• Title/Summary/Keyword: KSR-III Rocket

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Spin-Stabilization for the Second Stage of Korea Sounding Rocket-III (KSR-III 탑재부 스핀안정화 기법 연구)

  • Sun, Byung-Chan;Choi, Hyung-Don
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.30 no.7
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    • pp.137-143
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    • 2002
  • This paper concerns the spin-stabilization for the second stage of KSR-III(Korea Sounding Rocket-III). The error sources in the second stage are defined, and then the effect on attitude error of KSR-III is analyzed quantitatively and qualitatively. Based on the analysis, some conditions for optimal spinning frequency and optimal steady-spinning duration are suggested. Among several solutions, an optimal value can be determined in the point of minimum impact-point error. An approach to a sub-optimal solution is also suggested. Application to the KSR-III shows that a proper spinning frequency and a steady-spin duration to give the smallest impact-point error can be effectively determined.

Vibration Loads on KSR-III during Ground Transportation and Handling (KSR-III 로켓의 도로운송 및 핸들링에 의한 진동하중)

  • Chun, Young-Doo;Cho, Byoung-Gyu
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2002.11a
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    • pp.330.2-330
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    • 2002
  • It is conducted to analyze vibration loads on KSR-III and its major segments during their ground transportation and various handling process. These loads may be different from the real flight environment. Inadequate assessment of these loads can cause not only local damages on the rocket system but also the critical problem like flight mission failure. Therefore, transportation and handling loads must be considered during design and attenuated to ensure that the rocket structural damage does not occur. (omitted)

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Design of the Fire Control System for KSR-III (KSR-III 발사 통제 시스템 설계)

  • Hong, I.H.;Seo, J.H.;Kim, Y.M.;Ryu, H.S.
    • Proceedings of the KIEE Conference
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    • 2000.11d
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    • pp.721-723
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    • 2000
  • 국내 과학관측 로켓(Korea Sounding Rocket-III; 이하 KSR-III) 발사통제 시스템 개발 중 로켓 임무 달성에 필요한 시스템 구성과 제작에 대한 전반적인 설계내용을 기술하였다. 로켓 임무와 설계 요구 조건에 의해 각 통제 콘솔과 발사 상황판은 설계되었고 현재 제작 중에 있으며. 향후 KSR-III 발사시험 시 활용 할 계획이다.

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Development of KSR-III Fire Control System (KSR-III 발사통제시스템 개발)

  • Hong, Il-Hee;Seo, Jin-Ho;Shin, Myoung-Ho
    • Proceedings of the KIEE Conference
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    • 2002.07d
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    • pp.2662-2664
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    • 2002
  • 액체추진 과학로켓으로 개발되고 있는 KSR-III(Korea Sounding Rocket-III)의 발사통제시스템의 개발에 관하여 기술하였다. 발사통제시스템은 장기간에 걸쳐 개발된 로켓을 발사시키는데 필수적인 시스템으로서 신뢰성과 강인성이 최대한 요구된다. KSR-III 발사통제시스템의 하드웨어는 콘솔, PLC, 신호분배기, DAS로 구성되어 있으며 소프트웨어로서 HMI 및 DAS 제어프로그램이 있다.

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Pogo Analysis on the KSR-III Propulsion Feeding System (KSR-III 추진기관 공급계 pogo 해석)

  • Lee H.J.;Jung T.K.;Menshikova O. M.;Jung Y.S.;Cho I.H.;Oh S.H.;Seo K.S.
    • Proceedings of the KSME Conference
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    • 2002.08a
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    • pp.495-498
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    • 2002
  • This article deals with the introduction of longitudinal instability of liquid rocket (pogo) and the analytical results on the frequency responses of KSR-III propulsion feeding system. Both the stiffness of bellows and the cavitation volume of venturi affect the frequency response of the feeding system. Especially, bellows has a great roll to reduce the natural frequency of the feeding system. Also, oxidizer and fuel feeding systems of the KSR-III have natural frequencies of ${\~}280Hz\;and\;{\~}90Hz$, respectively.

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Development of KSR-III Propulsion Feeding System (KSR-III 추진기관 공급계 개발)

  • 이대성;조인현;정태규;강선일;김용욱;정영석;권오성;정동호;오승협
    • Journal of the Korean Society of Propulsion Engineers
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    • v.6 no.4
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    • pp.37-45
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    • 2002
  • The development process of KSR-III propulsion feeding system is subscripted. The purpose of propulsion feeding system is to feed a certain amount of propellant from propellant tank to engine by the end of combustion. Pressure-fed liquid rocket, KSR-III has the unique characteristics of both pressure regulator and cavitation venturi as a passive flow control device. Main parameters of feeding system are confirmed by both water test and CFD(전산유체) technique. Flow control effect with venturi is confirmed by water test. Initial stabilization characteristic of pressure regulator is confirmed by real propellant test. And, to avoid the effect of resonance between rocket and feeding system, this article deal with POGO(포고) analysis to the feeding system.

