Stephen Holden Wrote: >> I am developing a new hybrid propellant concept that I would like to >> discuss...It's basically very similar to any hybrid, except that the >> propellant consists of a cylindrical grain of lightly bonded magnesium >> powder onto which is sprayed through injectors the oxidizer.
>What proportion of the reaction products are gaseous at the expected >operating temperature? Russell McMahon Hey Ressell, I have recieved many many emails about the hybrid concept and slowly answering them, please be patient, especially those who have not had a response, I will respond to all emails:-) From my calculations (see Australian Experimental web site for update as I have added a brief thermochemical analysis) the proportion of gasses within the chamber is 67.8%. This means a faily high amount of solid phase primarily assumed to be MgO. The first propellant formulation considered, is ammonium nitrate, water and Mg. From the analysis we find: Optimum Isp(s)= 243s O/F = 1.9 Ratio of AN / water = 3 Tc = 3105 K Pc = 1000psi For a reasonble sized motor, it may be possible to achieve 200s of delivered Isp. It is most optimum to use a high as possible O / F ratio and to increase the amount of ammonium nitrate oxidizer and reduce the water content by increasing the concentration. Also, the lower the O/F and hence the amount of Mg fuel, the lower the losses due to residence time of the metals combustion within the chamber will be. However, the solubility limits this. A more oxidizing environment is desirable to, because it enhances the combustion efficiency of metals. Adding a proportion of AP would be desirable. We will also consider sodium nitrate & perchlorate. Cheers, Stephen ----- Stephen J. Holden Owner/Founder Mechanical Engineer Australian Experimental Email: [EMAIL PROTECTED] Web Page: http://www.australianexperimental.com.au _______________________________________________ ERPS-list mailing list [EMAIL PROTECTED] http://lists.erps.org/mailman/listinfo/erps-list
