N,N-bis-(2-cyano-ethyl)-naphthalene-1-sulfonamide | 2619-18-3

• 分子结构分类: 有机化合物 - 苯类化合物 - 萘
• 英文名称: N,N-bis-(2-cyano-ethyl)-naphthalene-1-sulfonamide
• 英文别名: N,N-Bis-(2-cyan-aethyl)-naphthalin-1-sulfonamid；N,N-bis(2-cyanoethyl)naphthalene-1-sulfonamide
• CAS: 2619-18-3
• 化学式: C₁₆H₁₅N₃O₂S
• 分子量: 313.38
• InChiKey: DYJQXKNLYDYALE-UHFFFAOYSA-N

计算性质

• 辛醇/水分配系数(LogP)：
  1.7
• 重原子数：
  22
• 可旋转键数：
  6
• 环数：
  2.0
• sp3杂化的碳原子比例：
  0.25
• 拓扑面积：
  93.3
• 氢给体数：
  0
• 氢受体数：
  5

反应信息

• 作为产物：
  描述：

  1-萘磺酰胺 、 丙烯腈 在 氢氧化钾 作用下， 生成 N,N-bis-(2-cyano-ethyl)-naphthalene-1-sulfonamide
  参考文献：
  名称：

  Kretow; Romasanowitsch, Zhurnal Obshchei Khimii, 1958, vol. 28, p. 1059,1061;engl.Ausg.S.1029

  摘要：

  DOI：

文献信息

• Misra; Asthana, Journal fur praktische Chemie (Leipzig 1954), 1957, vol. <4> 4, p. 270,274
  作者：Misra、Asthana

  DOI：——

  日期：——
• Unsteady Flow Separation Can Endanger the Structural Integrity of Aerospace Launch Vehicles
  作者：Lars E. Ericsson

  DOI：10.2514/2.3690

  日期：2001.3

  When during the ascent through the Earth's atmosphere the structural response of an aerospace launch vehicle changes from the usually benign case of the buffet response to wind gusts and air turbulence to the self-excited type, the response amplitude increases dramatically and could often endanger the structural integrity of the launch vehicle. This is what occurs when the structural response starts to interact with and modify the unsteady separated Bow characteristics, which generates aerodynamic negative damping or undamping of the low-frequency bending modes. A literature survey has been performed to document how this condition has affected the various aerospace vehicles launched since the early 1960s, The developed analytic means, described in the referenced publications, can predict the worst-case vehicle response with the accuracy needed for preliminary design, provided that sufficiently detailed static aerodynamic data are available, The purpose is to help the design engineer determine whether any of the described Row phenomena that have been experienced by earlier launch vehicles could possibly occur on the new launch vehicle design, in which case the recommended analysis described in full detail in the referenced publications would need to be performed.