Experimental Characterization of Combustion Instabilities in High-Mass-Flux Hybrid Rocket Engines

Fraters, Arjan; Cervone, Angelo

doi:10.2514/1.b35485

Cited by 11 publications

(4 citation statements)

References 14 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Constraints two, five, and eight could potentially be relaxed, but careful consideration of their implications is advised. According to Fraters and Cervone [66], higher values of oxidizer mass flux may be feasible, but additional studies are required to precisely assess their impact on engine performance. Regarding the upper limit of the static margin (SM) (constraint five), conventional practice uses a reference value of two to mitigate the excessive influence of lateral winds [67].…”

Section: Number Design Variables (Dvs) Lower Bound (Lb) Upper Bound (Ub)mentioning

confidence: 99%

A Multidisciplinary Optimization Framework for Ecodesign of Reusable Microsatellite Launchers

Musso,

Figueiras,

Goubel

et al. 2024

Aerospace

View full text Add to dashboard Cite

The commercial space launch sector is currently undergoing a significant shift, with increasing competition and demand for launch services, as well as growing concerns about the environmental impact of rocket launches. To address these challenges, within the New Space Portugal project scope, a multidisciplinary framework for designing and optimizing new launch vehicles is proposed. Creating a more resilient and responsible space industry can be achieved by combining technological innovation and environmental sustainability, as emphasized by the framework. The main scope of the framework was to couple all the disciplines relevant to the space vehicle design in a modular way. Significant emphasis was placed on the infusion of ecodesign principles, including Life Cycle Assessment (LCA) considerations. Optimization techniques were employed to enhance the design and help designers conduct trade-off studies. In general, this multidisciplinary framework aims to provide a comprehensive approach to designing next-generation launch vehicles that meet the demands of a rapidly changing market while also minimizing their environmental impact. A methodology that leverages the strengths of both genetic and gradient-based algorithms is employed for optimizations with the objectives of maximizing the apogee altitude and minimizing the Global Warming Potential (GWP). Despite only being tested at the moment for sounding rockets, the framework has demonstrated promising results. It has illuminated the potential of this approach, leading to the identification of three optimal designs: one for maximizing the apogee, another for minimizing GWP, and a compromise design that strikes a balance between the two objectives. The outcomes yielded a maximum apogee of 6.41 km, a minimum GWP of 9.06 kg CO2eq, and a balanced compromise design featuring an apogee of 5.75 km and a GWP of 25.64 kg CO2eq.

show abstract

Section: Number Design Variables (Dvs) Lower Bound (Lb) Upper Bound (Ub)mentioning

confidence: 99%

A Multidisciplinary Optimization Framework for Ecodesign of Reusable Microsatellite Launchers

Musso,

Figueiras,

Goubel

et al. 2024

Aerospace

View full text Add to dashboard Cite

show abstract

“…European efforts for N 2 O-based sounding rockets include the results from the HEROS (Hybrid Experimental Rocket Stuttgart) project [105], a project exploiting paraffin-based fuel that achieved three successful launches over four years of the project's duration, and the activities of the Delft Aerospace Rocket Engineering (DARE) of TU Delft [118][119][120][121][122][123]. In the most recent DARE activities, a N 2 O-Sorbitol propellant combination has been developed.…”

Section: Nitrous Oxidementioning

confidence: 99%

Test Activities on Hybrid Rocket Engines: Combustion Analyses and Green Storable Oxidizers—A Short Review

2023

View full text Add to dashboard Cite

Hybrid rocket engines (HREs) offer a low-cost, reliable, and environmentally friendly solution for both launch and in-space applications. Hybrid propellants have been identified as green thanks to their use of non-toxic, non-carcinogenic oxidizers. Of particular relevance are storable oxidizers, namely high-concentration (≥90 wt.%) hydrogen peroxide (HP, H2O2) and nitrous oxide (N2O). This work provides a survey of experimental activities based on H2O2 and N2O for hybrid rocket propulsion applications. Open literature data are completed with original thermochemical calculations to support the discussion.

show abstract

“…Combustion instabilities cause gas pressure peaks and increase the heat transfer to the combustor walls to such an extent that may destroy the whole system. Hybrid rocket pressure oscillations of low frequency and large amplitude have been observed by many researchers [2][3][4][5][6][7]. Such manifestation is not as catastrophic for hybrid rocket engines as it is for liquid and solid systems.…”

Section: Introductionmentioning

confidence: 99%

Role of Precombustion Chamber Design in Feed-System Coupled Instabilities of Hybrid Rockets

Lee

Bertoldi

Andrianov

et al. 2020

Journal of Propulsion and Power

View full text Add to dashboard Cite

Oxidizer feed-system coupled instabilities have been observed in several liquid and hybrid propellant rocket engines, though, not likely to be catastrophic for the latter. However, severe pressure oscillation in hybrid rocket may result in a significant reduction in the performance of the propulsion system restricting the application of the technology. In this research, it was studied, theoretically and experimentally, feed-system coupled instabilities for hybrid rocket engines. Two test campaigns were performed to investigate the effects of the pre-combustion chamber and oxidizer injector configurations on engine pressure oscillation. Then, an extended mathematical formulation, including the injector pressure drop, the pre-combustion chamber residence time, the gas residence time, and the combustion time lag, has been proposed. The investigation was based on a transfer function using the stability limit analysis and the root locus method. It has been found that the configuration of pre-combustion chamber plays an important role in the nature of the feed

show abstract

Experimental Characterization of Combustion Instabilities in High-Mass-Flux Hybrid Rocket Engines

Cited by 11 publications

References 14 publications

A Multidisciplinary Optimization Framework for Ecodesign of Reusable Microsatellite Launchers

A Multidisciplinary Optimization Framework for Ecodesign of Reusable Microsatellite Launchers

Test Activities on Hybrid Rocket Engines: Combustion Analyses and Green Storable Oxidizers—A Short Review

Role of Precombustion Chamber Design in Feed-System Coupled Instabilities of Hybrid Rockets

Contact Info

Product

Resources

About