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Daniele Cardillo, Francesco Battista, Giuseppe Gallo, Stefano Mungiguerra and Raffaele Savino
Firing test campaigns were carried out on a 200 N thrust-class hybrid rocket engine, using gaseous oxygen as an oxidizer and a paraffin-wax-based fuel. Different fuel grain lengths were adopted to extend the fuel characterization under different operatin...
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Ahmed Mahfouz, Gabriella Gaias, D. M. K. K. Venkateswara Rao and Holger Voos
In this paper, the problem of autonomous optimal absolute orbit keeping for a satellite mission in Low Earth Orbit using electric propulsion is considered. The main peculiarity of the approach is to support small satellite missions in which the platform ...
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Adrian Parzybut, Pawel Surmacz and Zbigniew Gut
This study investigates the use of MnxOy/Al2O3 and Pt/Al2O3 catalysts for the decomposition of hydrogen peroxide in thrusters. It describes the purpose, procedures, performance, and conclusions coming from the test campaign of the catalyst lifetimes. In ...
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Ruhao Hua, Qi Chen, Zhao Wan and Hao Chen
A body flap/RCS-integrated configuration is often used to achieve pitch trimming and controlled flight in near space for hypersonic vehicles. Under the high temperature and pressure load induced by the expansion wave at the nozzle exit, the body flap is ...
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Maël Renault and Vaios Lappas
The recent growth in maturity of paraffin-based hybrid propulsion systems reassesses the possibility to design an alternative Mars Ascent Vehicle (MAV) propelled by a European hybrid motor. As part of the Mars Sample Return (MSR) campaign, a Hybrid MAV w...
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Ye Chen, Zhongxi Hou, Bingjie Zhu, Zheng Guo and Boting Xu
The performance of a single expansion ramp nozzle (SERN) drastically declines on over-expanded conditions. A numerical code can accurately predict nozzle performance in the over-expanded state, which is crucial for the SERN configuration design. A Reynol...
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Henrik Feuk, Francesco Pignatelli, Arman Subash, Ruike Bi, Robert-Zoltán Szász, Xue-Song Bai, Daniel Lörstad and Mattias Richter
The surface temperature of a burner nozzle using three different pilot hardware configurations was measured using lifetime phosphor thermometry with the ZnS:Ag phosphor in a gas turbine model combustor designed to mimic the Siemens DLE (Dry Low Emission)...
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Songyan Tian, Yanhui Duan and Hongbo Chen
To facilitate future Hypersonic Flight Vehicle (HFV) implementation with high maneuverability throughout its reentry trajectory, an Active Jets-Matrix (AJM) is designed to serve as the flapless pitch control surface. The AJM consists of four control grou...
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Guangyu Wang, Shijie Liu, Haoyang Peng and Weidong Liu
A continuous detonation engine with various exhaust nozzles, analogous to typical scramjet cavity combustors with variable rear-wall heights, was adopted to perform a succession of cylindrical air-breathing continuous rotating detonation experiments fuel...
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Lucian Hanimann, Luca Mangani, Marwan Darwish, Ernesto Casartelli and Damian M. Vogt
The use of coupled algorithms for single fluid flow simulation has proven its superiority as opposed to segregated algorithms, especially in terms of robustness and performance. In this paper, the coupled approach is extended for the simulation of multi-...
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