Modeling the Thermal Rocket Fuel Preparation Processes in the Launch Complex Fueling System

• Main Authors: A. V. Zolin, V. V. Chugunkov
• Format: Article
• Language: Russian
• Published: MGTU im. N.È. Baumana 2015-01-01
• Series: Aèrokosmičeskij Naučnyj Žurnal
• Subjects: моделирование; углеводородное горючее; жидкий азот; температурная подготовка; охлаждение и нагрев
• Online Access: http://aerospace.elpub.ru:80/jour/article/view/31

<p>It is necessary to carry out fuel temperature preparation for space launch vehicles using hydrocarbon propellant components. A required temperature is reached with cooling or heating hydrocarbon fuel in ground facilities fuel storages. Fuel temperature preparing processes are among the most energy-intensive and lengthy processes that require the optimal technologies and regimes of cooling (heating) fuel, which can be defined using the simulation of heat exchange processes for preparing the rocket fuel.<br />The issues of research of different technologies and simulation of cooling processes of rocket fuel with liquid nitrogen are given in [1-10]. Diagrams of temperature preparation of hydrocarbon fuel, mathematical models and characteristics of cooling fuel with its direct contact with liquid nitrogen dispersed are considered, using the numerical solution of a system of heat transfer equations, in publications [3,9].<br />Analytical models, allowing to determine the necessary flow rate and the mass of liquid nitrogen and the cooling (heating) time fuel in specific conditions and requirements, are preferred for determining design and operational characteristics of the hydrocarbon fuel cooling system.<br />A mathematical model of the temperature preparation processes is developed. Considered characteristics of these processes are based on the analytical solutions of the equations of heat transfer and allow to define operating parameters of temperature preparation of hydrocarbon fuel in the design and operation of the filling system of launch vehicles.<br />The paper considers a technological system to fill the launch vehicles providing the temperature preparation of hydrocarbon gases at the launch site. In this system cooling the fuel in the storage tank before filling the launch vehicle is provided by hydrocarbon fuel bubbling with liquid nitrogen. Hydrocarbon fuel is heated with a pumping station, which provides fuel circulation through the heat exchanger-heater, with hydrocarbon fuel returning to the storage tank.<br />Mathematical models of cooling and heating processes are built on the assumption that the heat exchange process of storage and environment is quasistationary.<br />The paper presents relationships for determining the relative masses of nitrogen and time to perform the operation of cooling fuel from the initial to the desired final temperature as well as relationships to define the time of heating operation for a given capacity of the heat exchanger-heater and the pump station fueling system.<br />The results of calculations of the relative liquid nitrogen costs during cooling of hydrocarbon gases depending on the mass flow rate of nitrogen in the cooling fuel system are shown in comparison with experimental data and numerical calculations. The maximum error of analytical calculation results and experimental values of the relative cost of liquid nitrogen does not exceed 4.5% and the error in determining the time required for operations of temperature preparation does not exceed 5%.<br />Analytical relationships and results of calculations obtained on their basis are adequate and in compliance with experimental results, in accuracy are on a par with results of numerical calculations and, as compared to numerical solution, greatly simplify a procedure of implemented design calculations of fuel temperature preparation processes. Using these relationships allows to analyze the effectiveness of the operations of heating and cooling hydrocarbon fuel depending on the design parameters of the storage capacity, its thermal insulation, mass of fuel, thermal power of the heating devices, flow of nitrogen, as well as to determine the required mass of liquid nitrogen and the operation parameters of cooling (heating) fuel for filling systems of launch complexes for different values of the environmental parameters, the initial and desired final temperatures<br />of the fuel.</p>