DEVELOPMENT OF PARAFFIN BASED FUEL FOR HYBRID ROCKET MOTOR

DEVELPOMENT OF PARAFFIN BASED FUEL FOR HYBRID ROCKET MOTOR

Presented byJHUMKI NANDY

ME/SER/10005/2012

Under the Guidance of Dr. P.C.JOSHI

DEPARTMENT OF SPACE ENGINEERING & ROCKETRYBIRLA INSTITUTE OF TECHNOLOGY

MESRA , RANCHI - 835215

CONTENTSIntroductionObjectiveLiterature ReviewWork done Determination of Mechanical properties Determination of Heat of combustion Determination of Regression RateResults and DiscussionConclusionsFuture Scope of WorkReferences

INTRODUCTION

Introduction Rocket propulsion is a class of jet propulsion that produces thrust by ejecting stored matter, called the propellant. Rocket propulsion systems in which fuel & oxidizer are stored in different physical state prior to the combustion are called hybrid propulsion systems. Such systems most commonly employ a liquid oxidizer and solid fuel. In this hybrid motor concept, oxidizer is injected into a pre-combustion or vaporization chamber upstream of the primary fuel grain. The fuel grain contains numerous axial combustion ports to generate the fuel vapour to react with the injected oxidizer.

ADVANTAGES OF HYBRID ROCKET MOTOR Use of Energetic Propellant Ingredients.

Handling.

Casting.

Safety.

Reliability and Simplicity.

Fuel Versatility .

Oxidizer Control.

Environmental Friendliness.

Low Cost.

DISADVANTAGES OF HYBRID ROCKET MOTOR

Performance.

Low fuel regression rate.

Low Bulk Density.

Mixture Ratio Shifting.

Combustion Inefficiencies.

Slow Transient Response to Throttling

Wax was selected as a solid fuel – this fuel has several advantages over the classical fuel system e.g. HTPB system. These advantages are: • Paraffin wax on melting layer produces a very thin, low

viscosity, low surface tension liquid layer on the fuel surface when it burns.

• The instability of this layer is driven by the oxidizer gas flow in the port and leads to the lift-off of droplets and entrainment of droplets into the gas stream greatly increasing the overall fuel mass transfer rate.

• Regression rate is 3-5 times as high as the classic polymeric fuels (including HTPB) enabling efficient, single-port designs.

• The fuel is non-toxic, non-carcinogenic, non-hazardous and environmentally friendly.

• No polymerization reactions are involved. No curing agents are required.

• Being inert, paraffin based fuels effectively have an infinite storage life.

OBJECTIVE

Low regression rate problem for hybrid rocket propulsion system to be compensated by using paraffin wax as a solid fuel, solid paraffin fuels that burn at regression rates 3 to 4 times faster than polymeric fuels. One of the major short-coming with paraffin wax fuel grain is its poor mechanical strength. The present work is directed towards an attempt to improve the mechanical properties of paraffin wax by incorporating certain additives like stiffening agent stearic acid, low density poly ethylene, ethylene vinyl acetate co-polymer in a small percentage and then study.

LITERATURE REVIEWResearch at Stanford University in the late 1990’s by Karabeyoglu, Altman and Cantwell led to the identification of solid paraffin fuels that burn at regression rates 3 to 4 times faster than polymeric fuels. Heat transfer from the combustion zone and the action of the gas flow over the melting fuel surface, leads to the formation of a thin, hydro-dynamically unstable liquid film.

Karabeyuglu et al, put forward a mass transfer mechanism involving the entrainment of liquid droplets from the surface melt layer. As Karabeyuglu demonstrated, droplet formation is due to liquid layer instabilities, which result from the high-velocity gas flow in the port. Because of complex nature of the problem, the modelling was performed in three stages. Initially, the requirements for the formation of a melt layer on the fuel grain was investigated. In the second stage, the linear stability of a thin melt layer under the strong shear of a gas flow was considered.

