On solar thermal rocket engine structure and parameters selection

Аuthors

Finogenov S. L.

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

e-mail: sfmai2015@mail.ru

Abstract

The paper considers the solar thermal rocket engine (STRE) with isothermal (one-stage) and two-stage system concentrator-absorber system (CAS). It demonstrates their characteristics in the flight version, revealing rational parameters of the CASs under consideration, and inexpediency of attaining maximum possible hydrogen heating temperatures and maximal specific impulse with higher mirror booster accuracy in both structures.

For considered STRE schemes, implementation of heated hydrogen afterburning reveals the possibility of solar concentrator size reduction together with upper stage fuel compartment size reduction. Selection of expedient parameters of CASs under consideration may shift towards less accurate mirrors with less absorber heating temperatures followed by minor deterioration of upper stage ballistic characteristics.

To enhance STRE energy characteristics the authors suggest CAS with two-stage solar emission absorber, which heating level corresponds to the irradiance level in focal light spot. The highest hydrogen heating temperature occurs in the central part of the absorber. The specific impulse herein significantly exceeds the like when employing isothermal absorber.

Two-stage absorber efficiency computation regression model, based on energy balance of heating stages, allowing obtain rational temperatures relationship corresponding to maximum absorber efficiency, as well as optimal temperatures distribution along heating stages was developed. The obtained regression dependencies can be used for computation of real STRE, operating as a apart of space upper stage, flight characteristics. The paper demonstrates STRE flight characteristics with considered CASs, defines their specific flight It was demonstrated that in case of two-stage CAS mass efficiency exceeds the like for modern liquid means of interorbital transportation more than 2.3 times.

On oxidizer excess coefficient selection in case of hydrogen afterburning it is necessary take into account that for STRE with two-stage absorber each percent of concentrator diameter decrease corresponds to about one percent of payload weight reduction. This factor should be considered while practical design of various STRE structures.

Keywords:

solar thermal rocket engine, isothermal absorber, double-stage absorber, concentrator-absorber system, heated hydrogen afterburning, geostationary orbit, upper stage

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