• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.4
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• pp.40-49
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• 2001

The basic research on AKM(Apogee Kick Motor) for space launch vehicle was carried out. AKM which will be used as 3rd stage solid rocket motor in 3-stage Korean Sounding Rocket(III) has been developing. KM is a solid rocket motor using composite propellant based on HTPB and is composed of composite motor case and submerged nozzle. To develop KM rocket motor satisfing a given set of requirement, firstly the full-scale KM with diameter 520mm was designed, then sub-scale motors reduced about 60% were manufactured and tested. Full-scale ground firing test is accomplished two times.

• Aerospace Engineering and Technology
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• v.7 no.2
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• pp.131-143
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• 2008

Slag mass deposition was required to predict performance accurately of KSLV-I kick motor(KM) system. The validation of the numerical analysis was performed with mass flow rate measured at 4th ground test of the KM. The study described here included internal flow field of KM at various time steps during burning. Slag mass accumulation was computed through the aluminum oxide particle paths to deviate from the gas flow streamlines in flight. These numerical analysis was performed with Fluent 6.3 program The effects for the acceleration, origins and diameters of the aluminum oxide particles was analyzed, finally the total slag mass accumulation was acquired. We confirmed that the slag mass deposition was agreement well with predicted slag mass based on kick motor the grounded test.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.190-200
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• 2007

A pyrogen type igniter was designed to satisfy the requirements of KSLV-I Kick Motor system. To insure the reliability of the igniter before the production of the flight model, we have been performed the structure, environmental, combustion tests. The hydraulic test was carried out to confirm the strength of the components of the igniter. The shock and vibration tests were considered to check whether the igniter operates normally under the severe environmental condition. The combustion tests were also performed to understand the ignition characteristics with the variation of initial condition. Finally, we confirmed that the igniter could provide the acceptable energy to ignite the propellant of kick motor at the ground test.

• 한국전산유체공학회:학술대회논문집
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• 2008.03b
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• pp.428-431
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• 2008

Korea Aerospace Research Institute(KARI) is achieving the Korea Space Launch Vehicle(KSLV) program according to National Space Technology Development Program. KSLV-I will be composed to liquid propellant(first stage) and solid propellant(second stage) propulsion system. The propulsion system of KSLV-I second stage is solid kick motor with high expansion ratio and its starting altitude is 300km high. In order to verify the performance of upper stage propulsion system designed to operate in the upper atmosphere, test facility which can simulate high altitude is needed. High Altitude Simulation Test Facility is composed to Thrust Measurement System, Control & Measurement system, Diffuser, SKID for cooling water supply to diffuser, CCTV, fire protection system and so on. This paper introduces TMS adapted to High Altitude Simulation Test for KSLV-I Kick Motor Development and results of hot firing test for its performance verification.

• 한국전산유체공학회:학술대회논문집
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• 2008.03b
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• pp.220-223
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• 2008

A test facility to measure the performance of a KM(Kick Motor) is constructed, and prediction of blast wave propagation over the facility is performed to check if the safety of test personnel in MCC(Main Control Center) can be guaranteed even for the most severe explosion. Assuming that the initial explosion energy is contained in a sphere under the pressure of 500, 1000, 1500 psi, respectively, the radius of the sphere is determined for each pressure to set the mass of contained explosion gas to 35 kg. The material properties of explosion gas are set to be the ones of KM propellant combustion gas under normal condition. To reduce the effort and time required for a complex three-dimensional modeling, the flowfield is approximated to axismmetry. Calculations are performed for all three initial pressure conditions, and the analysis of the result is given for 1500 psi which is expected to be the worst case. The maximum pressure is 3.5 psig while the minimum pressure is -1.2 psig on the outer wall of MCC, and the maximum pressure difference between the inner and outer walls of protection wall amounts to 3.0 psi.

• Aerospace Engineering and Technology
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• v.5 no.2
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• pp.159-165
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• 2006

In this study, structural analysis is executed about cone structure of KSL V-1 2nd stage KMS(kick motor support structure) which is designed for support the load developed from 2nd stage kick motor. KMS is consisted of cone structure and truss structure which is designed for supporting load developed from 2nd stage payload. Applied loads to cone structure are tension load by inertia developed from kick motor and compression load developed from kick motor. Also, shear and bending load are developed according to flight condition. In this study, structural analysis of cone structure is executed under several load condition which may be applied to cone structure. Also, structural analysis with two finite element model is performed according to pressure vent scheme. In result of structural analysis, critical load condition is equivalent tension load with cut-out.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.209-215
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• 2005

A qualification of propellant for a AKM(Apogee Kick Motor) has been conducted by firing standard motors. The Standard motor used in developing process of KSLV-I's AKM is ST-6 whose diameter is about six inches. HTPB composite propellant are used in these motors. Several standard motors are fired and compared with simulation results. A mean value of characteristic velocity is 1518 m/s. The characteristic value for prediction is 1516 m/s, and the thrust loss is about 5.9%. Differences between the measurements and prediction are less than 3%.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.138-142
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• 2010

The thrust axis alignment of the launch vehicle is very important because of the misalignment causes the unstable attitude control and results in mission failure. Generally, optical methods such as digital theodolite and laser tracker and mechanical method such as turn table method are used to align thrust axis to vehicle axis. This article deals with the simple method of thrust axis alignment of Kick Motor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.705-706
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• 2010

The design analysis for the ignition transient combustion characteristics of a Kick Motor igniter indicated that the initial pressure condition would delay ignition time within a range from 100 to 500 ms. In the development tests, we confirmed that the igniter could provide the acceptable energy to ignite the main propellant at ignition transient.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.217-220
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• 2008

Slag mass deposition was required to predict accurate performance of kick motor (KM) system. Slag mass accumulation was analyzed through the aluminum oxide particle paths to predict slag mass deposition. Numerical analysis to solve both flow field and droplet accumulation was performed with Fluent 6.3 program. The effects for the acceleration and diameters of the aluminum oxide particles was analyzed, finally total slag mass accumulation was acquired. It confirmed that the slag mass deposition was agreed well with previously slag mass prediction based on KM ground test.