• Aerospace Engineering and Technology
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• v.11 no.1
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• pp.57-67
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• 2012

In this study, design of LCTS(Launch Complex Thermostatting System), which is one of ground support equipments for KSLV-I, is analyzed based on CDP(Critical Design Package) provided by Russia. The thermo-hydraulic design of air preparation compartment and hydraulic design of air heating & distribution compartment performed. Also numerical simulation of air heating & distribution compartment was conducted and compared with actual measurement data. Finally, insulation design of system was analyzed. Designing method of LCTS will be helpful in developing or modifying LCTS for new launch vehicle.

• Journal of the Korea Institute of Military Science and Technology
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• v.23 no.2
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• pp.176-184
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• 2020

In this paper, we have proposed hardware and software architecture of a launch control unit for the compatibility between air defense weapon systems loaded on shipboard. Until now, there is no compatibility between weapon systems loaded in battleships of korean navy. In the case of HaeGung system recently completed the test and evaluations, although it will be deployed on several kinds of shipboards, it has no compatibility and flexibility with other air defense weapon systems. Recently it reports that a long range air defense weapon system will be carried on future korean destroyer KDDX. Because the HaeGung and a long range air defense system will be operated together in KDDX, it is necessary to provide the compatibility between two weapon systems. So we have proposed architecture to provide the compatibility of the launch control unit that controls the launching system and the missile interface unit, and the missile in each weapon systems.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.9
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• pp.762-772
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• 2014

A weapon control algorithm equipped on a fighter is closely related to the mission accomplishment and fighter survivability during engagement. The weapon control algorithm typically provides a pilot the dynamic launch zone(DLZ), the target shoot-down range of air-to-air missiles, in the head-up display(HUD). DLZ is produced by an engagement range computation algorithm. In this paper, the components of DLZ for AIM-9 and AIM-120 air-to-air missiles are introduced. The real-time computation algorithm for DLZ based on the pseudo 6-DOF program is then addressed The operational aspects of DLZ algorithm for the air-to-air missiles to various engagement scenarios is investigated vis simulations.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.6
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• pp.517-522
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• 2017

Launch Acceptability Region(LAR) is a region for an aircraft which carries air-to-ground guided bombs to enter such that it can successfully hit the target. LAR should consider the release condition of an aircraft, impact condition for targets, and environmental condition of atmosphere. In this paper, LAR algorithm was developed using the database of many simulations which were varied by inputs, such as the release, impact, and environmental conditions. The algorithm was tested through the direct simulation results, and found that it was suitable to apply as LAR for air-to-ground guided bomb.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.7
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• pp.601-608
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• 2021

Launch Acceptability Region of Air-to-Surface Guided Bomb is defined as the set of release points in order to reach a target successfully. LAR is consisted of fixed target area and moving target area whether the target maneuvers or not. In this paper, the computational algorithm of LAR is studied for fixed and moving target. First, multi-simulations are performed varying platform, target, and atmospheric environment to attain Min/Max DB. Second, the LAR functions are obtained using regression and classification algorithm. For operational suitability, the algorithm for display of LAR is studied to obtain appropriate LAR. In this progress, the results of LAR are suitable to apply air-to-ground guided bomb for moving target.

• International Journal of Aeronautical and Space Sciences
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• v.11 no.2
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• pp.118-125
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• 2010

This paper describes a mid-course guidance strategy based on the earliest intercept geometry (EIG) guidance. An analytical solution and performance validation will be addressed for generalized mid-course guidance problems in area air-defence in order to improve reachability and performance. The EIG is generated for a wide range of possible manoeuvres of the challenging missile based on the guidance algorithm using differential geometry concepts. The main idea is that a mid-course guidance law can defend the area as long as it assures that the depending area and objects are always within the defended area defined by EIG. The velocity of Intercept Point in EIG is analytically derived to control the Intercept Geometry and the defended area. The proposed method can be applied in deciding a missile launch window and launch point for the launch phase.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.4
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• pp.53-60
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• 2004

Optimal design of the hybrid motor has been performed for the first stage of nanosat air launch vehicle using F-4E Phantom as mother plane. Selected design variables are number of ports, the initial oxidizer flux, the combustion chamber pressure, and the nozzle expansion ratio. GBM(Gradient Based Method) and GA(Genetic Algorithm) are simultaneously used to compare the versatility of each algorithm for optimal design in this problem. Also, two objective functions of motor weight, and length are treated separatedly in the optimization to study how the objective function can affect the optimal design. The design results show that the optimal design can be successfully achieved either using GBM or GA regardless of the choice of the objective function; motor weight or length. And nanosat air launch vehicle which has total mass of 704.74kg, and length of first stage 3.74m is designed.

• The Korean Journal of Air & Space Law and Policy
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• v.17
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• pp.163-174
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• 2003

The space center will be constructed by 2005 for launch of KSLV-I at Woinara-Do, Haban Village, Yenae-Ri, Bongrae-Myon, Kohung-Goon, Junlanam Province on the southern coast of the Korean peninsular. This will make Korea be the 13th advanced country in space development having launching site in the world. This paper presents licensing and safety requirements to protect the public from the risks associated with activities at a launch site.

• Journal of the Korea Society for Simulation
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• v.32 no.4
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• pp.1-10
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• 2023

This study examines the response when the shock by underwater explosion is transmitted to a vertical launch air-vehicle mounted on a ship using modeling and simulation, and is about a plan to increase method shock resistance to protect the air vehicle. In order to obtain an accurate mathematical model, a dynamic characteristic test was performed on similar equipment, and through this, the mathematical model could be supplemented. And, using the supplemented mathematical model, the air vehicle simulated the shock response by the underwater explosion specified in the BV043 standard. As a result of the first simulation, it was confirmed that air vehicle could not withstand shock, and air vehicle protection method using a ring spring type shock absorber was studied. In addition to the basic shape of abosber, it was confirmed that the ring spring absober can be used to increase the impact resistance of a shipborn vertical launch vehicle by performing simulations for each case by changing deseign varables.

• 한국전산유체공학회:학술대회논문집
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• 2005.10a
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• pp.269-273
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• 2005

The on-board system for the air supply to the payload fairing(PLF) of a launch vehicle using both high and low pressure air was designed. The design concept was obtained from the CFD analysis of a Russian interstage air supply system, and a collector was adopted to expand the high pressure air. To verify that the on-board system would work as designed, a simplified axisymmetric computational model was made and a CFD analysis was also performed. It was found that the flow ejected from the hole of the collector expands to the Mach number of 4 and is soon retarded due to the action of viscosity. It was also found that a small gap between the low pressure duct and equipment bay wall can cause large velocity in PLF over the velocity requirement and no gap should be allowed in the design.