• Title, Summary, Keyword: Propulsion performance

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Steady-State/Transient Performance Simulation of the Propulsion System for the Canard Rotor Wing UAV during Flight Mode Transition

  • Kong, Changduk;Kang, Myoungcheol;Ki, Jayoung
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.513-520
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    • 2004
  • A steady-state/transient performance simulation model was newly developed for the propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) during flight mode transition. The CRW type UAV has a new concept RPV (Remotely Piloted Vehicle) which can fly at two flight modes such as the take-off/landing and low speed forward flight mode using the rotary wing driven by engine bypass exhaust gas and the high speed forward flight mode using the stopped wing and main engine thrust. The propulsion system of the CRW type UAV consists of the main engine system and the duct system. The flight vehicle may generally select a proper type and specific engine with acceptable thrust level to meet the flight mission in the propulsion system design phase. In this study, a turbojet engine with one spool was selected by decision of the vehicle system designer, and the duct system is composed of main duct, rotor duct, master valve, rotor tip-jet nozzles, and variable area main nozzle. In order to establish the safe flight mode transition region of the propulsion system, steady-state and transient performance simulation should be needed. Using this simulation model, the optimal fuel flow schedules were obtained to keep the proper surge margin and the turbine inlet temperature limitation through steady-state and transient performance estimation. Furthermore, these analysis results will be used to the control optimization of the propulsion system, later. In the transient performance model, ICV (Inter-Component Volume) model was used. The performance analysis using the developed models was performed at various flight conditions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the turbine inlet temperature overshoot limitation as well as the compressor surge margin. Because the engine performance simulation results without the duct system were well agreed with the engine manufacturer's data and the analysis results using a commercial program, it was confirmed that the validity of the proposed performance model was verified. However, the propulsion system performance model including the duct system will be compared with experimental measuring data, later.

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Study of Cold Gas Propulsion System Utilizing Butane as Liquefied Propellant (부탄을 액화 연료로 사용한 냉가스 추진 시스템에 대한 연구)

  • Kang, Suk-Jin;Kwon, Ky-Beom;Cho, Dong-Hyun;Lee, Sang-Hyun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.4
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    • pp.323-328
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    • 2007
  • A direct application of liquefied gas propellants to a typical small satellite cold gas propulsion system was analyzed. Performance of systems using liquefied gas propellant under consideration was compared to that of a nitrogen cold gas propulsion system. Liquefied gas propellant propulsion system's performance, required tank volume, and required propulsion system mass has been calculated at the same mass, volume, and total impulse condition of a typical nitrogen cold gas propulsion system. It was found that the liquefied gas propulsion system has advantages in performance, volume, and mass, compared to a typical nitrogen cold gas system, and can be directly applied to a cold gas propulsion system.

In-Space Performance of "KAGUYA" Lunar Explorer Propulsion Subsystem

  • Masuda, Ideo;Goto, Daisuke;Kagawa, Hideshi;Kajiwara, Kenichi;Sasaki, Takeshi;Tamura, Masayuki;Takahashi, Mamoru;Kasuga, Kazuhito;Ikeda, Mizuho
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.407-412
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    • 2008
  • "KAGUYA"(SELENE) is a Japanese Lunar Explorer launched by H-IIA rocket from Tanegashima Space Center on 14 September 2007. The dual-mode bipropellant propulsion subsystem of KAGUYA includes two fuel tanks, an oxidizer tank, propellant and pressurant control components, twelve monopropellant 20N thrusters, eight monopropellant 1N thrusters, and a bipropellant 500N Orbit Maneuver Engine(OME). Once the KAGUYA separated from the rocket, it circled the Earth twice and traveled to the Moon, where it entered lunar orbit. All maneuvers were performed through multiple 500N OME/20N thruster firings. This paper describes the in-space performance of KAGUYA Lunar Explorer bipropellant propulsion subsystem.

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Study on the Propulsion System Integration Optimization for a Turboprop Aircraft (터보프롭 항공기 추진기관 시스템 종합 최적 설계 연구)

  • 공창덕;김진원
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.71-81
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    • 1995
  • The Propulsion System Integration can be defined as the optimization technology of combining the propulsion system components with the airframe to achieve the overall aircraft misson performance goals. The disposition of propulsion system components on engine compartment enveloped by front fuselage and fire bulkhead is very restricted because of the interference with nose L/G and engine mountig strut. The design of components depends on the traditional technical data base. The engine satisfying a customer's ROC was selected among worldwide existing engines by the comparision studies of performance analysis with enigine installed effect, future growth potential, ILS, and application to aircrafts, etc. The ground test of the propulsion system integration was performed in the test cell and on the aircraft to assure the function of the components. The flight test was performed to confirm complying the performance requirements.

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Effects of Manual Wheelchairs' Transmission on the Propulsion Motion (수동휠체어의 변속 기능이 추진 동작에 미치는 영향)

  • Shin, Eung-Soo
    • Korean Journal of Sport Biomechanics
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    • v.17 no.3
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    • pp.225-232
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    • 2007
  • This work intends to investigate the effects of shift characteristics on the propulsion performance of a manual wheelchair with an automatic transmission. A planetary gear train is employed to generate a two-stage shift automatically, based on the distance traveled from rest. Motion analysis has been performed for measuring kinematic properties of the arm and then the inverse dynamics has been applied for estimating joint forces/torques. Then, a parametric study has been performed to find a set of the shift ratios and the shift intervals for optimizing propulsion performance. Results show that the propulsion performance is closely related to the shift condition. It is found that a short shift interval is desirable for a short distance propulsion. However, an optimum shift interval for a long distance propulsion is inversely proportional to the shift ratio approximately. Consequently, the automatic transmission can greatly lower the joint loadings by the speed reduction, which eventually contribute to prevent joint injuries of wheelchair users.

