• Bulletin of the Korean Chemical Society
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• v.32 no.12
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• pp.4210-4214
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• 2011

Quasiclassical trajectory (QCT) calculations of Ne + ${H_2}^+$ reaction have been carried out on the adiabatic potential energy surface of the ground state $1^2$ A'. The reaction probability of the title reaction for J = 0 has been calculated, and the QCT result is consistent with the previous quantum mechanical wave packet result. Quasiclassical trajectory calculations of the four polarization-dependent differential cross sections have been carried out in the center of mass (CM) frame. The P(${\theta}_r$), P(${\phi}_r$) and P(${\theta}_r$, ${\phi}_r$) distributions, the k-k'-j' correlation and the angular distribution of product rotational vectors are presented in the form of polar plots. Due to the well in $1^2$ A' PES, the reagent vibrational excitation has greater influence on the polarization of the product rotational angular momentum vectors j' than the collision energy.

• Industrial Engineering and Management Systems
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• v.10 no.3
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• pp.232-237
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• 2011

Design for Six Sigma (DFSS) has been implemented in many companies to enhance their business performance and customer satisfaction. However, DFSS has not been widely applied to the aircraft industry which operates large, complex development programs. In this paper, the characteristics of an aeronautical product development program are analyzed to figure out the limitations of current DFSS methodology and the prerequisite to deployment of DFSS at the program level is suggested.

• Bulletin of the Korean Chemical Society
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• v.33 no.9
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• pp.2873-2877
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• 2012

Quasi-classical trajectory (QCT) calculations of H+HLi reaction have been carried out on a new potential energy surface of the ground state reported by Prudente et al. [Chem. Phys. Lett. 2009, 474, 18]. The four polarization-dependent differential cross sections have been carried out in the center of mass (CM) frame at various collision energies. The reaction probability for the depletion channel has been studied over a wide collision energy range. It has been found that the collision energy decreases remarkably reaction probability, which shows the expected behavior of the title reaction belonging to an exothermic barrierless reaction. The results are in good agreement with previous RMP results. The P(${\theta}_r$), P(${\phi}_r$) and P(${\theta}_r,\;{\phi}_r$) distributions, the k-k'-j' correlation and the angular distribution of product rotational vectors are presented in the form of polar plots. The average rotational alignment factor <$P_2(j{\prime}{\cdot}k)$> as a function of collision energy is also calculated. The results indicate that the collision energy has a great influence on the polarization of the product rotational angular momentum vector j'.

• Journal of Aerospace System Engineering
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• v.9 no.4
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• pp.43-48
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• 2015

This paper presents the systematic and procedural approaches to ensure the safety of the composite material domestically developed and produced, for its use in the structure of aeronautical product in accordance with the applicable international standard, and to enhance its creditability. Based on this approaches, this paper eventually proposes the practical future plan to encourage and expand the adoption of domestic composite material as part of aeronautical product by aircraft manufacturer in global market.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.9
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• pp.663-668
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• 2022

Since the early 2000s, the United States has applied TLCSM to reduce life cycle costs while maintaining the weapons system's combat readiness. With the application of TLCSM, the ILS concept centered on the acquisition stage shifted to IPS, a concept that manages life cycle costs throughout the entire life cycle. In addition, LSAR for developing ILS has switched to LPD for developing IPS. In this study, LSAR in Korea and LPD in the United States were compared and analyzed, and policies necessary for the introduction of LPD in Korea were proposed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.6
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• pp.513-518
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• 2018

Nitrogen charging trailer applied to KUH-1 is a device to charge Nitrogen in main front wheel buffer, tail bumper buffer, brake accumulator and tire of aircraft. As the name suggests, it is a device that has mobility along with nitrogen charging. Originally supplied by Tronair in the United States, it was imported from Korea, and the locally developed product not only satisfies the performance of the existing product, but also designed to be easier than the product introduced in the operation. It was selected as the joint investment project of the 15th civilian government building, and development needs analysis and test evaluation were carried out under the support of development and management of Korea Aerospace Industries and Defense Agency for Technology and Quality.

• International Journal of Aeronautical and Space Sciences
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• v.1 no.1
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• pp.62-69
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• 2000

Present study deals with performance analysis of an inert gas generator (IGG) which can be used as effective means to suppress fire. The IGG uses a turbo-jet engine to generate inert gas for fire extinguishing. It is generally known that a less degree of oxygen content in the product of combustion will increase the effectiveness of fire extinguishing. An inert gas generator system with water injection has advantages of suffocating and cooling effects that are very important factors for fire extinguishing. Some aspects of influencing parameters, such as, air excess coefficient, compressor pressure ratio, air temperature before combustion chamber, gas temperature after combustion chamber, mass flow rate of water injection etc. on the performance of IGG system are investigated.

• International Journal of Aeronautical and Space Sciences
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• v.15 no.2
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• pp.153-162
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• 2014

A novel robust $H_{\infty}$ switching tracking control design method with disturbance observer is proposed for the near space interceptor (NSI) with aerodynamic fins and reaction jets. Initially, the flight envelop of the NSI is divided into small subregions, and a slow-fast loop polytopic linear parameter varying (LPV) model is proposed, to approximate the nonlinear dynamic of the NSI, based on the Jacobian linearization and Tensor-Product (T-P) model transformation approach. A disturbance observer is then constructed, to estimate the modeled disturbance. Subsequently, based on the descriptor system method, a robust switching controller is developed, to ensure that the closed-loop descriptor system is stable with a desired $H_{\infty}$ disturbance attenuation level. Furthermore, the outcome of the proposed switching tracking control problem is formulated as a set of linear matrix inequalities (LMIs). Finally, simulation results demonstrate the effectiveness of the proposed design method.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.3
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• pp.195-202
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• 2016

There is two popular kites, Bangpae and Gaori. While the Bangpae kite is being widely loved by experts, the Gaori kite is popular for kids and beginners. Three types of Gaori kite product have been survayed on the tow point. The aerodynamic force on Gaori kite is numerically calculated by using Fluent. Through flight simulations at the tow point of each kite type, the new tow point, at which the required minimum velocity is lower than those of existing tow points, has been proposed as a standard. The required minimum velocity is the threshold wind velocity at which the kite begins to fly.

• International Journal of Aeronautical and Space Sciences
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• v.16 no.3
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• pp.437-444
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• 2015

Satellite selection and exclusion techniques have been applied to the global navigation satellite system (GNSS) with the aim of achieving a balance between navigational performance and computational efficiency. Conventional approaches to satellite selection based on the best dilution of precision (DOP) are excessively computational and complicated. This paper proposes a new method that applies a geometric sensitivity index of individual GNSS satellites. The sensitivity index is derived using the inner product of the line of sight (LOS) vector of each satellite. First, the LOS vector is computed, which accounts for the geometry between the satellite and user positions. Second, the inner product of each pair of LOS vectors is calculated, which indicates the proximities of the satellites to one another. The proximity can be determined according to the sensitivity of each satellite. A post-processing test was conducted to verify the reliability of the proposed method. The proposed index and the results of a conventional approach that measures the dilution of precision (DOP) were compared. The test results demonstrate that the proposed index produces results that are within 96% of those of the conventional approach and reduces the computational burden. This index can be utilized to estimate the sensitivity of individual satellites, obtaining a navigation solution. Therefore, the proposed index applies to satellite selection and exclusion as well as to the sensitivity analyses of multiple GNSS applications.