Rotor wing surface large water drop mass flow calculation method considering secondary impact, and terminal

Abstract

The invention discloses a rotor wing surface large water drop mass flow calculation method considering secondary impact, and a terminal, and belongs to the technical field of numerical simulation. The method comprises the following steps: calculating the secondary large water drop mass flow of the rotor wing surface under the condition that a water drop secondarily impacts a rotor wing; and according to the secondary large water drop mass flow, calculating the final large water drop mass flow of the rotor wing surface by combining the large water drop mass flow mtemp on the rotor wing surface under the condition that large water drop splashing does not occur and the mass loss rate fm of the water drops on the rotor wing surface under the large water drop splashing condition. In the calculation of the mass flow of the large water drops on the surface of the rotor wing, the final mass flow change of the large water drops caused by secondary impact of the splashed supercooled large water drops on the surface of the rotor wing is considered, so that more accurate final mass flow calculation of the large water drops is realized, and the numerical simulation of rotor wing icing is closer to the physical reality, therefore, the numerical simulation precision of rotor wing icing is improved, so that the flight safety of an aircraft is ensured.

Description

technical field [0001] The invention relates to the technical field of numerical simulation, in particular to a method and a terminal for calculating the mass flow rate of large water droplets on the rotor surface considering secondary impact. Background technique [0002] Helicopters are widely used in military operations, civilian rescue, etc. With the expansion of their use in wider fields, helicopters are required to have all-weather flight capabilities, which increases the probability of helicopters encountering dangerous situations of rotor icing. Rotor icing will change the shape of the rotor, increase the weight of the rotor, and reduce the rotational speed of the rotor, resulting in a decrease in the lift of the rotor. At the same time, the icing on the rotor may cause impact hazards to the airframe, weapon systems, electronic equipment, etc., and increase flight uncertainty. Therefore, it is of great significance to carry out research on rotor icing to improve flig...

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Problems solved by technology

[0005] The purpose of the present invention is to overcome the problem in the prior art that the mass flow of large water droplets on the surface of the rotor cannot be accurately calculated, and to provide a calculation method and terminal for the mass flow of large water droplets on the surface of the rotor considering secondary impact

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