CN107776911B

CN107776911B - PXI bus-based flight parameter system test platform and method

Info

Publication number: CN107776911B
Application number: CN201710822430.5A
Authority: CN
Inventors: 孙爱国; 刘生桂; 田博
Original assignee: Shaanxi Qianshan Avionics Co Ltd
Current assignee: Shaanxi Qianshan Avionics Co Ltd
Priority date: 2017-09-13
Filing date: 2017-09-13
Publication date: 2020-05-19
Anticipated expiration: 2037-09-13
Also published as: CN107776911A

Abstract

The invention belongs to the field of avionic testing, and relates to a PXI bus-based flight parameter system testing platform and a method. At present, the test of the flight parameter system usually adopts general test equipment based on a VXI bus or a PCI bus, which is suitable for the test of the flight parameter system, and has the defects of single signal type and insufficient signal channel quantity. The invention discloses a PXI bus-based flight parameter system test platform which comprises PXI test equipment, a power supply control box, a direct-current program control voltage-stabilized power supply and a KVM display. Based on the flight parameter system test platform, the PXI controller drives each module on the PXI bus to output simulation signals to the flight parameter system, data recorded by the flight parameter system are downloaded, and the data are compared with original uploaded data. The cost is reduced, and the functions of signal real-time dynamic simulation, signal synchronization simulation, switching value test and the like are provided.

Description

PXI bus-based flight parameter system test platform and method

Technical Field

The invention belongs to the field of avionic testing, and relates to a PXI bus-based flight parameter system testing platform and a method.

Background

The flight parameter system is a device for automatically collecting and recording various flight data, audio data and video data according to a convention format in the flight process of an airplane, and the data reflects the working state and the operation condition of a pilot when the airplane flies. The performance, quality and accuracy of recorded data of the flight parameter system directly influence the daily aircraft service of the airplane, the elimination of hidden trouble and fault, the development of a new airplane type, the search and rescue of the airplane in case of crash, and the like.

At present, the test of the flight parameter system usually adopts general test equipment based on a VXI bus or a PCI bus, which is suitable for the test of the flight parameter system, and has the characteristics of single signal type, insufficient number of signal channels, large volume of the test equipment, heavy weight, inconvenient movement and the like, and has the defects of high cost, backward technology, complex system, resource waste, insufficient verification of the flight parameter system and the like.

In order to adapt to the test characteristics of multiple signal types, large number of signal channels, complex internal logic and the like of the novel flight parameter system, enhance the requirements on the test depth and the test width of the flight parameter system and improve the automatic test efficiency, a new generation of flight parameter system test platform is urgently needed to be developed.

Disclosure of Invention

The invention aims to provide a PXI bus-based flight parameter system test platform and a PXI bus-based flight parameter system test method, so that simulation tests of all the flight parameter systems in China at present are realized, and a universal and automatic test method is provided.

The invention relates to a PXI bus-based flying parameter system test platform which comprises PXI test equipment, a power supply control box, a direct current program-controlled voltage-stabilized power supply and a KVM display, wherein the PXI test equipment is provided with a PXI controller, the PXI controller is respectively crosslinked with a frequency quantity module, a direct current analog quantity module, an HDLC bus module, an RS-422 bus module, an HB-6096 bus module, a DFTI and Harvard code bus module, a signal acquisition module, a switching value module and a multifunctional module through an internal PXI bus, the modules and the synchronizer module are respectively crosslinked with corresponding interfaces of a flying parameter system, the synchronizer module is crosslinked with the flying parameter system, and the multifunctional module controls the switching value module and the synchronizer module.

And the analog quantity module outputs alternating current analog quantity and direct current analog quantity to the flight parameter system through the alternating current analog quantity conditioning module.

And the direct current analog quantity module outputs direct current analog quantity to the flight parameter system through the direct current analog quantity conditioning module.

The PXI controller outputs bus signals to the flight parameter system through the HDLC bus module, the RS-422 bus module, the HB-6096 bus module, the DFTI and the Harvard code bus module and receives the bus signals output by the flight parameter system.

The flying parameter system test platform is installed in the shock absorption case.

A PXI bus-based flight parameter system test method is based on the flight parameter system test platform, the flight parameter system is correspondingly connected with each interface of the test platform, a PXI controller drives each module on the PXI bus to output simulation signals to the flight parameter system, data recorded by the flight parameter system are downloaded through an Ethernet interface of an HDLC or PXI controller and are compared with original uploaded data, whether the data comparison result is consistent or not is judged, an Excel test report is generated, if so, the recorded data of the flight parameter system are correct, and the test requirements are met; otherwise, the recorded data is wrong, and the flight parameter system works abnormally.

