Criteria for hypersonic airbreathing propulsion and its experimental verification

Jiang, Zonglin; Zhang, Zijian; Liu, Yunfeng; Wang, Chun; Luo, Changtong

doi:10.1016/j.cja.2020.11.001

Cited by 59 publications

(9 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…2019; Jiang et al. 2021). Hence, a comprehensive understanding of ODWs is fundamental for their successful utility in ODEs, and substantial progress in understanding ODWs has been achieved in recent decades.…”

Section: Introductionmentioning

confidence: 99%

“…Due to their self-ignition, fast energy release and high thermal cycle efficiency, detonation phenomena as a combustion mode have attracted increasing attention in the development of hypersonic propulsion systems (Kailasanath 2000;Wolański 2013;Lu & Braun 2014). Among the different kinds of detonation-based engines (Roy et al 2004;Higgins 2006;Ma et al 2020), the oblique detonation engine (ODE) is expected to have more applications in hypersonic air-breathing propulsion at high flight Mach numbers because of the additional stabilization and reduced compression losses of oblique detonation waves (ODWs) (Qin & Zhang 2018;Ren et al 2019;Jiang et al 2021). Hence, a comprehensive understanding of ODWs is fundamental for their successful utility in ODEs, and substantial progress in understanding ODWs has been achieved in recent decades.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner

2022

Self Cite

View full text Add to dashboard Cite

The stabilization of oblique detonation waves (ODWs) in an engine combustor is important for the successful applications of oblique detonation engines, and comprehensively understanding the effects of the inviscid reflection of ODWs on their stabilization and the relevant mechanisms is imperative to overall combustor design. In this study, the flow fields of ODW reflections in a space-confined combustor are numerically studied by solving the two-dimensional time-dependent multispecies Euler equations in combination with a detailed hydrogen combustion mechanism. The inviscid Mach reflections of ODWs before an expansion corner are emphasized with different flight Mach numbers, Ma, and different dimensionless reflection locations, ζ ≥ 0 (ζ = 0: the ODW reflects precisely at the expansion corner; ζ > 0: the ODW reflects off the wall before the expansion corner). Two kinds of destabilization phenomena of the inviscid Mach reflection of an ODW induced by different mechanisms are found, namely wave-induced destabilization at large ζ > 0 for moderate (not very low) Ma and inherent destabilization at any ζ > 0 for low Ma. Wave-induced destabilization is attributed to the incompatibility between the pressure ratio across the Mach stem and its relative propagation speed, which is triggered by the action of the secondary reflected shock wave or the transmitted Mach stem on the subsonic zone behind the Mach stem. Inherent destabilization is demonstrated through an in-depth theoretical analysis and is attributed to geometric choking of the flow behind the Mach stem.

show abstract

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner

2022

Self Cite

View full text Add to dashboard Cite

show abstract

“…A wealth of analytic [1,3,4,7], experimental [2,[8][9][10], and numerical studies on the fundamental issues about the ODW induced by the wedge can be found in the literatures. Due to the complex physical phenomena of oblique detonation and the very demanding requirements on experimental conditions, high-resolution numerical simulation is still a more effective research method on oblique detonation initiation mechanism than an analytic and experimental method.…”

Section: Introductionmentioning

confidence: 99%

Formation and Evolution of Cellular Structures in Wedge-Induced Oblique Detonations

Luan

Jin

et al. 2023

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

Numerical simulation of an oblique detonation induced by a wedge is performed to investigate the formation and evolution of the oblique cellular detonation structure and the quantitative comparison of the cellular structure of a normal and an oblique detonation. The compressible reactive Euler equations are solved using the seventh-order WENO scheme on an adaptive mesh based on the open source program Adaptive Mesh Refinement in Object-oriented C++ (AMROC). The numerical results show that there are two sets of transverse waves, the left-running transverse waves (LRTW) and the right-running transverse waves (RRTW), which form the oblique cellular detonation structure. Although both sets of transverse waves are convected downstream, they propagate at almost the same relative velocity in the opposite direction. The LRTWs start in the transition zone because of the detonation instability. However, the RRTWs form due to the interaction between the deformed detonation front and the reflected shock wave from the wedge. For the same degree of overdrive, numerical simulations reveal that the characteristic cell size of an oblique detonation is almost the same as that of a normal detonation.

show abstract

“…Due to the outstanding rapid arrival, strong maneuvering, and precision strike capabilities of the HFV, the important strategic significance and extremely high application value exist in applications such as ultra‐high‐speed aerospace transportation and fast space shuttles. The technology of the HFV includes multiple disciplines such as aerodynamics, 1 propulsion, 2 heat transfer, 3 materials, 4 and flight control, 5‐7 among which flight guidance and control technology is one of the cores and key technologies for the development of the HFV. Generally, in research, HFVs can be divided into air‐breathing powered HFVs, unpowered re‐entry HFVs, and powered autonomously accelerating HFVs 8 .…”

Section: Introductionmentioning

confidence: 99%

Integrated guidance and control of hypersonic flight vehicle with coordinated mission requirement and input constraint

Shou

Yan

et al. 2023

Intl J Robust & Nonlinear

View full text Add to dashboard Cite

An integrated adaptive guidance and control algorithm is investigated for the hypersonic flight vehicle (HFV) under the objection of coordinated for mission requirement and control capability. The design pressure to avoid input saturation is placed in the guidance loop by analyzing the hard restriction on the fuel-air equivalence ratio (FER) and the acceleration mission objective. Using the concept of model self-shaping, a loss function is established to achieve the self-optimization of the reference model bandwidth. The reference trajectory of the velocity slows down as the FER approaches its maximum value and becomes faster as the FER demand decreases. The backstepping frame is applied in the attitude control system, and the dynamics uncertainty with the unknown aerodynamic parameters is constructed using neural network. The Karush-Kuhn-Tucker multiplier is used as a link parameter of the guidance and control integrated framework and is introduced into the adaptive update law.An adaptive algorithm is proposed with the estimating evaluation derived from the serial-parallel estimation model. A HFV simulation test with FER constraint shows that the adaptive integrated guidance and control can follow the desired trajectory with high tracking accuracy, and the control input can be kept within a feasible value.

show abstract

Criteria for hypersonic airbreathing propulsion and its experimental verification

Cited by 59 publications

References 22 publications

Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner

Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner

Formation and Evolution of Cellular Structures in Wedge-Induced Oblique Detonations

Integrated guidance and control of hypersonic flight vehicle with coordinated mission requirement and input constraint

Contact Info

Product

Resources

About