Component and classification design method of aircraft aerodynamic error model based on control requirements

Abstract

The invention relates to a flight vehicle pneumatic error model component hierarchical design method based on control demands. The method sequentially includes the steps that 1, parameters are collected in real time; 2, a pitching moment coefficient increment produced by pitching rudder deviation is obtained, and a pitching moment coefficient increment, a yawing moment coefficient increment and a rolling moment coefficient increment, produced by rolling rudder deviation, are obtained; 3, a pitching constant value item deviation, a pitching steerage item deviation, a pitching moment coefficient deviation induced by the rolling rudder deviation, a yawing constant value item deviation, a yawing stable item deviation, a yawing moment coefficient deviation induced by the rolling rudder deviation, a rolling constant value item deviation, a rolling stable item deviation and a rolling steerage item deviation are obtained; 4, a pitching moment coefficient deviation, the yawing moment coefficient deviation and a rolling moment coefficient deviation are established; 5, a three-level pneumatic error model is divided. According to the method, design difficulty of various subsystems can be balanced in overall design, general plan closing is quickened, flight test risk points are fully indicated, and references are provided for pneumatic error quantity value diminishing after a flight test.

Description

technical field [0001] The present invention relates to an aircraft aerodynamic error model component and a hierarchical design method based on control requirements, in particular to an aircraft aerodynamic error model component based on control requirements that realizes the pull-off combination of bad control characteristics and strengthens ground prediction and control capabilities. Hierarchical design method. Background technique [0002] The aerodynamic error model is the most important part of error state selection in control system analysis, design, and simulation. The structure, value and usage of the aerodynamic error model determine the reliability of the design results of the control system. Therefore, it is necessary to conduct aerodynamic error analysis based on control requirements. Research on model design and use. [0003] For hypersonic gliding vehicles, aerodynamic control is mainly used to achieve gliding flight, and a fine characterization of the aerodyn...

AI Technical Summary

Problems solved by technology

Regarding the use and assessment methods of the aerodynamic error model, the general practice is to carry out simulations on the limit deviation combination for the first-level error zone, and it is required to achieve stable flight under the full deviation combination state. The problem often faced by this method is that it cannot be realized. The balance between error source design and control design, the solution is difficult to close

In order to realize the closure of the scheme, the aerodynamic error model needs to be reduced as much as possible, and the control capability needs to be enhanced as much as possible. As a result, the risk of insufficient ground prediction of aerodynamic error is increased, and for gliding flight mainly relying on air rudders However, there is a situation that the air rudder control ability is not fully exploited (here especially refers to the aircraft equipped with an attitude control power system, that is, in order to adapt to a large aerodynamic error, when the air rudder control ability has not fully functioned, that is, RCS is used for auxiliary control)

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