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In order to understand the dynamic behaviors of these "hot" structures, a double-wedge lifting surface with combining freeplay and cubic structural nonlinearities in both plunging and pitching degrees-of-freedom operating in supersonic/hypersonic flight speed regimes has been analyzed.
It is concluded that the hybrid design is a viable strategy for hot structures requiring damage tolerance.
Hybrid structures, for example metallic multiwall thermal protection systems, sandwiches or hot structures, consist of layers with different thermal conductivity.
The experimental method to obtain values of ¢ and m is described in detail and is based on unsteady state cooling of the hot structures in an air stream.
The experimentation plan on thermal protections is detailed; it includes ceramic matrix composite (CMC) hot structures, ceramic shingles and panels, metallic components, flexible blankets.
In order to apply carbon/carbon composites (C/Cs) to various hot structures, secondary bonding techniques effective at elevated temperatures are frequently required.
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The optimal distributions of gradient materials for the sharp hot structure are proposed.
The results will provide an important guidance for the design of the sharp hot structure.
In this paper, the shape and material gradient of the sharp hot structure are designed and optimized to meet the hypersonic flight conditions.
Finally, the ABAQUS software is used to simulate both the temperature and the stress distribution with different material gradient distributions for the sharp hot structure.
The hot structure of the cell, including the hot plate, the BASE tube support plate, the hot plenum wall and conduction stud, the evaporator standoff and porous wick and the side wall facing the BASE tubes, is made of Nb 1Zr.
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