Testing method and testing system for aircraft parameter display results

A technology of parameter display and test method, applied in general control systems, control/regulation systems, instruments, etc., to reduce work intensity, increase efficiency, and improve the test process.

Inactive Publication Date: 2016-08-03
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The object of the present invention is to provide a kind of aircraft parameter display result test met

Method used

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  • Testing method and testing system for aircraft parameter display results
  • Testing method and testing system for aircraft parameter display results

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Embodiment Construction

[0016] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention discloses a testing method and a testing system for aircraft parameter display results. The testing method comprises the steps that at the step S1, a test case is compiled or loaded; at the step S2, the test case at the step S1 is executed, and a source of data in the test case is formed; at the step S3, data corresponding to the test case is grasped from an airborne bus, and the data is compared with the source of the data in the test case; at the step S4, display data of a display picture of an avionic system is recognized, and a recognition result is compared with the source of the data in the test case; and at the step S5, the source of the data in the test case, analytical data of the airborne bus, and a list of the display picture recognition data are output. The testing system comprises a testing computer, an airborne display, a display control computer, the airborne bus, an airborne inertial navigation computer, an inertial navigation exciter, a reflective internal storage net, an atmospheric engine exciter and an airborne atmospheric computer. The testing method and the testing system disclosed by the invention have the advantages that testing efficiency of parameter display results of an avionic system is increased; and workloads of testing workers are reduced.

Description

technical field [0001] The invention relates to the technical field of aircraft parameter testing, in particular to an aircraft parameter display result testing method and a testing system. Background technique [0002] Many flight parameter information collected in real time during the flight of the aircraft are concentrated on the man-machine interface of the avionics system for display, such as speed, pitch angle, etc., and the display results directly affect the pilot's judgment on the status of the aircraft. Therefore, it is necessary to test the transmission and display results. [0003] In the process of testing it, the traditional method usually adopts the manual process of manually setting the exciter, manually observing the bus data, and manually observing and recording the data of the airborne display, which requires a lot of work and takes a long time. Contents of the invention [0004] The purpose of the present invention is to provide a test method and test ...

Claims

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Application Information

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IPC IPC(8): G05B17/02G01C21/00
CPCG01C21/00G05B17/02
Inventor 张原贾鑫辛国华
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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