scholarly journals Original Romanian Research for a Rocket Engine with Multiple Combustion Chambers during 1940 - 1944

2020 ◽  
Vol 12 (1) ◽  
pp. 229-241
Author(s):  
Nicolae-Florin ZAGANESCU ◽  
Constantin-Marcian GHEORGHE ◽  
Peter KALMUTCHI
Keyword(s):  
Rocket Engine ◽  
Mechanical Equipment ◽  
Technical Solution ◽  
Rocket Engines ◽  
Centrifugal Pumps ◽  
Combustion Chambers ◽  
Bypass Valve ◽  
Fuel Tanks ◽  
History Of ◽  
Points Of View

The paper presents certain points of view regarding the history of Romanian rocket engines, during 1940-1944. Working independently of other scientists, during 1942 – 1944 the Romanian Nicolae Văideanu has invented and designed, independently of other researchers, a liquid fuel missile called UDOVILUL-V [3]. According to the design drawings, this missile was equipped with aerodynamically profiled propelling nozzles and was provided with a special alternator – distributor, the bypass valve adjusting the fuel components dosage in the two combustion chambers, in fuel tanks and pipes, while a special designed gas turbine was driving the centrifugal pumps and other mechanical equipment. Within his main patent the Romanian inventor has included the design of several components [2], [4], [5]. The technical solution of this outstanding design in rocketry development could provide 20kN thrust after 60 sec, enabling a speed of 3200 km/h [10].

Large Rocket Engines for Space Vehicles and Missiles

1961 ◽  
Vol 65 (605) ◽  
pp. 321-331
Author(s):  
S. K. Hoffman
Keyword(s):  
Rocket Engine ◽  
Space Vehicles ◽  
Rocket Engines ◽  
Liquid Propellant ◽  
New Developments ◽  
Engine Component ◽  
Space Projects ◽  
History Of ◽  
Liquid Propellant Rocket Engine ◽  
Propellant Rocket

SummaryThe history of Rocketdyne's activity in the field of large liquid-propellant rocket engines is outlined in a chronological review of applicable United States ballistic and space projects. Within security limitations, major rocket engine component improvements and general fabrication techniques are discussed. The trends and new developments in liquid-propellant rocket engine designs are presented and a forecast of future engines is made.

COMBINED CHANNEL PROCESSING TECHNOLOGY BASED ON MULTI-LAYER TEMPLATES

2021 ◽  
pp. 89-96
Author(s):  
А.В. Щеднов ◽  
В.П. Смоленцев ◽  
Н.С. Поташникова
Keyword(s):  
Rocket Engine ◽  
High Heat ◽  
Rocket Engines ◽  
Combustion Chambers ◽  
Bottom Part ◽  
Narrow Channels ◽  
Engine Cooling ◽  
The Cost ◽  
New Generation ◽  
Combined Channel

Рассмотрена технология изготовления дополнительных элементов систем охлаждения ракетных двигателей в форме местных углублений, расположенных на имеющихся фрезерованных каналах на наружных поверхностях камер сгорания и реактивного сопла. Такая проблема требует решения в перспективных изделиях с повышенной теплонапряженностью зоны горения топлива. Проведен анализ конструкции и возможностей обработки дополнительных элементов охлаждения в донной части и на боковых поверхностях узких каналов с ограниченным доступом инструмента в зону удаления припуска. Изучены новые конструкции инструмента для комбинированной обработки с использованием шаблонов различной конструкции и обоснована возможность их использования для изготовления углублений в каналах. Предложены новые способы комбинированной локальной обработки углублений с несимметричной геометрией сечения, форма которых обоснована в процессе отработки технологичности конструкции создаваемых двигателей, что ранее считалось неосуществимым или чрезмерно трудоемким. Исследована возможность многоместной обработки локальных углублений для дополнительного охлаждения в каналах на участках с переменным профилем камер сгорания современных и перспективных изделий по многослойным шаблонам. Здесь разработанные комбинированные технологии дают наибольший эффект и способствуют повышению ресурса двигателей новых поколений до уровня, обеспечивающего многократное увеличение количества безотказных пусков космических систем, что значительно снижает затраты на изготовление ракетных двигателей новых поколений The article considers the technology of manufacturing additional elements of rocket engine cooling systems in the form of local recesses located on the existing milled channels on the outer surfaces of the combustion chambers and the jet nozzle. This problem requires solutions in promising products with high heat stress of the fuel combustion zone. We analyzed the design and processing capabilities of additional cooling elements in the bottom part and on the side surfaces of narrow channels with limited tool access to the allowance removal zone. We studied new tool designs for combined processing using templates of various designs and justified the possibility of their use for making recesses in channels. We propose new methods of combined local processing of recesses with an asymmetric cross-section geometry, the shape of which is justified in the process of testing the manufacturability of the design of the created engines, which was previously considered impossible or excessively labor-intensive. We investigated the possibility of multi-site processing of local recesses for additional cooling in channels in areas with a variable profile of the combustion chambers of modern and promising products using multilayer templates. Here, the developed combined technologies give the greatest effect and contribute to increasing the resource of new-generation engines to a level that provides a multiple increase in the number of trouble-free launches of space systems. This significantly reduces the cost of manufacturing new-generation rocket engines

