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Comparative Analysis of Different Grain Configurations for a Multi-thruster Kinetic Warhead
N. Ananthkrishnan,Hyun Ko,K. Sreesankar,R. Chakravarty,V.S. Renganathan 한국추진공학회 2016 한국추진공학회 학술대회논문집 Vol.2016 No.5
The S-DACS multi-thruster warhead consists of 4 divert and 6 attitude thrusters fed from a common gas generator. Successful S-DACS intercept requires careful selection of the internal ballistics (grain configuration, chamber pressure, etc.), the sensors (seeker range, guidance law, etc.) as well as the external ballistics and sizing (booster diameter, S-DACS release velocity, flight time, maneuverability, etc.). These requirements and constraints are inter-dependent making the S-DACS mission analysis and sizing a difficult task. This work explores the connections between the choice of S-DACS grain configuration and sizing with the chamber pressure as a key parameter. Various parameters and center of gravity/ moment of inertia variations are compared for three different S-DACS grain configurations. Keywords: DACS, grain configuration, mission analysis
Analysis of Thermal Choking in Arbitrary Duct with Application to Dual-mode Ramjet Combustor
N. Ananthkrishnan,P. Tarey,Hyun Ko,K. Gopinath,K. Sreesankar 한국추진공학회 2016 한국추진공학회 학술대회논문집 Vol.2016 No.5
Thermal choking is an important phenomenon in ram and scram combustors. A zero-dimensional model is used to analyze Rayleigh flows in real-life combustors that feature volume heat addition due to combustion, area variation, wall heat loss and frictional losses, as well as different fuel injection rates and mixing efficiency. The method is used to analyze the occurrence of thermal choking in a model scramjet combustor and in a realistic dual-mode combustor geometry.
Propulsion System Modeling and Control of a Warhead with Multi-thruster Configuration
Rajtilok Chakravarty,Nachiket Wadwankar,N. Ananthkrishnan,V.S. Renganathan,Hyun Ko,Ji-Hyung Lee 한국추진공학회 2013 한국추진공학회 학술대회논문집 Vol.2013 No.12
A novel internal pressure controller is developed for a Kinetic Energy Interceptor (KEI) equipped with a multi-thruster configuration. To that end, first the propulsion system model for solid fuel with a tubular grain burning configuration is detailed. Subsequently the internal pressure control logic design and implementation is laid out and a closed loop simulation is successfully demonstrated where varying chamber pressure is demanded and met by the controller by varying the thruster throat areas appropriately.
Chemical ablation of C-C/graphite nozzles in SRM environment
P. Tarey,H. S. Yang,N. Ananthkrishnan,D. S. Ha,J. H. Park 한국추진공학회 2016 한국추진공학회 학술대회논문집 Vol.2016 No.5
Chemical ablation in C-C/graphite rocket nozzles is an important but undesirable phenomenon. Numerical model using STAR CCM+, a commercial software is presented to predict the nozzle recession rate, taking into account the heterogeneous chemical kinetics and variable thermodynamic and transport properties. Coupled flow solver with Spalart-Allmaras turbulence closure is used. H2O was observed to be the major oxidizing agent followed by OH and CO2. The results were in good agreement with the existing experimental and numerical results.
변종열(Jong-Ryul Byun),안중기(Jungki Ahn),N. Ananthkrishnan 한국추진공학회 2017 한국추진공학회 학술대회논문집 Vol.2017 No.5
본 연구는 이중모드 스크램제트 엔진의 흡입구, isolator, 연소기, 노즐에서의 flowpath 유돟특성에 대한 해석적 연구결과이다. 이중모드 스크램제트 엔진의 설계와 성능을 파악하기 위해서는 공력, 열역학적 특성, 추진 그리고 전체 시스템에 대한 성능 모델과 해석 도구의 개발이 반드시 요구된다. 본 연구에서는 이중모드 스크램제트 엔진의 각 구성품인 흡입구, isolator, 연소기, 노즐에 대한 해석 모델을 정립하고, 개발된 해석 도구를 사용하여 이중모드 스크램제트 엔진의 성능특성을 파악해 보았다. This study is the results of the analytical research for a dual-model scramjet engine flowpath which is included inlet, isolator, combustor, and nozzle. To design a dual-mode scramjet engine and to investigate its performance, the performance analysis models and tools are required to develope for aerodynamic, thermodynamic characteristics, propulsion, and total system. Therefore, analysis models for air inlet, isolator, supersonic combustor, and nozzle of a dual-mode scramjet engine were accomplished, the performance characteristics of a dual-mode scramjet engine is investigated with using the developed analysis tools.