The Starting Transient in a Gas-Generator Hybrid Rocket Motor

Osherov, Alexander; Natan, Benveniste

doi:10.1002/1521-4087(200011)25:5<260::aid-prep260>3.0.co;2-o

Cited by 6 publications

(2 citation statements)

References 12 publications

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“…Hybrid rocket engines (HREs) are propulsive systems with different phases of oxidizer and fuel stockpiled separately [1,2]. Based on this special structure, hybrid rockets have the advantages of high safety, low cost, adjustable thrust and on-off capability compared with solid rockets, and the advantages of simple structure and convenient operation compared with liquid rockets [3][4][5]. In addition, the hydrocarbons as the commonly used fuels have a minimal impact on environment [2].…”

Section: Introductionmentioning

confidence: 99%

Mechanical Modifications of Paraffin‐based Fuels and the Effects on Combustion Performance

Tang

Chen

Zhang

et al. 2017

Propellants Explo Pyrotec

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In order to enhance the mechanical properties, 6 kinds of additives of stearic acid, polyethylene wax (AÀC6A), ethylene vinyl acetate copolymer (EVA), low density polyethylene (LDPE), polypropylene (PP) and high density polyethylene (HDPE) were blended in the paraffin fuel. Mechanical properties of paraffin-based fuels were investigated by mixing 5 % in mass of different additives and increasing the mass percent of AÀC6A and LDPE. In addition, the combustion performance of the so modified paraffin-based fuels were tested by a 2D-radial burner at Nanjing University of Science and Technology. The effects of additives on regression rate were analyzed by thermal performance test (melting point and DSC) and viscosity measurement. Overall, all the additives can improve mechanical properties and the mechanical properties are enhanced by increasing mass% of additives. AÀC6A revealed the best for improving compressive strength (64.0 % increase by blending 5 mass %), LDPE revealed the best for improving tensile strength (105.3 % increase by blending 5 mass %). For combustion performance, the regression rates of paraffin-based fuels blended with stearic acid increased owing to the decreased melting points while the regression rates of the other five formulations decreased due to the increased melted liquid viscosity. The relationship between regression rate and viscosity is a power function which is not affected by additives at high temperature, thereby it is convenient to predict the regression rate by measuring viscosity.Keywords: Hybrid rocket propulsion · mechanical modified paraffin-based fuel · thermal and mechanical properties · melted liquid viscosity · regression rate [a] Y.

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Section: Introductionmentioning

confidence: 99%

Mechanical Modifications of Paraffin‐based Fuels and the Effects on Combustion Performance

Tang

Chen

Zhang

et al. 2017

Propellants Explo Pyrotec

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“…The advantage traditional hybrids have is the fuel grain is total incom bustible without oxidizer so it receives a reduced hazardous safety des ignation. They also have the advantage in th a t the combustion process is fairly well understood and is generally dictated by the heat transfer, heterogeneous fuel decom position, and fuel/oxidizer mixing process in the boundary layer diffusion flame [36].…”

Section: Forw Ard and A Ft In Jected H Y B Rid Smentioning

confidence: 99%

Investigation of injector system and gas generator propellant for aft-injected hybrid propulsion

Pilon¹

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In vestigation o f Injector S y stem and G as G enerator P rop ellan t For A ft-In jected H ybrid P ro p u lsio nby B r y a n P ilo n , B . E n g . A thesis subm itted to the Faculty of G raduate Studies and Research in partial fulfillment of the requirements for the degree of M a s t e r o f A p p lie d S c ie n c e O ttaw a-C arleton In stitu te for Mechanical and Aerospace Engineering D epartm ent of Mechanical and Aerospace Engineering C arleton U n iv ersity O ttaw a, Ontario, Canada

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Small hybrid thruster development for small satellite attitude control system

Mingireanu

Stoia-Djeska

2013

2013 6th International Conference on Recent Advances in Space Technologies (RAST)

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Through this work we show the development of small hybrid rocket thrusters intended for attitude control systems of small satellites and space-crafts. These thrusters have the advantage of being controllable and having higher specific impulse than the traditional solid fuel thrusters or hydrazine based thrusters. An internal ballistic model of the small hybrid thrusters is shown together with numerical results for the thrust curves and other relevant parameters. The internal ballistic model is shown to be influenced by the regression speed and the need for higher regression speed fuel-oxidizer pairs is, hence, shown. In the present study we also show how to couple the hybrid combustion process with the unsteady flow. Moderately high specific impulses can be obtained by using polypropylene as fuel and N02 as oxidizer. Detailed discussion is done on the construction of the thrusters as well as the engineering solutions for the combustion chamber, injector and nozzle. Several experimental thrust-curves are shown together with the estimation of total impulse and specific impulse.

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The Starting Transient in a Gas-Generator Hybrid Rocket Motor

Cited by 6 publications

References 12 publications

Mechanical Modifications of Paraffin‐based Fuels and the Effects on Combustion Performance

Mechanical Modifications of Paraffin‐based Fuels and the Effects on Combustion Performance

Investigation of injector system and gas generator propellant for aft-injected hybrid propulsion

Small hybrid thruster development for small satellite attitude control system

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