Papers by Keyword: Rocket Engine

Abstract: Anti-violent rocket on small UAV creatively combines the anti-riot shell with the UAV,utilizing the theory of rocket lanching,realizing that Anti-violent Shell is launched far in the sky.It is significant for CAPF to realize variety of targets battle in the emergency and mission. This paper focuses on sumulation and testing of anti-violent rocket engine on Small UAV,and the flight test-fired experimental of engine is carried on with control system,which demonstrates its feasibility.

Abstract: This paper according to a certain type of cluster bomb warhead built pressure chamber technical index requirements, design process a set of gas pressure device built principle prototype, and experimental study was carried out. Based on gas build pressure device working process research has determined its three working section: pressure rise section, pressure balance segment and pressure drop section, and then according to the rocket engine interior ballistic principle for each work period respectively calculated, get gas build pressure device and build pressure chamber of the interior ballistic pressure curve, and finally use of principle prototype experimental study. The theoretical calculation curve and test the measured curve have very good consistency; prove this paper established pressure calculation model is reasonable and credible for future related problems research provides a basis.

Abstract: RETRACTED ARTICLE: Metal-CO2 propulsion is less known than in-situ resource utilization (ISRU) technologies. This concept, based on using Martian carbon dioxide as an oxidizer in jet or rocket engines, offers the advantage of no chemical processing for CO2 and thus requires less power consumption than ISRU alternatives. In this paper, we study the burning behavior of the Mg in a CO2 atmosphere to assess the feasibility of using Mg/CO2 reactions as an in situ resource utilization technology for rocket propulsion and energy generation on other planets. From the experimental results, we can see that the critical ignition temperature increases with increasing the particle size and decreases with increasing the ambient pressure. In the CO2 atmosphere, we found the complicated sequence of interaction modes including pulsating combustion in a wide range of ambient temperatures. The pulsation frequency is determined by the sample temperature at the phases of slow heterogeneous combustion between the flashes. The combustion mechanisms are discussed with consideration of processes in both a surface film and gas phase.

Abstract: In rocket engine combustion chambers, the cooling channels experience extremely high temperatures and environmental attack. Thermal protection can be provided by Thermal Barrier Coatings. Due to the need of good heat conduction, the inner combustion liner is made of copper. The performance of a standard coating system for nickel based substrates is investigated on copper substrates. Thermal cycling experiments are performed on the coated samples. Due to temperature limitations of the copper substrate material, no thermally grown oxide forms at the interface of the thermal barrier coating and the bond coat. Delamination of the coatings occurs at the interface between the substrate and the bond coat due to oxide formation of the copper at uncoated edges. In real service a totally dense coating can probably not be assured which is the reason why this failure mode is of importance. Different parameters are used for thermal cycling to understand the underlying mechanisms of delamination. Furthermore, laser heating experiments account for the high thermal gradient in real service. Pilot tests which led to a delamination of the coating at the substrate interface were performed successfully.

Abstract: In this work, potential problems with the application of polymer matrix composites (PMC) in extreme environments [1] is discussed. Then, two specific examples of the applications of PMCs in high voltage [2-7] and high temperature [8-15] situations are evaluated. The first example deals with damage evolution in high voltage composite insulators [2-7] with PMC rods subjected to a combined action of extreme mechanical, electrical and environmental stresses. These insulators are widely used in transmission line and substation applications around the world. Subsequently, advanced high temperature graphite/polyimide composites [8-15] are evaluated for aerospace applications. The composite investigated in this project were used to manufacture and successfully test a Rocket Based Combined Cycle (RBCC) third-generation, reusable liquid propellant rocket engine, which is one possible engine for a future single-stage-to-orbit vehicle [8].