ADVANTAGES OF ROCKET MADE FROM COMPOSITE MATERIAL

Abstract

The paper considers mass estimation of the one-stage launch vehicle with solid propulsion systems built of composite material, namely the calculation of the weight coefficient. The reduction of weight perfection rate is caused by the application of the innovative design and layout solutions, as well as the use of composite materials.  We suggest considering of the specific strength of "kevlar" composite material as the most widely used composite material in rocket engineering. At present, the great potential of rocket and aircraft engineering is attributed to the composite materials owing to their attractive mechanical properties. The paper provides examples of the launch vehicles of composite materials, which are currently in operation used in the following countries: USA, France. The paper suggests a solution to the problem of launching of the payload into the orbit on the one-stage launch vehicle with solid propulsion systems, while it is only the two-stage launch vehicle with liquid propulsion systems that is able to manage it. This paper suggests comparing the energetic capacities of the one-stage launch vehicle with solid propulsion systems and two-stage metal launch vehicle with liquid propellant system. The paper also considers a possibility of increasing the length of the combustion chamber of the solid propulsion system, and, therefore, of the whole launch vehicle (without reducing the stability of the airframe), when using the combustible composite case of the launch vehicle with solid propulsion systems. The advantages of using the airframe of the launch vehicle built of composite material are theoretically demonstrated, and the attempt is made to prove that, applying the approaches suggested by this paper, enables addressing the complex problem related not only to energy and mass properties of the launch vehicle, but also to the associated problems - design and ecological ones.