A combustion assembly capable of continuously burning monopropellant and bipropellant liquid fuels at pressures up to 80 bars (1145 psig) was designed constructed. The is based on a propellant strand burner where manifold maintains small positive differential the fuel maintain steady supply into reaction vessel. Optical ports enable direct visualization flame will allow for future spectroscopic...

This paper focuses on a qualitative fault diagnosis method based on the integration and fusion of shallow and deep knowledge for liquid-propellant rocket engines (LRE). The paper firstly clarifies the concept and the types of LRE diagnosis knowledge. Later, from the isomorphic transform point of view, the paper analyses the correlation of different knowledge and knowledge representation, and fo...

The performance metrics of a 2-kW-class thruster operated using magnesium propellant was measured and compared to the performance of the same thruster operated using xenon propellant. It was found that the magnesium thruster has thrust ranging from 34 mN at 200 V to 39 mN at 300 V with 1.7 mg/s of propellant. It was found to have 27 mN of thrust at 300 V using 1.0 mg/s of propellant. The thrust...

A new electric propulsion device concept takes advantage of residual helium gas that is trapped in the chemical propellant feed system and currently unused at end of life. The helium ion thruster provides additional propellant resources to extend satellite lifetimes and transfer geostationary orbit space assets to ultrasafe disposal orbits. The predicted capability, if fully allotted to the dis...

Figure 1 shows the ballistic results for propellants 1, A, and B. The burning rates show no signiŽ cant alteration among the three propellants. The differential scanning calorimetry plots for these three propellants shown in Fig. 2 tell a different story, however. Compared with the baseline, both the carbon and the fullerene soot appear to eliminate the secondaryexothermicpeak at approximately ...

Constellations and platoons of small satellites can offer an assortment of benefits over larger, single function spacecraft. The strict mass, volume, and power limitations of small satellites will require unique micro-technologies to help develop efficient propulsion systems for maneuvering. The Free Molecule Micro-Resistojet (FMMR) has been analyzed and tested in this study to determine its ap...

In propellant systems, fuels of choice continue to be hydrazine and its derivatives, even though they comprise a class of acutely carcinogenic and toxic substances which exhibit rather high vapor pressures and require expensive handling procedures and costly safety precautions. Only recently (2008), ionic liquids (salts with melting points less than 100 °C) with the dicyanamide anion were shown...

In airframe technology, designs have become progressively more compact, to accommodate internal and external carriage by aircraft, launch tubes on warships or torpedo tubes in submarines. Propulsion has evolved from simple pulse jets, through turbojets and liquid propellant rockets or ramjets to the current mix of: turbojets for subsonic tactical cruise missiles, turbofans for subsonic strategi...

This paper is a summary overview of a study conducted at the NASA Marshall Space Flight Center (NASAMSFC) during the initial phases of the Space Launch Initiative (SLI) program to evaluate a large number of technical problems associated with the design, development, test, evaluation and operation of several major liquid propellant rocket engine systems (i.e., SSME, Fastrac, J-2, F-I). One of th...