• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.645-648
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• 2011

Hydrazine which has been used as monopropellant shows high performance, but because of its high toxicity research for new green propellant that could replace hydrazine is going on. Ionic liquid propellant that is one of the green propellant has lower toxicity, higher specific impulse, and higher density than hydrazine. To design the thruster which use Hydroxylamine Nitrate (HAN), one of ionic liquid propellant, as a propellant, a quantity of catalyst for full decomposition of a propellant is needed. In this study, reference point for HAN thruster design could be suggested through a design of a small scale thruster which used HAN propellant, and propellant decomposition capability evaluation with characteristic velocity efficiency.

• Journal of the Korea Institute of Military Science and Technology
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• v.13 no.6
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• pp.1180-1187
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• 2010

In the last decade, hydrogen peroxide has received renewed interest as a green propellant which is non-toxic, environmentally clean and relatively easy to handle. This study was performed to acquire the design technique and combustion performance of a 200N bi-propellant engine using hydrogen peroxide and kerosene. The engine which used a catalytic ignition method was designed and cold flow tests were carried out to investigate atomization characteristics. Combustion tests including a pulse mode operation were performed to investigate the combustion performance on various O/F ratios. The results showed that the combustion efficiency and the repeatability of the engine performance were enough to use as an essential database for the development of a high performance engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.739-745
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• 2017

Research of ADN-based monopropellant thruster is progressed by developed countries in Europe to replace toxic hydrazine, and ADN-based monopropellant thruster system is the only system that was proved in space environment. In this research, ADN-based propellant and catalyst was fabricated to develop ADN-based monopropellant thruster, and catalytic combustion performance with fabricated propellant and catalyst were evaluated with DSC-TG analysis. Catalytic combustion of propellant and catalyst was determined with firing test using 5 N scale liquid monopropellant thruster.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1061-1067
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• 2017

Since the 1960s hydrazine is used as a propellant to power rocket, satellites or deep space missions. Due to hydrazine's high toxicity and operating cost, the request for Green Propellant as energetic ionic liquids(HAN, ADN), nitrous oxide blends is growing. Nitrous Oxide Fuel Blend(NOFB) having advantage of a bipropellant performance as well as the advantage of a mono-propellant in respect to the simple propellant tank and feed system. It is worth replacing traditional hydrazine based propellant system if handled and designed properly.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.4
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• pp.79-88
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• 2020

Hypergolic propellants have been widely used for space propulsion systems based their long-term storability and high ignition reliability. Since conventional hypergolic propellants are highly toxic and carcinogenic, handling and operating costs are significant. To overcome the drawbacks, numerous studies have been actively performed to develope new hypergolic propellants, ensuring that the combinations are high performance, low toxicity and low environmental impact. In the present study, a comprehensive survey was conducted to summarize the research and development of green hypergolic propellants involving hydrogen peroxide, nitric acid, and ionic liquids.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.4
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• pp.46-58
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• 2010

Hydrogen peroxide(HP) and liquid methane have deserved renewed considerations as green propellants in recent years, because main design concerns in the development of the new generation propulsion system for spacecrafts are concentrated on low operation cost and environmental cleanness. Although HP has a long history of application to aerospace propulsion systems due to high density, mono-propellant characteristics and low toxicity, it had been replaced by hydrazine and liquid oxygen due to extreme performance requirement during the cold war. But HP has received a renewed interest due to its increased stability and many researches have been conducted to develop high performance LREs(Liquid Rocket Engines) using HP. Liquid methane has also received a new interest in rocket propulsion system for the future space exploration according to its possibility of ISRU(In-Situ Resource Utilization).

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.100-103
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• 2012

The blending method that is an addition of small quantity of fuel was used to increase the performance of green propellant thruster. 90 wt.% hydrogen peroxide as a green propellant was selected, and ethanol was used as a blended fuel. The o/f ratio was chosen as 50 which has higher theoretical performance than 98 wt.% hydrogen peroxide. The chamber temperature of blended hydrogen peroxide was higher than adiabatic chamber temperature of hydrogen peroxide. Therefore, performance can be improved by ethanol blending. Several catalyst and its support were compared to find appropriate catalyst for decomposition and combustion of ethanol blended hydrogen peroxide. As a experimental results, Pt was suitable, but $MnO_2$ had a chamber instability when it was reused. The ${\alpha}-Al_2O_3$ which is high heat-resistant support showed very unstable performance in both Pt and $MnO_2$ catalyst since it has low decomposition performance.

• Applied Chemistry for Engineering
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• v.27 no.4
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• pp.397-401
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• 2016

A new solid oxidizer, pyridinium dinitramide (Py-DN) is a low toxic energetic material which can be utilized as a HPGP (high performance green propellant). In this work, Py-DN was synthesized using various starting materials including potassium sulfamate, pyridine hydrochloride, strong nitric acid and sulfuric acid. Physical and chemical properties of the Py-DN were characterized using UV-Vis, FT-IR and a thermal analyzer and their properties were compared to those of previously prepared salts including ammonium dinitramide[ADN, $NH_4N(NO_2)_2$] and guanidine dinitramide[GDN, $NH_2C(NH_2)NH_2N(NO_2)_2$] in our lab. Endothermic and exothermic decomposition temperatures of Py-DN were $77.4^{\circ}C$ and $144.7^{\circ}C$, respectively. The combustion caloric value was 1739 J/g, which is thermally more sensitive than that of conventional dinitramides. It may enable to lower the decomposition temperature, which can reduce preheating temperature required for satellite thruster applications.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.119-122
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• 2009

The purpose of this study is to design of film-cooling ring for the small thrust rocket engine using green propellants(Hydrogen peroxide and kerosene). Cold flow test was carried out to measure the mass flow rate and atomizing characteristic. Required mass flow rate was obtained from thermal analysis of the engine, and measured flow rate 42.25g/s was in the range of permissible coolant flow rate. With the same mass flow rate, cooling ring with more hole and high velocity shows better spray pattern. The result of thermal analysis, cooling ring has enough cooling performance.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.5
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• pp.20-28
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• 2012

Blending method was applied to increase the performance of hydrogen peroxide which is called green propellant. 90 wt.% hydrogen peroxide was blended with ethanol which is less toxic fuel, and there was no storability decrease due to fuel addition. Inconel X750 and Tophet A showed good compatibility and high heat resistance, and SUS 316L was compatible. $Al_2O_3$, $Y_2O_3$, and $ZrO_2$, were coated on the material to improve heat resistance, and it was proved from endurance test that $Y_2O_3$ coating is not suitable and adhesive strength between coating and material is related with allowable temperature of material. Thruster test was performed to confirm the performance increase by blending method, and chamber temperature was $870^{\circ}C$ which is higher than $760^{\circ}C$ that is adiabatic chamber temperature of 90 wt.% hydrogen peroxide.