• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.398-404
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• 2006

Recently in Korea, rocket technology is being taken a wide scope as government planning to build Oeinaro-do space center and to select First Korean astronaut. But compared to development in USA, there is a lack of safety rules in amateur rocket. So it is very essential to meet some powerful legal safety rules for keeping pace with increasing popularization of rocket technology. Herein we discuss, in the field of rocket design, making, launching and collecting stage with considering the rules of IRR, NURA and NAR-HIAA.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.419-422
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• 2006

Improvement of performance of sorbitol model rocket was studied. The rocket designed in this work was compared with the rocket manufactured previously with respect to the shape of body, grain of rocket motor, motor case and recovery system. From this comparative work, it is found that mass ratio is required to be increased and the rocket was designed under safety regulation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.11
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• pp.803-811
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• 2019

Water rocket is a non-chemical rocket mechanically powered by pressurized gas and liquid (water) propellants. Since water rockets share many engineering commonalities with liquid propellant rockets for space launch vehicles, it is as a education tool for rocket engineering. Present paper investigated the availability of water rocket as an engineering education model by surveying the history of water rocket and making examples from K-12 education, commercial products and club activities. Finally, a way of improvement is suggested for water rocket competitions make changes in the perception on water rockets by examining the limitations of present competitions.

• Aerospace Engineering and Technology
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• v.13 no.1
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• pp.129-141
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• 2014

Since 2006, an annual rocket competition for university students in America has been held by management of NASA to support the Space Launch System. This paper describes the significance and operational aspects of NASA Student Launch, a rocket competition for university students organized by NASA Marshall Center's Academic Affairs Office, to inspire students to pursue education and careers in science, technology, engineering, or mathematics (STEM) fields, which is Furthermore, It describes briefly activities of Korean national rocket competition for university students.

• Journal of Aerospace System Engineering
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• v.13 no.3
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• pp.70-77
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• 2019

This study presents the numerical investigation of the trajectory of rocket launched from a helicopter. The nonlinear mathematical model of armed configuration of UH-60 helicopter was developed while Hydra 70 unguided rocket was modeled to simulate the rocket behavior. The effects of various inflow models on the launched rocket trajectory are obtained. Similarly, rocket launch simulation was performed to determine the unsafe flight maneuver condition where the rocket trajectory is critically close to the helicopter main rotor tip path plane.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.7
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• pp.525-534
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• 2019

Water rocket is a pressurized liquid propellant rocket that shares the same basic principles of space launch vehicles. Water rockets can be used as an engineering educational material for the liquid rocket principles and the launch vehicle systems, far beyond the scope of K-12 level science education. In this paper, the principles and theories of water rocket propulsion and flight dynamics was investigated at the level of undergraduate rocket engineering classes. Also, the system level design and operation of water rocket is summarized by including the components of launch vehicle, launch pad, payload and recovery as well as altitude measurement methods.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.365-369
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• 2007

The solid rocket interacts circumscriptively in terms of is many more than liquid rocket. It is uncontrollable than liquid rocket because all part of combustion is decided such as Mixture ratio of propellant, burning time and area. However, production cost is cheap and because authoritativeness security can be easy and enlarge the early speed that follow thrust-to-weight ratio, it is used comprehensively by small size rocket. Considered about nozzle cooling to control phenomenon that burn by thermal conduction in interior wall of nozzle that follow in thrust increase of solid rocket and erosion phenomenon by combustion gas of high speed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.491-494
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• 2005

This paper describes the fundamental research of hybrid-propellant rocket system focusing the flight. The performance of the hybrid-propellant rocket system (using the background of lab-scale tests) for a small-scale launch vehicle could have been validated by static thrust tests and flight tests. Based on this system, it was found that hybrid rocket propulsion system was available in an application to a launch vehicle system.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.3
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• pp.41-48
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• 2012

A study to determine the optimal jet conditions for maximizing altitude of the sounding rocket is conducted. The behavior of a simplified one-dimensional momentum equation including aerodynamic drag is investigated. The case where an analytic solution exists and the case where the mass flow rate is constant are calculated. The solutions are compared with numerical solutions. It is shown that there are the optimal jet conditions for maximizing altitude of a sounding rocket and the optimal condition is a function of the rocket mass ratio.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.1
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• pp.71-84
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• 2007

The review of the liquid propellant rocket engine is presented. The combustion instabilities which were discovered on solid and liquid propellant rocket engines in 1930, have occurred on propulsion devices, such as gas turbine, ramjet, scramjet and rocket, and thus a study on the combustion instability became necessary. However, this problem has not been solved yet. Therefore, we investigated causes and mechanisms of the combustion instability and surveyed the efforts of solving combustion instability in various countries for developing stable liquid propellant rocket engines.