scholarly journals Special Issue “Advances in Hybrid Rocket Technology and Related Analysis Methodologies”

Aerospace ◽  
2019 ◽  
Vol 6 (12) ◽  
pp. 128 ◽  
Author(s):  
Carmine Carmicino
Keyword(s):  
Combustion Chamber ◽  
Solid Fuel ◽  
Special Issue ◽  
Hybrid Rocket ◽  
Propulsion Systems ◽  
Hybrid Rockets ◽  
Chemical Propulsion ◽  
Rocket Technology

Hybrid rockets are chemical propulsion systems that, in the most common configuration, employ a liquid oxidizer (or gaseous in much rarer cases) and a solid fuel; the oxidizer, stored in tanks, is properly injected in the combustion chamber where the solid fuel grain is bonded [...]

scholarly journals Challenges of Ablatively Cooled Hybrid Rockets for Satellites or Upper Stages

Aerospace ◽  
2021 ◽  
Vol 8 (7) ◽  
pp. 190
Author(s):  
Francesco Barato
Keyword(s):  
Combustion Chamber ◽  
Solid Fuel ◽  
Diameter Ratio ◽  
Propulsion System ◽  
Burning Time ◽  
Regression Rate ◽  
Hybrid Propulsion ◽  
Deep Impact ◽  
Time Ratio ◽  
Hybrid Rockets

Ablative-cooled hybrid rockets could potentially combine a similar versatility of a liquid propulsion system with a much simplified architecture. These characteristics make this kind of propulsion attractive, among others, for applications such as satellites and upper stages. In this paper, the use of hybrid rockets for those situations is reviewed. It is shown that, for a competitive implementation, several challenges need to be addressed, which are not the general ones often discussed in the hybrid literature. In particular, the optimal thrust to burning time ratio, which is often relatively low in liquid engines, has a deep impact on the grain geometry, that, in turn, must comply some constrains. The regression rate sometime needs to be tailored in order to avoid unreasonable grain shapes, with the consequence that the dimensional trends start to follow some sort of counter-intuitive behavior. The length to diameter ratio of the hybrid combustion chamber imposes some packaging issues in order to compact the whole propulsion system. Finally, the heat soak-back during long off phases between multiple burns could compromise the integrity of the case and of the solid fuel. Therefore, if the advantages of hybrid propulsion are to be exploited, the aspects mentioned in this paper shall be carefully considered and properly faced.

Variability analysis of ABS solid fuel manufactured by fused deposition modeling for hybrid rocket motors

2021 ◽  
Vol 15 (2) ◽  
pp. 8029-8041
Author(s):  
Jose Alejandro Urrego ◽  
Fabio Arturo Rojas ◽  
Jaime Roberto Muñoz
Keyword(s):  
Combustion Chamber ◽  
Solid Fuel ◽  
Fused Deposition Modeling ◽  
Rocket Engine ◽  
Acrylonitrile Butadiene Styrene ◽  
Hybrid Rocket ◽  
Rocket Motors ◽  
Fused Deposition ◽  
Manufacture Process ◽  
Direct Digital Manufacturing

The process of fused deposition material (FDM) was used to manufacture propellant grains of Acrylonitrile Butadiene Styrene (ABS) as novel rocket fuel grain, with three types of geometry in the burning port. These solid fuel grains were used to measure the typical characteristics of combustion in rocket motors such as thrust and pressure inside the combustion chamber, seeking to obtain preliminary characteristics of operation and analyze the effect of combustion port geometry on pressure and thrust, using Multivariate Analysis of Variance (MANOVA) as statistical method. Two of the three geometries were manufactured with a helical-finocyl configuration, specially designed to be fabricated by Direct Digital Manufacturing (DDM), the other one was a straight-bore geometry also by DDM. This characterization experiment was performed on a static hybrid rocket engine, designed to inject 99.98% pure nitrous oxide into a combustion chamber with capacity to withstand 6.9 MPa of pressure, with an easy-to-exchange nozzle, avoiding erosive behavior in the throat. Statistical analyses made with the ABS fuel grains, suggest a significant effect on rocket motor pressure and thrust, due to helical geometric changes made to the combustion port of solid fuel grains made by FDM manufacture process.

Some Problems Arising from the Use of Hydrogen-Fuelled Propulsion Systems

1964 ◽  
Vol 68 (647) ◽  
pp. 765-772 ◽  
Author(s):  
L. E. Maher
Keyword(s):  
Rocket Engine ◽  
Liquid Hydrogen ◽  
Propulsion System ◽  
Liquid Oxygen ◽  
Propulsion Systems ◽  
Vehicle Performance ◽  
Third Stage ◽  
Upper Stage ◽  
Chemical Propulsion ◽  
Rocket Technology

SummaryIt is now generally recognised that liquid hydrogen offers a considerable increase in vehicle performance over the more conventional fuels, despite its relatively low density.A design study on an upper stage, which uses a liquid hydrogen/ liquid oxygen chemical propulsion system, revealed a number of problem areas which extend beyond the current levels of experience and knowledge in rocket technology existing in the U.K. This study was made on the third stage of a communication satellite launching vehicle, and a number of the problems high-lighted during the course of the investigation, covering both the propulsion system and the structure, are described and discussed in terms of their importance and their effects on the launcher system. Solutions are suggested where possible—although, lacking practical confirmation, these must be tentative in the circumstances.While no fundamental difficulties are anticipated in the development of a rocket engine using hydrogen, it is essential to accumulate some background of data and experience to ensure that early policy and designs are sound; the importance of beginning practical work as soon as possible is emphasised.

An analytical and experimental study of a hybrid rocket motor

2014 ◽  
Vol 228 (13) ◽  
pp. 2475-2486 ◽  
Author(s):  
Hadi Rezaei ◽  
Mohammad Reza Soltani
Keyword(s):  
Flow Rate ◽  
Low Cost ◽  
Specific Impulse ◽  
Combustion Products ◽  
Rocket Motor ◽  
Chamber Pressure ◽  
Hybrid Rocket ◽  
Hybrid Rocket Motor ◽  
Chemical Propulsion ◽  
Rate Case

The hybrid rocket motor is a kind of chemical propulsion system that has been recently given serious attention by various industries and research centers. The relative simplicity, safety and low cost of this motor, in comparison with other chemical propulsion motors, are the most important reasons for such interest. Moreover, throttle-ability and thrust variability on demand are additional advantages of this type of motor. In this paper, the result of an internal ballistic simulation of hybrid rocket motor in a zero-dimensional form is presented. Further to validate the code, an experimental setup was designed and manufactured. The simulation results are compared with the experimental data and good agreement is achieved. The effect of various parameters on the motor performance and on the combustion products is also investigated. It is found that increasing the oxidizer flow rate, increases the pressure and specific impulse of the motor; however, the slope of the specific impulse for the high flow rate case reduces. In addition, by increasing the combustion chamber pressure, the specific impulse is increased considerably. The initial diameter of the fuel port does not have significant effect on the pressure chamber and on the specific impulse. Addition of a percentage of an oxidizer like ammonium perchlorate to the fuel increases the specific impulse linearly.

90% Hydrogen Peroxide/Polyethylene Solid Fuel Hybrid Rocket Engine

2005 ◽  
Author(s):  
Nobuo Tsujikado ◽  
Masatoshi Koshimae ◽  
Rikiya Ishikawa ◽  
Kazuki Kitahara ◽  
Atsushi Ishihara
Keyword(s):  
Hydrogen Peroxide ◽  
Solid Fuel ◽  
Rocket Engine ◽  
Hybrid Rocket ◽  
Hybrid Rocket Engine
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