Hypersonic Rocket Aerodynamic Heating Value Calculation Method

How to effectively solve the aerodynamic heating which produced on the hypersonic aircraft surface is always a topic that is consanguineously attentioned by people. And the principal job that solves the problem is well and truly confirming the aircraft's heat environment which is the quantity of heat flow and temperature distributing. Therefor, in this paper, there is a suit of aerodynamic heating numerical value calculative method that is investigated, which combines finite difference and finite cell methods.First of all, in this paper, analyzing, classifying and comparing the various internal and overseas developmental high exceeding velocity of sound aerodynamic heating calculative method are by the numbers, and recommending a sort of familiar project calculative method simply. Then, studying a combined by finite difference and finite cell method which can be used to calculate the pneumatic heat. Mostly contraposing onflow boundary layer, based on onflow boundary layer equation, this method progresses coordinate transforming firstly, and gains the wall surface heat current through the outside layer foreign aid parameters gained by the outside layer equation which is transformed from the finite difference method. And seemed as import condition by way of the heat current, the paper gains the temperature distributions through the finite software which is called Ansys.For the sake of validating the veracity of the numerical value calculative method, the project calculative method and the numerical value calculative method are calculated contrastively. The results of calculating indicate that the numerical value calculative method is more exact than the project calculative method. At last, the aerodynamic heating defending problem of a certain high altitude rocket was triumphantly solved by handling the numerical value calculative method studied in this paper.