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Method for automatically testing control law of flying control system

A flight control system and automatic testing technology, applied in the direction of electrical testing/monitoring, etc., can solve problems such as error-prone, heavy workload, and long time-consuming, and achieve the effect of not being easy to make mistakes, small workload, and high efficiency

Active Publication Date: 2010-12-08
FLIGHT AUTOMATIC CONTROL RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002]The current flight control system control law test method is to manually set or input the control law test program for each flight state that needs to be tested. Various initialization conditions of the test are added to the control stimulus, the time domain response of the system closed-loop related flight parameters is recorded, and the compliance degree and level of the flight quality are checked according to the corresponding time domain criteria; Thousands of manual operations are performed; the disadvantages are: the testing process is basically completed manually, with a large workload, low efficiency, time-consuming, and error-prone

Method used

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  • Method for automatically testing control law of flying control system
  • Method for automatically testing control law of flying control system

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0035] 1. Control law automatic test initialization condition setting;

[0036] 1.1. Write the following test input file;

[0037] No. Flight status Dx Dy Dz alf t1 t2 t3

[0038] 0001 0003 20 0 0 0 1 3 10

[0039] ………………………………

[0040] 1.2, above-mentioned file is read into in the computer that test program is stored on the main console 7;

[0041] 1.3. Determine other test conditions;

[0042] 2. Carry out automatic test of control law;

[0043] 2.1. Automatic trimming;

[0044] 2.2, enter the automatic test;

[0045] 2.3. According to the test input file, the test results are sequentially stored and recorded as data files in the following format;

[0046] 0001.dat:

[0047] Time Sideslip Angle Roll Rate Yaw Rate Roll Angle Lateral G Flaperon Rudder Stabilizer Differential Crossbar Pedals

[0048] 0.01000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000

[0049] 0.02000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0...

Embodiment 2

[0060] 1. Control law automatic test initialization condition setting;

[0061] 1.1. Write the following test input file;

[0062] No. Flight status Dx Dy Dz a1f t1 t2 t3

[0063] 0001 0004 30 0 0 0 1 3 10

[0064] ………………………………

[0065] 1.2, above-mentioned file is read into in the computer that test program is stored on the main console 7;

[0066] 1.3. Determine other test conditions;

[0067] 2. Carry out automatic test of control law;

[0068] 2.1. Automatic trimming;

[0069] 2.2, enter the automatic test;

[0070] 2.3. According to the test input file, the test results are sequentially stored and recorded as data files in the following format;

[0071] 0001.dat:

[0072] Time Sideslip Angle Roll Rate Yaw Rate Roll Angle Lateral G Flaperon Rudder Stabilizer Differential Crossbar Pedals

[0073] 0.01000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000

[0074] 0.02000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0...

Embodiment 3

[0085] 1. Control law automatic test initialization condition setting;

[0086] 1.1. Write the following test input file;

[0087] No. Flight status Dx Dy Dz alf t1 t2 t3

[0088] 0001 0506 0 0 60 0 1 3 10

[0089] ………………………………

[0090] 1.2, above-mentioned file is read into in the computer that test program is stored on the main console 7;

[0091] 1.3. Determine other test conditions;

[0092] 2. Carry out automatic test of control law;

[0093] 2.1. Automatic trimming;

[0094] 2.2, enter the automatic test;

[0095] 2.3. According to the test input file, the test results are sequentially stored and recorded as data files in the following format;

[0096] 0001.dat:

[0097] Time Joystick control Pitch rate Longitudinal overload Angle of attack Horizontal tail in same direction Front flap Altitude Mach number Pitch angle

[0098] 0.000000 30.810890 0.011197 1.017089 1.640179 1.976686 -0.438175 5000.000000 0.600000 1.639969

[0099] 0.010000 30.810890 0.018556 1.009...

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Abstract

The invention belongs to test technologies of flying control systems and relates to improvement on a test method of the control law of the flying control system. The method is developed based on a control law semi-physical bench test system consisting of a flying control computer [1], a steering engine [2], an airplane simulator [3], an angular speed rotary table [4], an angular speed sensor [5], data acquiring and processing equipment [6] and a main console [7]. The method is characterized by comprising the following test steps of: setting initial conditions for automatic test of the control law; and automatically testing the control law. The invention has the advantages of low workload, high efficiency, short time and less possibility on generating the errors.

Description

technical field [0001] The invention belongs to the test technology of flight control system and relates to the improvement of the control law test method of the flight control system. Background technique [0002] The current control law test method of the flight control system is to manually set or input various initialization conditions for the test and add manipulation incentives for each flight state that needs to be tested according to the control law test outline of the bench, and record the closed-loop correlation of the system. The time-domain response of flight parameters, according to the corresponding time-domain criteria, checks the degree of conformity and level of flight quality; the above-mentioned control law test needs to be manually operated thousands of times in accordance with the specified test state; its disadvantages are: the test process Basically, it is done manually, with heavy workload, low efficiency, time-consuming and error-prone. Contents of...

Claims

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Application Information

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IPC IPC(8): G05B23/02
Inventor 周成唐强黄飞何战斌
Owner FLIGHT AUTOMATIC CONTROL RES INST
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