An Optical Time-Resolved Technique of Solid Fuels Burning for Hybrid Rocket Propulsion

DeLuca, Luigi T.; Galfetti, L.; Maggi, F.; Colombo, G.; Paravan, Christian; Reina, A.; Tadini, P.; Sossi, Andrea; Duranti, E.

doi:10.2514/6.2011-5753

Cited by 13 publications

(7 citation statements)

References 9 publications

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“…De Luca et al [9] also use an optical technique to investigate the hybrid combustion process. They looked inside a pressurized chamber over a mirror setup inside the burning fuel grain and thereby measured the instantaneous regression rate.…”

Section: Optical Investigationsmentioning

confidence: 99%

Theoretical and experimental analysis of liquid layer instability in hybrid rocket engines

Kobald¹,

Verri

Schlechtriem³

2015

CEAS Space J

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Section: Optical Investigationsmentioning

confidence: 99%

Theoretical and experimental analysis of liquid layer instability in hybrid rocket engines

Kobald¹,

Verri

Schlechtriem³

2015

CEAS Space J

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“…They look inside a pressurized chamber over a mirror setup inside the burning fuel grain and thereby measured the instantaneous regression rate [17].…”

Section: Progress In Propulsion Physicsmentioning

confidence: 99%

Rheological, optical, and ballistic investigations of paraffin-based fuels for hybrid rocket propulsion using a two-dimensional slab-burner

Kobald

Toson

Ciezki

et al. 2016

Progress in Propulsion Physics

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This paper describes combined rheological, ballistic, and optical analyses performed on para©n-based mixtures that can be used as high regression rate hybrid rocket fuels. Experimental activities have been done at the DLR Institute of Space Propulsion in Lampoldshausen and at SPLab of Politecnico di Milano [1]. Herein, the experiments that were performed at the DLR are described in detail. Viscosity, surface tension, and regression rate of the fuels have been determined. Furthermore, the combustion was evaluated by optical measurements. Data collected so far indicate an increasing regression rate for decreasing viscosity of the liquid para©n which is in accordance with the current theories. Droplet entrainment, which is related to high regression rates, is only visible for the low-viscosity para©n-based fuels.

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“…An effective optical method has been developed to observe the combustion of metalized cylindrical fuel grains by Prof. Luigi De Luca of Polytecnico di Milano 22 . In this method, the combustion zone has been tracked visually over time to determine the fuel regression rate (see Figure 12).…”

Section: A Hybrid Rocket Fuel Additives -Reviewmentioning

confidence: 99%

Evaluation of Fuel Additives for Hybrid Rockets and SFRJ Systems

Karabeyoğlu¹,

Arkun²

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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A comprehensive assessment of fuel additives that are expected to improve the performance of hybrid rockets and solid fuel ramjet (SFRJ) systems is reported in this paper. A ranking of the selected fuel additives and binders have been made based on performance and other practical considerations including cost, availability and handling properties. One of the important conclusions of this study is that incorporating fuel additives into a binder is not an effective method to enhance the regression rate of hybrid rocket or SFRJ fuels. The key driver should be specific impulse and density impulse improvement. For low energy oxidizers such as nitrous oxide, aluminum turns out to be an excellent additive that strikes a good balance between the performance gain and key practical considerations such as availability/cost. Aluminum or other metals included in this study are not effective in improving Isp when they are used with oxygen. For hybrid rockets, AlH3 delivers the best performance benefit among all of the additives considered in this study. However its poor availability in the Western world diminishes its usefulness. Boron as an additive did not have a major performance impact for hybrid systems. It is believed that at the current energy and unit cost levels of the performance additives, they are not expected to generate an economical benefit (i.e. cost/payload mass) even for applications demanding high Isp's such as orbital launch vehicles. For SFRJ systems, boron and its compounds deliver significant performance improvement. Paraffin ranks as the best binder for both hybrids and also SFRJ's due to its high regression rate, good availability, hydrophobic nature, easy handling and low cost. NomenclatureAB = Ammonia Borane ADN = Ammonium dinitramide AMROC = American Rocket Company DCPD = Dicyclopentadiene GOX = Gaseous oxygen HTPB = Hydroxyl Terminated Polybutadiene LOX = Liquid oxygen NTO = Dinitrogen Tetraoxide (N2O4) pDCPD = Polydicyclopentadiene PE = Polyethylene polymer PMM = Polymethylmethacrylate SFRJ = Solid Fuel Ramjet Tf = Flame temperature, K

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An Optical Time-Resolved Technique of Solid Fuels Burning for Hybrid Rocket Propulsion

Cited by 13 publications

References 9 publications

Theoretical and experimental analysis of liquid layer instability in hybrid rocket engines

Theoretical and experimental analysis of liquid layer instability in hybrid rocket engines

Rheological, optical, and ballistic investigations of paraffin-based fuels for hybrid rocket propulsion using a two-dimensional slab-burner

Evaluation of Fuel Additives for Hybrid Rockets and SFRJ Systems

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