The conception of a launch vehicles with ramjet and rocket-ramjet engines for a small payload injection into Low Earth Orbit

Paper number

IAC-06-C4.5.10

Author

Prof. Valeriy Tymoshenko, Institute of Technical Mechanics NASU NSAU, Ukraine

Coauthor

Dr. Valeriy P. Galinsky, Institute of Technical Mechanics NASU NSAU, Ukraine

Coauthor

Dr. Igor S. Belotserkovets, Institute of Technical Mechanics NASU NSAU, Ukraine

Coauthor

Dr. Vjacheslav Gusinin, Ukraine

Year

2006

Abstract

The parallel evaluations of the power characteristics of the launch vehicles for the use of various types of a propulsion system and a launching trajectory for start of the launch vehicles from a surface of the Earth and with a carrier-aircraft are conducted.
 A three-stage rocket was selected as the launch vehicles which at the first and third stages had a liquid-propellant jet engine, and at the second stage the variants of various types propulsion system were considered: liquid-propellant jet engine, ramjet and rocket-ramjet. It is shown, that the use of start of the launch vehicles with a carrier-aircraft and the use of ramjet at the second stage allows essentially to increase weight payload output into predicted orbit. The calculations have shown, that ramjet and rocket-ramjet are more economic propulsion system and them expediently to use for flights at heights 30..60 km with Max numbers M>3.
The rocket with the following parameters is selected as the launch vehicle: length - 20 m, initial weight - 40 t. Dry weight of the first stage of the rocket was equalled 1300 kg, second stage - 400 kg and third stage - 300 kg. Weight of a removable payload should be not less than 200 kg. The kerosene was used as fuel for propulsion system at all stages. The character of program change of the pitch angle in case of application ramjet or rocket-ramjet at the second stage differs from used for liquid-propellant jet engine. The flight trajectory of the launch vehicle with ramjet or rocket-ramjet at the second stage is set so that the main set of speed of the launch vehicle was made in altitude range of 40-60 km.
The results of predicted estimation of orbital injection payload into the circle orbit of height 120 km for start from a surface of the Earth and with a carrier-aircraft are indicated below 
a) Start from surface of the Earth 200, 630 and 1180 kg for liquid-propellant jet engine at all stages, rocket-ramjet on II stage and ramjet on II stage, correspondingly 
b) Start  with carrier-aircraft 337, 1010 and 2100 kg for liquid-propellant jet engine at all stages, rocket-ramjet on II stage and ramjet on II stage, correspondingly 

Abstract document

IAC-06-C4.5.10.pdf

Manuscript document

IAC-06-C4.5.10.pdf (🔒 authorized access only).

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