Tilting wind speed estimation method and system for winged aircraft in vertical state

Abstract

The invention relates to a tilting wind speed estimation method and system for a winged aircraft in a vertical state. The method comprises the steps of determining an aerodynamic distribution analysiscondition according to a specific enclosing scheme of a wind-shielding and rain-proof enclosing device when the winged aircraft is in the vertical state; according to the obtained aerodynamic distribution analysis condition, calculating an aerodynamic resistance coefficient pressure center and an aerodynamic resistance coefficient; determining the quality characteristics of the winged aircraft inthe vertical state according to the dismounting moment of the windproof fixed aircraft device; determining other transverse loads of the winged aircraft in the vertical state, wherein the other transverse loads comprise a control surface load and a forced release load; determining a launching fulcrum scheme; determining a calculation formula for estimating the tilting wind speed of the winged aircraft in the vertical state, and calculating the tilting wind speed of the winged aircraft in the vertical state; and after the tilting wind speed of the winged aircraft in the vertical state is obtained, evaluating the tilting risk of the winged aircraft is so as to optimize the enclosure scheme.

Description

technical field [0001] The invention relates to a method for estimating the wind speed of a winged aircraft in an upright state and belongs to the technical field of load and mechanical environment. Background technique [0002] After the carrier is erected, it is erected on the launch pad through the launch fulcrum of the tail section. Under the action of surface wind, wind loads are generated. For traditional rockets, mature methods are used at home and abroad to calculate the dumping wind speed, so as to ensure the safety of the vehicle erection. At the same time, the wind load under the critical dumping wind speed is an important basis for the design of the tail section structure. Wind can vibrate slender cylindrical objects. There are many studies on axisymmetric aircraft in the erect state, and unsteady wind loads are generally obtained through elastic scale model wind tunnel tests. The launch fulcrum of the axisymmetric aircraft is also axisymmetric, and it is easi...

AI Technical Summary

Problems solved by technology

The launch fulcrum of the axisymmetric aircraft is also axisymmetric, and it is easier to obtain the dumping wind speed

[0003] However, at present, there are few domestic and foreign researches on the estimation method of tilting wind speed in the upright state of winged aircraft.

The main difficulty lies in the demonstration stage of the new aircraft scheme. The new aircraft generally has a large wing surface. Due to the limitation of funds and cycles, the unsteady wind load cannot be obtained efficiently and quickly. At the same time, the layout of the launching fulcrum is diversified, which brings challenges to the calculation of the dumping wind speed.

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