155,091 research outputs found
LEE CHANG HUN
No full text학위논문(석사)--아주대학교 교육대학원 :평생교육,2020. 8본 논문은 대기업에서 오랫동안 근무하다가 정년이전에 회사의 조기 퇴직제도에 의해 퇴직을 선택한 이들이 퇴직이후 새로운 직업을 찾는 과정에서의 경험과, 새로운 직업을 찾은 이후의 삶의 모습을 전환학습적 관점에서 탐구한 논문이다. 지금까지 대기업 출신 퇴직자를 대상으로 한 연구들은 주로 전직지원 프로그램이 구직 효능감 증대나 고용가능성에 미치는 효과 등 재사회화를 위한 외재화 가치에 역점을 둔 연구가 주를 이룬다. 반면에 퇴직이후 경험하는 상실감, 두려움 등 여러 어려움을 극복하고, 새로운 목표 설정을 통하여 도전하고 성취해 나가는 과정에서의 학습경험과 같은 내재적 가치를 드러내는 연구들은 활발히 이루어지지는 않았다. 이에 본 연구에서는 Mezirow의 전환학습이론을 이론적 틀로 하여 생애 전환기에 서 있는 중년들의 경험분석을 통하여 그 들의 삶의 맥락과 퇴직이후 새로운 직업 찾기 과정에서의 전환학습 양상을 명확히 드러낼 수 있었다. 따라서, 본 연구는 점점 더 증가추세에 있는 대기업 조기 퇴직자들이 새로운 삶을 마주하는 과정에서의 학습경험을 드러내는 노력을 통하여 내재적 가치를 발견하고, 이를 공유할 수 있는 의미있는 지점을 만들어 냈다는 데 의의가 있다고 할 수 있겠다.Ⅰ. 서론 1
1. 내러티브의 시작: 연구자의 이야기 1
2. 연구의 필요성 및 목적 5
3. 연구 문제 11
Ⅱ. 이론적 배경 12
1. 전환학습 12
가. 전환학습의 개념 12
나. 전환학습 단계의 핵심요인 17
다. 전환학습이론에 대한 다양한 논의 31
라. 전환학습 선행연구 검토 34
마. 새로운 직업 찾기 과정과 전환학습 37
2. 직업적응 및 퇴직 38
가. 직업적응이론 개념 38
나. 대기업 출신인력의 조기퇴직 의미 40
다. 조기 퇴직자의 실직경험 현상 42
III. 연구 방법 45
1. 내러티브 탐구 45
2. 연구 참여자 49
가. 연구 참여자 선정 49
나. 연구 참여자 소개 51
3. 연구절차 및 분석과정 55
가. 현장텍스트 수집 57
나. 텍스트 분석 61
4. 연구의 진실성 및 윤리 64
Ⅳ. 대기업에서 조기퇴직한 두 중년 가장의 새로운 직업 찾기 내러티브 67
1. 취미가 직업(덕업일치)이 된 ‘이건장’의 내러티브 67
가. 운동 매니아이자 모범생, 자동차 엔지니어를 꿈꾸다 69
나. 자동차 무대에 오른 캐스트, 그리고 고장난 네비게이션 75
다. 다시 단역으로 잠시 캐스팅, 그리고 연출가로의 변신 89
2. 적성에 맞는 직업 찾아 삼만리! ‘허배려’의 내러티브 96
가. 강원도 산골의 올곧은 나무처럼, 나이테를 형성해 나가다 97
나. 맞지 않는 옷, 계속 늘려 입다가 26년만에 벗다 102
다. 정말 좋아하고, 잘할 수 있는 직업을 향하여 108
라. 엔지니어에서 두 개의 기관을 거느린 사업가로 변신! 116
Ⅴ. 새 직업 찾기 과정에서의 전환학습 경험 122
1. 여행에서 돌아오니 여행에서 보지 못한 것이 보이네! 123
가. 경험이라는 씨앗, 또다른 경험의 양산 123
나. 직업과 삶의 진정한 통합을 위한 긴 여정 136
2. 세상의 규격화된 삶에서, 나대로의 삶으로! 150
가. 한 단계씩 정진하는 삶, 삶의 의미와 함께하는 과정 151
나. 희망의 지렛대, 조력(助力) 157
Ⅵ. 새로운 작업을 찾은 이후 삶의 모습 165
1. 세상에 보여 주기 식 삶에서, 나답게 살아가기 165
Ⅶ. 논의 및 결론 170
1. 논의 및 결론 170
2. 후속 연구 제언 178
참고문헌 180Maste
A Simple Outline of Methods for Protein Isolation and Purification
No full textAt the summer workshop of the Korean Endocrine Society held in 2016, some examples of protein experiments were discussed in the session entitled “All about working with proteins.” In contrast to what the title suggested, it was unrealistic to comprehensively discuss all protein analytical methods. Therefore, the goal was to outline protein experimental techniques that are useful in research or in bench work. In conversations with clinicians, however, I have always felt that researchers who do not engage in bench science have different demands than those who do. Protein research tools that are useful in bench science may not be very useful or effective in the diagnostic field. In this paper, I provide a general summary of the protein analytical methods that are used in basic scientific research, and describe how they can be applied in the diagnostic field
Lee, Chang-rae : interview; May 12th, 2006
No full textContents:
Interview Jim Schiff interviews Chang-rae LeeDescription on cassette : Chang-rae Lee - Interview w/Jim Schiff
May 12, 2006Digital Projects SAN: Folder and disc location for wav file: 20121005/Disc 1. Folder and disc location for mp3 file: 20121005/Disc 6/mp3
Nonlinear Three-Loop Autopilot Design for Spaceplanes
