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Error analysis method for semi-physical simulation system of aircraft

A technology of semi-physical simulation and analysis method, applied in the field of error analysis of aircraft semi-physical simulation system

Inactive Publication Date: 2020-02-04
ARMOR ACADEMY OF CHINESE PEOPLES LIBERATION ARMY +4
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Problems solved by technology

However, the calculation error of the mathematical equation of the flight control system of the aircraft is not included in the existing methods. Therefore, it is necessary to invent a method for analyzing the error of the hardware-in-the-loop simulation system of the aircraft, which includes the calculation error of the mathematical equation of the flight control system. The obtained error is used To reveal the abnormal phenomenon in the simulation experiment results, or to correct the simulation experiment results

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  • Error analysis method for semi-physical simulation system of aircraft
  • Error analysis method for semi-physical simulation system of aircraft
  • Error analysis method for semi-physical simulation system of aircraft

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Embodiment Construction

[0060] An error analysis method for an aircraft hardware-in-the-loop simulation system, the steps are as follows:

[0061] (a) Ignore the error of the target simulator

[0062] Although there is an error of the load simulator, there is no corresponding loading moment item in the mathematical model of the aircraft flight control system, and it cannot be combined with the mathematical equation of the flight control system for error analysis. The invention is based on the mathematical equation of the flight control system of the aircraft, the transfer function of the two-axis turntable and the transfer function of the three-axis turntable, establishes the mean value and covariance equation based on the covariance analysis description function method, and calculates the mean value and covariance at any time.

[0063] (b) Establish the state equation of the simulation system

[0064] The existing mathematical equations of aircraft flight control contain state variables, which are ...

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Abstract

The invention provides an error analysis method for a semi-physical simulation system of an aircraft. On the basis of mathematical equations of a flight control system of the aircraft, the transfer function of a two-axis turntable and the transfer function of a three-axis turntable, and with the simultaneous aircraft and target relative kinematic equation and proportional guidance equation, mean and covariance equations are established based on the covariance analysis description function method, and the errors of the semi-physical simulation system of the aircraft are solved using the mean and covariance equations. The problem that the calculation error of the mathematical equations of the flight control system of the aircraft is not included in the existing method of missiles and other hardware-in-the-loop simulation system errors is solved. The errors obtained by the invention include the calculation errors of the mathematical equations of the flight control system, and can be usedto reveal abnormal phenomena in simulation experiment results or to modify simulation experiment results.

Description

technical field [0001] The invention relates to an error analysis method for an aircraft half-physical simulation system. Background technique [0002] When the aircraft is connected to the hardware-in-the-loop simulation system, when the hardware-in-the-loop simulation experiment is carried out, there will be errors in the output results, and error analysis is required to reveal abnormal phenomena in the simulation experiment results, or to correct the simulation experiment results. [0003] There are existing error methods for hardware-in-the-loop simulation systems such as missiles, which are documented in [1]-[4]. However, the calculation error of the mathematical equation of the flight control system of the aircraft is not included in the existing methods. Therefore, it is necessary to invent a method for analyzing the error of the hardware-in-the-loop simulation system of the aircraft, which includes the calculation error of the mathematical equation of the flight cont...

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Application Information

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IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 张培忠杨明华张岩施长春
Owner ARMOR ACADEMY OF CHINESE PEOPLES LIBERATION ARMY
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