Study of Paraffin/H2O2 Hybrid Rockets for Launching Nanosats

Costa, F. P.; Contaifer, Ricardo A.; Albuquerque-Jr, José; Espaciais, Pesquisas; Paulista, C.; Gabriel, Stephen; Marques, Rodrigo Intini

doi:10.2514/6.2008-4542

Cited by 6 publications

(3 citation statements)

References 5 publications

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“…A 150-200 kg payload is planned to be launched into the 250-300 km orbit in Russia using a two-stage HRM-powered SLV [11]. 98% H 2 O 2 /paraffin is used for the air/ground-launched SLV to send a 20 kg payload into the 300 km circle orbit [12]. Rhee et al have conducted research on application of the HRM with HTPB/LOX combination to the first stage of an air launch system [13].…”

Section: Introductionmentioning

confidence: 99%

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Zhu

Wang

et al. 2021

International Journal of Aerospace Engineering

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In this paper, the effects of different grain shapes of a hybrid rocket motor (HRM) and different payload mass/orbit heights on the design of small launch vehicles (SLVs) are systematically discussed. An integrated overall design model for the hybrid rocket motor-powered small launch vehicle (HPSLV) is established, and two groups of three-stage SLVs capable of sending small payloads to the low earth orbit (LEO) are designed and optimized. In the first group, the SLVs with different grain shapes and different numbers of chambers in HRMs at the 1st and the 2nd stages are optimized and analyzed. In the second group, the SLVs capable of sending different payload mass to different orbit heights are optimized and analyzed. Pareto graphs of the design results show that the design of HRM at the 1st stage has the greatest impact on the take-off mass, total velocity increment, and maximum axial overload of the SLV. Self-organizing maps show that the take-off mass, maximum diameter, overall length, and velocity increment of the SLVs have the same variation tendency. For the 1-chamber HRM at the 1st stage, the wheel-shaped grain is better than circle-shaped and star-shaped grains in terms of reducing the total mass and length of the SLV, and the 4-chamber parallel HRM has more advantages over all 1-chamber designs for the same reason. The theoretical velocity increments are calculated by the Tsiolkovsky formula, and the actual velocity increments are obtained based on the trajectory simulation data. The results indicate that the HPSLV has a regular distribution in terms of the ratio of theoretical (actual) velocity increments at three different stages, and the estimated distribution ratio is around 1 : 1.55 : 1.69 (1 : 1.9 : 2.39), which can provide some reference for future development of HPSLV.

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Section: Introductionmentioning

confidence: 99%

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Zhu

Wang

et al. 2021

International Journal of Aerospace Engineering

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“…Its maiden flight reached an altitude of 107 km [43]. While these advances stimulated further work on small launch vehicles using hybrid HTP stages [43,64], such concepts were already proposed earlier [65][66][67][68] and thrust ranges tested in the United States in around 1950 also considered the use of HTP hybrids in large vehicles. As for nowadays, the Australian company Gilmour Space Technologies develops HTP hybrids [36] with thrust up to 91 kN-demonstrated during a single port motor firing in early 2021 [69].…”

Section: Introductionmentioning

confidence: 99%

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

et al. 2021

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This paper presents the development of indigenous hybrid rocket technology, using 98% hydrogen peroxide as an oxidizer. Consecutive steps are presented, which started with interest in hydrogen peroxide and the development of technology to obtain High Test Peroxide, finally allowing concentrations of up to 99.99% to be obtained in-house. Hydrogen peroxide of 98% concentration (mass-wise) was selected as the workhorse for further space propulsion and space transportation developments. Over the course nearly 10 years of the technology’s evolution, the Lukasiewicz Research Network—Institute of Aviation completed hundreds of subscale hybrid rocket motor and component tests. In 2017, the Institute presented the first vehicle in the world to have demonstrated in-flight utilization for 98% hydrogen peroxide. This was achieved by the ILR-33 AMBER suborbital rocket, which utilizes a hybrid rocket propulsion as the main stage. Since then, three successful consecutive flights of the vehicle have been performed, and flights to the Von Karman Line are planned. The hybrid rocket technology developments are described. Advances in hybrid fuel technology are shown, including the testing of fuel grains. Theoretical studies and sizing of hybrid propulsion systems for spacecraft, sounding rockets and small launch vehicles have been performed, and planned further developments are discussed.

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“…Moreover,t he inherent nature of most current conventional solid propellants can't meet the requirementso fe nvironmental protection.C ompared with current solid propellants, some current liquid propellants, such as LO 2 /LH 2 and H 2 O 2 /kerosene have higher I sp performance and possess environmentallyf riendly properties. However,t he complicated system of these liquid propellants is ad isadvantage for their application.T oa void the disadvantage of conventional solid propellants and liquid propellants, some new kinds of propellants haveb een explored by researchers,s uch as cryogenic solid propellant (CSP) [1],s olid-liquid hybrid propellant [2],g el propellant [3],e tc. Among them, CSP is more attractive because it combinest he simplicity of solid propellants and high I sp performance of liquid propellants.…”

Section: Introductionmentioning

confidence: 99%

A Novel Kind of Green Solid Propellant Containing H₂O₂ Cured at Room Temperature (SPHP)

Zhang

Pang²,

Xiao³

et al. 2015

Propellants Explo Pyrotec

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A novel kind of green solid propellant containing H2O2 cured at room temperature (SPHP) was prepared by a “two‐steps” method, and its stability, mechanical properties, sensitivity, and combustion behavior were characterized. Stable storage of SPHP can be achieved at room temperature by selecting propellant ingredients with perfect compatibility with H2O2 and the addition of a complex stabilizer into propellant formulation. In addition, the obtained SPHP showed a lower tensile strength and higher elongation compared with conventional solid propellant. The experimental results showed that the sensitivity of SPHP was considerably low, but its combustion efficiency and C* efficiency were really high. The hot firing tests demonstrated the stable and smokeless combustion of SPHP, as well as its combustion behavior within the pressure range of 2–10 MPa was in agreement with Vieille’s law and thus can be represented by r=9.95P0.57.

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Study of Paraffin/H2O2 Hybrid Rockets for Launching Nanosats

Cited by 6 publications

References 5 publications

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

A Novel Kind of Green Solid Propellant Containing H₂O₂ Cured at Room Temperature (SPHP)

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Study of Paraffin/H2O2 Hybrid Rockets for Launching Nanosats

Cited by 6 publications

References 5 publications

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Design Optimization and Parameter Analysis of a Hybrid Rocket Motor-Powered Small LEO Launch Vehicle

Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer

A Novel Kind of Green Solid Propellant Containing H2O2 Cured at Room Temperature (SPHP)

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A Novel Kind of Green Solid Propellant Containing H₂O₂ Cured at Room Temperature (SPHP)