No full textThis paper deals with the nonlinear autopilot design for spaceplanes based on the three-loop autopilot architecture. To this end, the nonlinear dynamics equations for spaceplanes during the reentry phase are first determined. The dynamic characteristics of the dynamics model are then investigated. The analysis results show that the time-scale separation is valid in the autopilot design for spaceplanes. Accordingly, based on the approximation of the time-scale separation, the proposed autopilot is designed by leveraging the feedback linearization control technique in conjunction with specific forms of the desired error dynamics. The key feature of the proposed autopilot lies in the fact that the resultant autopilot is given by the nonlinear three-loop autopilot structure, which has been widely applied to various flight vehicles. Thus, favorable characteristics of the three-loop autopilot are inherited. Numerical simulations verify our findings in this study
An Analysis of the Point-to-Point Cargo Transportation System using Reusable Launch Vehicles
No full textThis paper aims to analyze the mission profile of the point-to-point cargo transportation system that employs reusable launch vehicles. We establish the mission profile concept referred to return to launch site which is appropriate for short-distance transportation. Also, we describe the characteristics of each flight phase in detail. The trajectory optimization problem is defined to obtain the optimal trajectory of proposed mission profile with the main parameters of flight phases as optimization variables. Various flight constraints are considered to derive feasible trajectories of the rocket cargo transportation system. Given that the goal of this system is to maximize the cargo mass under specific conditions, we set the payload ratio as the objective function. This trajectory optimization problem is solved using the evolutionary algorithm to derive the optimal trajectory and state variables. Furthermore, we perform parametric studies of the given conditions to analyze the characteristics of the proposed mission profile
Powered Descent Guidance for a Reusable Launch Vehicle Demonstrator Using a Customized Convex Optimization Solver
No full text본 연구에서는 재사용 발사체 시연체를 위한 컨벡스 최적화 기반의 동력 하강 유도를 설계하고, 시뮬레이션 및 수치 실험을 통해 성능과 실현 가능성을 평가하였다. 설계된 동력 하강 유도는 컨벡스 최적화를 통해 연료 소모를 최소화하는 최적 궤적 도출과 최적 궤적 추종을 위한 피드백 유도 루프로 구성된다. 온보드 컴퓨터 상에서 실시간 최적화를 수행하기 위해 자체 개발한 커스텀 컨벡스 최적화 솔버를 활용하였으며, 온보드 컴퓨터 상에서 몬테카를로 시뮬레이션을 수행하여 실시간성과 알고리즘의 강건성을 검증하였다. 마지막으로 시연체 착륙 임무에 대한 시뮬레이션을 수행하여 설계된 유도 기법이 최적 궤적을 잘 추종하며 원하는 지점에 연착륙을 달성함을 확인하였다
Multi-phase and dual aero/propulsive rocket landing guidance using successive convex programming
No full textThis paper aims to suggest a new landing guidance algorithm for reusable launch vehicles (RLVs) to enable generation of fuel-efficient trajectories based on successive convex programming. To this end, a dual aero/propulsive landing guidance problem is first formulated to fully exploit the additional moment generated by the aerodynamic control to reduce the propulsion demand required for attitude control. As the result of the aerodynamic landing phase could greatly affect the fuel-optimal trajectory during the vertical landing phase, the formulation is further extended to the multi-phase optimal guidance problem using state-triggered constraints. The proposed guidance strategy is then obtained by solving the formulated optimal control problem based on the successive convex optimization framework using an interior point method The main contribution of this study lies in forming new RLV landing guidance problems to get an optimal trajectory and transforming the corresponding nonconvex problem into a convex optimization problem by introducing appropriate combinations for convexification techniques. Additionally, this paper introduces several practical constraints, such as the maximum slew rate of aerodynamic control fins and nozzle angles, which are not considered in previous works. In this paper, the performance of the proposed method with the potential for online computation is investigated through numerical simulations.