Changjin6, et al. conducted a series of experimental investigation to optimise the conditions of oxidiser swirl flow and grain configuration for enhancement of regression rate of solid fuel. PMMA with gaseous oxygen was the solid fuel for investigation.

The ignition of the paraffin/polyethylene as solid fuel, regression rates and burning performance with gaseous oxygen were studied by Santos et al. The main conclusion of their work was that the regression rate of paraffin-based fuel enhanced two to three folds compared to the ultra-high molecular weight polyethylene.

Daniel B. Larson,John D. Desain, Eric Boyer studied the inclusion of various additives to paraffin wax for use in a hybrid rocket motor. Some of the paraffin-based fuels were doped with various percentages of LiAlH4 (up to 10%). Addition of LiAlH4 at 10% was found to increase regression rates between 7 – 10% over baseline paraffin through tests in a gaseous oxygen hybrid rocket motor.

The Peregrine Sounding Rocket Programme is a collaborative effort between the NASA Ames Research Centre, NASA Wallops, Stanford University, and the Space Propulsion Group (SPG) in an attempt to flight test a liquefying fuel hybrid sounding rocket to an altitude of 100 km. Dyer et al. initiated the propulsion system comprises of liquid nitrous oxide and paraffin-based fuel, which delivers a 5 kg payload to its predetermined altitude.

WORK DONE

1.Formulation of different fuel composition using certain additives like stiffening agent stearic acid, araldite, low density polyethylene, ethylene vinyl acetate.

2.Determination of Mechanical Properties of Fuel Samples.

3. Determination of Heat of Combustion of Fuel Samples.

4. Regression Rate Study.

5. To Study the Regression Rate in Hybrid Test Motor Essential Components like Combustion Chamber, Injector, Nozzle, have been Designed and Fabricated.

6.Calculation of regression rate.

MECHANICAL PROPERTIES OF THE FUEL SAMPLES

StressStrainElasticityStrengthTensileElongationDuctileFractureTensionFlexuralPlasticity

DETERMINATION OF THE MECHANICAL PROPERTIES OF SOLID FUEL FOR HYBRID ROCKET PROPULSION SYSTEM

• In case of hybrid system the fuel is a solid material that must be stored and held together by the material properties of the fuel grain itself.

• For large scale motors the tensile properties must be known in order to understand how the fuel grain will respond during storage, assembly and usage.

In the present work an attempt has been made to improve the mechanical properties of wax by adding the strength enhancer in different proportions. The experimental data have been obtained by analyzing stress-strain curve obtained using Universal Test Machine (UTM-made by INSTRON-model no: 1133). Eight fuel compositions were prepared using the various ingredients in different proportion and subjected to stress-strain analysis.

Sample No:

Paraffin Wax in

(%)

Stearic Acid in (%)

Araldite in (%)

Hardener in (%)

Carbon

Black in (%)

1.

2.

3.

4.

5.

100

90

90

85

93

0

10

9

8

0

0

0

0

4

4

0

0

0

0.85

0.93

0

0

0.9

0.85

0.93

GROUP-I

Sample No:

Paraffin

Wax in

(%)

Stearic

Acid in

(%)

Araldite

in (%)

Hardener

in (%)

Carbon

Black in (%)

LDPE

in (%)

EVA

in (%)

6.

7.

8.

82

82

78

8

8

7.8

4

4

3.9

0.82

0.82

0.78

1.0

1.0

1.0

4

0

4

0

4

4

GROUP-II

STRESS vs %STRAIN RATE GRAPH

Fig (1):TENSILE TEST GRAPH FOR P.W

% STRAIN

Fig (1):FLEXURAL TEST GRAPH FOR P.W

SAMPLENO:

Pmax E EU Et Neckingstrain

1. 20 2.84 109 0.6 1 2.4 4 1.6

Pmax= Maximum Load in (N)=Maximum Flexural Strength in (MPa)E=Young Modulus in (MPa)=Ultimate Tensile Strength in (MPa)=Yield Strength in (MPa)EU=Uniform ElongationEt=Total Elongation STR

