Thermal calculations of liquid low thruster on pollution-safe fuel

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


Аuthors

Sinitsin A. P.1*, Goza D. A.1*, Rumyantsev А. V.2**

1. Experimental Design Bureau “Fakel”, 181, Moskovsky av, Kaliningrad, 236001, Russia
2. Immanuel Kant Baltic Federal University, IKBFU, 14, A. Nevskogo str., Kaliningrad, 236041, Russia

*e-mail: info@fakel-russia.com
**e-mail: albert37@list.ru

Abstract

The article presents the results of development and application of the thermal model of a stationary liquid thruster on alternative mono-fuel. It allows calculate the thermal field, and determine internal and external conductive and radiation thermal fluxes, temperature variation gradients speeds in stationary and dynamic modes operating modes of the engine, and calculate heat emission in combustion chamber with subsequent recommendations on upgrading the engine thermal scheme and its reliability.

The purpose of the above said thermal calculation consisted in determining the thermal state parameters and characteristics of the low thrust rocket engine on alternative fuel. The thermal calculations using mathematical model developed and presented in this document solved the following problems: developing the engine thermal model, its verification by the thermal test results, calculation substantiation of the solutions,directed to temperature reduction of propellant delivery valve and capillary delivery tube.

The three-dimensional engine thermal model was built with SolidWorks Flow Simulation 2014, which employs the finite volume method ( a numerical method for integrating the systems of partial differential equations. In heat calculations, the boundary conditions were set identical to the conditions for thermal vacuum tests, which imitated the outer space in full-scale operating conditions.

The experimental data of the engine thermo-vacuum tests, obtained with the development design office Fakel test-bench, were used for the calculation thermal model verification. Verification of the thermalmodel consisted in heaters power selection from the condition of compliance of temperatures in the controlled points and measured ones.

Recommendations on thermal scheme optimization and constructional materials selection were developed according to the thermal calculation results.

Recommendations were also given on optimal structure selection of low-thrust liquid engine on alternative fuel for valve temperature reduction and power consumption reduction while thermocatalytic pack heating-up to +400 °C.

Several design options were considered, and recommendations were given on heat sink application and its impact on the thermal condition of the product, and the effect of the rack material on the thermal condition of the product. According to the results of thermal calculation of the engine structure in functioning mode recommendations are given on substitution of the engine structural elements (heater) and mounting blocks materials not answering the thermal criteria (working values the engine structural units temperature should not exceed qualification value of the temperature).

Keywords:

low-thrust liquid rocket engine, thermal model, SolidWorks Flow Simulation, thermal calculation, thermal-vacuum testing, temperature

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