Ultrasonic Measurement of the Regression Rate of the Melting Interface in Burning Metal Rods

2009 ◽  
pp. 122-122-13 ◽  
Author(s):  
TA Steinberg ◽  
M Veidt
Keyword(s):  
Ultrasonic Measurement ◽  
Regression Rate

Ultrasonic Measurement of Sheet Steel Texture and Formability: Comparison with Neutron Diffraction and Mechanical Measurements

1990 ◽  
Vol 2 (1) ◽  
pp. 239-257
Author(s):  
A. V. Clark ◽  
R. B. Thompson ◽  
Y. Li ◽  
R. C. Reno ◽  
G. V. Blessing ◽  
...  
Keyword(s):  
Neutron Diffraction ◽  
Sheet Steel ◽  
Ultrasonic Measurement ◽  
Mechanical Measurements

A Visual Study of the Combustion of High-Regression Rate and Classical Hybrid Rocket Fuels

2015 ◽  
Author(s):  
Elizabeth T. Jens ◽  
Victor A. Miller ◽  
Flora S. Mechentel ◽  
Brian J. Cantwell ◽  
Scott Hubbard
Keyword(s):  
Hybrid Rocket ◽  
Regression Rate ◽  
Visual Study

Pressure calibration based on the ultrasonic measurement in multi-anvil apparatus

2020 ◽  
pp. 1-13
Author(s):  
Wei Song ◽  
Qizhe Tang ◽  
Chang Su ◽  
Xiang Chen ◽  
Yonggang Liu
Keyword(s):  
Ultrasonic Measurement ◽  
Pressure Calibration

scholarly journals Challenges of Ablatively Cooled Hybrid Rockets for Satellites or Upper Stages

Aerospace ◽  
2021 ◽  
Vol 8 (7) ◽  
pp. 190
Author(s):  
Francesco Barato
Keyword(s):  
Combustion Chamber ◽  
Solid Fuel ◽  
Diameter Ratio ◽  
Propulsion System ◽  
Burning Time ◽  
Regression Rate ◽  
Hybrid Propulsion ◽  
Deep Impact ◽  
Time Ratio ◽  
Hybrid Rockets

Ablative-cooled hybrid rockets could potentially combine a similar versatility of a liquid propulsion system with a much simplified architecture. These characteristics make this kind of propulsion attractive, among others, for applications such as satellites and upper stages. In this paper, the use of hybrid rockets for those situations is reviewed. It is shown that, for a competitive implementation, several challenges need to be addressed, which are not the general ones often discussed in the hybrid literature. In particular, the optimal thrust to burning time ratio, which is often relatively low in liquid engines, has a deep impact on the grain geometry, that, in turn, must comply some constrains. The regression rate sometime needs to be tailored in order to avoid unreasonable grain shapes, with the consequence that the dimensional trends start to follow some sort of counter-intuitive behavior. The length to diameter ratio of the hybrid combustion chamber imposes some packaging issues in order to compact the whole propulsion system. Finally, the heat soak-back during long off phases between multiple burns could compromise the integrity of the case and of the solid fuel. Therefore, if the advantages of hybrid propulsion are to be exploited, the aspects mentioned in this paper shall be carefully considered and properly faced.

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