ESS

in (

MPa

)ST

RE

SS in

(M

Pa)

% STRAIN

Fig(2):PW-STEARIC ACID


Fig(2):PW-STEARIC ACID

SAMPLENO:


2. 9 4.48 157.72

0.58 1.17 1.55 3.09 1.174

Pmax= Maximum Load in (N)=Maximum Flexural Strength in (MPa)E=Young Modulus in (MPa)=Ultimate Tensile Strength in (MPa)=Yield Strength in (MPa)EU=Uniform ElongationEt=Total Elongation

STR

ESS

in (

MPa

)

% STRAIN

STR

ESS

in (

MPa

)

% STRAIN

Fig:(3)PW-STEARIC ACID-CARBON BLACKFig(3):PW-S.A.-CARBON BLACK


SAMPLENO:


3. 19 2.74 136 0.65 0.66 0.94 2.65 1.70


STR

ESS

in (

MPa

)

% STRAIN

STR

ESS

in (

MPa

)

% STRAIN

Fig:(4)PW-S.A-ARALDITE-CARBON BLACK-HARDENER

Fig(4):PW-S.A-ARALDITE-HARDENER-Carbon black


SAMPLENO:


4. 15 2.82 75.5 0.79 0.44 1.10 2.57 1.471


STR

ESS

in (

MPa

)

% STRAIN

STR

ESS

in (

MPa

)

% STRAIN


Fig(5):PW-ARALDITE- HARDENER-Carbon black

Fig(5):PW-ARALDITE-HARDENER-Carbon black

SAMPLENO:


5. 15 3.17 56.41

0.48 0.53 1.16 1.93 0.76


STR

ESS

in (

MPa

)

% STRAIN

STR

ESS

in (

MPa

)

% STRAIN

Fig:(6)PW-S.A-ARALDITE-HARDENER-C.B-LDPE

Fig(6):PW-ARALDITE-HARDENER-Carbonblack-LDPE


SAMPLENO:


6. 46 3.07 50.99 0.80 0.58 1.89 2.49 0.6


STR

ESS

in (

MPa

)

% STRAIN

STR

ESS

in (

MPa

)

% STRAIN

Fig(7):PW-S.A-ARLD-HARDENER-Carbon black-EVA

Fig(7):PW-S.A-ARLD-HARDENER-Carbon black-EVA


SAMPLENO:


7. 43 3.29 22.6 0.90 0.67 2.11 9.70 0.67


STR

ESS

in (

MPa

)

% STRAIN

STR

ESS

in (

MPa

)

% STRAIN

Fig(8):PW-S.A-ARLD-HARDENER-Carbon black-EVA-LDPE Fig(7):PW-S.A-ARLD-HARDENER-Carbon

black-EVA-LDPE


SAMPLENO:N


8. 41 5.86 225 1.38 1.42 1.65 1.98 0.32


STR

ESS

in (

MPa

)

% STRAIN

STE

SS in

(M

Pa)

% STRAIN


SAMPLENO:


1. 20 2.84 109 0.64 1.00 2.45 4.06 1.60

2. 9 4.48 157 0.58 1.17 1.55 3.09 1.17

3. 19 2.74 136 0.65 0.66 0.94 2.65 1.70

4. 15 2.82 75 0.79 0.44 1.10 2.57 1.47

5. 15 3.17 56 0.48 0.53 1.16 1.93 0.76

6. 46 3.07 50 0.80 0.58 1.89 2.49 0.6

7. 43 3.29 22 0.90 0.67 2.11 9.70 0.67

8. 41 5.86 225 1.38 1.42 1.65 1.98 0.32

Discussions of the results

It is observed that the value of total elongation obtained after addition of polymers LDPE & EVA is twice than that of pure paraffin wax. Young modulus for pure paraffin wax has been found to be 109.52MPa whereas the Young modulus obtained after the addition of second composition of additives comes out to be 225.62MPa, which is twice the value of Young modulus of pure paraffin wax. It is observed that the value of total elongation obtained after addition of polymers LDPE & EVA is twice than that of pure paraffin wax.

