• Title, Summary, Keyword: Solid propellant

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Design of a Microthruster using Laser-Sustained Solid Propellant Combustion

  • Kakami, Akira;Masaki, Shinichiro;Horisawa, Hideyuki;Tachibana, Takeshi
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.605-610
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    • 2004
  • Solid propellants allow thrusters to be light-weight, com-pact and robust because they require neither tank nor valve, Moreover, the solid propellant will not leak, spill or slosh. Consequently, the solid propellant thruster is one of the potential candidates for the microthruster. On the other hand, the control of the solid propellant combustion is difficult, since the conventional solid propellant continues to bum until all the stored propellant is consumed. Although particular devices like thrust reverser were designed to control the combustion, these devices were rarely used in the practical rocket motors. These devices rise thruster weight as well as complicate the thruster operation. In this study, a solid propellant microthruster using laser sustained combustion was designed in order to develop a high-efficiency microthruster overcoming the previously-mentioned difficulty. This designed thruster has semiconductor lasers and non-self-combustible solid propellants in addition to the conventional solid propellant thruster. In this designed thruster, the semiconductor laser controls the combustion of the non-self-combustible solid propellant. In order to demonstrate that the solid propellant combustion is controllable with laser, some non-self-combustible solid propellants were irradiated with the laser at a back-pressure of about 1㎪. A 40-W class Neodymium Yttrium Aluminum Garnet (ND:YAG) laser was used as a tentative alternate to the semiconductor laser. This experiment has shown that the solid propellant combustion was controllable with 10- W class laser irradiation.

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Development of Components in Micro Solid Propellant Thruster. (마이크로 고체 추진제 추력기의 요소 개발)

  • 이종광;이대훈;권세진
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.147-150
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    • 2003
  • The purpose of this research was to develope components of micro solid propellant thruster. Micro solid propellant thruster had four basic components: combustion chamber, nozzle, solid propellant and micro heater for ignition. A performance of micro heater and characteristic of solid propellant was investigated. Micro heater was fabricated by conventional MEMS process and Platinum layer was used for heating element. Effect of geometry parameters on micro heater was tested. The temperature responses of heater with respect to each parameters was compared for a given electrical power. The characteristic of solid propellant(HTPB/AP) was investigated to obtain burning velocity in small chamber. Additionally, a capacity of filling propellant with high viscosity in small chamber was checked to guarantee for the micro fabrication.

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Performance Evaluation of Components of Micro Solid Propellant Thruster (마이크로 고체 추진제 추력기 요소의 성능 평가)

  • Lee, Jong-Kwang;Lee, Dae-Hoon;Kwon, Se-Jin
    • Proceedings of the KSME Conference
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    • pp.1280-1285
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    • 2004
  • Microsystem technology has been applied to space technology and became one of the enabling technology by which low cost and high efficiency are achievable. Micro propulsion system is a key technology in the miniature satellite because micro satellite requires very small and precise thrust force for maneuvering and attitude control. In this paper research on micro solid propellant thruster is reported. Micro solid propellant thruster has four basic components; micro combustion chamber, micro nozzle, solid propellant and micro igniter. In this research igniter, solid propellant and combustion chamber are focused. Micro igniter was fabricated through typical micromachining and evaluated. The characteristic of solid propellant was investigated to observe burning characteristic and to obtain burning velocity. Change of thrust force and the amount of energy loss following scale down at micro combustion chamber were estimated by numerical simulation based on empirical data and through the calculation normalized specific impulses were compared to figure out the efficiency of combustion chamber.

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Performance Evaluation of Components of Micro Solid Propellant Thruster (마이크로 고체 추진제 추력기 요소의 성능 평가)

  • Lee Jongkwang;Lee Dae Hoon;Choi Sunghan;Kwon Sejin
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.28 no.10
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    • pp.1264-1270
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    • 2004
  • In this paper research on micro solid propellant thruster is reported. Micro solid propellant thruster has four basic components; micro combustion chamber, micro nozzle, solid propellant and micro igniter. In this research igniter, solid propellant and combustion chamber are focused. Micro igniter was fabricated through typical micromachining and the effect of geometry was evaluated. The characteristic of solid propellant was investigated to observe burning characteristic and to obtain burning velocity. Change of thrust force and the amount of energy loss following scale down at micro combustion chamber were estimated by numerical simulation based on empirical data and through the calculation normalized specific impulses were compared to figure out the efficiency of combustion chamber.

Fabrication method and performance evaluation of components of micro solid propellant thruster (마이크로 고체 추진제 추력기 요소의 가공 방법 및 성능 평가)

  • Lee, Jong-Kwang;Park, Jong-Ik;Kwon, Se-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.225-228
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    • 2007
  • Micro solid propellant thruster is the most feasible for development with current MEMS. Basic components of micro solid propellant thruster are diverging nozzle, micro igniter, combustion chamber, and solid propellant. Micro nozzles and micro chambers were fabricated using photosensitive glass by anisotropic wet etching technique. Micro Pt heaters on glass membrane which ignited solid propellant were developed. Components of thruster were integrated. Successful ignition was observed.