Study of Hydraulic Characteristics of the Cooling Path of a Model Liquid Rocket Engine Manufactured using Additive Technology of Selective Laser Melting

2019 ◽  
pp. 41-52
Author(s):  
D.A. Yagodnikov ◽  
V.P. Aleksandrenkov ◽  
K.E. Kovalev ◽  
A.G. Grigoryants ◽  
A.A. Drenin
Keyword(s):  
Selective Laser Melting ◽  
Rocket Engine ◽  
Rocket Engines ◽  
Hydraulic Characteristics ◽  
Combustion Chambers ◽  
Laser Melting ◽  
Melting Technology ◽  
Model Liquid ◽  
Cooling Path ◽  
Liquid Rocket

The article discusses hydraulic tests of a model combustion chamber of a liquid-propellant rocket engine with a cooling path made using additive selective laser melting technology. The values of the coefficient of hydraulic resistance in the range of Re = 10--2500 are obtained and the influence of the design features of the cooling tract and its manufacturing technology on the hydraulic characteristics is determined. The results of the performed hydraulic tests confirm the possibility of using additive technologies based on selective laser melting technology for the manufacture of fire and power walls of combustion chambers of liquid rocket engines.

Existing Concepts and Review of Experimental Studies of a Laser Rocket Engine

2021 ◽  
pp. 20-52
Author(s):  
B.P. Ziganshin ◽  
A.V. Sochnev
Keyword(s):  
Space Debris ◽  
Rocket Engine ◽  
Specific Impulse ◽  
Experimental Studies ◽  
Rocket Engines ◽  
Space Systems ◽  
Physical Processes ◽  
Near Space ◽  
Thrust Measurement ◽  
History Of

Currently, there is a problem of making engines for the exploration of near space, and one of the solutions to this problem is the use of a laser rocket engine. This type of engine has a number of advantages and, as calculations have shown, it is economically profitable during active operation, which is very important for space systems. The principle of operation of a laser rocket engine allows it to be used not only as a power plant and a system for launching spacecraft, but also as a system for the destruction of space debris, the problem of which is becoming more and more urgent every day. The paper shows the results of a review of domestic and foreign works on the history of creation and the concept of application of currently existing samples of laser rocket engines, on experimental data obtained by measuring the specific impulse and thrust, measurement methods, and describes the principle of operation and basic physical processes occurring in laser rocket engines

SIMULATION OF THE CURRENT-VOLTAGE CHARACTERISTICS OF SOLAR BATTERIES WITH CONSIDERING DECREASE OF LIGHTING DUE TO THE INFLUENCE OF JETS OF THE ELECTRIC PROPULSION

2019 ◽  
pp. 56-64
Author(s):  
Ya.N. MIGUNOV ◽  
V.V. ONUFRIEV
Keyword(s):  
Solar Cells ◽  
Temperature Gradient ◽  
Electric Propulsion ◽  
Protective Coatings ◽  
Rocket Engine ◽  
Solar Array ◽  
Rocket Engines ◽  
Lighting Conditions ◽  
Main Equation ◽  
Voltage Current Characteristic

A model for calculating the voltage-current characteristic of a solar array in the presence of a temperature gradient by its photovoltaic converters and their variable illumination due to possible pollution under the action of space factors, including operation of electric rocket engines, is described. The model is based on the main equation of a solar cell. In this case both a one-dimensional and a two-dimensional temperature gradients are taken into account. The principles of constructing a model are given, and the initial data selection is made. To simulate the lighting conditions of the solar array such a concept as effective illumination is used, i.e. the density of the radiation flux which falls on photovoltaic converters passing through the protective coatings. The features of simulation of the temperature distribution in the solar array and the effective illumination of its surface in cases of parallel, serial and mixed switching of solar cells are described. The calculation procedures and examples of solar cells are given. The construction of the model in universal mathematical package Mathcad is described. Some simulation results are discussed. Key words: solar array, mathematical simulation, illumination, temperature gradient, electric rocket engine, spacecraft, Mathcad.

