scorpaena : Performance of Metal Hydride Fuel Additives for Rocket Propellant Applications
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Data on the performance of both hybrid and liquid propellants with metal hydride additives
The use of specific metal hydride fuel additives is shown to raise a propellant formulation’s overall specific impulse, by as much as 17% when beryllium hydride is considered [1]. Other metal hydrides, such as alane and lithium aluminum hydride, increase propellant specific impulse by approximately 4%. Density specific impulse is seen to increase by 6% and 7% with zirconium hydride and titanium hydride, respectively.
The peak performance was found by varying the oxidizer-to-fuel ratio (O/F) in increments of 0.1 until the maximum Isp was found. Sea level expansion Isp, vacuum Isp and density Isp provide the basis for performance comparison. The following assumptions were applied within CEA to all equilibrium calculations:
- Motor chamber pressure of 6.895 MPa (1000 psia)
- Isp (s) - nozzle is perfectly expanded to sea level atmospheric pressure, 1.013 MPa (14.7 psia)
- Vacuum Isp (s) - nozzle has an expansion ratio of 40
- Shifting equilibrium within the nozzle flow field
- Hybrid fuel composition: 50 wt.% MH / 50 wt.% DCPD
- Bi-propellant fuel composition: 55 wt.% MH / 45 wt.% RP-1
This repository contains data and corresponding relations of the specific impulse vs oxidizer to fuel ratios for various bi-propellant and hybrid fuel combinations.
Source:
[1] Steven C. Shark, Travis R. Sippel, Steven F. Son, Stephen D. Heister, Timothee L. Pourpoint. Theoretical Performance Analysis of Metal Hydride Fuel Additives for Rocket Propellant Applications. 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011. 10.2514/6.2011-5556.
Data on the performance of both hybrid and liquid propellants with metal hydride additives
The use of specific metal hydride fuel additives is shown to raise a propellant formulation’s overall specific impulse, by as much as 17% when beryllium hydride is considered [1]. Other metal hydrides, such as alane and lithium aluminum hydride, increase propellant specific impulse by approximately 4%. Density specific impulse is seen to increase by 6% and 7% with zirconium hydride and titanium hydride, respectively.
The peak performance was found by varying the oxidizer-to-fuel ratio (O/F) in increments of 0.1 until the maximum Isp was found. Sea level expansion Isp, vacuum Isp and density Isp provide the basis for performance comparison. The following assumptions were applied within CEA to all equilibrium calculations:
- Motor chamber pressure of 6.895 MPa (1000 psia)
- Isp (s) - nozzle is perfectly expanded to sea level atmospheric pressure, 1.013 MPa (14.7 psia)
- Vacuum Isp (s) - nozzle has an expansion ratio of 40
- Shifting equilibrium within the nozzle flow field
- Hybrid fuel composition: 50 wt.% MH / 50 wt.% DCPD
- Bi-propellant fuel composition: 55 wt.% MH / 45 wt.% RP-1
This repository contains data and corresponding relations of the specific impulse vs oxidizer to fuel ratios for various bi-propellant and hybrid fuel combinations.
Source:
[1] Steven C. Shark, Travis R. Sippel, Steven F. Son, Stephen D. Heister, Timothee L. Pourpoint. Theoretical Performance Analysis of Metal Hydride Fuel Additives for Rocket Propellant Applications. 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011. 10.2514/6.2011-5556.
