Yuzhnoye Design Office performs thermal analyses for space, aviation, and commercial products.

Selection of thermal protection methods and optimal thermal protection for launch vehicles and spacecraft, using engineering approaches based on analysis of Yuzhnoye’s experience and best practices

Yuzhnoye developed software and procedures for selection of optimal thermal protection, using effective analyses of launch vehicle (LV) and spacecraft (SC) heat-shielding materials ablation and heating. The software and procedures were verified by full-scale tests of Yuzhnoye products.

The procedure allows quick calculation of linear ablation of LV and SC heat-shielding materials, analysis of temperature profile over the thickness of the coating and load-bearing shell, selection of required thickness of heat-shielding materials in ascent and atmospheric reentry phases.

The proposed software was widely used in the development and verification of heat insulation for several generations of launch vehicles and spacecraft designed by Yuzhnoye.

Determination of launch vehicle aerodynamic heating

Estimation of heat fluxes affecting the launch vehicle surface in atmospheric flight.

Simple and accurate determination of thermal conditions is sufficient for solution of a wide range of engineering problems related to determination of launch vehicle aerodynamic heating. Aerodynamic heat flux towards the launch vehicle surface in powered flight can be estimated based on systematic design and experimental data on incident-flow parameters. The heat flux determination error is ~15%.

Widely used in space launch system development, this approach can be successfully applied to thermal conditions analysis in aviation engineering.

Determination of integrated spacecraft temperature and humidity conditions in all operational phases

Temperature and humidity around spacecraft are estimated during operations in the integration facility, launch vehicle transit to the launch pad (and back in case of launch abort), and launch operations at the launch pad.

The developed software allows quick end-to-end calculations of temperature and humidity around spacecraft in all phases of operation (from encapsulation in the integration facility until liftoff). Besides spacecraft temperature and humidity conditions, spacecraft thermal loads can be evaluated in all phases of operation. The software allows calculating air temperature and humidity time histories in any conditionally airtight volumes (compartments, dog-houses, containers, etc.)

Calculation of convection and radiant heating in engine ducts

Determination of non-stationary thermal condition of a multiplayer wall (flat, cylindrical, spherical) with temperature-variant thermal and physical characteristics of materials, taking into account two sided heating and ablation in time-variant Type I, II and III boundary conditions and chemical reaction heat. The method is used for designing solid rocket motor (SRM) nozzles, metallurgical installations (dog houses, mixers), exhausts, etc.

• Calculation of temperature fields of SRM nozzles with mixed Type I, II and III boundary conditions; setting of experimental ablation rates and initial thermal condition of the structure
• User interface to build fields of temperature, ablation, and heat exchange parameters in the reference section.

The thermal analysis requires the following inputs: reference-section design, thermal and physical characteristics of the materials, chemical composition of combustion products, engine power settings, and flight trajectory parameters.

The program was used for analysis of thermal condition of special-purpose hardware and metallurgical devices (converters, mixers, exhausts, etc.), wind-driven power plants, and other commercial installations.

Analysis of liquid-propellant engine chamber cooling

The program and procedure were developed for analysis of liquid-propellant engine chamber cooling. Basic analysis output parameters:

• Coolant temperature
• Wall temperature on the gas side and on the coolant side
• Specific heat flux density.

The procedure takes into account convective heat exchange and radiative heat exchange. The analysis of heat convective fluxes from gas towards the wall takes into account a relationship between thermal and physical properties of combustion products and the chamber pressure and the mixture ratio distribution in the wall layer along the chamber length. The distribution was defined by analysis. The coefficient of heat transfer from the wall towards the liquid is calculated by criterion equations obtained after processing of empirical data on heat exchange in channels with different cross-sections. The analysis takes into account thermal and physical properties of the wall materials as a function of temperature.

The procedure allows quick calculation and optimization of the chamber cooling system basic parameters in various liquid-propellant engine running conditions. The approach was successfully verified during cooling system design and development tests.

The proposed procedure is currently used for design of combustion chambers for various liquid-propellant engines. Calculation data obtained by this procedure were confirmed by experimental data.

Launch vehicle structure thermal conditions analysis

Analysis of launch vehicle structure thermal conditions.

Simple and accurate determination of launch vehicle structure temperature fields is sufficient for solution of a wide range of engineering problems related to determination of launch vehicle thermal behavior in flight.

Systematic design and experimental data can be used for analysis of thermal conditions of structural components, with due account for longitudinal and lateral framework, propellant tank panels, and intratank processes during aerodynamic and exoatmospheric heating.

Widely used in space launch system development, this approach can be successfully applied to thermal conditions analysis in aviation engineering and civil engineering, viz. for solving problems of heat transfer in a solid body with a specified heat load.

Thermal conditions of launch vehicle instruments and electronic systems

Determination of temperatures of launch vehicle instruments and electronic systems during prelaunch processing and in flight.

Quick and accurate determination of temperature fields of instruments and electronic systems is sufficient for solution of a wide range of engineering problems related to determination of launch vehicle instruments and electronic systems thermal behavior.

Systematic design and experimental data can be used for analysis of thermal conditions of instruments and electronic systems, with due account for internal heat generation, reciprocal influence of environment and launch vehicle structure.

Widely used in space launch system development, the developed software can be successfully applied to thermal conditions analysis of aviation and other industrial instruments and electronic systems.

Thermal conditions of propellants during launch vehicle filling and standing on launch pad (heating, evaporation, thermal stratification)

Definition of parameters of the temperature field of propellants in launch vehicle tanks (bulk temperature, temperature lapse, low-boiling propellant evaporating rate) depending on ambient meteorological conditions (temperature, wind speed, solar radiation, humidity, and atmospheric pressure, with due account for potential moisture condensation on the tank walls.

Quick and accurate determination of propellant thermal conditions in launch vehicle tanks during prelaunch processing.

Thermotechnical calculations based on the proposed techniques can be used in

• Ballistic analyses, to determine propellant batch temperature
• Selection of pneumohydraulic supply system parameters, to determine temperature of the first and last batches of propellant at engine inlets, tank pressurization parameters, minimum ullage volume in the tanks, etc.

The developed procedure allows determining vertical temperature profiles for fluids in oil storages, tankers, containers, etc.
 

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