• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.4
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• pp.18-25
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• 2011

Solid propulsion systems have simple structures compared to other propulsion systems and are suitable for long-term storage. However the systems generally have limits on control of thrust levels. In this paper we suggest control algorithms for combustion chamber pressure of variable thrust solid propulsion systems using special nozzles such as pintle valve. For the pressure control within the chamber, we use a simple pressure change model by considering only mass conservation within the combustion chamber, design a classical algorithm and also a nonlinear controller using the feedback linearization technique. Also we derive the equation of the thrust for an under-expanded one-dimensional nozzle and then design a proportional-intergral controller after linearizing the thrust model for an operating point. Finally, we demonstrate the performance of the controller through a numerical simulation.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.4
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• pp.73-78
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• 2020

The main reasons that ignite the propellant in the process of producing solid rocket motor are worker mistakes, wrong working process, mechanical defects, impact, friction, electrostatic and short circuits. In the past decades, many accidents have occurred in the process of producing solid rocket motor, accidents investigation have confirmed that the sensitivity of electrostatic is very high under specific condition. In this paper, we analyzed overseas accident cases and measured the sensitivity of electrostatic in the situation of confinement and pressure load by considering the manufacturing process. As a result of the test, the sensitivity of propellant was increased in the situation of confinement and pressure load and the propellant reacted more sensitively to electrostatic in the situation of confinement than pressure load.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.197-200
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• 2007

This paper presents solid propulsion manufacturing processes. Solid rocket motors propellants are made of several batches of propellant being mixed in mixers and made of continuous mixers. This paper discusses the technology of continuous mix process of Aerojet, US and SNPE Materiaux Energetiques, France.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.528-531
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• 2004

For a simple one-dimensional ignition problem a mathematical model is described to investigate the difficulties in numerical simulations. Some computation results are obtained and comparison is made with analytical solution. Discussions are made on topics such as 1) coordinate transformation, 2) gas-phase and solid-phase analysis; (divergence form of the governing system, a finite-volume discretization, implicit time integration, upwind split flux, spatial accuracy improvement are described. Mass, reagent mass, and energy conservations are solved.), and 3) method to determine quantities on the burning surface (matching). Results obtained for small values of the non-dimensional pressure show a steady-combustion and good agreement with the analytical solution. Numerical instability appeared for larger values of the pressure, discussion on the cause of the problem is made. This effort is a part of a study of flame spread phenomena on solid propellant surface.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1995.11a
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• pp.3-8
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• 1995

An experimental investigation was conducted in order to figure out the multiple fire effects on the combustion efficiency and fuel properties of the solid fuel ramjet. Pure HTPB and metallized $B_4$C/HTPB fuel were studied. Fuel property effects were analyzed by using differential scanning calorimetry, The thermal or mechanical properties of the fuel grain were not affected and the combustion efficiency was a little increased.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.1-1
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• 2005

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.1
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• pp.76-81
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• 2009

A nonlinear pressure controller to actively regulate the thrust of a solid propulsion system is presented. To compensate for the parametric uncertainties with respect to the chamber pressure induced by changing nozzle throat area, Lyapunov-based parameter adaptation method has been applied. In order to verify the effectiveness of the proposed control method, the experiments were carried out using the cold gas test equipment that can simulate the operating environment of variable thrust solid propulsion system. The experiment results show that the nonlinear pressure controller has better performance than conventional P and PI controller.

• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.2
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• pp.26-31
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• 2017

Environmental problem of the solid propellants is an issue of growing importance in solid rocket. For examples, ammonium perchlorate (AP) as an solid propellants oxidizer could create a poisonous gas and atmospheric pollutions, such as HCl. Among the several oxidizers, N-guanylurea dinitramide (GuDN) is an effective candidate substance for eco-friendly oxidizer, which has high performance, pressure exponent, and eco-friendly smog during combustion for solid propellant of gas generator. In this paper, the theoretical analysis of characteristics as a gas generator propellant, propellant manufacturing processability, propellant hardness properties and combustion characteristics were studied.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.543-545
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• 2008

The Inner Arch developed several softwares: $\circ$ One dedicated to solid propulsion project : APSOL $\circ$ One dedicated to liquid propulsion projects ELIS A third one, PERFOL, is used to optimize the trajectory and the propulsion parameters The paper will describe the main software used for this study and illustrate the interest of these tools to make the first design of a new version of a launch vehicle with optimisation both of intrinsic propulsion parameters and of the trajectory.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.5
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• pp.12-18
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• 2014

A study of gas generator Fuel-Rich propellant for air-breathing propulsion system was performed in this paper. General solid propellant comprises a mean of 60% or more oxidizing agents. but, to develop the fuel-rich solid propellant increased the content of the metal fuel and reduced the content of the oxidizing agents by approximately 30%. Very high amount of heat per volume of fuel into the metal having the Boron was used. Amorphous Boron Powder was applied to propellant as beads type and it allowed to design more amount of metal fuel in the fuel-rich propellant. And the Combustion characteristics and properties of fuel-rich solid propellant according to the Boron-bead sizes were confirmed.