Graphic method for assessing the margins of resistance to acoustic vibrations in the chambers of rocket engines by combustion noise

2020 ◽  
pp. 15-21
Author(s):  
R.A. Tsarapkin ◽  
V.N. Ivanov ◽  
V.I. Biryukov
Keyword(s):  
Rocket Engine ◽  
Spectral Characteristics ◽  
Combustion Process ◽  
Combustion Noise ◽  
Rocket Engines ◽  
Acoustic Vibrations ◽  
Statistical Regression ◽  
Unknown Parameters ◽  
Damping Decrement ◽  
Resonance Frequencies

An experimental method is proposed for estimating the damping decrements of pressure fluctuations in the combustion chambers of forced rocket engines. The method is based on the statistical processing of noise pressure pulsations in the vicinity of natural resonance frequencies for normal modes of acoustic vibrations of the reaction volume and the subsequent prediction of the instability of the combustion process relative to acoustic vibrations. Based on the theory of statistical regression for multidimensional experimental data, the problem of predicting unknown parameters of sample distributions is solved by asymptotic determination of the correlation coefficient of the damping decrement of pressure vibrations through optimal linear predictors and the Kolmogorov distribution. Keywords rocket engine, combustion chamber, acoustic vibrations, combustion noise, spectral characteristics, Kolmogorov criterion, damping decrement. [email protected]

‘A great deal of historical claptrap’

2018 ◽  
Author(s):  
Martha Vandrei
Keyword(s):  
History Of ◽  
Points Of View

This chapter’s focus is the later nineteenth and early twentieth centuries, during which Boudica was immortalized in Thomas Thornycroft’s statue on Westminster Bridge. This chapter seeks to provide a thick and thorough contextualization of this event and its precursors, focusing in particular on Boudica’s role in the history of London, but also on Thornycroft’s own motivations and preoccupations, which have been overlooked by historians. This chapter also explores the first novelization of Boudica’s deeds, a firmly imperialistic account by Marie Trevelyan. This period has been read as the climax of Boudica’s association with imperial greatness—a connection I do not seek to wholly refute. However, Thornycroft’s own understanding of his statue challenges this, while Trevelyan’s conviction was met with credulity by contemporaries. Focusing on these hitherto overlooked points of view sheds light on the complicated relations between pasts and presents.

The History of the Creation of the VII State Pharmacopoeia of the USSR (Review)

2021 ◽  
Vol 10 (2) ◽  
pp. 128-135
Author(s):  
K. S. Guzev
Keyword(s):  
Detailed Analysis ◽  
The State ◽  
Main Text ◽  
Scien Tists ◽  
History Of ◽  
Points Of View ◽  
The Creation ◽  
Objective Necessity

Introduction. The objective necessity of the appearance of this code of laws for the pharmaceu-tical industry is shown. The proofs of the readiness of all branches of pharmacy to develop the text of the Pharmacopoeia, taking into account modern international requirements for scientific and practical activities in the development, manufacture and production of medicines, are presented.Text. The work presents the history of the creation of the VII edition of the State Pharmacopoeia of the USSR. The sequence of steps for the formation of the Pharmacopoeia Commission, the stages of its activities for the preparation of the updated text of the Pharmacopoeia is described, a detailed analysis of the prepared text is given in comparison with the current Pharmacopoeia of the VI edition (1910). Various points of view of experts on the content of the main text are cited, which served as the basis for the new document. The role of domestic scien-tists-pharmacists in the development and publication of the VII edition of the State Pharmacopoeia of the USSR is evaluated.Conclusion. The role of the Pharmacopoeia Commission in the timely development of the text of the new edition of the State Pharmacopoeia is emphasized. The fact of its wide discussion among experts and the novelty of the approach, which gave a powerful impetus to the development of the entire industry, are noted.

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