Selection of temperature and power parameters for multi-modular lunar jet penetrator

The questions and the particularity of the choice of design parameters of multi-module lunar jet penetrators are considered. A constructive layout of the penetrator is proposed and the advantages of a multi-modular design are presented. In particular, the limitation on the depth of penetration of th...

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Bibliographic Details
Published in:INCAS bulletin 2019-08, Vol.11 (S), p.231-241
Main Authors: ZAGOVORCHEV, Vladimir А., TUSHAVINA, Olga V.
Format: Article
Language:English
Subjects:
Algorithms
Combustion chambers
Combustion products
Composite materials
Design parameters
Elongation
Engines
gas dynamics
Heat
Mathematical analysis
Mechanics
Modular design
Modules
moon
Nozzles
penetrator
Physics
Process parameters
regolith
Remote control
Solid fuels
solid propellant rocket engine
Solid propellant rocket engines
Temperature
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Summary:The questions and the particularity of the choice of design parameters of multi-module lunar jet penetrators are considered. A constructive layout of the penetrator is proposed and the advantages of a multi-modular design are presented. In particular, the limitation on the depth of penetration of the reactive penetrator of the standard scheme, associated with the characteristics of the flow of combustion products from the nozzle into a variable length channel left after the passage of the apparatus, is described. An algorithm is suggested for solving the problem of design parameters of multi-module lunar jet penetrators, which is based on the same methods for finding design parameters of single-module penetrators. Nonetheless, in this case, among the main design parameters that uniquely determine the appearance of both individual modules and the apparatus as a whole, in addition to pressure in the combustion chamber, elongation, pressure relationships at the nozzle and in the chamber, engine running time in air, structural mass and angle, contents of the head including, multiple modules (or sections of the remote control) of the device. By the above method, the calculation of the gas-dynamic parameters for the operation process in solid propellant rocket engines was carried out. Critical temperatures of solid fuel and pressure in the combustion chamber are limited by the ones leading to destruction of the engine and the penetrator.
ISSN:2066-8201
2247-4528
DOI:10.13111/2066-8201.2019.11.S.23