Numerical simulation method for liquid rocket after-combustion reaction calculation

Abstract

The invention discloses a numerical simulation method for liquid rocket after-combustion reaction calculation, and the method comprises the steps: taking a liquid carrier rocket launching platform asa research object, and analyzing the impact on a tail flame impact flow field from an after-combustion reaction; in the numerical simulation, adopting a three-dimensional compressible Reynolds averageN-S equation and a realizable k-epsilon turbulence model to obtain a gas jet flow field; simulating a chemical reaction process by adopting a finite-rate chemical kinetic model, establishing a multi-component tail flame after-combustion model and comparing the multi-component tail flame after-combustion model with literature data, and verifying the effectiveness and correctness of the algorithm.The numerical simulation method is high in precision, low in calculation cost and suitable for engineering practice, and is determined after a large number of numerical simulation tests are carried out and numerical results are compared with test results.

Description

technical field [0001] The invention belongs to the technical field of thermal protection design for launch platforms of carrier rockets, in particular to a numerical simulation method for calculating the reflashing reaction of liquid rockets. Background technique [0002] In order to realize the deep space exploration of the moon, Jupiter and Mars as soon as possible, as well as the manned interstellar landing program, and to develop and utilize space resources, some aerospace technology powers in the world are developing a new generation of launch vehicle technology to increase the payload. Among them, heavy-duty launch vehicle technology has become an international research hotspot. The main characteristics of high-thrust rockets are: First, the configuration revolves around the bundled booster and multi-stage combination configuration to improve mission adaptability. After the 1980s, the Energia rocket, Ares V rocket, H-IIA rocket, and heavy-duty Falcon launch vehicle al...

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Problems solved by technology

[0003] However, most of the current research objects are single-engine solid launch vehicles (Jiang Y, Ma Y, Wang W, Shao L., "Inhibition effect of water injection on afterburning of rocket motor exhaust plume," Chinese Journal and Aeronautics, Vol.23, 2010, pp.653-659.), the research on the effect of reflashing reaction on the plume flow field of multi-engine liquid launch vehicle is not perfect

At the same time, due to the limitation of computing resources, most scholars have simplified numerical modeling to a large extent, for example, only considering simple two-dimensional models, quarter-simplifying geometric models, and computing grids without boundary layer networks. Negishi H, Yamanishi N, Arita M, Namura E, Ohkubo S., "Numerical analysis of plume heating environment for H-IIA launch vehicle during powered ascent," 43rd AIAA / ASME / SAE / ASEE Joint Propulsion Conference and Exhibit, AIAA Paper 2007-5505, July2007.), these processing methods affect the calculation accuracy to varying degrees

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