Axial Temperature Behavior of a Heat Exchanger Tube for Microwave Thermal Rockets

Bruccoleri, Alexander R.; Parkin, Kevin; Barmatz, M.

doi:10.2514/1.27847

Cited by 6 publications

(3 citation statements)

References 2 publications

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“…In their concept, high-power microwaves heat a propellant in the dielectric heat exchanger tube; the heated propellant is exhausted through a nozzle, similarly to a conventional rocket. Bruccoleri et al [9] measured the temperature of helium in a mullite tube using 2.45 GHz microwaves. These early studies are based on steady operation.…”

mentioning

confidence: 99%

Thrust Performance of Microwave Rocket Under Repetitive-Pulse Operation

Oda¹,

Shibata²,

Komurasaki³

et al. 2009

Journal of Propulsion and Power

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An experiment was conducted on a microwave rocket (repetitive-pulse millimeter-wave-beam-powered thruster) with repetitive pulses. A thruster model with a forced-breathing system was used. The forced-breathing system supplies fresh air from the thrust wall into the thruster. The pressure histories in the thruster were measured and the propagation velocity of the shock wave and the thrust impulse were deduced. Results show that although the propagation velocity was identical to the result for the single-pulse operation at the first pulse, the propagation velocity increased after the second pulse. Similarly, the impulse decreased after the second pulse. The dependence of the propagation velocity of the shock wave and the thrust performance on the partial-filling rate of the fresh air was compared with that of the thrust-generation model with a forced-breathing system. The experimental results showed good agreement with those obtained using the model.

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mentioning

confidence: 99%

Thrust Performance of Microwave Rocket Under Repetitive-Pulse Operation

Oda¹,

Shibata²,

Komurasaki³

et al. 2009

Journal of Propulsion and Power

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“…This concept requires an average flux of 10 MW m −2 at a range of a few hundred kilometers to work as a payload delivery scheme to LEO. Parkin (Bruccoleri, Parkin and Barmatz, 2007) proposed a system concept using a 140-GHz microwave beam. The beam is projected upon the flat microwave-absorbent underside of a reusable lifting body with double the I sp of conventional rocket engines.…”

Section: Heat Exchanger Thrustersmentioning

confidence: 99%

Laser Propulsion

Komurasaki

Wang

2010

Encyclopedia of Aerospace Engineering

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“Beamed Energy Propulsion” is distinguished by its use of a collimated laser or microwave beam that enables long‐distance wireless power supply, no‐fuel airbreathing flight, high heating rates (detonation and ablation) by beam focusing, and other useful features. Remotely powered space propulsion is a potential alternative to chemical and electric propulsion. Compact onboard laser thrusters also provide unique features. This chapter presents a worldwide review of beamed energy propulsion studies, most of which have been reported at the series of International Symposium on Beamed Energy Propulsion (ISBEP).

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“…Two kinds of thrust generation mechanism for Microwave Rocket are proposed, namely CW type and repetitive pulse type. CW type utilizes heat exchange system or steady plasma to heat up propellant by microwave power [1,2]. The repetitive pulse type utilizes aerial breakdown which induces shock wave (or blast wave) causes impulsive thrust [3].…”

Section: Introductionmentioning

confidence: 99%