Balancing rudder deflection angle determining method applicable to reentry vehicle with multiple rudder surfaces

Abstract

The invention provides a balancing rudder deflection angle determining method applicable to a reentry vehicle with multiple rudder surfaces. The method comprises the following steps: converting a reentry vehicle balancing rudder deflection angle calculation problem into a nonlinear equation solving problem based on a pneumatic database; establishing a nonlinear equation related to a virtual rudder deflection angle of the reentry vehicle based on a reentry vehicle control channel equivalent virtual rudder deflection angle concept; performing Taylor expansion approximation to obtain a linear equation set for balancing calculation; finally realizing calculation on the balancing rudder deflection angle of the reentry vehicle with multiple rudder surfaces by virtue of a discrete Newton iteration algorithm and a graded balancing strategy. According to the method, a rudder surface function combination method and a graded balancing strategy are applied, so that the method is applicable to the balancing calculation for multiple channels of the reentry vehicle with multiple rudder surfaces, and rudder surface cross-linked coupling influence can be considered. The method is a rapid, high-precise and universal calculation method which is applicable to balancing of multiple channels and is designed for the reentry vehicle with multiple rudder surfaces, and also can be applied to a common airplane and a conventional aircraft.

Description

Technical field [0001] The invention relates to a method for determining the deflection angle of a trim rudder suitable for a reentry aircraft with multiple rudder surfaces, and belongs to the technical field of flight control of the reentry aircraft. Background technique [0002] Trim characteristics are important dynamics characteristics of aircraft. In the process of designing the flight control system, the aircraft model needs to be linearized with small disturbances, and the balance state is required first. Trim is based on the dynamics model of the aircraft and certain constraint conditions to obtain the various state variables of the aircraft during balance, the deflection angle of the rudder surface and other parameters. Traditional trimming methods often ignore the cross-linking coupling of the rudder surface, and have problems such as low trimming accuracy, unsuitable for multi-channel trimming at the same time, complicated trim calculations, and hard constraints of non...

AI Technical Summary

Problems solved by technology

For reentry vehicles with multiple rudder surfaces, the cross-linking coupling of rudder surfaces is often serious, so the calculation of the trim rudder deflection angle is more complicated

Aiming at the problems of low trim accuracy, complicated tri

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