HEAT OF COMBUSTION OF FUEL SAMPLES

HEAT OF COMBUSTION MEASUREMENT

The adiabatic Bomb Calorimeter supplied by Arico Indian Laboratory is used to evaluate the calorific value of fuel of following three compositions:

Composition-1 Composition-2 Composition-3

Paraffin Wax

(100%)

Paraffin Wax (85.47%) Paraffin Wax

(78.36%)-------

Stearic Acid(8.54%) Stearic Acid(7.38)--------

Araldite(4.2%) Araldite(3.9%)--------

Hardener(0.85%) Hardener(0.78%)-------

Carbon Black(0.85%) LDPE(4%)-------

--------- EVA(4%)-------

--------- CarbonBlack(1%)

The calorific values of the above mentioned compositions obtained in the present work, is the following:

( )composition-1 =

( )composition-2 =

( )composition-3 =

It is found that the calorific value of pure paraffin wax alone and the sample composed of Paraffin Wax- Stearic Acid- Araldite –Hardener-LDPE-EVA- Carbon Black are same whereas the sample composed of Paraffin Wax- Stearic Acid- Araldite –Hardener- Carbon Black is much higher as compared to pure paraffin wax.

DESIGN AND FABRICATION WORK COMBUSTION CHAMBER The combustion chamber has an internal diameter of 79mm, outer diameter of 91.8mm, length of 275.4mm. At either end of chamber flanges of 168.5mm diameter were welded. The head-end flange is 23mm thick whereas the nozzle-end flange is 20mm thick. Six equidistant holes of 14mm diameter have been made at 128.1mm p.c.d on both the flanges to attach it with the injector and nozzle respectively.

INJECTOR In the present investigation swirl injector was used to feed the gaseous oxygen into the combustion chamber. It consists of a hollow cup of inner length 25mm and diameter 40mm and a centrally fitted tapered cylindrical block of length 30mm, maximum diameter 39mm and minimum diameter 30mm. This arrangement gives the oxidizer outlet area about 62mm2. A 5mm diameter hole was made tangentially at a distance of 5mm from the top for inletting the oxidizer.

NOZZLE

A water cooled straight cone convergent-divergent nozzle was used in the present investigation. The convergent angle was kept at 450 whereas the divergent angle was at 150. The total length of the nozzle was 66.7mm, the exit diameter 26.06mm, and maximum convergent side diameter was 79.4mm matching to the inner diameter of the combustion chamber. The wall thickness of nozzle was 5mm. It has a flange of diameter 110mm and thickness 20mm at the end of the convergent section to hold the nozzle to the combustion chamber by means of a nozzle retainer ring made of mild steel of diameter 168.5mm and having six equidistant holes of diameter 14mm at p.c.d 128.1mm with the help of nuts and bolts. A hollow cylindrical section of diameter 90mm and thickness 10mm was welded around this nozzle. Provisions were made in it for in-letting and out-letting the water in the vacant space between the nozzle and the cylinder. The water was fed into it with the help of 0.25hp water pump.

Fig. 1: Line diagram of combustion chamber (All dimensions are in mm)

Fig. 2 : Line diagram of swirl injector (All dimensions are in mm) Fig. 3 : Schematic Diagram of Nozzle and

Nozzle Retainer Ring (All dimensions are in mm)

Plate.1: Head end injection test motor assembly

PREPARATION OF GRAINSThe fuel mixture as obtained after mixing of the ingredients was casted in the clean mould and kept for curing first at low temperature and them at ambient temperature for 3hrs. The cylindrical port burning fuel grains of dimensions length-200 mm, O.D-68.5 mm, I.D-30mm were processed . The following ingredients were used to make the grains :PARAFFIN WAX : C28H58

