Vertical type method for processing nozzle cooling channel of liquid-propel land rocket engine

Abstract

The invention relates to a method for vertically processing a cooling passage of a liquid rocket engine thrust jet, which belongs to the processing method field of liquid rocket engine thrust jet. In the invention, the thrust jet adopts a vertical clamp; a single-point laser sensor scans bus bars strip by strip to acquire the actual profile of the thrust jet and a sampled data set to reconstruct the bus bars of the thrust jet strip by strip; the buses of the sampled data set are smoothed strip by strip to acquire a thrust jet smoothed data set; the data set of all the bus bars are compressed to acquire a compressed data set; and a cubic spline is used for performing interpolation to approximate the actual bus bars of the thrust jet. The milling tool position is calculated by dual milling head for symmetrical milling and high speed back chipping. The method realizes the integration of measurement and processing, finishes the treatments of profile measurement, milling groove and back chipping by one clamping, can satisfy the processing requirements on different physical dimensions and different bus bar linetypes, has high processing efficiency and good consistency, and realizes the digital processing with high efficiency and high precision of the cooling passage of the liquid rocket engine thrust jet.

Description

technical field

[0001] The invention belongs to the field of processing methods for nozzles of liquid rocket engines, and in particular relates to a vertical processing method for cooling passages of nozzles. Background technique

[0002] With the development of the aerospace industry, new liquid rockets have higher and higher requirements on the production efficiency and production quality of the engine. The rocket nozzle is the main part of the liquid rocket engine, and it is also a key part that is difficult to process. A large number of vertical straight grooves are evenly distributed on the outer surface of the nozzle, and the longitudinal liquid fuel channel is formed after covering the metal skin, which plays the role of cooling the pipe wall and preheating the liquid fuel. The rocket nozzle has the following geometric characteristics: large geometric size (shaft section diameter and axial dimension are both 1-2m), thin wall (5-6mm), large number of grooves (more tha...

Images