• Title/Summary/Keyword: Aircraft Installation

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Performance Evaluation of Hypersonic Turbojet Experimental Aircraft Using Integrated Numerical Simulation with Pre-cooled Turbojet Engine

  • Miyamoto, Hidemasa;Matsuo, Akiko;Kojima, Takayuki;Taguchi, Hideyuki
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.03a
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    • pp.671-679
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    • 2008
  • The effect of Pre-cooled Turbojet Engine installation and nozzle exhaust jet on Hypersonic Turbojet EXperimental aircraft(HYTEX aircraft) were investigated by three-dimensional numerical analyses to obtain aerodynamic characteristics of the aircraft during its in-flight condition. First, simulations of wind tunnel experiment using small scale model of the aircraft with and without the rectangular duct reproducing engine was performed at M=5.1 condition in order to validate the calculation code. Here, good agreements with experimental data were obtained regarding centerline wall pressures on the aircraft and aerodynamic coefficients of forces and moments acting on the aircraft. Next, full scale integrated analysis of the aircraft and the engine were conducted for flight Mach numbers of M=5.0, 4.0, 3.5, 3.0, and 2.0. Increasing the angle of attack $\alpha$ of the aircraft in M=5.0 flight increased the mass flow rate of the air captured at the intake due to pre-compression effect of the nose shockwave, also increasing the thrust obtained at the engine plug nozzle. Sufficient thrust for acceleration were obtained at $\alpha=3$ and 5 degrees. Increase of flight Mach number at $\alpha=0$ degrees resulted in decrease of mass flow rate captured at the engine intake, and thus decrease in thrust at the nozzle. The thrust was sufficient for acceleration at M=3.5 and lower cases. Lift force on the aircraft was increased by the integration of engine on the aircraft for all varying angles of attack or flight Mach numbers. However, the slope of lift increase when increasing flight Mach number showed decrease as flight Mach number reach to M=5.0, due to the separation shockwave at the upper surface of the aircraft. Pitch moment of the aircraft was not affected by the installation of the engines for all angles of attack at M=5.0 condition. In low Mach number cases at $\alpha=0$ degrees, installation of the engines increased the pitch moment compared to no engine configuration. Installation of the engines increased the frictional drag on the aircraft, and its percentage to the total drag ranged between 30-50% for varying angle of attack in M=5.0 flight.

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Propulsion System Modeling and Reduction for Conceptual Truss-Braced Wing Aircraft Design

  • Lee, Kyunghoon;Nam, Taewoo;Kang, Shinseong
    • International Journal of Aeronautical and Space Sciences
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    • v.18 no.4
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    • pp.651-661
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    • 2017
  • A truss-braced wing (TBW) aircraft has recently received increasing attention due to higher aerodynamic efficiency compared to conventional cantilever wing aircraft. For conceptual TBW aircraft design, we developed a propulsion-and-airframe integrated design environment by replacing a semi-empirical turbofan engine model with a thermodynamic cycle-based one built upon the numerical propulsion system simulation (NPSS). The constructed NPSS model benefitted TBW aircraft design study, as it could handle engine installation effects influencing engine fuel efficiency. The NPSS model also contributed to broadening TBW aircraft design space, for it provided turbofan engine design variables involving a technology factor reflecting progress in propulsion technology. To effectively consolidate the NPSS propulsion model with the TBW airframe model, we devised a rapid, approximate substitute of the NPSS model by reduced-order modeling (ROM) to resolve difficulties in model integration. In addition, we formed an artificial neural network (ANN) that associates engine component attributes evaluated by object-oriented weight analysis of turbine engine (WATE++) with engine design variables to determine engine weight and size, both of which bring together the propulsion and airframe system models. Through propulsion-andairframe design space exploration, we optimized TBW aircraft design for fuel saving and revealed that a simple engine model neglecting engine installation effects may overestimate TBW aircraft performance.

