At development of systems of launch of small spacecraft (SLC) from various launch platforms it is necessary to conduct optimization, both of launch vehicles themselves, and arising at it sets of systems and technical decisions having narrow target purpose, influencing cost of the project, reliability and on decision-making on its use .
In rocket research systems, as well as in rocket-space technology, the technical and economic efficiency of products is achieved by rational management of resources used in the performance of work at various stages of the life cycle by organizing continuous information support for the development of systems.
The possibilities of application of such an approach at the initial stage of development of ultra-lightweight transport systems (ULTS) are considered. The criteria of perfection of the considered systems are defined, the influence of various factors (such as: fuel type, launch site, etc.) on the structure of launch vehicles (LV) and their demand at the launch services market, to form the areas of competitive use of the developed system is analyzed .
The analysis of the possibility of forming TSSC with different combinations of basic parameters, both subsystems and elements of a complex organizational and technical system (OTS), mass efficiency criteria, economic indicators, the degree of readiness, etc. is given .
Proposed an algorithm for system analysis to create systems NE taking into account a number of problem factors as ground control complex, launch preparation, launch and withdrawal efficiency for solutions of varying degrees of readiness, technological excellence and technical solutions, including possible changes in the target load .
Additional design and engineering organizational and technical solutions are involved for a balanced decision on the project. Evaluation of related industry solutions is provided, key metrics are used to measure the degree of risk, the degree of feasibility associated with the readiness of technology and production [5, 6].
A systematic analysis and study of the main design parameters of an ultralight launch vehicle launched from a carrier aircraft (air launch type) was carried out, the main technical characteristics of the TSSK object, external factors affecting the appearance of the rocket, parameters determined by the developer, level indicators technology readiness. Algorithms for solving the design problem and project implementation under the constraints of the assigned task have been developed .
Verification of the methodology application is demonstrated by examples of the development of rocket-space research systems projects based on the upgraded domestic rocket technology as an effective demonstrator of new technologies for advanced flight tests to implement various research programs for the sustainable development of society.