sent to Input the AD acquisition module for analog-to-digital conversion, and also send it to the digital multimeter. The AD acquisition module sends the generated digital signal to the data interpretation module for data interpretation, and then sends it to the measurement and control computer through the 1553B bus and the bus controller in turn. ;The digital multimeter sends the measurement results directly to the measurement and control computer through the 1553B bus and the bus controller;

The data interpretation is specifically: if the converted digital signal is within the preset range, then the converted digital signal is sent to the measurement and control computer through the 1553B bus and the bus controller in turn; if the converted digital signal exceeds the preset range, then An abnormal data prompt signal is generated, and the abnormal data prompt signal and the converted digital signal are sent to the measurement and control computer through the 1553B bus and the bus controller. The digital multimeter includes a digital ammeter and a digital voltmeter, which are used to test the voltage value and current value of the analog signal, and the precision is higher than six and a half digits.

The bus data signal generated when the aircraft operates is sent to the bus protocol conversion module through the test interface adapter for bus protocol conversion, and then sent to the measurement and control computer through the 1553B bus and the bus controller in turn.

The power distribution conversion module, DC power supply, DC power supply controller, AC power supply, and AC power supply controller cooperate to complete the power supply for an aircraft integrated test system based on the 1553B bus, wherein the power distribution conversion module converts the external power supply into a system The required AC and DC quantities are output by the DC power supply and the AC power supply. When the output voltage value and current value of the DC power supply or the AC power supply exceed the preset normal range, the DC power supply controller or the AC power supply controller will Control the output voltage or current value of the DC power supply or AC power supply, increase or decrease the corresponding voltage value and current value, and realize the stable power supply of the integrated test system.

The main function of the measurement and control computer is to send control commands to the aircraft through the 1553B bus, and at the same time receive the response signal from the aircraft, and integrate the functions of displaying, storing, and printing data. equipment.

The bus controller is designed and implemented by a mature bus controller chip on the market. Its main function is to convert the control instructions sent by the measurement and control computer from the computer bus data format into the 1553B data bus protocol format, and return the collected 1553B bus protocol data packets to the Pass it to the measurement and control computer to manage the data transmission on the 1553B bus.

The test interface adapter provides the electrical interface between the aircraft and the integrated test system, including various data bus interfaces required by the equipment on the aircraft, such as CAN bus, RS422 bus, SPI bus, etc., and key parameters are directly transmitted back to the measurement and control computer. Analog quantity, switch quantity data, and unified test interface are important foundations for the smooth realization of the integrated test system.

The bus protocol conversion module is designed and realized by the bus protocol conversion board. The bus protocol conversion board is realized by FPGA, various bus controller chips, manager chips, and level matching circuit hardware. The FPGA is controlled by writing the hardware description language to complete the 1553B bus and The protocol conversion between other data buses on the aircraft converts various traditional data buses into the 1553B bus format uniformly used by the integrated test system, and the verification method of the 1553B bus effectively improves the reliability of data transmission, and due to The transmission rate of the 1553B data bus is faster than the CAN bus, RS422 bus and SPI bus, which can effectively increase the transmission rate of the bus and improve the overall working efficiency of the integrated test system. In addition, the 1553B bus can mount multiple peripherals at the same time, which is more efficient than the traditional data bus point-to-point transmission mode, and is conducive to the miniaturization and portability of the integrated test system.

The AD acquisition module is responsible for collecting the analog data sent back from the aircraft and converting it into a digital signal that can be recognized by the integrated test system.

The digital multimeter can collect high-precision analog data (higher than six and a half digits) uploaded by the aircraft, and send the collected high-precision analog data to the measurement and control computer, and display it in real time on the display interface of the measurement and control computer. Provide reference for the working status of each part of the aircraft during the test.

The signal conditioning module converts the analog signal amplified and filtered by the aircraft through the test interface adapter into a standard signal that the integrated test system can recognize. To be correctly identified, it must be cleared after conditioning.

The data interpretation module interprets the collected data of the aircraft. When the collected voltage and current values are within the preset range, it is considered that the relevant systems of the aircraft are working normally, and the interpretation results are sent to the measurement and control computer. The corresponding position of the display will give a prompt message indicating that the result is normal; if the collected voltage value and current value exceed the preset range, it will be determined that the relevant system of the aircraft is working abnormally, and the fault information will be sent to the measurement and control computer, and the corresponding position of the display on the measurement and control computer will be A fault report message will be displayed and the operator will be prompted to perform an emergency power-off.

Parts not described in detail in the present invention belong to the common knowledge of those skilled in the art.

Claims (3)

1. an aircraft integrated test system based on 1553B bus, it is characterized in that comprising: power distribution conversion module, DC power supply, DC power supply controller, AC power supply, AC power supply controller, measurement and control computer, bus controller, test interface adapter , bus protocol conversion module, AD acquisition module, digital multimeter, test control module, signal conditioning module and data interpretation module; The external power supply supplies power to the DC power supply and the AC power supply through the power distribution conversion module. The DC power supply controller controls the DC power supply to provide DC power to the test interface adapter. The AC power supply controller controls the AC power supply to provide AC power to the test interface adapter. The measurement and control computer sends test instructions to the bus. controller, the bus controller converts the test instructions into 1553B bus data packets and sends them to the test control module through the 1553B bus, and the test control module generates corresponding test excitation signals according to the test instructions in the data packets, and passes the bus protocol conversion module Perform bus protocol conversion, and then send the test excitation signal to the aircraft through the test interface adapter to control the aircraft to perform corresponding actions. The analog signal generated when the aircraft operates is sent to the signal conditioning module through the test interface adapter for signal conditioning. After conditioning, the signal is sent to Input the AD acquisition module for analog-to-digital conversion, and also send it to the digital multimeter. The AD acquisition module sends the generated digital signal to the data interpretation module for data interpretation, and then sends it to the measurement and control computer through the 1553B bus and the bus controller in turn. ;The digital multimeter sends the measurement results directly to the measurement and control computer through the 1553B bus and the bus controller; The bus data signal generated when the aircraft operates is sent to the bus protocol conversion module through the test interface adapter for bus protocol conversion, and then sent to the measurement and control computer through the 1553B bus and the bus controller in turn. 2. A kind of aircraft integrated test system based on 1553B bus according to claim 1, it is characterized in that: data interpretation is specifically: if the digital signal that conversion generates is in preset range, then the digital signal that conversion generation is successively Send it to the measurement and control computer through the 1553B bus and the bus controller; if the digital signal generated by the conversion exceeds the preset range, an abnormal data prompt signal will be generated, and the abnormal data prompt signal and the digital signal generated by the conversion will pass through the 1553B The bus and the bus controller are fed into the measurement and control computer. 3. a kind of aircraft integrated test system based on 1553B bus according to claim 1, is characterized in that: described digital multimeter comprises digital ammeter and digital voltmeter, is used for testing the voltage value and current value of analog signal , and the precision is higher than six and a half digits.

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