Forming cyclogram of energy-propulsion system for prospective inter-orbital space transportation vehicle with electric propulsion and liquid stages

DOI: 10.34759/vst-2020-1-180-190

Аuthors

Biruykov V. I.^*, Kurguzov A. V.^**

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: aviatex@mail.ru
**e-mail: mandigit@yandex.ru

Abstract

At present, liquid rocket-thrusters are employed mainly as cruise engines for inter-orbital transportation means. These engines efficiency is limited by the energy capability of the fuels being used. Electric propulsion application, in which reactive mass and energy source are separated, is seemed promising. Due to the high exhaust velocity of the reactive mass, the electric propulsion employs reactive mass an order of magnitude higher efficiently than the chemical one.

The available limitations of the power source energy and high specific impulse allows the electric propulsion ensure only insignificant thrust, which limits the scope of its application. That is why more often chemical and electric rocket engines are used conjointly. Transportation is performed firstly by the chemical stage, then it is separated, and finishing is executed by the electric propulsion stage.

It is necessary to validate scientifically parameters selection for the energy-propulsion system and electric propulsion stage of the prospective inter-orbital transportation vehicle. To do this, criteria, characterizing the effectiveness of transportation operation performing, obtaining at the specified input parameters of the energy-propulsion system is required. Some of these criteria can be obtained analytically, while the other by the simulation results only. Thus, a technique allowing planning cyclogram of the transfer with specified input parameters, this planning validation, and obtaining trajectory information, based on the cyclogram, which allows evaluate space factors impact, depending on location, and the effect of radiation of the Van Allen belts.

The article proposes analytical dependencies, on which basis cyclogram of the transfer from the low near-Earth orbit to a geostationary orbit can be formed. The flight is performed by the super–synchronous highly elliptical orbit. The energy- propulsion system of the vehicle consists of chemical and electric propulsion stages. The liquid stage puts the payload, consisting of electric propulsion stage and target spacecraft, on the super-synchronous geot–ransition orbit, and separates. Further finishing is performed by the electric propulsion. The power source are solar batteries with the preset power.

To verify correctness of the cyclogram analytical construction, a random set of points is formed in the studied space of the input parameters. For each point, a propulsion system cyclogram is generated, and numerical simulation is performed. Deviation of the last trajectory point from the radius, specified while the cyclogram construction, is evaluated. Dependencies of the volume of trajectory information on the input parameters are formed. Based on the results of the study, a conclusion was made that the proposed technique for cyclogram generating of the transfer can be employed when selecting design parameters of the energy-propulsion system of a perspective inter-orbital transportation vehicle.

Keywords:

energy-propulsion system, inter-orbital transportation vehicle, separable stages, satellite platform, transfer cyclogram

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