Experimental Study of Test Medium Vitiation Effects on Dual-Mode Scramjet Mode Transition

2010 ◽  
Author(s):  
Robert Rockwell ◽  
Christoper Goyne ◽  
Willie Haw ◽  
Roland Krauss ◽  
James McDaniel ◽  
...  
Keyword(s):  
Experimental Study ◽  
Mode Transition ◽  
Test Medium ◽  
Dual Mode

Experimental Study of Test-Medium Vitiation Effects on Dual-Mode Scramjet Performance

2011 ◽  
Vol 27 (5) ◽  
pp. 1135-1142 ◽  
Author(s):  
Robert D. Rockwell ◽  
Christopher P. Goyne ◽  
Willie Haw ◽  
Roland H. Krauss ◽  
James C. McDaniel ◽  
...  
Keyword(s):  
Experimental Study ◽  
Test Medium ◽  
Dual Mode

Experimental Study on Mode Transition in a Dual-Mode Scramjet Combustor

2019 ◽  
Vol 192 (5) ◽  
pp. 852-870 ◽  
Author(s):  
Jianping Li ◽  
Kai Wang ◽  
Guiqian Jiao ◽  
Jinyuan Luo ◽  
Wenyan Song
Keyword(s):  
Experimental Study ◽  
Mode Transition ◽  
Dual Mode ◽  
Scramjet Combustor

Experimental study on ejector-to-ramjet mode transition in a divergent kerosene-fueled RBCC combustor with low total temperature inflow

2020 ◽  
Vol 99 ◽  
pp. 105734 ◽  
Author(s):  
Lei Shi ◽  
Guojun Zhao ◽  
Yiyan Yang ◽  
Fei Qin ◽  
Xianggeng Wei ◽  
...  
Keyword(s):  
Experimental Study ◽  
Mode Transition ◽  
Total Temperature

Pressure rising slope variation accompanying with combustion mode transition in a dual-mode combustor

2017 ◽  
Vol 68 ◽  
pp. 370-379 ◽  
Author(s):  
Chenlin Zhang ◽  
Juntao Chang ◽  
Shuo Feng ◽  
Jicheng Ma ◽  
Junlong Zhang ◽  
...  
Keyword(s):  
Mode Transition ◽  
Combustion Mode ◽  
Dual Mode

Distributed parameter control arithmetic for an axisymmetrical dual-mode scramjet

2008 ◽  
Vol 112 (1135) ◽  
pp. 557-565 ◽  
Author(s):  
C. Tao ◽  
Y. Daren ◽  
B. Wen
Keyword(s):  
Control Theory ◽  
Shape Control ◽  
Distributed Parameter ◽  
Mode Transition ◽  
Dual Mode ◽  
Transition Control ◽  
Wide Range ◽  
Mode Transition Control ◽  
Control Arithmetic ◽  
Smooth Transitions

AbstractDual-mode scramjet is one of the candidates for hypersonic flight propulsion system which will be used in wide range of flight Mach numbers from 4 to 12 or higher, wherein dual-mode scramjet should be well designed to be suitable for subsonic/supersonic combustion operation according to the flight conditions. Therefore this system is required to operate in a finite number of operational modes that necessitate robust, stable, and smooth transitions between them by which selective operability of supersonic/subsonic combustion modes and efficient combustor operation in these modes may be realised. A key issue in making mode transition efficient and stable is mode transition control. The major problem in mode transition control is the handling of the various flow and combustion coupling effects of dual-mode scramjet whose physical states are spatially coupled and whose governing equations are partial differential equations. Involving these distributed parameter issues, our basic idea is using the shape control theory to study the control problems of mode transition for dual-mode scramjet with the aim of achieving the desirable design properties and increasing control reliabilities. This specific approach is motivated by the promise of novel techniques in control theory developed in recent years. Concrete control arithmetic of this approach, such as shape control model, sensitivity analysis and gradient-based optimisation procedure, are given in this paper. Simulation results for an axisymmetric, wall-injection dual-mode scramjet show the feasibility and validity of the method.

Sign in / Sign up

Export Citation Format

Share Document