Aircraft Fuel Efficiency Improvement and Effect through APMS (APMS 활용을 통한 항공기 연비향상 및 기대효과 )

  • Jae Leame Yoo
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.31 no.2
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    • pp.81-88
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    • 2023
  • SHM (Structural Health Monitoring) technique for monitoring aircraft structural health and damage, EHM (Engine Health Monitoring) for monitoring aircraft engine performance, and APM (Application Performance Management) is used for each function. APMS (Airplane Performance Monitoring System) is a program that comprehensively applies these techniques to identify the difference between the performance manual provided by the manufacturer and the actual fuel mileage of the aircraft and reflect it in the flight plan. The main purpose of using APMS is to understand the performance of each aircraft, to plan and execute flights in an optimal way, and consequently to reduce fuel consumption. First, it is to check the fuel efficiency trend of each aircraft, check the correlation between the maintenance work performed and the fuel mileage, find the cause of the fuel mileage increase/decrease, and take appropriate measures in response. Second, it is to find the cause of fuel mileage degradation in detail by checking the trends by engine performance and fuselage drag effect. Third, the APMS is to be used in making maintenance work decisions. Through APMS, aircraft with below average fuel mileage are identified, the cause of fuel mileage degradation is identified, and appropriate corrective actions are determined. Fourth, APMS data is used to analyze the economic analysis of equipment installation investment. The cost can be easily calculated as the equipment installation cost, but the benefit is fuel efficiency improvement, and the only way to check this is the manufacturer's theory. Therefore, verifying the effect after installation and verifying the economic analysis is to secure the appropriateness of the investment. Through this, proper investment in fuel efficiency improvement equipment will be made, and fuel efficiency will be improved.

Modification and Installation Design of Airframe Structures for Performance Improved Aircraft (성능개량 항공기의 기체구조물 개조 및 장착설계)

  • Dae Han Bang;Hyeon Seok Lee;Min Soo Lee;Min Ho Lee;Jae Man Lee
    • Journal of Aerospace System Engineering
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    • v.17 no.4
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    • pp.87-94
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    • 2023
  • This paper addresses the installation and modification design of airframe structures for new and modified equipment installations that are essential for aircraft performance improvement. Typical performance improvement equipment mounted on the exterior of the aircraft include antenna, radar, electro-optical/infrared (EO/IR), and self-protection system equipment, which require structural reinforcement, modification, and mounting design of the green aircraft for operation. In the interior of the aircraft, console and rack structures are modified or added according to user operation requirements. In addition, this is accompanied by the installation design of equipment to be replaced and added for performance improvement, and the according modification of environmental control system components for internal cooling. The engineering process and cases in which airworthiness was verified through the detailed design of airframe structures with structural integrity, operability, and maintainability of performance-improved aircraft are presented.

A Case Study on Collaborative Activities for Newly Installation of an Engine in a Helicopter (헬기 엔진의 신규장착을 위한 지원 사례 연구)

  • Ahn, Ieeki;Kim, Jae-Hwan;Sung, Oksuk
    • Journal of Aerospace System Engineering
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    • v.8 no.2
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    • pp.27-32
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    • 2014
  • From the flight safety and the performance point of views, a new engine installation impacts an helicopter development or upgrade program significantly. More than a close relationship between an aircraft manufacturer and an engine manufacturer is necessary for the best integration work from the program initiation phase. In this paper, technical cooperation between aircraft and engine companies, and technical supports by the engine manufacturer for the T700/701K engine during the Surion development program are summarized. The applications of official technical program documents, US Mil-spec, France airworthiness regulations as the standard of the engine installation work, and engineering activities at each phase such as contract, design and manufacturing, flight clearance, ground and flight tests are described. This paper would be a cornerstone for the future domestic helicopter development program.

Structural Analysis for Newly Installed Blade Antenna of Rotorcraft (신규 블레이드 안테나 장착을 위한 노후 회전익 항공기 구조 해석 연구)

  • Yu, Jeong-O;Kim, Jae-Yong;Choi, Hang-Suk
    • Journal of Aerospace System Engineering
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    • v.15 no.5
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    • pp.106-112
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    • 2021
  • In this study, we performed a design and structural analysis of a blade-shaped antenna installation on the rear fuselage of a rotary wing aircraft operated by the military. When the structure is damaged while the aircraft is in operation, it is separated from the aircraft main structure and may collide with the rotor or blades to cause the aircraft to crash. Therefore, structural safety for the modified structure must be secured. The design requirement for the newly installed modified part were established, and the load condition was constructed by applying the load that may occur in the aircraft after the modification. Structure safety for the modified structure was secured by performing structure analysis. To analysis stress and deformation of aircraft structure, we developed finite element model and verified it by using hand calculation method. We confirmed the safety of the modified structure through the final structural integrity analysis.

