Development of a reusable aerospace system concept for launching payloads into low Earth orbit considering aerodynamic and thermal load impacts


Аuthors

Titov D. M.*, Bon A. F., Ermakov V. Y., Tufan A. **

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

*e-mail: d.titov@mai.ru
**e-mail: anttufan@gmail.com

Abstract

Currently, there is a stable trend toward a significant increase in cargo flow both to and from low Earth orbit. In accordance with the goals and objectives outlined in the “Development Strategy of the State Corporation for Space Activities “Roscosmos” for the period up to 2025 and outlook until 2030”, the task is proposed to build a domestic orbital station; deploy large groups of artificial satellites of various purposes; and pursue plans for lunar exploration – namely, the construction of a lunar base; exploration of Mars and Venus; projects for mineral extraction on celestial bodies (small planets, asteroids), and others. In this context, the use of single-use space launch vehicles becomes impractical both practically and economically. One of the promising solutions to this problem is the implemen-tation of reusable space systems, including launch vehicles with reusable components or fully reusable launch vehicles, as well as the use of reusable aerospace systems.

To objectively assess the prospects of using reusable aerospace systems in comparison with reusable launch vehicles, a comprehensive analysis was conducted based on key technical characteristics, which include types of power plants and their efficiency, features of inter-flight maintenance, reliability indicators, requirements for ground infrastructure, and launch trajectories.

A new concept of a reusable aerospace system has been proposed, featuring an aerodynamic scheme of a “tailless” configuration with a low-mounted trapezoidal wing, and a fuselage designed according to a load-bearing scheme.

It has been shown that, compared to traditional launch vehicles, the proposed concept of a reusable aerospace system offers the following advantages: increased reliability in delivering payloads to the designated orbit due to improved aerodynamic quality, which allows for a significant reduction in aero-dynamic losses associated with air resistance; no need to build specialized launch complexes. Instead, it is proposed to use airfields that significantly reduce the cost of servicing and launching the reusable aerospace system due to their multifunctionality; the ability to ensure all azimuths, enabling the system to be launched into a wide range of orbital inclinations, as well as land on any suitable existing airfield.

Numerical modeling, taking into account limitations such as insufficient thrust capacity, excessive thermal flux, and inadequate lift, was conducted to construct the possible flight trajectory regions of the reusable aerospace system on both “atmospheric” and “ex-atmospheric” segments. The results showed that increasing flight speed sharply increases the mass and specific weight of the payload, demonst-rating the effectiveness of using a reusable aerospace system for various transport and cargo operations.

Keywords:

reusable aerospace system, combined air-jet engine, liquid rocket engine, increased pay-load capacity, aerodynamic and thermal loads

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