Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Aerothermal Simulation Method of Inlet Leading Shock Wave

A technology of simulation analysis and air intake, applied in the direction of design optimization/simulation, geometric CAD, calculation, etc., to achieve the effect of avoiding heat flow

Active Publication Date: 2021-06-08
上海索辰信息科技股份有限公司
View PDF12 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Such high temperature conditions will bring great challenges to the thermal protection of aircraft bulkheads

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Aerothermal Simulation Method of Inlet Leading Shock Wave

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0026] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0027] Such as figure 1 As shown, this embodiment provides a method for aerothermal simulation analysis of inlet leading edge shock wave, which includes the following steps:

[0028] Step 101: Carry out grid division for the simulated flow field of the shock wave at the leading edge of the inlet, initialize the grid, simulate the molecules t...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The air inlet leading edge shock wave aerodynamic thermal simulation analysis method of the present invention comprises: S1, the simulated molecule proceeds at the current speed and direction for a duration of Δt m Uniform linear motion; S2, the interaction between the simulated molecular motion and the boundary, and different processing methods for different boundaries; S3, sort the simulated molecules according to the grid number; S4, sample the molecular collision pairs; S5, determine the collision Molecular energy distribution, determine the molecular energy relaxation process during collision, determine the redistribution of internal energy after molecular collision according to the molecular internal energy transfer model; S6, simulate the chemical reaction of the sampled molecular collision pairs, and obtain the thermodynamics of each molecular collision pair State parameter; S7, repeat S1‑S6, after N time steps, judge whether the simulation time reaches the sampling time, if it enters S8, otherwise repeat S1‑S7; S8, count the simulated molecules in each grid unit Calculate the temperature field of the shock wave at the leading edge of the inlet.

Description

technical field [0001] The invention relates to a method for aerodynamic thermal analysis of shock wave at the leading edge of an inlet, in particular to an aerothermal simulation method for shock wave aerodynamic and thermal analysis at the leading edge of an inlet when an aircraft flies at a high Mach number. Background technique [0002] When the aircraft flies at a high Mach number (Ma>5), the gas at the leading edge of the inlet is a hypersonic flow, and the rapid change of flow velocity from the free flow to the wall of the inlet of the aircraft causes a strong bow-shaped excitation around the leading edge of the inlet. Wave. In addition to the heat generated by the friction between the incoming air and the aircraft cabin, the bow shock wave will also generate strong aerodynamic heat. The temperature of the flow field at the leading edge of the inlet of a hypersonic aircraft is close to 2000K. Such high temperature conditions will bring great challenges to the ther...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20G06F30/15G06F119/08
CPCY02T90/00
Inventor 赵杰陈灏毛为喆
Owner 上海索辰信息科技股份有限公司
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com