Microwave Air Plasma Supersonic Hydrocarbon Combustion Enhancement Experiments PDF Download
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Author: S. G. Chianese
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Languages : en
Pages :
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Author: S. G. Chianese
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Category :
Languages : en
Pages :
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Author: Paul David Rudolph
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Category :
Languages : en
Pages : 306
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Category : Aeronautics
Languages : en
Pages : 776
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Author: Ashley Marie Brandon
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Category :
Languages : en
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The purpose of this experiment is to improve upon a preexisting beamed microwave propulsion system by bringing the exit flow to supersonic speeds. This research builds upon an experiment previously designed at Penn State. The working fluid of this experiment, nitrogen, must be transported from tanks pressurized to 6,000 psig to the chamber of an electric propulsion system. Improving the mass flow rate of the system ensures supersonic flow to the exit of the nozzle and furthers the goal of optimizing the systems thrust and specific impulse. Increasing the mass flow rate will also eliminate undesirable characteristics that previously manifested in the flow. Both experimental and theoretical calculations revealed the presence of shock waves in the prior experiment, which have substantially impaired the propulsion systems performance. The improved experimental design increases the effective feed system flow area that follows the nitrogen tank orifice. Further improvements include the addition of a high mass flow rate pressure regulator, an additional two nitrogen tanks, and various safety measures. The results of the experiment demonstrated that the new experimental design eliminated the presence of shocks in the nozzle. Though a chamber pressure of over 900 psig has already been achieved, further experiments are being conducted to test the viability of increasing the chamber pressure to 2,000 psig.
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Category : Rocketry
Languages : en
Pages : 822
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Author: Chien Hsiu Ho
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Languages : en
Pages :
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Beamed-energy propulsion provides a possible advanced propulsion method for Earth-launch systems with high-specific-impulse electric thrust and high payload mass fraction. The concept behind beamed-energy propulsion is the generation of thrust by heating up propellant with off-vehicle beamed energy, either by laser or microwaves, instead of with the inner (chemical) energy of propellants in traditional propulsion systems. This method can provide higher theoretical specific impulse than traditional chemical propellants. Furthermore, the separation of the energy source from the vehicle can increase the payload mass fraction. In this research, the proposed method to transform beamed energy of continuous-wave (CW) microwaves to thrust is by the focusing of beamed microwaves onto a supersonic nitrogen flow to generate a plasma that can absorb the microwave energy and heat the supersonic flow. In this dissertation, work in three aspects were reported: theoretical investigation, generating Mach 5 supersonic flow in a parabolic supersonic nozzle, and simulation of the electric field distribution in the parabolic nozzle. The mechanisms about how energy transfers from a microwave to gas were investigated. After a microwave breakdown, the energy in the microwaves is transferred first to the kinetic energy of electrons. Due to the large mass difference between an electron and a gas particle, the energy of electrons is transferred to gas particles mainly through inelastic collisions. Energy absorption and release via three types of inelastic collisions and excitations of rotational states, vibrational states, and electronic states are discussed in this dissertation. With the understanding of how the energy is transferred from microwaves to a gas, the coupling coefficients between microwaves and supersonic flow were estimated for two situations. One situation is simulating the environment at sea level. At sea level, a launch vehicle applies highest thrust to lift the payload and all the fuel. In this situation, it is the coupling between a high-power microwave and a supersonic flow with high flow rate. The other situation is simulating the low-pressure environment at high altitude. A launch vehicle needs lower thrust compared with the thrust at sea level due to most of the propellant having been consumed by the time the launch vehicle has reached high altitude. In this situation, coupling occurs between moderate-power microwaves and supersonic flow with low flow rate. Quasi-one-dimensional simulations were conducted to understand the thrust augmentations in different heating conditions in a supersonic flow. The quasi-one-dimensional simulation can be used to analyze the experimental data in future and increase our understanding about the coupling between a microwave and a supersonic flow. To generate a supersonic flow in our converging--diverging (supersonic) nozzle, a gas feed system capable of supplying higher flow rate is needed according to preliminary experiments. The earlier gas feed system failed to supply enough mass flow rate and generated a shock wave in the nozzle. An improved gas feed system was designed to supply a mass flow rate of 2.53 kg/s and stagnation pressure higher than 2000 psig. The pressure distribution in the improved gas feed system and the maximum flow rate of the system were estimated. At the same time, flow tests were executed to understand the capability of the improved gas feed system. Computational electromagnetics was utilized to simulate the electric field distribution in our parabolic nozzle. The simulation results obtained with COMSOL Multiphysics showed that there was resonance in the stagnation chamber of our first nozzle design. To eliminate the resonance in the stagnation chamber, a new nozzle was designed with the aid of the computational simulation. At the same time, the electric field distributions in the new nozzle under different incident microwaves were simulated to further understand the electric field distribution in real condition.
Author: American Institute of Aeronautics and Astronautics
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Category : Aeronautics
Languages : en
Pages : 958
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Author:
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Category : Airplanes
Languages : en
Pages : 510
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Author:
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Category : Aeronautics
Languages : en
Pages : 1032
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Author:
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Category : Lasers
Languages : en
Pages : 660
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