Dynamic Performance Simulation of the Propulsion System for the CRW Type UAV Using $SIMULINK^{\circledR}$

  • Changduk Kong;Park, Jongha;Jayoung Ki
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.499-505
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    • 2004
  • A Propulsion System of the CRW(Canard Rotor Wing) type UAV(Unmanned Aerial Vehicle) was composed of the turbojet engine to generate the propulsive exhaust gas, and the duct system including straight bent ducts, tip-jet nozzles, a master valve and a variable main nozzle for three flight modes such as lift/landing mode, low speed transition flight mode and high speed forward flight mode. In this study, in order to operate safely the propulsion system, the dynamic Performance behavior of the system was modeled and simulated using the SIMULIN $K^{ }$, which is the user-friendly GUI type dynamic analysis tool provided by MATLA $B^{ }$. In the transient performance model, the inter-component volume model was used. The performance analysis using the developed models was performed at various flight condition, valve angle positions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the inlet temperature overshoot limitation as well as the compressor surge margin. Performance analysis results using the SIMULIN $K^{ }$ performance program were compared with them using the commercial program GSP.m GSP.

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Investigation on the Powering Performance Prediction for Azimuth Thrusters

  • Van, Suak-Ho;Yoon, Hyun-Se
    • Journal of Ship and Ocean Technology
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    • v.6 no.1
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    • pp.27-33
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    • 2002
  • Recently, the application of the electric propulsion system becomes popular because of its advantage over conventional propulsion. However, the complicated flow mechanism and interaction around the azimuth thruster are not fully understood yet, and the studies on the powering performance characteristics with azimuth/pod thrusters are now in progress. The experimental method developed in KRISO(Korea Research Institute of Ships & Ocean Engineering) is introduced and the results of the powering performance tests, consisting of resistance, self-propulsion and propeller open water tests for a cable layer with two azimuth thrusters are presented. For the analysis of powering performance with azimuth thrusters, it is necessary to evaluate the thrust/drag for components of a thruster unit, Extrapolation results could differ according to the various definitions of the propulsion unit; that is the pod, thruster leg and/or nozzle can be treated as hull appendages or as part of propulsion unit, The powering performances based on several definitions are investigated for this vessel. The results of the measurements for the 3-dimensional velocity distribution on the propeller plane are presented to understand the basis of the difference in propulsion characteristics due to the propeller rotational directions.

Flexible CFD meshing strategy for prediction of ship resistance and propulsion performance

  • Seo, Jeong-Hwa;Seol, Dong-Myung;Lee, Ju-Hyun;Rhee, Shin-Hyung
    • International Journal of Naval Architecture and Ocean Engineering
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    • v.2 no.3
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    • pp.139-145
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    • 2010
  • In the present study, we conducted resistance test, propeller open water test and self-propulsion test for a ship's resistance and propulsion performance, using computational fluid dynamics techniques, where a Reynolds-averaged Navier-Stokes equations solver was employed. For convenience of mesh generation, unstructured meshes were used in the bow and stern region of a ship, where the hull shape is formed of delicate curved surfaces. On the other hand, structured meshes were generated for the middle part of the hull and the rest of the domain, i.e., the region of relatively simple geometry. To facilitate the rotating propeller for propeller open water test and self-propulsion test, a sliding mesh technique was adopted. Free-surface effects were included by employing the volume of fluid method for multi-phase flows. The computational results were validated by comparing with the existing experimental data.

Comparison Study on the Propulsion Performance for Icebreaker with Synthetic ice and Refrigerated ice (합성얼음과 냉동얼음을 사용한 쇄빙선의 추진 성능 비교 연구)

  • Kim, Moon-Chan;Lim, Tae-Wook;Jo, Jun-Cheol;Chun, Ho-Hwan;Wang, Jung-Yong
    • Journal of Ocean Engineering and Technology
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    • v.23 no.1
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    • pp.129-134
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    • 2009
  • This paper reports on experimental investigations of self propulsion performance with synthetic (model) ice and refrigerated ice, which were conducted in a typical towing tank and ice tank, respectively. The main purpose of this research was to find the correlation between the selfpropulsion performance with synthetic ice in a typical towing tank and that with refrigerated ice in an ice tank. The different stresses between the synthetic ice and refrigerated ice influenced the self propulsion performance due to different ice and propeller interactions. A further study on the ice property variation for a self propulsion performance comparison is to be conducted in the near future.

The Performance Evaluation of C/SiC Composite for Rocket Propulsion Systems (추진기관용 C/SiC 복합재료의 특성 평가)

  • Kim, Yun-Chul
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.433-438
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    • 2009
  • The main objective of this research effort is to develop the performance of C/SiC composites manufactured by LSI (Liquid Silicon Infiltration) method for solid and liquid rocket propulsion system and ensure the performance analysis technique. The high performance and reliability of C/SiC composite are proved for solid and liquid rocket propulsion system. And the performance analysis technique related to mathematical ablation model is originated.

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