• Title/Summary/Keyword: 추력조절기

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ATTITUED CONTROL BY ASYMMETRIC THRUSTERS’INDEPENDENT OFF MODULATION DURING ORBIT ADJUSTMENT MANEUVERS (궤도조절시 비대칭추력기 독립 비분사 조절에 의한 자세제어)

    • Journal of Astronomy and Space Sciences
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    • v.16 no.2
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    • pp.265-272
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    • 1999
  • A thrusters modulation method is suggested for spacecraft attitude control with asymmetric configured thrusters during orbit adjustment maneuvers. Attitude is controlled by thrusters off-modulation during orbit maneuvers. Usual control method for symmetric configured thrusters cam not be applied for asymmetric configured thrusters. Disturbance induced from thrusters asymmetricity shall be compensated during pulsing. In this paper, a thrusters control method using null solution is suggested, which is shown working well without inducing disturbance.

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Effect of Bore an Aerodynamic Loads in Modulatable Thrust Devices (노즐목 가변 추력기에서 Bore가 구동기의 공력하중에 미치는 영향)

  • Wang, Seung-Won;Huh, Hwan-Il
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.189-192
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    • 2011
  • In solid rockets, a pintle thruster is a modulatable thrust device which controlls nozzle throat area. In this study, effect of bore on aerodynamic loads in a SNECMA modulatable thruster was carried out. Existence of bore resulted in reduced aerodynamic load.

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Analysis of Heat Transfer considering thickness of Thermal Barrier Coating (열차폐 코팅 두께를 고려한 핀틀의 열전달 해석)

  • Jang, Han Na;Lee, Ji Hoon;Kwak, Jae Su;Cho, Jin Yeon;Kim, Jae Hoon;Ko, JunBok;Heo, Jun-Young
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.392-394
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    • 2017
  • In this study, the surface heat transfer coefficient of the 3D model of a thruster regulator in the high temperature and high pressure environment was estimated using the CFD. The thermal barrier coating (TBC) on the surface of the thruster regulator was modeled and the effect of the thickness of the TBC on the temperature of the thruster regulator was investigated. The thickness of the TBC was varied from $100{\mu}m$ to $500{\mu}m$. Results showed that the temperature of the surface and the inside the thruster regulator was lower for the thicker TBS case.

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Heat Transfer Characteristics of Thruster Controller According to Thickness of Thermal Barrier Coating (열차폐 코팅의 두께에 따른 추력 조절기의 열전달 특성 연구)

  • Jang, Han Na;Lee, Ji Hoon;Kwak, Jae Su;Cho, Jin Yeon;Kim, Jae Hoon;Ko, Jun Bok;Heo, Jun Young
    • Journal of Aerospace System Engineering
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    • v.11 no.4
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    • pp.15-21
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    • 2017
  • In this study, the surface heat transfer coefficient of the 3D model of a thruster regulator in the high temperature and high pressure environment was estimated using the commercial CFD code. The thermal barrier coating (TBC) on the surface of the thruster regulator was modeled and the effect of the thickness of the TBC on the temperature of the thruster regulator was investigated. The thickness of the TBC was varied from $100{\mu}m$ to $500{\mu}m$. Results showed that the temperature of the surface and the inside the thruster regulator was lower for the thicker TBC case.

Gain Scheduling Controller Design and Performance Evaluation for Thrust Control of Variable Thrust Solid Rocket Motor (가변 추력 고체추진기관의 추력 제어를 위한 이득 계획 제어기 설계 및 성능 분석)

  • Hong, SeokHyun
    • Journal of the Korean Society of Propulsion Engineers
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    • v.20 no.1
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    • pp.28-36
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    • 2016
  • Theoretical model of a variable thrust solid rocket motor with a pintle nozzle was derived. For the chamber pressure control, classical model linearization and proportional-intergral controller was used. And then two types of gain scheduling controller were suggested to imporve controller performance for the non-linear propulsion model. Considering characteristics of systems, control gains were scheduled by chamber pressure or free volume. Step responses of each controllers were compared. As a result, the proper control algorithm about characteristics of variable thrust rocket motor was suggested.

수격현상을 고려한 하이드라진 추력기 시스템 기초 설계 연구

  • 김병훈;조인현;나한비;최진철;하성업
    • Bulletin of the Korean Space Science Society
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    • 2004.04a
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    • pp.97-97
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    • 2004
  • 현재 KSLV-I에서 탑재부의 Pitch, Yaw, Roll의 3축 제어 및 2단부의 Roll 제어를 위해 사용되는 보조 추진 시스템은 구성이 단순하며, 신뢰성이 높은 것으로 알려져 있는 단일 추진제인 하이드라진을 이용하는 추진 시스템을 고려하고 있다. 이러한 하이드라진 추진 시스템은 추력실 전방에 설치되어 있는 추력기 밸브의 ON/OFF를 이용하여 추력을 조절하게 되는데, 이 때 추력기 밸브의 빠른 작동으로 인해 수격현상에 의한 급격한 압력 상승이 발생하게 되어 구조물의 손상을 발생하게 된다. (중략)

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Technology and Developing Trends of Pintle Injector for Throttleable Engine (가변추력 엔진용 핀틀 분사기 분석 및 개발동향)

  • Lee, Suji;Koo, Jaye;Yoon, Youngbin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.21 no.4
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    • pp.107-118
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    • 2017
  • As the interest in lunar exploration increases, a throttleable engine is regarded as a important technology. Variable area injectors have been identified to be the most reliable throttling method. Pintle injector is a representative injector of the variable method. It has a simple design and inherent combustion stability. Therefore, it is necessary to research the pintle injector. The present study investigates the concept of the injector, the design factors, and the latest development trends for pintle injector design.

Actuator and load test system development for continuous variable thruster (연속가변 추력기용 구동장치 및 부하시험장비 개발)

  • Kim, Namjin;Kim, Hyoungkwon;Park, Hyunho;Lim, Jinwan;Suh, Suhkhoon;Park, Iksoo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.401-405
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    • 2017
  • Continuous variable thrusters require precise thrust control to change the position or attitude of the aircraft and to control the pressure inside the combustion chamber. For this purpose, the thrust is adjusted by moving the pintle structure near the nozzle neck inside the combustion chamber by moving the pintle structure forward and backward, and the actuator is used to move the pintle structure. In this paper, we developed a actuator system for continuous variable thruster and load test system to simulate the load under operating conditions. Also, the performance test of the actuator was performed using the developed load test system

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Effect of Nozzle Contraction Angle on Performance of the SNECMA Modulatable Thrust Devices (노즐 수축각이 SNECMA 노즐목 가변 추력기 성능에 미치는 영향)

  • Wang, Seung-Won;Huh, Hwan-Il
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.14-17
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    • 2011
  • Numerical simulation was carried out for the SNECMA modulatable thrust devices, with four different nozzle contraction angle $45^{\circ}$, $60^{\circ}$, $83^{\circ}$, and $90^{\circ}$, respectively. Results show that $83^{\circ}$ nozzle contraction is better in that it comes up with good thrust level with small aerodynamic load.

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