• Journal of Aerospace System Engineering
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• v.2 no.1
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• pp.1-6
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• 2008

In this paper, full body modeling and analysis of nose and main landing gear's characteristics of a helicopter are performed using the dynamics analysis program ADAMS. Also, when land limiting about helicopter body's degree-of-freedom, compared the characteristics. In the case of helicopter, because there are a lot of dangerous missions under flight condition that is disadvantageous than fixed wing airplane, need more detailed research for a helicopter.

• Journal of Biosystems Engineering
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• v.31 no.2 s.115
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• pp.95-101
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• 2006

Present chemical application system using a power sprayer has been a labor intensive, ineffective and shirking task in farming. Therefore, a small RF controlled (unmanned) helicopter was suggested to replace the conventional spray system. The aerial application using the unmanned helicopter has been already utilized in Japan, where total area applied up to 704,000 ha in 2005. In this article, the status and cost analysis on the unmanned agricultural helicopter were studied. The aerial application using the agricultural helicopter helps precise and timely spraying and reduces labor intensity and pollution. The field capacity of the helicopter was found to be 60-70 ha a day. The break even point was estimated near the operating area of 750 ha annum. The development of an agricultural helicopter was necessary for taking advantages of both technique and economy.

• Journal of Biosystems Engineering
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• v.32 no.4
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• pp.230-236
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• 2007

In this study, a tail rotor system for an agricultural RF controlled helicopter was developed and tested. This study concluded the mechanical development of the 'Agro-heli' by completing the tail rotor system and its radio console. The RF control system was closely related with the tail system for the control of flying attitude. The thrust of the tail system balance off the reaction torque, created by the main rotor. Lifting tests with and without the tail system were compared for estimating the consumption of power. The tail system would use $4{\sim}5%$ of the total power which was in an acceptable range. Flying performance and attitude was visually inspected. It showed reliable and safe control during the distance flying trials and could be adapted for utilization in aerial applications. Aerial application using an RF controlled agricultural helicopter may make precise and timely spraying possible.

• Journal of Aerospace System Engineering
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• v.14 no.6
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• pp.10-17
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• 2020

The Korean medical evacuation helicopter was developed based on the Korean Utility Helicopter (hereafter referred to as 'Surion'). It uses an auxiliary power unit and engine for heating during winter operation. The helicopter maintains the internal temperature of the aircraft using its bleed air to satisfy its operational capability. However, due to the air inflow through the gap between the aircraft skin and door, additional heating for operating the portable medical equipment and preventing hypothermia in evacuated patients is required. Accordingly, an electric auxiliary heater was developed for additional heating during winter operation, and environmental, durability, and performance tests were conducted per MIL-STD-810G and MIL-STD-461F. The auxiliary heater was verified per the tailored airworthiness certification criteria.

• 제어로봇시스템학회:학술대회논문집
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• 1995.10a
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• pp.384-387
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• 1995

A helicopter is used in a variety of situations because of its usability. Its operation, needs human skill. The authors are working on automatization of human skill. Helicopter operation is one of such fields of practicing human skill. This is why the present paper deals with helicopter (model helicopter) operation. Full operation of a helicopter needs more complicated system in both aspects of software and hardware, and also requires more training for operation. From the purpose here that helicopter operation is for checking the applicability of the authors' idea for automatization based on experience, attitude regulation in hovering is the target. In the present paper, a human operator's operation is recorded as a time series of operation actions, and the record is reorganized as the correspondence between the helicopter's attitude and the proper operation action required in that particular situation.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2013.04a
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• pp.383-389
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• 2013

Rotor system is a very important part which produces lift, thrust and control force in helicopter. Component of rotor system must endure various flight load for the required life. In helicopter rotor system, bearingless rotor system is the highest technology rotor system compare with articulated and hingeless rotor system. Baaringless rotor system is not include mechanical flap hinge, lag hinge and pitch bearing. Bearingless rotor component flexbeam which made by composite material has conduct hinge and bearing role instead of mechanical flap hinge, lag hinge and pitch bearing. These characteristics has less part number and lass weight than others. In this paper, conduct safe life analysis of bearingless composite component flexbeam and torque tube applying to utility helicopter load condition.

• Journal of the Korea Institute of Military Science and Technology
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• v.17 no.4
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• pp.448-455
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• 2014

Virtual Fire Control System(VFCS) in attack helicopter is developed. VFCS is comprised of multifunction display, store management computer, mission computer, target acquisition and designation system, mission planning system, weapon simulator and flight simulator. Weapon engagement process under the operational environment of helicopter was considered by using the VFCS. We considered hellfire missile, tow missile, unguided rocket and turret gun. The results of this study will be utilized efficiently on integrated fire control system SIL(System Integration Lab.) in attack helicopter.

• Proceedings of the KIEE Conference
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• 1999.07b
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• pp.556-559
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• 1999

In this paper, the Observer Controller IDentification/Eigensystem Realization Algorithm(OCID/ERA) is applied to identify the state space model of a helicopter in hover from a given set of the general input-output data. The objective of this paper is the evaluation of the utility of the OCID/ERA approach to the system identification of a system which has natural unstable mode like a helicopter and to give some guidelines before applying the technique to the real system. As it mentioned above, since a model helicopter is unstable naturally, the closed-loop system identification method(OCID/ERA) using excitation, output and feedback signals of the simulated system is applied.

• Proceedings of the Korean Institute of Intelligent Systems Conference
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• 2001.05a
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• pp.144-147
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• 2001

This paper presents adaptive fuzzy controller which is uncertainty or unknown variation in different parameters with nonlinear system of helicopter. The proposed adaptive fuzzy controller applied TSK(Takagi-Sugeno-Kang) fuzzy system which is not only low number of fuzzy rule, and a linear input-output equation with a constant term, but also can represent a large class of nonlinear system with good accuracy. The adaptive law was designed by using Lyapunov stability theory. The adaptive fuzzy controller is a model reference adaptive controller which can adjust the parameter $\theta$ so that the plant output tracks the reference model output. First of all, system of helicopter was considered as stopping state, and design of controller was simulated from dynamics equation with stopping state. Results show that it is controlled more successfully with a model reference adaptive controller than with a non-adaptive fuzzy controller when there is a modelling error between system and model or a continuous added noise in such unstable system.

• Journal of Biosystems Engineering
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• v.31 no.3 s.116
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• pp.182-187
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• 2006

Aerial application using an unmanned agricultural helicopter can reduce labor and pollution. The development of an agricultural helicopter became urgent for both precise and timely spraying. In this study, a rotor system for unmanned helicopter capable of 20 $kg_f$ payload, was developed and lift capability was evaluated. A lift force over the dead weight of the helicopter was obtained at the pitch angle of $6^{\circ}$. As the pitch angle increased to $8^{\circ}\;and\;10^{\circ}$, the total lift increased to $74{\sim}81\;kg_f\;and\;86{\sim}93\;kg_f$, respectively. A range of engine speed at the rated flight condition, lifting mean payload of 23 $kg_f$ was determined. The data acquired from this study will be used for designing tail system and RF console in the next stage of the research. The rated lift capability was enough for loading 20 liters of spray material including spraying equipments.