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Ground-based simulation test method for automatic navigation function of inertial navigation system

An inertial navigation system and automatic navigation technology, applied in the field of inertial navigation, can solve the problems of complex cross-linking relationship, difficult organization and implementation, long test time, etc., and achieve the effect of reducing cross-linking, easy organization and implementation, and simple and clear simulation system

Inactive Publication Date: 2013-05-08
AVIC XIAN FLIGHT AUTOMATIC CONTROL TECH
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  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

In this kind of automatic navigation test, there are many devices involved in the test, the cross-linking relationship is complicated, the test time is long, the cost is high, and the organization and implementation are difficult

Method used

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  • Ground-based simulation test method for automatic navigation function of inertial navigation system
  • Ground-based simulation test method for automatic navigation function of inertial navigation system
  • Ground-based simulation test method for automatic navigation function of inertial navigation system

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Embodiment Construction

[0019] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0020] (1) First, fix the inertial navigation components on the two-axis manual turntable, according to figure 2 Connect the control display, inertial navigation components, ARINC-429 bus collector and RS-232 collector, and the ARINC-429 bus collector and RS-232 collector collect and monitor the pilot control signal and navigation output from the inertial navigation system parameter;

[0021] (2) implanting the automatic navigation simulation module program in the inertial navigation component, simulating the air flight state; the step of the automatic navigation simulation module program is,

[0022] (1) Establish a scheduled route;

[0023] (2) Enter the air dynamic simulation state from the static state on the ground;

[0024] (3) Receive the navigation parameters in the inertial navigation system;

[0025] (4) Simulate and calculate the navigation parameters...

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Abstract

The invention belongs to the technical field of inertial navigation and relates to a ground-based simulation test method for the automatic navigation function of an inertial navigation system. The ground-based simulation test method is free of the involvement of a flight control system and has low requirements for a turntable; a dual-axis hand-operated turntable is employed in stead of a three-axis hydraulic automatic turntable, and mutual cross-linking is reduced; besides, instruments such as an angular rate gyroscope and the like are reduced; the section of air routes covers all possible flight modes; people and devices joining in the test are few, so that the test is easy to organize and implement; the test is short in period and low in cost; and the method is simple and practicable.

Description

technical field [0001] The invention belongs to the technical field of inertial navigation, and relates to a ground simulation test method for an automatic navigation function of an inertial navigation system. Background technique [0002] At present, the automatic navigation test is a closed-loop feedback control system composed of inertial navigation system, flight control system, three-axis hydraulic simulation turntable, HMJ-200 analog computer and angular velocity gyroscope, such as Image 6 shown. [0003] Among them, the HMJ-200 analog computer simulates the lateral motion of the aircraft, calculates the roll, heading and angular velocity of the aircraft according to the equation of motion of the aircraft, controls the roll and heading loops of the simulated turntable, and reproduces the lateral motion of the aircraft. The meter sends a lateral acceleration signal to the flight control system. [0004] The inertial navigation system measures the roll and heading of t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B17/02
Inventor 熊长安陈彦恒杨黎肖鹏
Owner AVIC XIAN FLIGHT AUTOMATIC CONTROL TECH
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