• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.235-242
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• 2008

An innovative Panel ExTension SATellite(PETSAT) and propulsion system for PETSAT, are presented in this paper. First, we outline what PETSAT is. Next, based on PETSAT ethos, design policy of the propulsion system is provided. According to the policy, we designed propulsion system and concretely estimated and assembled mono-propellant and bi-propellant systems, and it indicated that mono-propellant propulsion with 50-60 seconds of specific impulse and 1 N of thrust is probable. In the case of bi-propellant, 120-150 seconds of specific impulse is valid even based on the design policy. We conducted captive tests of mono-propellant and bi-propellant propulsions with a breadboard model of propulsion system for PETSAT, and obtained good operations and performances. Based on the test results, we designed and manufactured flight model propulsion system for PETSAT. We are planning to demonstrate it in SOHLA-2L project progressed by the Space Oriented Higashiosaka Leading Association(SOHLA). SOHLA-2L will be the first on-orbit demonstrator of PETSAT in 2008.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.159-167
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• 2005

Considering the increase of interest in $H_{2}O_2$ as a rocket propellant, a test facility and a rocket engine have been developed to research in areas of $H_{2}O_2$ mono-propellant propulsion. A detailed design-study of a $H_{2}O_2$ mono-propellant rocket engine of 100-N thrust is presented. Several firings attempted in early stage had some problems with misfire and chamber pressure decrease. Low environmental temperature and impurities included in hydrogen peroxide were considered to be the reasons. Addressing these points resulted in successful firing of the rocket engine and obtained thrust about $100\sim107-N.$

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.110-117
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• 2006

Considering the increase of interest in $H_2O_2$ as a rocket propellant, a test facility and a rocket engine have been developed to research in areas of $H_2O_2$ mono-propellant propulsion. A detailed design-study of a $H_2O_2$ mono-propellant rocket engine of 100-N thrust is presented. Several firings attempted in early stage had some problems with misfire and chamber pressure decrease. Low environmental temperature and impurities included in hydrogen peroxide were considered to be the reasons. Addressing these points resulted in successful firing of the rocket engine and obtained thrust about $100\sim107-N$.

• 한국연소학회:학술대회논문집
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• 2003.12a
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• pp.153-157
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• 2003

Supersonic and hypersonic aircrafts must pass wide range of speed to reach high speed region. But for existing engines the most efficient operating speed ranges are decided according to their flying speed, so an engine which mixes several engines like TRJ (Turbo Ramjet) and ARJ (Air Turbo Ramjet) has been planed. This mixed type engine has inefficiency that more than two engines must be installed simultaneously, but the pulse detonation engine (PDE) that uses detonation wave has a strong point that it can operate in all speed range with single engine. This paper deals with the simulation of the pulse detonation engine which uses hydrogen peroxide $(H_2O_2)$ mono propellant. Hydrogen peroxide is low-cost propellant, and it is reacted without oxidizer. Comparison between $H_2-O_2$ mixture with $H_2O_2$ mono propellant about thrust, pressure, temperature and velocity shows that $H_2O_2$ is a very useful propellant.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.597-600
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• 2004

Fabrication technique and performance test of catalytic micro propulsion are treated based on MEMS technology. This propulsion is designed to use hydrogen peroxide as liquid mono-propellant for attitude control of pica-satellite. The propellant is fed into the micro reactor channel and decomposed into hot gas yielding controllable thrust by catalyst. In order to increase the efficiency of the reaction that depends on the contact area of propellant and catalyst, porous surface formation on the channel accompanied by platinum particle deposition has been performed using H$_2$PtCl$_{6}$ solution as a precursor. Several thrusters were fabricated in different concentration of H$_2$PtCl$_{6}$ solution to determine the best quantity of Pt particles. For the comparison of the performance of each thruster, the volume of oxygen generated by the decomposition of hydrogen peroxide and the thrust were measured.red.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.61-64
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• 2003

A comprehensive understanding is given for the hot-firing test results, which were obtained throughout the verification program of mono-propellant hydrazine thrusters producing 0.95 lbf (4.2 Newtons) of nominal steady-state thrust at an inlet pressure of 350 psia (2.41 ㎫). The scrutiny is made in terms of thrust and temperature behavior of steady state firing mode at the given propellant injection pressures of 400, 250, 100, and 50 psi. Engineering philosophy of data measurement and reduction is shortly mentioned, too.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.4
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• pp.84-90
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• 2004

A performance evaluation is made in terms of thrust, impulse bit. and specific impulses for a set of mono-propellant hydrazine thrusters producing 0.95 lbf of nominal thrust at an inlet pressure of 350 psia. With a brief description on the hot-firing test configuration and procedures. a typical data obtained from steady-state firing mode is given directly showing the variational behavior of propellant supply pressure, mass flow rate, vacuum condition, and thrust. The performance features are successfully compared to the reference criteria of 1-lbf standard mono-propellant rocket engine. Additionally. a statistical inter-thruster treatment is concisely depicted for the justification of selected thrusters as a grouped member of flight model for spacecraft propulsion system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.105-108
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• 2008

Nowadays, as there is so much interest in environment, hydrogen peroxide attracts attention as an eco-propellant. Hydrogen peroxide is widely used for mono-propellant of thruster, and oxidizer of bi-propellant rocket. Especially, it is used as mono-propellant of the thruster for attitude control of satellite and military weapons. So, the need of long time storage of hydrogen peroxide appears and storage test is required. In this paper, necessity of storage test of hydrogen peroxide and some conditions and methods are introduced. In addition, the results of storage tests under some condition are compared and analyzed.

• 한국가시화정보학회:학술대회논문집
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• 2006.12a
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• pp.63-67
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• 2006

Spray characteristics of an injector employed in mono-propellant hydrazine thrusters were investigated by PIV(particle image velocimetry) and PDA(phase Doppler anemometry) techniques. The instantaneous plane images captured by PIV measurement were examined in order to judge the pass-fail criteria of spray injection performance according to the specific pressure supplied. PDA technique was also applied to measure the velocity and droplet size of spray which were not obtainable by PIV measurement. The objective of this experimental study is the evaluation of the injector performance which may be utilized for the design of brand-new injector through the clear understanding of spray characteristics.

• 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.