13762-80-6 Usage
Uses
Used in Aerospace Industry:
Hydrazine, perchlorate (1:1) is used as a propellant in rocketry for its high energy release and thrust-generating capabilities, which are crucial for space exploration and satellite deployment.
Used in Manufacturing of Pyrotechnics:
In the pyrotechnic industry, Hydrazine, perchlorate (1:1) serves as a powerful oxidizing agent, enhancing the performance of fireworks and other pyrotechnic devices by supporting combustion reactions.
Used in Chemical Synthesis:
Hydrazine, perchlorate (1:1) is utilized as an intermediate in the synthesis of various chemicals, including pharmaceuticals and agricultural chemicals, due to its reactive nature and ability to participate in multiple chemical reactions.
Check Digit Verification of cas no
The CAS Registry Mumber 13762-80-6 includes 8 digits separated into 3 groups by hyphens. The first part of the number,starting from the left, has 5 digits, 1,3,7,6 and 2 respectively; the second part has 2 digits, 8 and 0 respectively.
Calculate Digit Verification of CAS Registry Number 13762-80:
(7*1)+(6*3)+(5*7)+(4*6)+(3*2)+(2*8)+(1*0)=106
106 % 10 = 6
So 13762-80-6 is a valid CAS Registry Number.
13762-80-6Relevant academic research and scientific papers
Patil, Kashinath C.,Nesamani, C.,Verneker, Venkatesh R. Pai
, p. 2047 - 2050 (1983)
Infrared spectra, differential thermal analysis, and conductivity studies have been carried out to determine the nature of water of constitution in hydrazine salt hydrates.The possibility of water being present as the oxonium ion, H3O(1+), has been invest
Some properties of cocrystallizates of hydroxylammonium and hydrazonium perchlorates
Makhonina,Lempert,Nechiporenko
, p. 167 - 170 (2008/10/08)
Anhydrous mixed perchlorates of hydroxylamine and hydrazine were synthesized by coprecipitation from aqueous solutions. Their melting temperatures were determined, the moisture effect on the salt phase states was studied, and thermal analysis of the compounds was performed. The thermal stability of the salts in the temperature range 60 to 80°C and their compatibility with the components of composite propellants were investigated. Copyright