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Design, Fabrication and Testing of Planar Type of Micro Solid Propellant Thruster (평판형 마이크로 고체 추진제 추력기의 설계, 제작 및 평가)

  • Lee, Jong-Kwang;Kwon, Se-Jin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.10 no.4
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    • pp.77-84
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    • 2006
  • With the development of micro/nano spacecraft, concepts of micro propulsion are introduced for orbit transfer and drag compensation as well as attitude control. Micro solid propellant thruster has been attention as one of possible solution for micro thruster. In this paper, micro solid propellant thruster is introduced and research on basic components of a micro solid propellant thruster is reported. Micro Pt igniter was fabricated through negative patterning and quantitative effect of geometry was estimated. The characteristic of HTPB/AP solid propellant was investigated to measure the homing velocity. A combustion chamber was fabricated by means of anisotropic etching of photosensitive glass. Finally, micro solid propellant thrusters having various geometries were fabricated and tested.

The Study of Solid Propellant to Reduce Infrared Signature (적외선(IR, Infrared) 신호가 감소된 고체추진제 개발)

  • Lee, Jongseop;Yim, Yoojin;Park, Euiyong;Han, Houkseop
    • Journal of Aerospace System Engineering
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    • v.7 no.4
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    • pp.42-48
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    • 2013
  • In this paper, a study of solid rocket propellant formulation is performed to suppress plume and reduce IR(infrared) signature which occurs in propellant combustion. The solid propellant to enhance the stealthy ability was formulated in terms of the kinds and the effects of afterburning suppressant on the ballistic performance and the amount of primary smoke. In addition, substantial decrease in plume and IR signature is confirmed by static firing test by a 4 inch standard motor.

Experimental Study on the Extinction Characteristics of the Solid Properllant (고체 추진제어의 소화특성 연구)

  • Hwang Yong Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.8 no.3
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    • pp.61-67
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    • 2004
  • The extinction characteristics of the solid propellant were studied experimentally in this paper. These characteristics are required for designing TCO (thrust cut off) system of the solid rocket motor Parameters to characterize solid propellant extinction were defined by physical observation. A device was designed (or acquiring these parameters and the firing tests were implemented to get the preliminary data for the extinction characteristics of HTBP propellant.

ALE-BASED FSI SIMULATION OF SOLID PROPELLANT ROCKET INTERIOR (ALE 기반의 고체 로켓 내부 유체-구조 연동 해석)

  • Han, Sang-Ho;Min, Dae-Ho;Kim, Chong-Am
    • 한국전산유체공학회:학술대회논문집
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    • pp.71-77
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    • 2010
  • As a hybrid model of continuum motion description which combines the advantages of classical kinematical descriptions i.e. Lagrangian and Eulerian description, the ALE (Arbitrary Lagrangian Eulerian) description is adopted for the simulation of a fluid-structure interaction of solid propellant rocket interior. The fluid-structure interaction phenomenon with the deformation of solid domain during the simulation. The developed solver is applied flow and propellant structure. The computed results show complex flow physics in the combustion chamber and the behavior of a solid propellant deformation.

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An Ultrasonic Measurement Model to Predict a Reflected Signal from Non-Linear Burning Surface of Solid Propellants

  • Song, Sung-Jin;Kim, Hak-Joon;Oh, Hyun-Taek;Lee, Sang-Won;Song, Seung-Hyun;Kim, In-Chul;Yoo, Ji-Chang;Jung, Jung-Yong
    • Journal of the Korean Society for Nondestructive Testing
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    • v.27 no.6
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    • pp.531-540
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    • 2007
  • While determination of the solid propellant burning rates by ultrasound, it has been reported that the frequent data scatters were caused by two major factors; 1) variation in the acoustical properties, and 2) non-linear burning of a solid propellant sample under investigation. This work is carried out for the purpose of investigating the effect of non-linear burning of solid propellant samples. Specifically, we propose an ultrasonic measurement model that can predict the reflections from solid propellant surfaces with non-linear burning by the combination of two ingredients; 1) a pulse-echo ultrasonic measurement model for a planar, circular reflector imbedded in the second medium in an immersion set-up, and 2) an efficient model of non-linear burning surfaces with a number of small, planar circles. Then, we demonstrate the capability of the proposed measurement model by simulation of the surface echo signals from four different burning surfaces that have been generated by the combination of two factors; the base shape (flat or paraboloidal) and the surface roughness (perfectly smooth or randomly rough). From the simulation presented here, we can confirm the fact that the non-linear burning of the propellant can cause the waveform change of the burning surface echo and the corresponding spectrum variation.