scholarly journals Pressure Drop Changes at Engine Fuel Inlet Filter according to Water Contents Management of KSLV-II Liquid Rocket Fuel

2020 ◽  
Vol 24 (6) ◽  
pp. 120-125
Author(s):  
Changhwan Hwang ◽  
Inho Kim ◽  
Jaeyoung Park ◽  
Seonglyong Kim ◽  
Byungil Yoo ◽  
...  
Keyword(s):  
Pressure Drop ◽  
Engine Fuel ◽  
Rocket Fuel ◽  
Liquid Rocket ◽  
Water Contents

scholarly journals Nanocarbon from Rocket Fuel Waste: The Case of Furfuryl Alcohol-Fuming Nitric Acid Hypergolic Pair

Nanomaterials ◽  
2020 ◽  
Vol 11 (1) ◽  
pp. 1
Author(s):  
Nikolaos Chalmpes ◽  
Athanasios B. Bourlinos ◽  
Smita Talande ◽  
Aristides Bakandritsos ◽  
Dimitrios Moschovas ◽  
...  
Keyword(s):  
Nitric Acid ◽  
Furfuryl Alcohol ◽  
Materials Science ◽  
Ambient Conditions ◽  
Materials Synthesis ◽  
Rocket Fuel ◽  
Carbon Nanosheets ◽  
New Synthesis ◽  
Fuming Nitric Acid ◽  
Liquid Rocket

In hypergolics two substances ignite spontaneously upon contact without external aid. Although the concept mostly applies to rocket fuels and propellants, it is only recently that hypergolics has been recognized from our group as a radically new methodology towards carbon materials synthesis. Comparatively to other preparative methods, hypergolics allows the rapid and spontaneous formation of carbon at ambient conditions in an exothermic manner (e.g., the method releases both carbon and energy at room temperature and atmospheric pressure). In an effort to further build upon the idea of hypergolic synthesis, herein we exploit a classic liquid rocket bipropellant composed of furfuryl alcohol and fuming nitric acid to prepare carbon nanosheets by simply mixing the two reagents at ambient conditions. Furfuryl alcohol served as the carbon source while fuming nitric acid as a strong oxidizer. On ignition the temperature is raised high enough to induce carbonization in a sort of in-situ pyrolytic process. Simultaneously, the released energy was directly converted into useful work, such as heating a liquid to boiling or placing Crookes radiometer into motion. Apart from its value as a new synthesis approach in materials science, carbon from rocket fuel additionally provides a practical way in processing rocket fuel waste or disposed rocket fuels.

Rotordynamic analysis of a high thrust liquid rocket engine fuel (Kerosene) turbopump

2013 ◽  
Vol 26 (1) ◽  
pp. 169-175 ◽  
Author(s):  
Seong Min Jeon ◽  
Hyun Duck Kwak ◽  
Suk Hwan Yoon ◽  
Jinhan Kim
Keyword(s):  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Engine Fuel ◽  
Liquid Rocket ◽  
High Thrust

Assessment of contamination by rocket fuel components of remedied sites of silo launchers

2021 ◽  
Vol 61 (9) ◽  
pp. 567-571
Author(s):  
Olga N. Semenova ◽  
Tatyana V. Ryabova ◽  
Olga M. Hudyakova ◽  
Svetlana V. Smirnova
Keyword(s):  
Building Materials ◽  
Degradation Products ◽  
Well Being ◽  
Environmental Safety ◽  
Ecological Condition ◽  
Chemical Safety ◽  
Rocket Fuel ◽  
Nature Restoration ◽  
Liquid Rocket ◽  
Chelyabinsk Region

Introduction. The use of highly toxic and highly hazardous components of liquid rocket fuel in silo-based intercontinental ballistic missiles makes it necessary to assure the health and epidemiological well-being of the population and environmental safety when eliminating silo launchers. The study aims to assess the chemical safety of the sites of silo launchers after their elimination by detonation and remediation of disturbed lands. Materials and methods. Samples of soil, water, vegetation were taken at 20 remedied sites of the former silo launchers of "single start" located in the Chelyabinsk region and the Altai Territory. These samples were analyzed in an accredited laboratory for the content of unsymmetrical dimethyl-hydrazine and its degradation products using certified photometric methods. Results. At the time of the survey in 2019, in 19 of 20 sites of former silo launchers, facts of unauthorized intrusion to the remedied sites were established in order to recover a scrap of non-ferrous and ferrous metals, building materials up to the depth of the location of the destroyed shafts of mine structures. In soil samples from 3 sites of silo launchers located in the Chelyabinsk region, asymmetric dimethyl-hydrazine was found in concentrations exceeding the MPC by 1.02 - 1.6 times. In water samples from open and water-flooded shafts of silo launchers, degradation products of unsymmetrical dimethyl-hydrazine were absent. Contamination of herbaceous and coniferous vegetation with asymmetric dimethyl-hydrazine at the surveyed sites has not been established. Conclusion. Soil contamination with asymmetric dimethyl-hydrazine at three remedied sites of 20 surveyed ones may be the result of their unauthorized opening. After the intrusion, the orphan sites of the silo launchers become objects of increased chemical hazard and environmental risk. Such things require carrying out nature restoration work, strengthening supervision over their technical, health and ecological condition.

