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공중모의비행시험기 개조개발 위험도 분석 및 감항인증 연구
고준수,안종민,Ko, Joon Soo,Ahn, Jong Min 한국군사과학기술학회 2013 한국군사과학기술학회지 Vol.16 No.2
Airworthiness certification is a government certification for the military aircraft to safely attain, sustain and terminate flight and It is a mandatory process of qualifying the flight safety within the operational boundaries of a military aircraft. To save the manhour, time and cost for applying all the airworthiness certification criteria to the aircraft equipped with flight control switching mechanism development program, an identification of the risk and systematic assessment of risk is analysed. Airworthiness redesign actions so called software switching mechanism for the modified aircraft in the flight technology and electric system area are suggested to reduce the risk hazard index.
고준수,Ko, Joon Soo 한국항공운항학회 2013 한국항공운항학회지 Vol.21 No.4
Airworthiness certification is a repeatable process implemented to verify that a specific aircraft can be safely maintained and operated within its approved flight envelope. Airworthiness certification activity for the FA-50 aircraft has been performed according to the Airworthiness Certification Criteria, issued in 2011 by DAPA. It is a right time to study the application of those existing ACC process and tools to the hypothetical modification aircraft. This paper describes airworthiness engineers view of the integrated activities required to substantiate the modified aircraft performance. The compliance methods applicable to the airworthiness certification criteria is also suggested. It will be useful for the establishment of the future Korea modified military aircraft's ACC with the risk assessment and methods of compliances tailored to the legacy aircraft.
고준수,김경목,Ko, Joon Soo,Kim, Kyungmok 항공우주시스템공학회 2016 항공우주시스템공학회지 Vol.10 No.2
Multi disciplinary approach for aerodynamics, structure, propulsion, and flight control system is necessary to develop High Altitude Long Endurance Unmanned Aerial Vehicles (HALE UAV). Various HALE UAV development trends are surveyed to understand their operational requirements. Separating the UAV Take Off Weight by 150kg, Airworthiness implementation direction for HALE UAV is studied under the current Airworthiness regulations. NATO STANAG 4671 and STANAG 4703 Airworthiness certification criteria are analyzed, and their applicability was proposed for future HALE UAV development. In addition, minimization of the risk for UAV is studied by considering probability of cumulative catastrophic failure for HALE UAV. This Hazard Risk Index can support the future UAV Airworthiness Certification Criteria.
고준수,안종민,박성수,Ko, Joon-Soo,Ahn, Jong-Min,Park, Sung-Su 한국군사과학기술학회 2011 한국군사과학기술학회지 Vol.14 No.6
This paper presented here contains development of variable stability system(VSS) control laws for the KIFS (Korean In-Flight Simulator) aircraft to simulate the dynamics of F-16 aircraft. Development of VSS Control law for pitch rate, roll rate, yaw rate simulation for three specified flight conditions using Model Following Technique with rate feedback autopilot for stability provision. The direct lift force controller was also added to the developed VSS control law to simulate the pitch rate and normal g-load simultaneously. The simulation results show high accuracy of F-16 aircraft's pitch, roll, yaw rate and g-load simulation.
고준수,박성수,김경목,Ko, Joon Soo,Park, Sungsu,Kim, Kyungmok 한국항공운항학회 2015 한국항공운항학회지 Vol.23 No.2
This paper presents the algorithm for envelope protection of helicopters. The algorithm consists of two feedback control loops: inner loop and outer loop. As an inner loop control, model following control is designed to meet the ADS-33 handling qualities specification by minimizing the tracking errors between the responses of the actual model and those of the command filter. In order to implement envelope protection, saturation limiter is imposed to command channels in command filter, whose limits are computed corresponding to the envelope limit. Fast model predictive control is designed as an outer loop control to deal with saturation constraints generated by the inner loop envelope protection and also imposed by outer loop envelope protection variables. Simulation results show that the proposed algorithm yields good envelope protection performance.