The simulation signals comprise direct current analog signals, alternating current analog signals, frequency signals, switching value signals, synchronizer signals, RS-422 bus signals, HB-6096 bus signals, DFTI bus signals or Harvard code bus signals.

Compared with the previous generation of flight parameter infield test equipment, the invention has the following advantages:

1. a multi-channel signal interface is provided, so that various signals are independent from each other, and the problem of signal parallel connection among the signals is solved;

2. the weight is reduced, the volume is reduced, the weight is about 90kg, and the height is 1.1 m;

3. the technology is advanced, the cost is reduced, and the design of a PXI bus structure is adopted, so that the technology is more advanced and the price is lower than the prior VXI and PCI system equipment technology.

4. The functions of signal real-time dynamic simulation, signal synchronization simulation, switching value test and the like are provided.

Drawings

FIG. 1 is a block diagram of the test platform of the present invention;

FIG. 2 is a block diagram of the components of the power control box;

fig. 3 is a block diagram of the test apparatus.

Detailed Description

The invention is described in further detail below with reference to the accompanying drawings, which refer to fig. 1-3.

The invention relates to a PXI bus-based flight parameter system test platform which is a hardware platform based on a PXI bus and comprises PXI test equipment, a power supply control box, a direct-current program-controlled voltage-stabilized power supply, a KVM display, a shock absorption case and a drawer.

The PXI test equipment takes a PXI controller as a core, the PXI controller utilizes an internal PXI bus to control a frequency quantity module, a direct current analog quantity module, an HDLC bus module, an RS-422 bus module, an HB-6096 bus module, a DFTI and Harvard code bus module, a signal acquisition module, a switching quantity module, a multifunctional module, a synchronizer module and other signal modules, and outputs simulation signals required by various flight parameter systems, meanwhile, all the modules are installed on a backboard, and a power supply module provides working power supply for all the signal modules through the backboard.

The power control box comprises 4 power modules, working power supplies required for conditioning are provided for the direct current analog quantity conditioning module and the alternating current analog quantity conditioning module through the 4 power modules, and meanwhile, required reference power supplies are provided for the switching value module and the multifunctional module.

The direct current program control voltage-stabilized power supply has the function of providing a normal/emergency power supply for the flight parameter system.

The KVM display integrates keyboard, display and mouse functions.

The main functions of the shock absorption case are to place PXI test equipment, a power supply control box, a direct-current program-controlled voltage-stabilized power supply and a drawer.

Claims

1. A flying parameter system test platform based on PXI bus is characterized in that: the test platform comprises PXI test equipment, a power supply control box, a direct-current program-controlled stabilized voltage supply and a KVM display, wherein the PXI test equipment is provided with a PXI controller, the PXI controller performs signal transmission through an internal PXI bus and a frequency quantity module, a direct-current analog quantity module, an HDLC bus module, an RS-422 bus module, an HB-6096 bus module, a DFTI (distributed data integrity and transmission efficiency) and Harvard code bus module, a signal acquisition module, a switching value module and a multifunctional module, all the modules performing signal transmission with the PXI controller and a synchronizer module are respectively crosslinked with corresponding interfaces of a flight parameter system, and the multifunctional module controls the switching value module and the synchronizer module; the PXI controller outputs bus signals to the flight parameter system through the HDLC bus module, the RS-422 bus module, the HB-6096 bus module, the DFTI and the Harvard code bus module and receives the bus signals output by the flight parameter system.

2. The flying reference system test platform of claim 1, wherein: and the analog quantity module outputs alternating current analog quantity and direct current analog quantity to the flight parameter system through the alternating current analog quantity conditioning module.

3. The flying reference system test platform of claim 1, wherein: and the direct current analog quantity module outputs direct current analog quantity to the flight parameter system through the direct current analog quantity conditioning module.

4. The flying reference system test platform of claim 1, wherein: the flying parameter system test platform is installed in the shock absorption case.

5. A test method of a flight parameter system based on a PXI bus is based on the flight parameter system test platform of any one of claims 1-4, and is characterized in that: correspondingly connecting the flight parameter system with each interface of the test platform, driving each module on an internal PXI bus to output simulation signals to the flight parameter system through a PXI controller, downloading data recorded by the flight parameter system through an Ethernet interface of an HDLC or PXI controller, comparing the data with original uploaded data, judging whether the data comparison result is consistent, generating an Excel test report, and if so, indicating that the data recorded by the flight parameter system is correct and meeting the test requirement; otherwise, the recorded data is wrong, and the flight parameter system works abnormally.

6. The flight parameter system test method according to claim 5, characterized in that: the simulation signals comprise direct current analog signals, alternating current analog signals, frequency signals, switching value signals, synchronizer signals, RS-422 bus signals, HB-6096 bus signals, DFTI bus signals or Harvard code bus signals.