A preliminary design of a magnesium fueled martian ramjet engine

Jesse A. Linnell, Timothy Francis Miller

Research output: Chapter in Book/Report/Conference proceedingConference contribution

9 Citations (Scopus)

Abstract

This paper presents a preliminary design study for a solid fuel ramjet containing a super-stoichiometric loading of magnesium for operation in the Martian atmosphere. The methods and theory used for analysis are derived from first principles. A feasible ramjet design was obtained which has an operational speed of Mach 4 to 5, requires nine times the mass intake of atmosphere relative to the mass flow rate of solid grain, and a chamber pressure of approximately 250 kPa. The length of the combustion chamber is approximately 0.1 meters for the case of 100-micron diameter magnesium particles, and 3 to 10 meters for the case of 500-micron particles. The ratio of grain burn area to throat area is approximately 17. A suitable inlet design was made which would have nine 8-degree ramps. The inlet height and length would be 0.35 and 1.0 meter, respectively. An end-burning grain design was selected with a burn area of 0.45 m2. Hypothetical ballistic values of the magnesium/ sodium nitrate mixture of n=0.15 and a=0.002125 m/s-1 Pa-0.15 (where the regression rate is br=aPch n), produce a thrust of 2900 N and a specific impulse (adjusted for gas augmentation) of 400 seconds. Thrust predictions obtained by varying the ballistic pressure exponent indicate an upper limit above which the thrust curve falls below the drag curve and operation is not possible.

Original languageEnglish (US)
Title of host publication38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
StatePublished - Dec 1 2002
Event38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2002 - Indianapolis, IN, United States
Duration: Jul 7 2002Jul 10 2002

Publication series

Name38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Other

Other38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2002
CountryUnited States
CityIndianapolis, IN
Period7/7/027/10/02

Fingerprint

Ramjet engines
Magnesium
Ballistics
Combustion chambers
Mach number
Drag
Nitrates
Sodium
Flow rate
Gases

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

Cite this

Linnell, J. A., & Miller, T. F. (2002). A preliminary design of a magnesium fueled martian ramjet engine. In 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit (38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).
Linnell, Jesse A. ; Miller, Timothy Francis. / A preliminary design of a magnesium fueled martian ramjet engine. 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2002. (38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).
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abstract = "This paper presents a preliminary design study for a solid fuel ramjet containing a super-stoichiometric loading of magnesium for operation in the Martian atmosphere. The methods and theory used for analysis are derived from first principles. A feasible ramjet design was obtained which has an operational speed of Mach 4 to 5, requires nine times the mass intake of atmosphere relative to the mass flow rate of solid grain, and a chamber pressure of approximately 250 kPa. The length of the combustion chamber is approximately 0.1 meters for the case of 100-micron diameter magnesium particles, and 3 to 10 meters for the case of 500-micron particles. The ratio of grain burn area to throat area is approximately 17. A suitable inlet design was made which would have nine 8-degree ramps. The inlet height and length would be 0.35 and 1.0 meter, respectively. An end-burning grain design was selected with a burn area of 0.45 m2. Hypothetical ballistic values of the magnesium/ sodium nitrate mixture of n=0.15 and a=0.002125 m/s-1 Pa-0.15 (where the regression rate is br=aPch n), produce a thrust of 2900 N and a specific impulse (adjusted for gas augmentation) of 400 seconds. Thrust predictions obtained by varying the ballistic pressure exponent indicate an upper limit above which the thrust curve falls below the drag curve and operation is not possible.",
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Linnell, JA & Miller, TF 2002, A preliminary design of a magnesium fueled martian ramjet engine. in 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2002, Indianapolis, IN, United States, 7/7/02.

A preliminary design of a magnesium fueled martian ramjet engine. / Linnell, Jesse A.; Miller, Timothy Francis.

38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2002. (38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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AB - This paper presents a preliminary design study for a solid fuel ramjet containing a super-stoichiometric loading of magnesium for operation in the Martian atmosphere. The methods and theory used for analysis are derived from first principles. A feasible ramjet design was obtained which has an operational speed of Mach 4 to 5, requires nine times the mass intake of atmosphere relative to the mass flow rate of solid grain, and a chamber pressure of approximately 250 kPa. The length of the combustion chamber is approximately 0.1 meters for the case of 100-micron diameter magnesium particles, and 3 to 10 meters for the case of 500-micron particles. The ratio of grain burn area to throat area is approximately 17. A suitable inlet design was made which would have nine 8-degree ramps. The inlet height and length would be 0.35 and 1.0 meter, respectively. An end-burning grain design was selected with a burn area of 0.45 m2. Hypothetical ballistic values of the magnesium/ sodium nitrate mixture of n=0.15 and a=0.002125 m/s-1 Pa-0.15 (where the regression rate is br=aPch n), produce a thrust of 2900 N and a specific impulse (adjusted for gas augmentation) of 400 seconds. Thrust predictions obtained by varying the ballistic pressure exponent indicate an upper limit above which the thrust curve falls below the drag curve and operation is not possible.

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Linnell JA, Miller TF. A preliminary design of a magnesium fueled martian ramjet engine. In 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2002. (38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).