A study of upwind schemes on the laminar hypersonic heating predictions for the reusable space vehicle

Qu, Feng; Sun, Daoyuan; Zuo, Guang

doi:10.1016/j.actaastro.2018.03.046

Cited by 22 publications

(10 citation statements)

References 20 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Therefore, the control input could also consist of thrust and lift coefficients. Let X and U respectively denote the state and control vector, as shown in (12).…”

Section: Periodic Hypersonic Cruise Trajectory a Problem Formulamentioning

confidence: 99%

“…The optimal control problem could be expressed as one to optimize the state and control variables shown in (12) and limited by (22) and 23to maximize the performance measure of (33), while satisfying the boundary conditions in (20) and (21).…”

Section: B Reference Trajectory: Optimal Steady Cruisementioning

confidence: 99%

“…To withstand the aerothermodynamics over a long range, a comprehensive and complicated thermal protection/management system is demanded [10], [11]. This would lead to a higher empty ratio, which means decline of structural efficiency [12]. To obtain a long range, lightweight materials for thermal protection is a research hotspot at present [13].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Optimal Periodic Control of Hypersonic Cruise Vehicle: Trajectory Features

et al. 2019

View full text Add to dashboard Cite

Optimal periodic control is an effective technique to reduce aerodynamic heating and fuel consumption of hypersonic cruise vehicles. Herein, this optimal control problem has been solved by nonlinear programming and passed the posteriori check of optimality. The results indicate that the lift coefficient and velocity in dynamical model could be recognized as constants. Accordingly, the original 3D system consists of velocity, flight path angle, and altitude, which could be decoupled into a 2D subsystem and a 1D one. The 2D subsystem could describe the correlation between the flight path angle and altitude. And the period length is mainly dependent on the maximum altitude difference. The 1D subsystem has been proved to be feasible to describe the variation of kinetic energy or velocity. On basis of the subsystems, the heating and fuel performances of periodic cruise have been studied. The heating performance is mainly dependent on the maximum altitude difference, and the fuel consumption is mainly dependent on the drag coefficient. The features concluded in this paper can support rapid trajectory planning or suboptimal feedback design of hypersonic cruise vehicles. INDEX TERMS Optimal periodic control, hypersonic cruise vehicle, trajectory features, performances.

show abstract

“…Therefore, the control input could also consist of thrust and lift coefficients. Let X and U respectively denote the state and control vector, as shown in (12).…”

Section: Periodic Hypersonic Cruise Trajectory a Problem Formulamentioning

confidence: 99%

Section: B Reference Trajectory: Optimal Steady Cruisementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Optimal Periodic Control of Hypersonic Cruise Vehicle: Trajectory Features

et al. 2019

View full text Add to dashboard Cite

show abstract

“…In addition to grid research, there are many issues worthy of attention, such as turbulence models and discretization schemes. The results of hypersonic verification and evaluation show that different turbulence models and discretization schemes have great differences in predicting the accuracy of aerodynamic heating [13,20]. The existing studies separate influencing factors independently, but CFD simulation is a whole process.…”

Section: Introductionmentioning

confidence: 99%

CFD Simulation Strategy for Hypersonic Aerodynamic Heating around a Blunt Biconic

Chen

2021

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

The design of the thermal protection system requires high-precision and high-reliability CFD simulation for validation. To accurately predict the hypersonic aerodynamic heating, an overall simulation strategy based on mutual selection is proposed. Foremost, the grid criterion based on the wall cell Reynolds number is developed. Subsequently, the dependence of the turbulence model and the discretization scheme is considered. It is suggested that the appropriate value of wall cell Reynolds number is 1 through careful comparison between one another and with the available experimental data. The excessive number of cells is not recommended due to time-consuming computation. It can be seen from the results that the combination of the AUSM+ discretization scheme and the Spalart-Allmaras turbulence model has the highest accuracy. In this work, the heat flux error of the stagnation point is within 1%, and the overall average relative error is within 10%.

show abstract

“…Moreover, to endure the long-time aerodynamic heating, a comprehensive thermal protection system (TPS) consists of passive, radiative, and active cooling techniques is demanded [34], [35]. This would lead to a higher empty ratio [36].…”

mentioning

confidence: 99%

Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

et al. 2019

View full text Add to dashboard Cite

In the design of hypersonic cruise vehicles, great effort is demanded to improve the performances of subsystems, namely structure, aerodynamics, and propulsion. Herein, effort demanded to realize a subsystem performance is quantified by technical merit. To achieve a feasible design, excessive technical merit of any one subsystem should be avoided. Accordingly, a lowest-technical-merit (LTM) design methodology has been proposed in this work. By this methodology, the design problem could be interpreted into a parametric optimization. The solution to such an optimization corresponds to the highest feasibility. The methodology has been implemented on two cases: deriving a hydrocarbon-fueled long-range cruiser from Boeing X-51A, and a hydrogen-fueled LAPCAT scenario from PREPHA. The simulation results show that LTM could achieve optimal allocations while satisfying different payload/range performances. The design methodology could help to improve the feasibility of hypersonic cruise vehicles. Furthermore, it could also be used in the design of other systems.

show abstract

A study of upwind schemes on the laminar hypersonic heating predictions for the reusable space vehicle

Cited by 22 publications

References 20 publications

Optimal Periodic Control of Hypersonic Cruise Vehicle: Trajectory Features

Optimal Periodic Control of Hypersonic Cruise Vehicle: Trajectory Features

CFD Simulation Strategy for Hypersonic Aerodynamic Heating around a Blunt Biconic

Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

Contact Info

Product

Resources

About