Case Study: Space rocket air start from cargo airplane
Case Highlights:
- Client: One of main design bureau of rocket engineering
- Objectives: Determine the dynamic loads that occur when the rocket leaves the airplane
- Scope of Work: Simulation compressible air flow across the two moving bodies system: airplane and rocket with transonic effects
- Inputs: 3D SolidWorks geometry, weight and size characteristics of airplane and rocket, height, velocity and angle of attack of airplane at the leaving moment
- Output: Under given conditions, flow trajectories, distribution pressure and forces profiles across compute domain
- Software used: ANSYS Fluent
- Team: 1 CFD Consultant
- Elapsed time: 3 weeks
Case Study: Analysis of liquid propellant rocket engine RD-170
Case Highlights:
- Client: One of main design bureau of rocket engineering
- Objectives: Determine trust and species distribution into the nozzle, thermodynamic state at the camera
- Scope of Work: Simulation compressible liquid kerosene and oxygen (RP-1/L02) kinetics and fluid flow across the nozzle
- Inputs: Nozzle profile,
- Output: Under given conditions, flow trajectories, distribution mach number and species profiles at nozzle exit
- Software used: ANSYS Fluent
- Team: 1 CFD Consultant
- Elapsed time: 1 week
- Project features: Reduced kinetic model of mixture combustion was developed
Case Study: Optimization of the radiator thermal efficiency
Case Highlights:
- Client: Zlatoust Machine-Building Plant
- Objectives: Determine thermal state in the room and optimize the aluminium radiator design for high transfer
- Scope of Work: Simulation coupled incompressible water-air flows and solid thermal transfer with byonancy effects
- Inputs: radiator geometry,
- Output: Under given conditions, distribution of heat transfer coefficients and average exit water temperature
- Software used: ANSYS CFX, FlowVision
- Team: 1 CFD and 1 heat transfer consultants
- Elapsed time: 3 week
Case Study: Research of ejection processes at launch of rockets
Case Highlights:
- Client: A design bureau of rocket engineering
- Objectives: Determine and minimize ejection values under full-scale launch conditions
- Scope of Work: Simulation compressible kerosene-oxygen burning flows
- Inputs: Space vehicle and launch system geometries
- Output: Structure of the vortex flow, the evolution of the shock-wave process at the initial time
- Software used: ANSYS CFX, Fluent
- Team: 2 CFD consultants
- Elapsed time: 12 weeks
|
|
