Experimental Performance Analysis (c* &amp; c* Efficiency) of a Premixed Green Propellant consisting of N2O and C2H4

Werling, Lukas; Haßler, Matthias; Bätz, Patrick; Ciezki, Helmut; Schlechtriem, Stefan

doi:10.2514/6.2017-5069

Cited by 15 publications

(20 citation statements)

References 6 publications

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“…Table 3. Physical properties and performance (@ 1 MPa chamber pressure, 100:1 expansion ratio, and vacuum conditions, using NASA Chemical Equilibrium Analysis (CEA) [32] and verified from [4,30,33,36,37,[44][45][46]). HNP225 is the one among the family with the least adiabatic flame temperature around 1000 K (even less than hydrazine ∼1200 K), while HNP221 is approximately 1400 K [33,43].…”

Section: Energetic Ionic Liquids (Eils)mentioning

confidence: 99%

Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers

2021

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Current research trends have advanced the use of “green propellants” on a wide scale for spacecraft in various space missions; mainly for environmental sustainability and safety concerns. Small satellites, particularly micro and nanosatellites, evolved from passive planetary-orbiting to being able to perform active orbital operations that may require high-thrust impulsive capabilities. Thus, onboard primary and auxiliary propulsion systems capable of performing such orbital operations are required. Novelty in primary propulsion systems design calls for specific attention to miniaturization, which can be achieved, along the above-mentioned orbital transfer capabilities, by utilizing green monopropellants due to their relative high performance together with simplicity, and better storability when compared to gaseous and bi-propellants, especially for miniaturized systems. Owing to the ongoing rapid research activities in the green-propulsion field, it was necessary to extensively study and collect various data of green monopropellants properties and performance that would further assist analysts and designers in the research and development of liquid propulsion systems. This review traces the history and origins of green monopropellants and after intensive study of physicochemical properties of such propellants it was possible to classify green monopropellants to three main classes: Energetic Ionic Liquids (EILs), Liquid NOx Monopropellants, and Hydrogen Peroxide Aqueous Solutions (HPAS). Further, the tabulated data and performance comparisons will provide substantial assistance in using analysis tools—such as: Rocket Propulsion Analysis (RPA) and NASA CEA—for engineers and scientists dealing with chemical propulsion systems analysis and design. Some applications of green monopropellants were discussed through different propulsion systems configurations such as: multi-mode, dual mode, and combined chemical–electric propulsion. Although the in-space demonstrated EILs (i.e., AF-M315E and LMP-103S) are widely proposed and utilized in many space applications, the investigation transpired that NOx fuel blends possess the highest performance, while HPAS yield the lowest performance even compared to hydrazine.

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Section: Energetic Ionic Liquids (Eils)mentioning

confidence: 99%

Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers

2021

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“…Various alternatives for hydrazine are currently under investigation. A prospective low-cost and high-performance alternative is the mixtures of nitrous oxide (N 2 O) and fuels [69,[78][79][80]. Here nitrous oxide and a fuel, or a fuel combination, are stored pre-mixed as monopropellant.…”

Section: Liquid Monopropellants Based On Hydrocarbons and Nitrous Oximentioning

confidence: 99%

“…More detailed information about the work conducted within this subproject is presented in [67]. Lists of the relevant literature and surveys in relation to these green advanced rocket propellants or references to surveys are given in [67][68][69][70][71][72][73][74][75].…”

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confidence: 99%

Future Fuels—Analyses of the Future Prospects of Renewable Synthetic Fuels

et al. 2019

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The Future Fuels project combines research in several institutes of the German Aerospace Center (DLR) on the production and use of synthetic fuels for space, energy, transportation, and aviation. This article gives an overview of the research questions considered and results achieved so far and also provides insight into the multidimensional and interdisciplinary project approach. Various methods and models were used which are embedded in the research context and based on established approaches. The prospects for large-scale fuel production using renewable electricity and solar radiation played a key role in the project. Empirical and model-based investigations of the technological and cost-related aspects were supplemented by modelling of the integration into a future electricity system. The composition, properties, and the related performance and emissions of synthetic fuels play an important role both for potential oxygenated drop-in fuels in road transport and for the design and certification of alternative aviation fuels. In addition, possible green synthetic fuels as an alternative to highly toxic hydrazine were investigated with different tools and experiments using combustion chambers. The results provide new answers to many research questions. The experiences with the interdisciplinary approach of Future Fuels are relevant for the further development of research topics and co-operations in this field.Synthetic fuels based on renewable energies (RE) are widely seen as a key element to achieving climate-neutral transport (e.g., [1,2]). As liquid hydrocarbons have a high energy and power density, they are primarily discussed as fuels for (heavy) road vehicles, ships, and aircraft. Due to their low storage and transport losses, they are also conceivable as a complementary long-term electricity storage option [3]. The challenges of producing and implementing these fuels are manifold. Chemical processes and renewable electrical or thermal energy can be used to produce liquid hydrocarbons from various carbon sources and hydrogen (and sometimes oxygen). Synthetic fuels have several advantages: they can be easily integrated into our existing energy and mobility infrastructures, can be used in all areas of the transport sector, and they can be optimized with regard to their chemical properties. The main disadvantages are the high energy losses and production costs.In this research context, eleven research groups at the German Aerospace Center (DLR) are working together on the Future Fuels project on synthetic fuels. The aim of the interdisciplinary approach is to realize synergies and joint research activities, as well as new research impulses through different perspectives. The scientists and engineers are investigating how synthetic fuels can be produced using solar energy and electrolysis processes (Solar Fuels), and are developing concepts for the re-conversion of these fuels into electricity. They are working on emission-optimized fuels for transport and aviation (Designer Fuels), as well as advanced space ap...

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“…AF-M315E has a higher density and similar I sp compared to FLP-106. However, it has a higher health hazard [29].…”

Section: A System Types and Trade-offmentioning

confidence: 99%

Combined Chemical–Electric Propulsion for a Stand-Alone Mars CubeSat

Mani

Cervone

Topputo

2019

Journal of Spacecraft and Rockets

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Stand-alone interplanetary CubeSats require primary propulsion systems for orbit maneuvering and precise trajectory control. The current work focuses on the design and performance characterization of the combined chemical-electric propulsion systems that shall enable a stand-alone 16U CubeSat mission on a hybrid high-thrust-low-thrust trajectory from a Supersynchronous Geostationary Transfer Orbit to a circular orbit about Mars. The high-thrust chemical propulsion is used to escape Earth and to initiate stabilization at Mars. The low-thrust electric propulsion is used in heliocentric transfer, ballistic capture, and circularization. For chemical propulsion, design and performance characteristics of a monopropellant thruster and feed system utilizing ADN-based FLP-106 propellant are presented. For electric propulsion, a performance model of an Iodine-propelled inductively coupled miniature radiofrequency ion thruster is implemented to calculate the variation of thrust, specific impulse and efficiency with input power. A power constrained low-thrust trajectory optimization utilizing the thruster performance model is pursued to calculate the transfer time, ∆V and the required propellant mass for fuel-optimal and time-optimal transfers. Overall, the combined chemical-electric systems yield a feasible propulsion solution for stand-alone CubeSat missions to Mars that balances propellant mass and transfer time.

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Experimental Performance Analysis (c* & c* Efficiency) of a Premixed Green Propellant consisting of N₂O and C₂H₄

Cited by 15 publications

References 6 publications

Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers

Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers

Future Fuels—Analyses of the Future Prospects of Renewable Synthetic Fuels

Combined Chemical–Electric Propulsion for a Stand-Alone Mars CubeSat

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