Thrust Modulation in a Nitrous Oxide/Hydroxyl-Terminated Polybutadiene Hybrid Rocket Motor

Rajesh, K.

doi:10.2514/6.2006-4503

Cited by 7 publications

(2 citation statements)

References 2 publications

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“…The enthalpies of formation of HTPB have been previously published and can vary widely as the relative degrees of polymerization and curative treatments for the mix are modified [10][11][12]. To verify applicability of the group addition process for rocket combustion, the method described in the preceding paragraph was used to calculate the enthalpy of formation of HTPB.…”

Section: Chemical Analysis Of Hydroxyl-terminated Polybutadiene mentioning

confidence: 99%

Comparing Hydroxyl Terminated Polybutadiene and Acrylonitrile Butadiene Styrene as Hybrid Rocket Fuels

Whitmore

Peterson

Eilers

2013

Journal of Propulsion and Power

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Acrylonitrilebutadiene-styrene thermoplastic, widely mass-produced for noncombustion applications including household plumbing and structural materials, is evaluated and compared with hydroxyl-terminated polybutadiene as a potential fuel for hybrid rocket motors. Acrylonitrilebutadiene-styrene has several mechanical properties, including its ability to be fabricated into a wide variety of shapes using fused deposition modeling, which are very attractive as a potential hybrid rocket fuel. The acrylonitrilebutadiene-styrene grains were fabricated using fused deposition modeling from existing rapid-prototyping stock materials composed of 50∶43∶7 butadiene, acrylonitrile, and styrene mole fractions. The acrylonitrilebutadiene-styrene grains were burned with nitrous oxide as the matching oxidizer and compared for performance and consistency against fuel grains of equal size cast from hydroxylterminated polybutadiene and burned with nitrous oxide. Test results demonstrate a higher burn-to-burn consistency for acrylonitrilebutadiene-styrene, but slightly reduced overall performance. Methods for increasing the burn energy of the acrylonitrilebutadiene-styrene fuel grains were investigated. Equilibrium chemistry calculations conclude that, for a given oxidizer-to-fuel ratio, varying the butadiene mole fraction in the acrylonitrilebutadiene-styrene formulation has a significant effect on the propellant performance. A major result of this research is the demonstrated viability of thermoplastic as a hybrid rocket fuel grain material.

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Section: Chemical Analysis Of Hydroxyl-terminated Polybutadiene mentioning

confidence: 99%

Comparing Hydroxyl Terminated Polybutadiene and Acrylonitrile Butadiene Styrene as Hybrid Rocket Fuels

Whitmore

Peterson

Eilers

2013

Journal of Propulsion and Power

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“…The capability of a N 2 O/HTPB hybrid rocket motor for thrust modulation for a specified mission is demonstrated by calculation 34 . For most of the present-day applications, the system design is optimised over the range of mixture ratios encountered with very little degradation of average specific impulse due to throttling.…”

Section: Issues Of Thrust Throttlingmentioning

confidence: 99%

Hybrid Rocket Technology

Venugopal¹,

Rajesh²,

Ramanujachari³

2011

DSJ

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With their unique operational characteristics, hybrid rockets can potentially provide safer, lower-cost avenues for spacecraft and missiles than the current solid propellant and liquid propellant systems. Classical hybrids can be throttled for thrust tailoring, perform in-flight motor shutdown and restart. In classical hybrids, the fuel is stored in the form of a solid grain, requiring only half the feed system hardware of liquid bipropellant engines. The commonly used fuels are benign, nontoxic, and not hazardous to store and transport. Solid fuel grains are not highly susceptible to cracks, imperfections, and environmental temperature and are therefore safer to manufacture, store, transport, and use for launch. The status of development based on the experience of the last few decades indicating the maturity of the hybrid rocket technology is given in brief.

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Design and integrated simulation of a pressurized feed system of the dual-thrust hybrid rocket motor

Junhai

Zeng

et al. 2013

Sci. China Technol. Sci.

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Thrust Modulation in a Nitrous Oxide/Hydroxyl-Terminated Polybutadiene Hybrid Rocket Motor

Cited by 7 publications

References 2 publications

Comparing Hydroxyl Terminated Polybutadiene and Acrylonitrile Butadiene Styrene as Hybrid Rocket Fuels

Comparing Hydroxyl Terminated Polybutadiene and Acrylonitrile Butadiene Styrene as Hybrid Rocket Fuels

Hybrid Rocket Technology

Design and integrated simulation of a pressurized feed system of the dual-thrust hybrid rocket motor

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