Wax is an organic, plastic-like substance that is solid at ambient temperature and becomes liquid when melted. STEARIC ACID: C18H36O2

Stearic acid supplied by CDH was used in the present work. Its molecular formula is C18H36O and molecular weight is 284.5 gm. It is a hard white or faintly yellowish crystalline solid. Stearic acid is using as a good hardener and making easy to take out the grain from the mould.EPOXY RESIN: C13H18O2

An epoxy resin is defined as a molecule with more than one epoxy group, which can be hardened into a usable plastic. Such a substance in this context is called a hardener. One of epoxy plastic’s most characteristic properties is the capacity to adhere to most substrates.

EPI-CHLOROHYDRIN: (HARDENER) C3H5ClO

Epi-chlorohydrin is a colourless, volatile and flammable liquid with an irritating chloroform-like odour which emits toxic fumes when heated to decomposition.

EVA-COPOLYMER: (C2H4)n (C4H6O2)m

EVA-copolymer is a high flow-ability and high VA content ethylene vinyl acetate copolymer (EVA) with many excellent properties, such as characteristic flexibility and elasticity, thermal stability, good low temperature resistance, good compatibility and non-toxicity, etc. It possesses excellent heat stability flexibility and good compatibility with the petroleum wax. The hot melt made by EVA adheres with other materials which possess good adhesive strength.

LDPE: (C2H4)n

Polyethylene is a thermoplastic polymer consisting of long hydrocarbon chains. For common commercial grades of medium- and high-density polyethylene the melting point is typically in the range 120-1300C. The melting point for average, commercial, low-density polyethylene is typically 105-1150C.

Prepared grains has been shown in plate 2,3 and 4 respectively.

COMPOSITIONS:Composition No:

Paraffin wax in%

Stearic acid in %

Araldite in %

Hardener (epichlorohydrin) in%

Carbon black in %

LDPE in (gm )& %

EVA in (gm) & %

1. 100% 0 0 0 0 0 0

2. 85.47% 8.54% 4.27% 0.85% 0.85% 0 0

3. 78.36% 7.8% 3.91% 0.78% 1.01% 4% 4%

Plate 2: Hollow Cylindrical Grain of Pure Paraffin Wax

Plate3 : Hollow Cylindrical Grain of The Composition 1

Plate4 : Hollow Cylindrical Grain of The Composition 2

REGRESSION RATES FOR THE FUELS GRAINS

In the present investigation an attempt has been made to increase the mechanical strength of pure paraffin wax using different additives like stiffening agent stearic acid, araldite, hardener and other polymers in small proportion. A total of eight compositions were formulated using the above ingredients. From these formulations the following three compositions were subjected to regression rate study in a stream of gaseous oxygen using head end injection hybrid test motor in order to evaluate the relative regression rate of these formulations.

Composition-1 Composition-2 Composition-3

Paraffin Wax

(100%)

Paraffin Wax (85.47%) Paraffin Wax

(78.36%)-------

Stearic Acid(8.54%) Stearic Acid(7.38)--------

Araldite(4.2%) Araldite(3.9%)--------

Hardener(0.85%) Hardener(0.78%)-------

Carbon Black(0.85%) LDPE(4%)-------

--------- EVA(4%)-------

--------- CarbonBlack(1%)

The local regression rate along the length for fuel grain of different compositions have been prescribed in fig 4 and fig 5 for oxidizer injection pressure 300 p.s.i and 480 p.s.i respectively.

