SBIR-STTR Award

Magnesium Based Rockets for Martian Exploration
Award last edited on: 7/10/2020

Sponsored Program
SBIR
Awarding Agency
NASA : DRFC
Total Award Amount
$699,992
Award Phase
2
Solicitation Topic Code
S3.08
Principal Investigator
James J Szabo

Company Information

Busek Company Inc (AKA: Busek Co Inc)

11 Tech Circle
Natick, MA 01760
   (508) 655-5565
   info@busek.com
   www.busek.com
Location: Single
Congr. District: 05
County: Middlesex

Phase I

Contract Number: ----------
Start Date: ----    Completed: ----
Phase I year
2010
Phase I Amount
$99,993
We propose to develop Mg rockets for Martian ascent vehicle applications. The propellant can be acquired in-situ from MgO in the Martian regolith (5.1% Mg by mass) and combusted with H20 that exists at the poles and below the surface. The vacuum Isp of a Mg-H20 rocket would be ~300 s. Mg can also be combusted with CO2 condensed from the Martian atmosphere to yield Isp ~215 s. The technology can also be used on the Moon, where regolith is 5.5% Mg. Al-H20 rockets would also be enabled; like Mg, Al is present in Martian and Lunar regolith. In Phase I, we will prove the feasibility of Mg rockets. Chemical Equilibrium Analysis codes will be used to predict rocket performance at various operating conditions and O/F ratios. Combustion with CO2, H20, and pure O2 will be considered. Experiments will focus on developing and characterizing delivery, ignition and combustion systems, starting with ARL's existing Mg combustion system. Ways to achieve low temperature, electrolytic ignition and stable combustion will be studied. Drawing upon both experimental and theoretical results, we will then design a 5-10 N metal-water rocket system to be built and tested in Phase II.

Phase II

Contract Number: ----------
Start Date: ----    Completed: ----
Phase II year
2011
Phase II Amount
$599,999
In the proposed Phase II program, we will continue the development of Mg bipropellant rockets for Martian PAV applications. In Phase I, we proved the feasibility of this game-changing technology. Through chemical analysis, we determined that Mg can be combusted with CO2 condensed in-situ from the Martian atmosphere to yield Isp ~240 s. We then successfully demonstrated a low fidelity Mg-CO2 rocket in the laboratory, achieving combustion for 43s before voluntary termination. We also analyzed the use of H2O and H2O2 as oxidizers, and Al as a propellant. H2O exists at the Martian poles and below the surface, while both Mg and Al can be acquired in-situ from the Martian regolith. We determined that the ideal vacuum Isp of a 10 bar Mg-H20 rocket would be as high as ~340 s, while the Isp of a Al-steam rocket would be ~380 s, and hydrogen peroxide could yield higher density Isp and operational benefits. In Phase II we plan to develop and test an integrated high performance laboratory model system. We will first fully characterize multiple propellant oxidizer combinations in a linear combustor. Then we will design, build, and test an integrated system including both a rocket and a propellant management system. Comprehensive test results would feed back into the design, culminating in an advanced system sized for prospective near-term applications.