• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.275-278
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• 2010

By changing the nozzle throat area during the operation, thrust of a pintle thruster can be adjusted easily such as a liquid propulsion. In this paper, numerical analysis was carried out for SNECMA's pintle thruster with different pintle shapes. Flow field and aerodynamic load changed drastically with pintle shapes. Bore in the pintle decreased aerodynamic load significantly.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.5
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• pp.476-482
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• 2009

The effect of pintle shape on the thrust level of pintle-nozzle Solid Rocket Motor(PNSRM) was studied numerically using the Spalart-Allmaras turbulent model of Fluent. Mass flow rate of PNSRM was always less than theoretical value and the extent of decrease in mass flow rate grew in the large pintle because of increase in the relative boundary layer thickness between pintle body and nozzle wall. The bigger pintle size was, the more thrust of pintle tip pressure was obtained. Meanwhile the more thrust of nozzle and chamber pressure decreased. Hence, total thrust of big pintle was less than a small pintle under same throat area condition. Specific impulse was relatively flat for all pintle shape.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.167-174
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• 2011

Solid propulsion systems have simple structures compared to other propulsion systems and are suitable to 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 this 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 feedback linearization technique. Derived thrust equation and designe a thrust control model. We design the proportion-integral controller for linearizing about operating point. We also demonstrate the performance of controller model through numerical simulations.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.197-201
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• 2010

Precise control of oxidizer mass flow rate is important for hybrid rocket thrust control. In this study, oxidizer mass flow rate control system is developed by using stepping motor which is controlled by Labview program. Gox is used for oxidizer and PolyCarbonate, PolyEthylene, and PMMA is used for solid propellant. To suppress thrust oscillation during thrust control experiment, schematics of the experiment is analysised and revised. Results show that thrust oscillation is suppressed successfully.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.237-240
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• 2011

Numerical simulation was carried out to investigate the effect of pintle inflection point on the performance of the SNECMA modulatable thrust devices. Results show that the effect of inflection points in the pintle is to decrease aerodynamic load while maintaining required thrust level.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.288-291
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• 2010

Numerical analysis was conducted on thrust vector control using multi-nozzle system. The nozzle using flow valve switch to control mass flow of multi scarfed nozzle to manage thrust was considered. The operating characteristics of scarfed nozzle, thrust component and moment of multi nozzle in terms of mass flow rate were investigated by three dimensional flow simulation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.153-156
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• 2011

Steady state experiment was carried out for modulatable thruster applications, with four different pintles. Results show that thrust can be modulated by changing nozzle throat area with pintle penetration. However, effect of pintle shape on the thruster performance is yet to be concluded.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.365-368
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• 2009

A new concept of a small thruster for altitude control of a micro/nano class satellite is developed, which utilizes the pulsed laser energy. As the laser-based thruster does not require burning of any fuel, it gives promise of small satellite design criteria, namely light weight and cost effectiveness. In this paper, we develop gel-type material for generating strong plasma plume for enhancing thrust for propulsion. Moreover, we quantify the level of thrust via the momentum coupling coefficient measured by the pendulum system. We discover that the driving force is significantly improved via the gel-typed propellant for laser ablation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.526-529
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• 2009

In this study, we analyze the characteristic of burning classified by a propellant according to a flux of an oxidizer to analyze propellant regression distance in accordance with a thrust control and burning time of hybrid rocket using hybrid combustor of Lab-Scale. To control a flux of an oxidizer, we design flow control system to regulate the mount of opening and shutting of a needle valve by a driving of stepping motor by a combination the needle valve with stepping motor. We derive the relationships between mass flow rate and regression rate according to a propellant through the oxidizer flux change. While doing the thrust control, we estimate regression distance through the oxidizer flux in accordance with thrust and confirm the creditability through the actual thrust control burning experimentation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.12
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• pp.1071-1078
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• 2015

Numerical computations were performed to investigate the effects of pintle stroke, altitude, and bore on the performance of an external pintle thruster. Results show that under-expansion flow occurs always, independent of pintle stroke. An external pintle thruster shows good performance in that it is capable of good amount of thrust control, while aerodynamic loads are increased due to shock waves on the pintle support. When altitude is increased to 20 km, the nozzle exit velocity, Mach number, thrust as well as aerodynamic loads are increased. Bore increases aerodynamic load 5.9%, and therefore pintle shape without bore is preferred for lower aerodynamic load of a pintle in order to actuate the pintle.