Sounding Rocket Preliminary Design

This article aims at studying sounding rocket (SR) class, or those vehicles launched from the earth and carrying out various experiments high altitudes. After end of their mission, rockets should deliver a payload to given point give range.
 In general, design tasks are divided into direct inverse ones. paper focuses on designing tasks. this respect, set values maximum range, mass restrictions construction. As result, SR general technique is proposed. includes selection initial parameters, number stages, relative weights fuel components, specific thrust engines for each stage transverse load SR. selecting composition, engine features as an object, starting can be represented complex mathematical function. Moreover, predetermined payload, selected structural design, materials, parameters allow definite weight determination. Finally, overall power characteristics proposed within technique. Such accepted parameters.