The Effect of an Installation Angle of IMFP sensors on Estimation of Altitude of T-50 Aircraft in the Transonic Region (IMFP 장착각도가 T-50 초음속 고도정보에 미치는 영향)

  • Nam, Yong-seog;Kim, Yeon-hi;Song, Seok-bong;Kim, Seong-jun
    • Journal of Aerospace System Engineering
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    • v.3 no.1
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    • pp.1-5
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    • 2009
  • The flight control of the T-50 advanced trainer is conducted by the digital FBW (Flight-by-Wire) control system. The system input data consist of flight conditions such as altitude, airspeed, and angle of attack. And the flight conditions of the aircraft are obtained from IMFP (Integrated Multi-Function Probe). The T-50 aircraft equip three IMFP sensors. To ensure reliability in flight condition data obtained from each IMFP sensor, the mean value of flight conditions is used as the input of the control system. In this study, the effect of an installation angle of IMFP sensors on estimation of flight altitude was investigated by flight test results in the supersonic region.

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Verification of Winglet Effect and Economic Analysis Using Actual Flight of A321 Sharklet Model (A321 Sharklet 모델의 운항실적을 이용한 윙렛 장착 효과 검증 및 경제성 분석)

  • Jang, Sungwoo;Lee, Youngjae;Kim, Kangwook;Yoo, Jae Leame;Yoo, Kwang Eui
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.49 no.4
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    • pp.273-279
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    • 2021
  • Winglets are specialized wingtip devices to reduce induced drag, and they have been installed on Boeing-made aircraft since the 1980s, Airbus has also developed a winglet named 'Sharklet' since 2009 and has started providing them as an option to the A320 Family. The winglet has the effect of improving take-off performance, reducing fuel consumption, increasing payload, and increasing flight distance by reducing the induced drag generated at the tip of the wing. The purpose of this study is to analyze the actual flight data of the sharklet-installed and non-sharklet-installed models of the A321 aircraft to verify the fuel efficiency improvement due to the winglet installation, and to analyze the economic analysis accordingly. Through this, it can be used to determine the winglet installation when introducing an aircraft or to make a decision for upgrading the existing aircraft. To this end, a case study on the aerodynamic characteristics and effects of the winglet installation was conducted, and the economic analysis was verified.

Propulsion Installation Design on Wing-Mounted-Nacelle Type (주익장착방식의 추진기관 장착설계)

  • 진광석;최광윤;공창덕
    • Journal of the Korean Society of Propulsion Engineers
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    • v.2 no.1
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    • pp.88-94
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    • 1998
  • Installation design methods and results of an aircraft engine on the wing-mounted-nacelle type aircraft has been presented in this paper. The design process starts from design requirements and constraints and covers some major aspects of the engine installation design such as wing-nacelle interference drag, roll clearance, ground clearance, nose gear collapse margin, rotor burst and fuel tank capacity. The method was applied to 100-seat class airplane(K100). Results of the design suggest optimum nacelle location and nacelle installation angle(toe-in, incidence, droop angle) which satisfies in stalled engine performance and size/location of wing dry day.

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항공기용 타이어의 기술표준품 형식승인에 대한 연구

  • Park, Guen-Young;Lee, Kang-Yi;Jin, Young-Kwon
    • Aerospace Engineering and Technology
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    • v.4 no.2
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    • pp.236-243
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    • 2005
  • Civil aircraft tires require a certification according to the Technical Standard Order Authorization(TSOA) procedure. TSO-C62d contains minimum performance standards for aircraft tires. The TSOA covers design and manufacturing of the tire only. To install a TSO article on aircraft requires an installation approval. In this paper, TSOA procedure and the certification requirements for aircraft tires will be presented.

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