scholarly journals The position of liquid fuel residues in tank of worked-off rocket stage during ballistic descent

2021 ◽  
Vol 5 (1) ◽  
pp. 53-60
Author(s):  
V. Yu. Kudentsov ◽  
◽  
A. V. Kudentsov ◽  
Keyword(s):  
High Speed ◽  
Liquid Fuel ◽  
Side Surface ◽  
Fuel Tank ◽  
Rocket Fuel ◽  
Coverage Area ◽  
Fuel Component ◽  
Ballistic Trajectory ◽  
Liquid Rocket ◽  
Total Coverage

The results of modeling the behavior of liquid residues of the rocket fuel component in the fuel tank of the worked-off rocket stage on a ballistic trajectory are presented. The simulation is carried out for the following variants: during the controlled descent of the rocket stage and when using the technology of evaporation of liquid rocket fuel residues in the tanks of the spent stage. It is established that during the controlled descent of the spent rocket stage along the ballistic trajectory at the site of its turn and up to heights of 20 km, the liquid under the influence of overloads is distributed in the form of a film in the area of the bottom and side surface with a coverage area of up to 35 %. At the height of the maximum value of the axial overload, liquid fuel residues in the form of a film move to the area of the bottom and the adjacent side surface of the fuel tank. The total coverage area is about 22 %. The introduction of a hot coolant into the fuel tanks to vaporize the liquid remnants of rocket fuel radically changes the picture of the behavior of the liquid. Due to the high speed of the coolant in the tank, axial overload has little effect on the distribution of fuel residues in the rocket tank

Automatic Unloading Liquid Rocket Engine Fuel Feed System Booster Pump Radial Thrust Bearings from Axial Force

2021 ◽  
pp. 54-61
Author(s):  
S.F. Timushev ◽  
A.A. Frolov
Keyword(s):  
Axial Force ◽  
High Speed ◽  
Rocket Engine ◽  
Liquid Rocket Engine ◽  
Engine Fuel ◽  
Fuel Feed ◽  
Thrust Bearings ◽  
Booster Pump ◽  
Liquid Rocket ◽  
Radial Thrust

Increasing the suction capacity, efficiency and energy parameters of high-speed pumps is an important task in the development of power systems in the aerospace industry, as well as in their application in energy and oil production. With improved cavitation properties, the pumps can operate at a higher shaft speed, and at its given value - with lower cavitation reserves, i.e. at a reduced inlet pressure. When the shaft speed increases, the pump weight and overall dimensions decrease. To increase the anti-cavitation qualities of pumps in the power system, auxiliary (booster) pumping units are used, creating the pressure necessary for the cavitation-free operation of high-pressure and high-speed main pumps of the engine fuel supply system. In accordance with its purpose, the booster pump must provide the required supply pressure of the specified flow rate at the lowest possible liquid pressure at the inlet. At the same time, the efficiency of the booster pump unit should be maximum, and the overall dimensions and weight should be minimal. The last two characteristics predetermine the maximum possible number of revolutions of the pump shaft. Ensuring the operability of the ball-bearing supports of the fuel supply units is one of the most important and complex tasks in the development of modern and promising liquid rocket engines (LRE), especially reusable ones. This task has always been one of the priorities in the fine-tuning the fuel feed units of such engines. The article proposes a method for calculating and controlling the unloading liquid rocket engine booster pump radial thrust bearings from axial force. The method can be applied in the entire range of liquid rocket engine calculations. The further development of this work will be mathematical modeling of the operation of the booster pump automatic axial force unloading.

Elastomers for Liquid Rocket Fuel and Oxidizer Application

1963 ◽  
Vol 2 (2) ◽  
pp. 126-133 ◽  
Author(s):  
Joseph Green ◽  
N. B. Levine ◽  
R. C. Keller
Keyword(s):  
Rocket Fuel ◽  
Liquid Rocket
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