Fig. 4: Local Regression Rate Variation At Injection Pressure-300 p.s.i

Fig. 5: Local Regression Rate Variation At Injection Pressure-480 p.s.i

Firing Duration in (sec)

Fuel mass consumption rate in(gm/sec)

Average Regression Rate in (mm/sec)

Composition 1 6.071 59.66 5.07Composition 2 5.03 69.18 5.36Composition 3 4.625 36.41 4.10

Average Regression Rate and Average Mass Consumption Rate of Fuels at Injection Pressure 300 p.s.i & 480 p.s.i

Duration in (sec)

Fuel mass consumption rate in(gm/sec)

Average Regression Rate in (mm/sec)

Composition 1 5.16 68.91 5.48

Composition 2 5.20 89.53 6.14Composition 3 3.92 43.41 5.05

RESULTS It has been observed that the regression rate is highly uneven all along the length of the grain. In all cases the grain was completely consumed at-least up to 4cm of length at the beginning of the grain. It is also observed that the regression rate increase with composition change in order of sample1sample3 for both of the injection pressures. Further from the analysis of mechanical properties, it is seen that the tensile strength and young modulus for these samples is in order of sample.3. It has been observed that the composition which has higher mechanical strength has lower regression rate and lower mechanical strength has higher regression rate.

The average regression rate and average mass consumption rate for all three compositions at injection pressure 300 p.s.i are presented and for 480 p.s.i were observed higher for the composition of lower mechanical strength and lower for the composition of higher mechanical strength.

The exhaust flame in all these test firings was highly smoky except for composition-3 The appearance of such smoky flames, indicate that although the fuel grain is regressing it is not combusting properly within the combustion chamber.

Exhaust Plume of Grain of Paraffin Wax at Starting of firing at the Injection Pressure-300 p.s.i

Exhaust Plume of Grain of Paraffin Wax after 2sec of firing at the Injection Pressure 300 p.s.i

Exhaust Plume of Grain of Composition Paraffin Wax at the Starting of firing at the Injection Pressure-480 p.s.i

Exhaust Plume of Grain of Composition Paraffin Wax after 2sec of firing at the Injection Pressure-480 p.s.i

Exhaust Plume of Grain of Composition Paraffin Wax-Stearic acid-Araldite-Carbon Black at Starting of firing at the Injection Pressure-300 p.s.i

Exhaust Plume of Grain of Composition Paraffin Wax-Stearic acid-Araldite-Carbon Black After 2sec of firing at the Injection Pressure-300 p.s.i

Exhaust Plume of Grain of Composition Paraffin Wax-Stearic acid-Araldite-Carbon Black after 2 sec. of firing at the Injection Pressure-480 p.s.i

Exhaust Plume of Grain of Composition Paraffin Wax-Stearic acid-Araldite-Carbon Black after 2 sec. of firing at the Injection Pressure-480 p.s.i

Exhaust Plume of Grain of Composition Paraffin Wax-Stearic acid-Araldite-LDPE-EVA-Carbon Black at Starting of firing at the Injection Pressure-480 p.s.i

Exhaust Plume of Grain of Composition Paraffin Wax-Stearic acid-Araldite-LDPE-EVA-Carbon Black After 2sec of firing at the Injection Pressure-480 p.s.i

Exhaust Plume of Grain of Composition Paraffin Wax-Stearic acid-Araldite-LDPE-EVA-Carbon Black at Starting of firing at the Injection Pressure-300 p.s.i

Exhaust Plume of Grain of Composition Paraffin Wax-Stearic acid-Araldite-LDPE-EVA-Carbon Black After 2sec of firing at the Injection Pressure-300 p.s.i

CONCLUSIONS On comparing the different parameters concerning to mechanical properties of

the fuel formulations resulted in the outcome that the total elongation, young modulus and maximum tensile strength of pure paraffin wax has been changed to a great extent with addition of LDPE-EVA , stiffening agent stearic acid and araldite- hardener in 5:1 proportion.

It is found that the calorific value of paraffin wax along and the sample composed of Paraffin Wax- Stearic Acid- Araldite –Hardener-LDPE-EVA- Carbon Black are same whereas the sample composed of Paraffin Wax- Stearic Acid- Araldite –Hardener- Carbon Black is much higher as compared to paraffin wax. So, it has been concluded that the calorific value of paraffin wax can be improved by adding some particular type of additives.

