Development test objectives analysis of reusable space rocket system

Аuthors

Nesterov V. E., Rudakov V. B., Makarov M. I.^*

Khrunichev State Research and Production Space Center, 18, Novozavodskaya St., Moscow, 121087, Russia

*e-mail: niiks@khrunichev.com

Abstract

Paper considers the Reusable Space Rocket System (RSRS) developed by the Khrunichev State Research and Production Space Center. The system includes Reusable Space Launch Vehicle (RSLV) and the ground complex facilities.
RSLV represents the multipurpose launch vehicle for the launch to the Earths orbits the automated spacecraft of various applications, manned cargo spacecrafts under the near Earth outer space exploration programs, for the Moon, Mars and other solar system planets exploration.
Basic element of RSLV is the Recovery Rocket Package (RRP). RRP aerodynamic configuration represents the design amalgamation of rocket (tanks, dry modules, liquid-propellant main rocket engine) and aircraft engineering (wing, vertical fin, tail unit, air- breathing propulsion system, landing gear) technologies. Thats why RRP is a very complex system, development and testing of which integrates not only rocket but the aircraft technologies and makes necessary the RRP and its components development test objectives and special features analysis. Paper shows that RRP and its components development test have the following special features:
— components development test is subsequently conducted with testing according to the components hierarchy level raising;
— during the RRP optimization the volume and depth of testing are limited, that is probabilistic because estimations of technical features based on the limited data amount are random;
— during the RRP development test the compatibility of systems and its components interference, and influence on operational capability of RRP can be evaluated only at the highest hierarchy levels;
— in the course of RRP development test its components technical features testing can be nondestructive or destructive. It leads to the variation of testing costs from tens of thousands rubles for the low level components nondestructive testing to millions and hundreds of millions rubles for destructive testing of finished products;
— products manufactured in present time by aerospace and aircraft industry enterprises have sufficient continuity of structural schemes and used technologies, mostly they directly borrowing some elements of equipment, systems and etc. from earlier realized projects. This statement is the basic point for qualification method which allows to avoid excessive
— during the development test the specific decisions are taken at each hierarchy level, it could be right or wrong because of the limited depth of testing and various level of technical parameters measurement instrumentation errors, and the consequences of wrong decisions are different for the specific levels.
All the foregoing particular issues arising during the RRP parts specifications control at the stage of development test should be considered in their testing plan at every level. At the same time, present methodical support for the development test does not provide this opportunity and it leads to the necessity for development of the new mathematical models, algorithms and RRP parts engineering data hierarchical control of optimization methods.

Keywords:

recovery rocket package, probabilistic errors, reusable space rocket system, decision making, launch vehicles (LV-s) requirements, economic expenditures

References

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