Evaluation of the results of the flight tests of the small research rocket K80 Meteo 7000 on the way to the creation of the Ukrainian family of suborbital launch vechicles

Abstract

The object of this research is the process of choice the strategy for the development of the Ukrainian segment of suborbital launch vehicles (SOLVs). Problems arising in this process are analyzed and a search of ways of overcoming them was carried out. The strategy of development of a family of SOLVs is based on the previous experience of developing SOLVs in other countries. A family of SOLVs is proposed which includes five rockets with the apogee from 2 to 150 kilometers. The problem of the exclusion zones which can be reserved for falling of discarded parts of vehicles during the launch was considered. Experience of other countries in overcoming this problem was analyzed. It was decided to begin the process of formulation of a concept of a simplified SOLVs control system that would ensure keeping the rocket over the area of the launch. Within this task, a choice of components of the onboard electronic equipment (OBEE) was made. For testing the OBEE in the conditions of a real flight, a K80 Meteo 7000 rocket, a member of the proposed SOLV family, was chosen. In flight tests, most of the chosen OBEE components confirmed their operability, though some showed shortcomings in their operation. Main flight parameters of the K80 Meteo 7000 rocket were demonstrated. The reach of the apogee of 6,375 m and the velocity of Mach 1.733 was confirmed.
 This research sets preconditions for practical implementation of launches of SOLVs with substantial altitudes of the apogee, while limiting the areas reserved for falling parts of the rockets. Availability of such SOLVs will enable solution of a wide range of problems in many fields of scientific research and the use of SOLVs as platforms for working out new technical solutions for other branches of rocketry