• 대한기계학회논문집A
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• 제25권12호
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• pp.1950-1959
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• 2001

An active control of the vibration transmitted by longitudinal load in flight control system is investigated numerically. The flight control system is modeled as a finite, thin shell cylinder with constant thickness. A vibration source is generated by exterior monopole source. Distributed piezoelectric actuator is used to control of the vibration. Thin shell theory is used to formulate the numerical models. The amplitude of vibration at discrete location and power transmission are minimized by analytical optimization method. Genetic algorithm is used as numerical optimization method to search optimal actuator position and size which amplitude of vibration is minimized.

• International Journal of Aeronautical and Space Sciences
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• 제13권1호
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• pp.117-125
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• 2012

This paper presented the design of SRPS, ground function test, and the deployment test on a high speed taxi of KC-100 airplane. KAI has developed a spin recovery system in collaboration with Airborne Systems for KC-100 general aviation airplane. Spin mode analysis, rotary balance and forced oscillation tests were performed to obtain the rotational, dynamic derivatives in the preliminary design phase. Prior to the detailed design process of SRPS, approximations for initial estimation of design parameters- fineness ratio, parachute porosity, parachute canopy filling time, and deployment method- were considered. They were done based on the analytical disciplines such as aerodynamics, structures, and stability & control. SRPS consists of parachute, tractor rocket assembly for deployment, attach release mechanism (ARM) and cockpit control system. Before the installation of SRPS in KC-100 airplane, all the control functions of this system were demonstrated by using SBTB(System Breakout Test Box) in the laboratory. SBTB was used to confirm if it can detect faults, and simulate the firing of pyrotechnic devices that control the deployment and jettison of SRPS. Once confirmed normal operation of SRPS, deployment and jettison of parachute on the high speed taxiing were performed.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1994년도 Proceedings of the Korea Automatic Control Conference, 9th (KACC) ; Taejeon, Korea; 17-20 Oct. 1994
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• pp.271-276
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• 1994

In this paper we deal with a design of CCV adaptive flight control system having adaptive observer under the mircroburst circumstances. First, based on the observerbility indices of the controlled system, which is a general multi-variable one, the adaptive observer is constructed, and the unknown interactor matrix can be estimated by using the identified parameters. Next, CCV adaptive flight control law is calculated based upon the estimated ones. Finally, the proposed CCV adaptive flight controller is applied to STOL flying boat and numerical simulations under the microburst circumstances can be show to justify the proposed scheme.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1994년도 Proceedings of the Korea Automatic Control Conference, 9th (KACC) ; Taejeon, Korea; 17-20 Oct. 1994
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• pp.659-664
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• 1994

In this paper we deal with a synthesis of flight control system via nonlinear model matching theory. First, the longitudinal and lateral-directional equations of aircraft motion an CCV mode are considered except the assumption "variations on steady straight flight due to disturbances are very small". Next, a design method of the dynamic model matching control system based on Hirschorn's Algorithm is proposed to the above nonlinear system. Finally, the proposed control system is applied to the small sized, high speed aircraft, T-2 on CCV mode and numerical simulations are shown to justify the proposed scheme.ed scheme.

• 한국항공우주학회지
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• 제32권4호
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• pp.95-100
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• 2004

본 논문에서는 기계적 링키지의 가역 (Reversible) 비행조종장치를 갖는 항공기익 조종간 조종력 재현 시스템 (CLS : Control Loading System) 개발을 목적으로 조종력 재현 장치 제어기 설계, 시스템 구성, 조종력 재현 장치 운용 환경을 구축하고 시험평가를 수행한 내용을 기술한다. 시스템 구성은 기계적인 외형부분과 힘을 측정하는 센서부분과 스틱에서의 반력을 재현하는 모터부분과 안전장치로 되어 있다. 하드웨어와 PC간의 입출력 신호 연결 및 제이기로 dSpace 사의 DS1103 DSP장치를 사용하였다. 대상항공기 (KT-1)의 비행 조종장치 모델링을 바탕으로 피치축과 롤축에 대한 CLS를 구성하고, 조종력 재현장치 제어법칙 설계와 모니터링 S/W 및 실시간 시험평가도구를 포함한 시험평가 및 운용환경 대해 기술하였다. 정적 및 동적시험을 수행하여 실제 대상항공기 데이터와 비교함으로써 개발한 시스템을 검증하였다.

