Study of Spacecraft Launch System Based on Solid Propellant Technology from Different Launch Platforms

Язык труда и переводы:
УДК:
520.607
Дата публикации:
12 января 2022, 22:16
Категория:
Секция 09. Космонавтика и устойчивое развитие общества (концепции, проблемы, решения)
Авторы
Matveev Yuriy Aleksandrovich
Moscow Aviation Institute (National Research University)
Аннотация:
The paper considers the analysis of methods for developing a launch system for small spacecraft based on solid-fuel technologies from various launch platforms, discusses the specifics of setting the task of analyzing the structure of subsystems, and provides examples of decision-making efficiency indicators. A system analysis algorithm is proposed for creating launch systems taking into account a number of problematic factors such as ground control complex, launch preparation, launch and launch efficiency for solutions of various degrees of readiness, technological perfection and technical solutions, including sudden problems.
Ключевые слова:
small spacecraft, ultra-lightweight transport systems, ultra-lightweight launch vehicle, complex organizational and technical system
Основной текст труда

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 [1].

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 [2].

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 [3].

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 [4].

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 [6].

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.

Литература
  1. Kozedra P.A., Matveev Yu.A., Pozin A.A., Chikacheva Yu.V., Shershakov V.M. Otsenka vozmozhnosti proekta rakety-nositelya sverkhlegkogo klassa dlya formirovaniya sputnikovykh gruppirovok [Assessment of the possibility of the project of ultra-light-class launch vehicle for the formation of satellite constellations]. Engineering Journal: Science and Innovation, 2021, iss. 2. (in Russ.). DOI: 10.18698/2308-6033-2021-2-2055
  2. Matveev Yu.A., Pozin A.A., Shershakov V.M. Raketnye tekhnicheskie sredstva geofizicheskogo monitoringa, ikh razvitie i vozmozhnosti [Rocket technical means of geophysical monitoring, their development and capabilities]. Polet [Flight], 2017, no. 8, pp. 26–31. (in Russ.).
  3. Danilyuk A.Yu., Klyushnikov V.Yu., Kuznetsov I.I., Osadchenko A.S. Trebovaniya k obliku i osnovnym proektnym parametram mikroraketnogo kompleksa, prednaznachennogo dlya zapuska malykh letatel'nykh apparatov razmernostey “nano”, “piko” i “femto” [Requirements for the appearance and basic design parameters of a microrocket complex designed to launch small aircraft of “nano”, “pico” and “femto” dimensions]. Vestnik NPO imeni S.A. Lavochkina [Herald of the NPO im. S.A. Lavochkin], 2015, no. 3 (29), pp. 107–113. (in Russ.).
  4. Matveev Yu.A., Pozin A.A., Shershakov V.M. Sistemnye voprosy sozdaniya raket-nositeley sverkhlegkogo klassa [Systemic issues of creating ultra-light launch vehicles]. Vestnik NPO imeni S.A. Lavochkina [Herald of the NPO im. S.A. Lavochkin], 2019, no. 2 (44), pp. 37–43. (in Russ.).
  5. Bakhvalov Yu.A. Osobennosti perekhoda na mnogorazovye sredstva vyvedeniya [Features of the transition to reusable launch vehicles]. Polet [Flight], 2019, no. 2, pp. 3–14. (in Russ.).
  6. Ganonenko O.V. Ispol'zovanie metodov upravleniya riskami pri razrabotke i upravlenii programm tekhnologicheskogo razvitiya raketno-kosmicheskoy promyshlennosti [The use of risk management methods in the design and management of technological development programs of the rocket and space industry]. Kosmonavtika i raketostroenie [Cosmonautics and rocket engineering], 2019, iss. 6 (111), pp. 130–144. (in Russ.).
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