Numerical Investigation on Influence on the Regression Rate of the Inlet Parameters in Solid Fuel Scramjet Combustor

2014 ◽  
Author(s):  
Changxiu Liu ◽  
Zhi-jun Wei ◽  
Hongwei Chi ◽  
Lihe Wang
Keyword(s):  
Numerical Investigation ◽  
Solid Fuel ◽  
Regression Rate ◽  
Scramjet Combustor

Numerical Investigation on Internal Regressing Shapes of Solid-Fuel Scramjet Combustor

2013 ◽  
Vol 29 (5) ◽  
pp. 1041-1051 ◽  
Author(s):  
Xinyan Pei ◽  
Zhiwen Wu ◽  
Zhijun Wei ◽  
Junyi Liu
Keyword(s):  
Numerical Investigation ◽  
Solid Fuel ◽  
Scramjet Combustor

Numerical investigation on operation characteristic of ramjet projectile

2019 ◽  
Vol 91 (7) ◽  
pp. 967-976
Author(s):  
Chang-Fei Zhuo ◽  
Ming-Xiao Wang ◽  
Wen-Jin Yao ◽  
Wen-ke Xu
Keyword(s):  
Mach Number ◽  
Kinetic Energy ◽  
Numerical Investigation ◽  
Solid Fuel ◽  
High Speed ◽  
Combustion Characteristic ◽  
Regression Rate ◽  
Content Type ◽  
Fuel Surface ◽  
Attachment Point

Purpose The purpose of this paper is to study the operation performance of the high-speed ramjet kinetic energy projectile using solid fuel ramjet as power plant that is a new short-range and small caliber projectile. Design/methodology/approach The numerical investigation on combustion characteristic of polyethylene in high-speed ramjet kinetic energy projectile is carried out in this paper. The flow characteristics’ differences are analyzed when ramjet works or do not work, and both the combustion characteristics and propulsive performance are analyzed when ramjet works. Findings The results show that with the increase of the abscissa x, the flame front is close to solid fuel surface at first and then keeps away from solid fuel surface. With the increase of the abscissa x, the temperature of solid fuel surface and regression rate of solid fuel continues to increase before re-attachment point and then decreases, which a maximum locate at the re-attachment point. Both the average temperature and the regression rate on the surface of the solid fuel tend to rise as the increase of inflow Mach number. As the inflow of Mach number increases, the mass flow rate of gaseous fuel increases. Practical implications The research results can provide useful database for the subsequent research on high-speed ramjet kinetic energy projectile. Originality/value This paper studies the operation characteristics of the ramjet projectile, especially the effect of the change of the flight velocity on the performance of high-speed ramjet projectile.

Experimental and Numerical Investigation of a Solid-Fuel Rocket Scramjet Combustor

2016 ◽  
Vol 32 (2) ◽  
pp. 273-278 ◽  
Author(s):  
Zhong Lv ◽  
Zhi-xun Xia ◽  
Bing Liu ◽  
Yuan-chun Liu
Keyword(s):  
Numerical Investigation ◽  
Solid Fuel ◽  
Scramjet Combustor

Numerical investigation of a combined solid fuel scramjet combustor

2018 ◽  
Vol 148 ◽  
pp. 210-219 ◽  
Author(s):  
Ming Hu ◽  
Zhijun Wei ◽  
Shiqi Ding ◽  
Ningfei Wang
Keyword(s):  
Numerical Investigation ◽  
Solid Fuel ◽  
Scramjet Combustor

Numerical Investigation of Self-Ignition Characteristics of Solid-Fuel Scramjet Combustor

2015 ◽  
Vol 31 (4) ◽  
pp. 1019-1032 ◽  
Author(s):  
Hong-wei Chi ◽  
Zhi-jun Wei ◽  
Li-he Wang ◽  
Biao Li ◽  
Zhi-wen Wu
Keyword(s):  
Numerical Investigation ◽  
Solid Fuel ◽  
Scramjet Combustor ◽  
Ignition Characteristics

scholarly journals Challenges of Ablatively Cooled Hybrid Rockets for Satellites or Upper Stages

Aerospace ◽  
2021 ◽  
Vol 8 (7) ◽  
pp. 190
Author(s):  
Francesco Barato
Keyword(s):  
Combustion Chamber ◽  
Solid Fuel ◽  
Diameter Ratio ◽  
Propulsion System ◽  
Burning Time ◽  
Regression Rate ◽  
Hybrid Propulsion ◽  
Deep Impact ◽  
Time Ratio ◽  
Hybrid Rockets

Ablative-cooled hybrid rockets could potentially combine a similar versatility of a liquid propulsion system with a much simplified architecture. These characteristics make this kind of propulsion attractive, among others, for applications such as satellites and upper stages. In this paper, the use of hybrid rockets for those situations is reviewed. It is shown that, for a competitive implementation, several challenges need to be addressed, which are not the general ones often discussed in the hybrid literature. In particular, the optimal thrust to burning time ratio, which is often relatively low in liquid engines, has a deep impact on the grain geometry, that, in turn, must comply some constrains. The regression rate sometime needs to be tailored in order to avoid unreasonable grain shapes, with the consequence that the dimensional trends start to follow some sort of counter-intuitive behavior. The length to diameter ratio of the hybrid combustion chamber imposes some packaging issues in order to compact the whole propulsion system. Finally, the heat soak-back during long off phases between multiple burns could compromise the integrity of the case and of the solid fuel. Therefore, if the advantages of hybrid propulsion are to be exploited, the aspects mentioned in this paper shall be carefully considered and properly faced.

scholarly journals NUMERICAL INVESTIGATION OF THE EFFECT OF AERODYNAMIC FRAGMENTATION OF CONDENSATE PARTICLES ON THE TWO-PHASE IMPULSE LOSSES IN A SOLID-FUEL ROCKET ENGINE NOZZLE

2017 ◽  
pp. 88-94
Author(s):  
Nikolay Nikolaevich DYACHENKO ◽  
◽  
Lyudmila Ivanovna DYACHENKO ◽  
Valeriya Sergeevna GUROVA ◽  
Sofiya Aleksandrovna SINEOKAYA ◽  
...  
Keyword(s):  
Numerical Investigation ◽  
Solid Fuel ◽  
Rocket Engine ◽  
Two Phase
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