Cycles for Earth-to-Orbit Propulsion

Abstract

The reduction of Earth-to-orbit launch costs in conjunction with an increase in launcher reliability and operational ef ciency are the key demands on future space transportation systems. Results of various system analyses indicate that these demands can be met with future single-stage-to-orbit (SSTO) vehicles using advanced technologies for both structure and propulsion systems. This paper will provide a classi cation and description of all turbopump feed liquid rocket engine cycles, followed by a combined vehicle/propulsion analysis of the design parameters for the propulsion systems and their associated thermodynamic cycles for the launch of future SSTO vehicles. Existing and projected rocket engine cycles capable of SSTO missions will be presented.

High-elevation equatorial catapult-launched RBCC SSTO spaceplane for economic manned access to LEO

“…Their main finding was that to increase the rocket-mode performance, rocket area ratio must be maximized. Manski et al (1998) discuss thermodynamic cycles for Earth-to-orbit propulsion. As per authors, the technology levels for single-mode cycle engines for future SSTO have already been achieved by Space Shuttle Main Engine (SSME) and RD-O120 engines.…”

“…A single radial turbine powers both LOX and LH2 turbo-pumps through different gearing ratios. Turbine is powered by gas-generator or staged-combustion cycles (Haidn, 2008;Manski et al, 1998). Higher combustion chamber pressures also require more powerful turbo-pumps increasing the weight and power requirements.…”

Effects of a Bearing Strut on the Performance of a Turbopump Inducer

“…Because high efficiency and thrust in the propulsion cycle entails high chamber pressure, a pressure-feed cycle is less desirable for highly loaded propulsion systems due to its excessively high tank pressure requirement. On the other hand, a turbopump-feed cycle leads to a comparatively lower system weight and improved performance [1,2]. Therefore, turbopump systems, which pressurize liquid oxidizers and fuels, are frequently employed to achieve a high specific impulse.…”

Main Chamber Injectors for Advanced Hydrocarbon Booster Engines

“…9 Main chamber design farameters were summarized by Sutton and Biblarz. 1 Sketches of an injector for a ORSC cycle MCC, with important design features, were provided in a U.S. Patent application submitted by Katorgin, et al 11 These three sources provided the basis for the design of the baseline element.…”

“…The element OIF and oxidizer properties were determined from the RD-170 cycle data provided by Manski et a1. 9 The composition and properties of the combustion gas from the oxidizer-rich preburner (ORPB) were determined first. The ORPB exhaust temperature is approximately 750OP,9 which determines the OIF of the preburner and the composition of the oxidizer-rich gases entering the injector.…”