It is also observed that the regression rate increase with composition change in order of sample-1sample.3 at both of the oxygen injection pressure. Further from the analysis of mechanical properties, it is seen that the tensile strength and young modulus for these samples are in order of sample.3. These results suggest that the composition which has higher mechanical strength has lower regression rate and the composition with lower mechanical strength has higher regression rate.

It has been observed that all the test firings except of composition-3 was highly smoky. appearance of such smoky flames indicates that although the fuel grain is regressing but it is not combusting properly within the combustion chamber.

FUTURE SCOPE OF WORK Enhancement of mechanical strength of paraffin wax without sacrificing the

regression rate requires extensive research and development work to meet the requirement of high thrust engine.

A potential study of combustion chamber pressure at different location during course of firing and analysis the pressure fluctuation for the unstable liquid layer combustion will be a great help in designing the hardware components, injector for hybrid rocket motor.

A through study of thermal properties of paraffin wax with different additives such as stearic acid-LDPE-EVA in a great proportion for developing a challenging hybrid fuel will be an interesting piece of investigation.

A computational analysis of combustion process using different fuel grain configuration in combination of different type of oxidizer injection system and different type of motor design will be helpful for further development of paraffin wax fuel based hybrid propulsion system.

REFERENCESKarabeyoglu, M.A., Cantwell, B.J., and Altman, D., “Development and Testing of Paraffin-Hybrid Rocket Fuels”, AIAA, July 2001, pp.2001-4503 paper.

Karabeyoglu, M.A., Zillac, G., Cantwell, B.J., De Zilwa, S.R.N., and Castelucci, P., “Scale-up Tests of High Regression Rate Paraffin-Based Hybrid Rocket Fuels”, Journal of Propulsion and Power, Vol.20, No.6, November-December 2004, pp. 1037-1045.

Smoot, L.D., Price, C.F., “Regression Rate Mechanism of non-metalized Hybrid Fuel System”, AIAA Journal, Vol.3, No.8, Aug. 1965, pp. 1408-1413.

Jacob, Eric J., “Nonlinear Combustion Instability Generalized Framework,” PhD Dissertation, Department of Aerospace Engineering, The University of Tennessee Knoxville, TN, 2009 .

Karabeyoglu, M. A., Thermal Transients in Hybrid Rocket Fuel Grains – Nonlinear Effects, 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 8-11 July 2007, Cincinnati, OH

Chiaverini, M. J., Serin, N., Johnson, D. K., Lu, Y.-C., Kuo, K. K. and Risha, G.A., 2000, “Regression Rate Behaviour of Hybrid Rocket Solid Fuels”, Journal of Propulsion and Power, Vol. 16, No. 1, pp. 125-132

Santos, L.M.C.; Almeida, L.A.R.; Fraga, A.M. & Veras, C.A.G. Experimental investigation of a paraffinbased hybrid rocket. J. Engenharia Térmica (Thermal Engineering), 2006, 5(1), 08-12.

1Dyer, J., Doran, E., Dunn, Z., and Lohner, K., “Design and Development of a 100 km Nitrous Oxide/Paran Hybrid Rocket Vehicle," Joint Propulsion Conference and Exhibit, July 2007.

Larson, D. B., et al., “Characterization of the Performance of Paraffin/LiAlH4 Solid Fuels in a Hybrid Rocket System,” AIAA 2011-5822, 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, San Diego, CA, July 31 – August 3, 2011.

Karabeyoglu, M.A., Cantwell, B.J. and Altman, D., 2001,“Development and Testing of Paraffn-Based Hybrid RocketFuels”, in Proceedings of the 37th AIAA/ASME/SAE/ASEEJoint Propulsion Conference and Exhibit, July 2001, AIAA Paper2001-4503.

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DEVELOPMENT OF PARAFFIN BASED FUEL FOR HYBRID ROCKET MOTOR

Engineering

Transcript of DEVELOPMENT OF PARAFFIN BASED FUEL FOR HYBRID ROCKET MOTOR