Aerospace Technic and Technology

The subject of the study in the article is the mathematical model of the propulsion system. It is built on the basis of the formed transfer functions of the elements. The goal is to rationalize the process of heating the onboard propulsion system on the basis of mathematical model under given constraints. Tasks: formalization of processes in an electric heating engine with a working body ammonia; formalization of the model of the onboard propulsion system; formation of the structural scheme; consideration of physical processes occurring in the nodes of the propulsion system; description of gas and hydraulic processes; the description of thermodynamic and electrokinetic processes; The construction of a mathematical model based on transfer functions. The methods used are: models of transfer functions of a tank, a filter, a steam generator, a receiver and a jet, an engine with their ranges of work. The following results are obtained. A block diagram of the onboard propulsion system was added, supplemented with a control unit and a power supply system. A formalized mathematical model of an onboard propulsion system with working body ammonia is created. From it formed a model consisting of the key elements that make up the onboard propulsion system, which is used when rationalizing the heating of the working fluid. The scientific novelty of the results is as follows. The mathematical model of the electro-heating propulsion system onboard small space vehicles has been further developed through its application to calculate the traction characteristics of the dispenser, which makes it possible to use an ammonia electric heating rocket engine in the formation of a constellation of satellites. The limitations of the operating parameters of the model are introduced. It was proposed to conduct the further workability of the model in Matlab Simulink. Thus, a rational value of the current and voltage parameters will be obtained, at which the time of the system's output to the operating mode will be minimal, and the thrust is maximum for the given operating temperature and pressure ranges

mathematical model; space vehicle; airborne propulsion system; electric heating motor; working body; control unit; tank; filter; steam generator; electro-valve; receiver; jet

Pogudin, A. V. Substantiation of the selection of the simulation environment for power supply of the electric heating engine of small space vehicles. Zbіrnik materіalіv konferentsії “Vseukraїns'ka naukovo-tekhnіchna konferentsіya Іntegrovanі komp’yuternі tekhnologії v mashinobudu-vannі ІKTM-2017” [Proc. of the conference "All-Ukrainian Scientific and Technical Conference Integrated Computer Technologies in Machine-Building ICTM-2017"]. Kharkіv, 2017, vol. 1, pp. 220 (In Russian).

Pogudin, A. V., Gubin, C. N. Obzor kharakteristik i metodov sozdaniya gruppirovki malykh kosmicheskikh apparatov [Overview of the characteristics and methods of creating a small spacecraft group] Otkrytye informatsionnye i komp'yuternye integrirovannye tekhnologii, 2017, no. 75, pp. 57 – 66.

Daniev, Yu. F. Kosmicheskie letatel'nye apparaty. Naznachenie, struktura i osnovnye etapy sozdaniya: Ucheb. posobie dlya studentov inzhener. spets. VUZov [Spacecraft. Purpose, structure and main stages of creation: Proc. allowance for student’s engineer. specialist. Universities]. Dnepr, Sistemnye tekhnologii Publ., 2005. 124 p.

Lev, D. R., Herscovitz, J., Kariv, D., Mizrach, I. Heated Gas Propulsion System Conceptual Design for the SAMSON Nano-Satellite (Propulsion). Small Satellites, 2017, vol. 6, no. 1, pp. 551-564.

Pogudin, A. V., Gubin, S. V. Osobennosti ra-tsional'nogo upravleniya dvigatel'nykh ustanovok dlya formirovaniya sputnikovoi gruppirovki [Features of the rational control of propulsion systems for the formation of a satellite constellation]. Otkrytye informatsionnye i komp'yuternye integrirovannye tekhnologii, 2017, no. 78, pp. 74 – 82.

Parker, K. I. State-of-the-Art for Small Satellite Propulsion Systems, 2016. Available at: https://

ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20160010571.pdf (аccessed 1.06.2018).

DSTU GOST 28326.2:2009 (ISO 7103:2005) Ammiak zhidkii tekhnicheskii. Opredelenie massovoi doli vody metodom Fishera [State Standard 28326.2.2009 Ammonia liquid technical. Determination of the mass fraction of water by the Fisher method]. Kiiv, Derzhspozhivstandart Ukraїni Publ., 2007. 8 p.

Rhodes, Brandie L., Mueller, Mark J. Satellite Fuel Estimation Algorithm and Application to the Defense Satellite Communication System III (DSCS III) Available at: https://doi.org/10.2514/6.2015-4150 (аccessed 1.06.2018).

Zhao, J., Wang, M., Wang, Z. Different boost voltage effects on the dynamic response and energy losses of high-speed solenoid valves. Available at: https://doi.org/10.1016/j.applthermaleng.2017.05.117 (аccessed 1.06.2018).

Peyman, Sindareh-Esfahani, Ali, Ghaffari, Pouria, Ahmadi Thermodynamic modeling based optimization for thermal systems in heat recovery steam generator during cold start-up operation. Available at: ttps://doi.org/10.1016/j.applthermaleng.2013.11.031 (аccessed 1.06.2018).

Gaidukov, V. F., Kovalevskii, V. V. Vybor parametrov i raschet elektronagrevnogo raketnogo dvigatelya. Ucheb. posobie dlya studentov inzhener. spets. VUZov [Selection of parameters and calculation of an electro-heated rocket engine. Textbook. allowance for students engineer. specialist. Universities] Kharkіv, Khar'kovskii aviatsionnyi institut, 1988, 50 p.