Adaptive Weight Model Predictive Path Integral Control for Multi-constrained Missile Guidance
No full textThis paper aims to propose a new computational guidance method for missiles that can satisfy multiple practical constraints, such as impact angle and time, seeker's field-of-view, and acceleration constraints. The proposed method is based on the model predictive path integral (MPPI) with a novel adaptive weight scheme. MPPI control is a numerical optimization approach that solves optimal control problems using a stochastic process. In this approach, the optimal control inputs are repeatedly updated to minimize the cost functions of sampled state trajectories generated by propagating the system model with a noise input. However, in the conventional MPPI architecture, the cost functions for constraints are typically formulated using fixed weight values, and it is also challenging to handle terminal constraints. Finding appropriate weight values for each cost function and the terminal constraints requires a lot of effort, making the conventional MPPI approach inadequate for solving optimal control problems with multiple constraints and terminal constraints, such as multiconstrained guidance problems. To solve this problem, we propose a new method called adaptive weight MPPI control. The cost weights are automatically adjusted using the estimated states from the sampled state trajectories. This proposed MPPI architecture allows us to solve multiconstrained guidance problems without carefully tuning the weight values. Moreover, the proposed method can be easily applied to various multiconstrained guidance problems without significant configuration changes in guidance algorithms. Numerical simulations are performed for various engagement conditions to verify the effectiveness and feasibility of the proposed guidance algorithm in this study.
A disturbance rejection control for urban air mobility using artificial sensor-based Gaussian process regression
No full textThis paper presents a learning -based disturbance rejection control strategy for Urban Air Mobility (UAM) with vertical take -off and landing capability, which is subject to uncertainties in system parameters. The two primary sources of uncertainty during UAM operation, specifically moment of inertia uncertainty and center of gravity variation, are thoroughly analyzed as they negatively impact control performance. Building upon the analysis outcomes, a novel adaptive scheme is proposed that employs the modeling capabilities of Gaussian process regression for online learning to estimate model uncertainties. To ensure the collection of high -quality training data without relying on state derivatives, a nonlinear disturbance observer is employed as an artificial sensor. The suggested control algorithm is formulated by integrating Gaussian process regression with a baseline control derived using the feedback linearization control technique. Theoretical analysis grounded in the Lyapunov theorem reveals that the tracking error of the closed -loop system is semi -globally uniformly and ultimately bounded. Numerical simulations are conducted to validate the effectiveness of the proposed approach. The results obtained confirm that the proposed method can achieve superior tracking performance, even in the presence of model uncertainties and time -varying disturbances, surpassing existing approaches.
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