• Bulletin of the Korean Chemical Society
• /
• 제32권12호
• /
• pp.4210-4214
• /
• 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
• /
• 제10권3호
• /
• pp.232-237
• /
• 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
• /
• 제33권9호
• /
• pp.2873-2877
• /
• 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'.

• 항공우주시스템공학회지
• /
• 제9권4호
• /
• pp.43-48
• /
• 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.

• 한국항공우주학회지
• /
• 제50권9호
• /
• pp.663-668
• /
• 2022

미국은 2000년대 초반부터 무기체계의 전투준비태세를 유지하면서 수명주기비용을 줄이기 위해서 TLCSM를 적용하였다. TLCSM이 적용되면서 획득단계 중심의 ILS 개념에서 전체 수명주기 동안 수명주기비용을 관리하는 개념인 IPS로 전환하였다. 또한 ILS를 개발하기 위한 LSAR은 IPS을 개발하기 위한 LPD로 전환하였다. 본 연구에서는 한국의 LSAR과 미국의 LPD를 비교 및 분석하여 LPD의 한국 도입 시 필요한 정책을 제안하였다.

• 한국항공우주학회지
• /
• 제46권6호
• /
• pp.513-518
• /
• 2018

KUH-1에 적용되는 질소충전트레일러는 항공기의 주/전륜 완충기, 테일범퍼완충기, 브레이크 축압기, 타이어 등에 질소를 충전하는 장비이다. 명칭에서 알 수 있는 것과 같이 질소충전트레일러는 질소 충전과 더불어 이동성을 가지고 있는 장비이다. 기존 미국의 Tronair사에서 독점 공급하여 국내에서는 수입에 의존하던 품목이며, 본 국산화 개발품은 도입품의 성능을 만족할 뿐만 아니라 운용 시 도입품보다 용이하도록 설계를 추진하였다. 제15-4차 민관공동투자사업으로 선정되어 개발이 진행되었으며, 민관투자기업인 한국항공우주산업과 국방기술품질원의 개발관리 지원하에 개발요구도 분석 및 시험평가가 수행되었으며, 2017년 5월 군사용 적합 판정 결과 승인을 받았다.

• International Journal of Aeronautical and Space Sciences
• /
• 제1권1호
• /
• pp.62-69
• /
• 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
• /
• 제15권2호
• /
• pp.153-162
• /
• 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.

• 한국항공우주학회지
• /
• 제44권3호
• /
• pp.195-202
• /
• 2016

대중적인 연에는 방패연과 가오리연 두 종류가 있다. 방패연은 전문가들에게 널리 사랑 받고 있는 반면, 초보자들에게는 가오리연이 더 익숙하다. 가오리연의 세 종류의 제품들에 대하여 목줄의 매듭을 조사하였다. 가오리 연에 작용하는 공기역학적 힘들을 Fluent를 사용하여 수치적으로 계산하였다. 각 종류의 매듭에 대한 비행 시뮬레이션을 수행함으로써, 기존보다 최소요구풍속이 더 낮은 새로운 매듭을 제안하였다. 최소요구풍속은 연이 날기 시작하는 한계 풍속이다.

• International Journal of Aeronautical and Space Sciences
• /
• 제16권3호
• /
• pp.437-444
• /
• 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.