Two-stage reusable space transportation system implementing liquid rocket engine and scramjet demonstrator

Аuthors

Kozlov A. A.^1*, Avrashkov V. N.^1**, Borovik I. N.^1***, Chudina Y. S.^1****, Kozlov O. A.²

1. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
2. 36/23, Kutuzovskii av., Moscow, 121170, Russia,

*e-mail: kozlov202@yandex.ru
**e-mail: aerospace@mai.ru
***e-mail: borovik.igor@mai.ru
****e-mail: y.chudina@gmail.com

Abstract

The paper tackles the issue of effective space system design. The experience of developed countries proves that such transportation system may include hypersonic loop. The Faoulty of Flying Vehicles Engines in Moscow Aviation Institute (National Research University) has developed the conception of the reusable space transportation system (STS) based on liquid rocket engine (LRE) and scramjet.

The idea of using available stock of propulsion systems development forms the basis of the concept. Space Transportation System consists of two stages: the booster (first) stage and the orbital (second) stage. We plan to include RD-161P engine into the booster stage of the propulsion system. This engine is in progress at «Scientific-production association „Energomash named after academician V.P. Glushko“».

Orbiter has a dual-loop propulsion installation consisting of a scramjet and a low-thrust thrust (500 N) rocket engine. These engines are developed at the Faoulty of Flying Vehicles Engines in Moscow Aviation Institute.

To select the fuel type for the use in space transportation system, we compared several fuel compositions that meet the environmental requirements, high efficiency and assimilation. As a result, we chose the fuel: high-concentrated hydrogen peroxide and kerosene.

The successful flight of a returnable STS requires taking into account the effect of flight conditions on the flying vehicle control. We propose to create a demonstrator and simulate all phases of flight STS with the aircraft of significantly smaller size.

The following demonstrator flight scheme is assumed: after orbital stage separation, the first stage continues moving along its ballistic trajectory. Parachute is ejected, and then at the height of 3km helicopter grabs the first stage. The helicopter delivers dry assembly to the launch pad for reuse.

We conducted ballistic calculations and preliminary design studies. As a result, we obtained weight characteristics and the model of a demonstrator. Payload weight is about 4% of the take-off weight of a

demonstrator. With an increase of take-off weight of an aircraft up to actual STS weight levels (100-200 tons), the aircraft placing into LEO payload efficiency reaches 10% of the take-off weight.

Using well-known and calculated demonstrator performance we developed demonstrator flight control system: ground control post hardware and on-board equipment.

Phases and modes of flight demonstrator are similar to space station Buran project. It facilitates the implementation of the existing stock and flight control algorithms.

The developed concept of a two-stage reusable space transportation system is designed with two types of propulsion — LRE and scramjet, operating with high-concentrated hydrogen peroxide and kerosene. We suggest to use the demonstrator to make more precise the impact of flight conditions on the efficiency of STS. Calculations кreveal that the efficiency of the aircraft payload placing into LEO reaches 10% of the take-off weight.

Keywords:

demonstrator, two-stage reusable space transportation system, scramjet, liquid rocket power plant, high-concentrated hydrogen peroxide and kerosene, flight control system

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