• Advances in aircraft and spacecraft science
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• 제1권3호
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• pp.353-378
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• 2014

This paper deals with the early development of the Anuloid, an innovative disk-shaped VTOL aircraft. The Anuloid concept is based on the following three main features: the use of a ducted fan powered by a turboshaft for the lift production to take-off and fly; the Coanda effect that is developed through the circular internal duct and the bottom portion of the aircraft to provide further lift and control capabilities; the adoption of a system of ducted fixed and swiveling radial and circumferential vanes for the anti-torque mechanism and the flight control. The early studies have been focused on the CFD analysis of the Coanda effect and of the control vanes; the flyability analysis of the aircraft in terms of static performances and static and dynamic stability; the preliminary structural design of the aircraft. The results show that the Coanda effect is stable in most of the flight phases, vertical flight has satisfactory flyability qualities, whereas horizontal flight shows dynamic instability, requiring the development of an automatic control system.

• 한국항공우주학회지
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• 제50권7호
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• pp.489-496
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• 2022

본 논문에서는 한국항공대학교에서 설계 및 개발한 태양광 무인기인 KAU-SPUAV의 시스템을 소개하고 비행시험을 통하여 성능을 검증하였다. 두 가지 버전의 태양광 무인기의 제원과 전장 구성 그리고 지상 관제 시스템을 소개하였다. 제시한 시스템으로 전파맵 구축, 제주도 해안선 일주 그리고 장기 체공 비행의 세 가지 임무 비행을 수행하였다. 각 임무는 태양광 무인기의 특성을 이용하는 비행으로서 주로 장시간 및 장거리 임무로 구성되었다. 본 연구를 통하여 태양광 무인기의 장기체공 능력을 이용해 다양한 임무에 사용될 수 있음을 보였다. 비행 시험 결과를 기반으로 시스템 추가 개선을 통하여 성능 향상을 도모할 수 있음을 확인하였다.

• 천문학회보
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• 제44권2호
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• pp.57.2-57.2
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• 2019

BITSE is a balloon mission, which is a solar coronagraph to measure speed and temperature of the solar wind using 4 different wavelength filters and an pixelated polarization camera. KASI and NASA jointly designed, developed, and tested the solar coronagraph. Mainly KASI developed an imaging system and a control system, and NASA developed an optical system and mechanical structures. We mount the BITSE on Wallops Arc-Second Pointer (WASP) of Wallops Flight Facility, and launch it with a 39 mcf balloon of Columbia Scientific Ballon Facility. We will introduce the overall system of the BITSE.

• 대한기계학회논문집A
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• 제40권4호
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• pp.343-352
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• 2016

멀티로터 비행체는 여러 개의 로터로 이루어진 무인 비행로봇으로서, 로터의 개수에 따라서 트라이로터, 쿼드로터, 헥사로터, 옥토로터 등으로 나누어 진다. 멀티로터는 수직이착륙 및 정지비행과 같은 높은 기동성으로 인하여 다른 무인 비행로봇에 비하여 험준한 산학지역 및 건물이 밀집되어 있는 도심과 같은 지역의 정찰 및 감시 등 여러 응용분야에 유용하게 활용될 수 있다. 하지만, 멀티로터는 불확실한 외부 환경 및 외란의 영향에 쉽게 노출될 수 있어 강건한 자세 및 비행제어 기법의 적용을 필요로 한다. 본 논문에서는 강인제어기법 중 하나인 슬라이딩 모드제어기를 설계 및 임베디드 알고리듬을 구현을 통하여 실시간 실내 비행실험을 위한 시스템을 구성하고, 실시간 위치제어 및 자세 안정화에 대한 실내 비행실험을 수행하였다. 특히, 불확실한 외부환경에 대한 강건한 비행특성을 검증하기 위하여 외란을 삽입하여 비행시험을 통해 성능을 검증하였다.

• 대한기계학회논문집
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• 제18권6호
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• pp.1399-1411
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• 1994

A model helicopter has more versatile flight capability than the fixed-wing aircraft and it can be used as an unmaned vehicle in hazardous area. A helicopter, similar to other aircrafts, is an unstable, multi-input multi-output nonlinear system exposed to strong disturbance. So it should be controlled by robust control theories that can be applied to multivariable systems. In this study, motion equations of hovering are established, linearized and transformed into a state equation form. Various parameters are measured and calculated in other to obtain the stability derivatives in the state equation. Hovering flight controller is designed using the digital LQG/LTR(Linear Quadratic Gaussian/Loop Transfer Recovery) control theory. The designed controller is tested by the nonlinear simulations and implemented on an IBM-PC/386. Experiments were carried out on a model helicopter attached to the 3-DOF gimbal. The designed controller showed satisfactory hovering capability to maintain the hovering for more than 40 seconds.