Thermochemical Performance Analysis of Liquid Rocket Nozzle (액체로켓 노즐의 열화학적 성능 해석)

  • Choe,Jeong-Yeol;Choe,Hwan-Seok
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.31 no.1
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    • pp.85-96
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    • 2003
  • For a design of rocket engine nozzle, chemical equilibrium analysis which shares the same numerical characteristics with frozen flow analysis can be used as an efficient design tool for predicting maximum thermodynamic performance of the nozzle. 10 this study, a chemical equilibrium flow analysis code was developed for the design of hydrocarbon fueled rocket engines. 10 oder to understand the thermochemical characteristics occurring in a nozzle through the expansion process, such as recombination of chemical components and the accompanying energy recovery, chemical equilibrium flow analysis was carried out for the KSR-III rocket engine nozzles together with frozen flow and non-equilibrium flow analyses. The performance evaluation based on the present KSR-III nozzle flow analyses has provided an understanding of the thermochemical process in the nozzle and additionally, it has confirmed that the newly designed nozzle shape modified to have a reduced exit area ratio is an adequate design for obtaining an increased ground thrust.

A Study on the Cyclogram for the Firing Test of KSR-III Liquid Rocket Engine (KSR-III 주엔진 연소시험 Cyclogram에 대한 고찰)

  • 한영민;조남경;박성진;이수용;이대성
    • Journal of the Korean Society of Propulsion Engineers
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    • v.6 no.3
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    • pp.19-27
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    • 2002
  • The sequence of the propellant supply for ignition of a liquid rocket engine combustor is very important in the reliable and safe operation of the engine. The ignition sequence of KSR-III main engine was briefly described and the measuring parameters and their reliability determining ignition sequence were examined in this paper. The filling time of the engine propellant manifolds and the valve open/close time were reviewed to obtain the exact and reliable time of the propellant supply to the combustor. The combustion characteristics of the engine at starting were discussed at different supply lead of propellant. Finally, the hot firing test results with cyclogram determined by measuring parameters were presented.

Control System Modeling and Optimal Bending Filter Design for KSR-III First Stage (KSR-III 1단 자세제어 시스템 모델링 및 벤딩필터 최적 설계)

  • Ahn, Jae-Myung;Roh, Woong-Rae;Cho, Hyun-Chul;Park, Jeong-Joo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.30 no.7
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    • pp.113-122
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    • 2002
  • Control system modeling and optimal bending filter design for KSR-III (Korea Sounding Rocket III) are performed. Rigid rocket dynamics, aerodynamics, sloshing, structural bending, actuator dynamics, sensor dynamics and on-board computer characteristics are considered for control system modeling. Compensation for time-varying control system parameters is conducted by gain-scheduling. A filter to stabilize bending mode is designed using parameter optimization technique. Resultant attitude control system can satisfy required frequency domain stability margin.

DESIGN AND PRELIMINARY TEST RESULTS OF MAGNETOMETERS (MAG/AIM & SIM) FOR SOUNDING ROCKET KSR-III (KSR-III 과학 관측 로켓 자력계(MAG/AIM & SIM)의 초기 시험 모델 개발)

  • KIM HYO-MIN;JANG MIN-HWAN;SON DE-RAC;LEE DONG-HUN;KIM SUN-MI;HWANG SEUNG-HYUN
    • Publications of The Korean Astronomical Society
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    • v.15 no.spc2
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    • pp.57-64
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    • 2000
  • It is realized that the extraterrestrial matter is in ionized state, plasma, so the matter of this kind behaves as not expected because of its sensitiveness to electric and magnetic fields and its ability to carry electric currents. This kind of subtle change can be observed by an instrument for the magnetic field measurement, the magnetometer usually mounted on the rocket and the satellite, and based on the ground observatory. The magnetometer is a useful instrument for the spacecraft attitude control and the Earth's magnetic field measurements for the scientific purpose. In this paper, we present the preliminary design and the test results of the two onboard magnetometers of KARl's (Korea Aerospace Research Institute) sounding rocket, KSR­III, which will be launched during the period of 2001-02. The KSR-III magnetometers consist of the fluxgate magnetometer, MAG/AIM (Attitude Information Magnetometer) for acquiring the rocket flight attitude information, and of the search-coil magnetometer, MAG/SIM (Scientific Investigation Magnetometer) for the observation of the Earth's magnetic field fluctuations. With the MAG/AIM, the 3-axis attitude information can be acquired by the comparison of the resulting dc magnetic vector fields with the IGRF (International Geomagnetic Reference Field). The Earth's magnetic field fluctuations ranging from 10 to 1,000 Hz can also be observed with the MAG/SIM measurement.

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