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Langasite (LGS) Surface Acoustic Wave (SAW) Pressure Sensor with Kovar Alloy Point-Force Packaging for High-Temperature Environments. [PDF]
Sensors (Basel)Ke Y +5 more
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Bio-inspired multi-dimensional deep fusion learning for predicting dynamical aerospace propulsion systems. [PDF]
Commun EngVergnolle MQ, Wu EZY, Sui Y, Wang Q.
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Free-flight and tracking experiments of a multi-parabola laser propulsion vehicle. [PDF]
Sci RepTakahashi M +3 more
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Study on jet dynamic impact performance under the influence of standoff. [PDF]
Sci RepWang Y, Yin J, Zhang X, Yi J, Li X.
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Modeling and Validation of Electrostatic Sensing for UAV Targets in High-Dynamic Encounter Scenarios. [PDF]
Sensors (Basel)Xia R +5 more
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Advances in High-Temperature Sensor Technologies: Material System, Sensing Principles, Drift Compensation, and Encapsulation Reliability. [PDF]
ACS OmegaHuang X +6 more
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The Journal of the Royal Aeronautical Society, 1957
The 1,000th Lecture to be given before the Society and the 27th Main Lecture to be held at a Branch of the Society was held under the auspices of the Henlow Branch. The lecture, “Rocket Engines,” was given by Mr. S. Allen, F.R.Ae.S., on 11th October 1956. Professor A. J. Murphy, A.F.R.Ae.S., President of the Henlow Branch, opened the meeting, and Mr. E.
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The 1,000th Lecture to be given before the Society and the 27th Main Lecture to be held at a Branch of the Society was held under the auspices of the Henlow Branch. The lecture, “Rocket Engines,” was given by Mr. S. Allen, F.R.Ae.S., on 11th October 1956. Professor A. J. Murphy, A.F.R.Ae.S., President of the Henlow Branch, opened the meeting, and Mr. E.
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THE NEXT GENERATION ROCKET ENGINES
Acta Astronautica, 1989Abstract This paper examines propulsion system technologies for earth-to-orbit vehicles, and describes several propulsion system concepts which could support the recommendations of the Commission for Space Development for the year 2000. The hallmark of that system must and will be reliability.
Rudi Beichel +2 more
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Gas-core nuclear rocket engine
2nd Propulsion Joint Specialist Conference, 1966The major components of a gas-core nuclear rocket engine are studied, on the assumption of satisfactory hydrodynamic containment of the core. The core cavity was assumed to have a diameter and length of 60 in., a hydrogen cavity temperature of 12,000°R, a hydrogen flow rate of 200 Ib/sec, and a chamber pressure of 10,000 psia.
EDWARD E. DUKE, WILLIAM J. HOUGHTON
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