Sensitivity analysis of flowfield modeling parameters upon the flow structure and aerodynamics of an opposing jet over a hypersonic blunt body

Guo, Jinghui; Lin, Guiping; Bu, Xueqin; Li, Hao

doi:10.1016/j.cja.2019.08.025

Cited by 19 publications

(6 citation statements)

References 54 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Step 6: Input the FER Φ and rudder deflection 𝛿 e into the dynamics model (1) to control the velocity V and altitude h to the desired conditions V * ∞ and h * ∞ , respectively.…”

Section: Algorithm 1 Guidance and Control Integration Design Algorithmmentioning

confidence: 99%

“…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%

See 1 more Smart Citation

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

“…Step 6: Input the FER Φ and rudder deflection 𝛿 e into the dynamics model (1) to control the velocity V and altitude h to the desired conditions V * ∞ and h * ∞ , respectively.…”

Section: Algorithm 1 Guidance and Control Integration Design Algorithmmentioning

confidence: 99%

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

show abstract

“…Another popular aspect of research is the drag reduction, which includes research from [27][28][29][30]. A sensitivity analysis is available from Guo et al [31], which reveals that the total pressure ratio between the opposing jet and the free flow, the jet exit Mach number, and the free flow Mach number contribute to 92% of the change in model surface pressure, providing helpful guidance for the design of the opposing jet. Some other research had studied the opposing jet parametrically, such as [32][33][34].…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on the Thermal Protection Characteristics of a New Active Jet Design Parameter for Hypersonic Flight Vehicle

Tian

Duan

Chen

2023

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

This study investigated the thermal protection performance of an active jet thermal protection system (PRsAJ-TPS) based on a new jet design parameter PRs for hypersonic flight vehicles (HFVs). The new parameter PRs is defined as the relationship between the jet flow total pressure and the free flow total pressure behind the outer bow shock. A 20° tilted nozzle design is employed together with the PRs to form the PRsAJ-TPS. Theoretical and numerical analysis is performed to prove the advantages of using the PRs. A conventional in-house CFD solver with the k ‐ ω SST turbulence model is utilized to perform the calculation. The influence of different PRs (working in the short penetration mode) and flight angles of attack on the performance of the PRsAJ-TPS is also studied. The simulation results confirmed that with a constant PRs, the Mach disk location stays the same and the normalized heat flux reduction is similar at different flight conditions. Nearly linear relationships exist between the new design parameter PRs and thermal protection performance indicators. The PRsAJ-TPS also exhibits good protection when flight angle of attack (AoA) varies between 0° and 40°, with the best results achieved at AoA = 0 ° . This study provides valuable information for the engineering application of the jet-based TPS to future HFVs.

show abstract

“…Luo et al 9 used Fourier transform and high-speed schlieren image processing methods to study the control effect of high-frequency plasma synthetic jet on low-frequency instability of shock boundary layer interaction. Guo et al 10 designed a reverse jet of hypersonic bluff body, which significantly changed the external flow and produced considerable aerodynamic drag reduction. Wallis 11 conducted a jet interaction test on a flat plate in a supersonic wind tunnel, observed the shock structure and pressure-sensitive coating with schlieren image, and obtained the surface pressure diagram.…”

Section: Introductionmentioning

confidence: 99%

Unsteady test technique of jet control with multi-parameter coupling

Xue

Cao

et al. 2022

Advances in Mechanical Engineering

View full text Add to dashboard Cite

In this paper, the jet control effect of air vehicle is studied, and a new multi parameter coupling unsteady test technique is established, which can ensure that the test model is consistent with the real air vehicle, and the jet is carried out under the condition of complete freedom and no support constraints, so that the wind tunnel test can better simulate the jet control effect of real air vehicle. The new technique overcomes the shortcoming that the previous jet test can only carry out unsteady flow field or unsteady aerodynamic force research, and can ensure that in the whole process of jet flow, the interference flow field at the nozzle, the aerodynamic force of the air vehicle, especially the movement of the air vehicle, are coupled with each other all the time, so as to achieve the same effect as the real air vehicle. The establishment of the new technique overcomes many problems, including the total length of the model is 167 mm, no support for the model, storage of small volume/high-pressure gas in free state, on-time unlocking of sealed gas source in free state of the model, and connection of gas source and nozzle in the model. The test results show that when no jet, the revolution body is head up, which affected by the cavity shock wave. When jet on, the jet force continues to act on the revolution body, resulting in the revolution body lowering its head until it diverges. The new technique can achieve more advanced technical indicators, including: ensuring jet Mach number >1; Ensure that the static pressure ratio of the jet is more than 10 (the static pressure ratio can be greater at hypersonic speed). After the establishment of the new technique, the supersonic wind tunnel test is carried out, and the ideal test results are obtained, which shows that the new technique is reliable.

show abstract

Sensitivity analysis of flowfield modeling parameters upon the flow structure and aerodynamics of an opposing jet over a hypersonic blunt body

Cited by 19 publications

References 54 publications

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

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

Numerical Investigation on the Thermal Protection Characteristics of a New Active Jet Design Parameter for Hypersonic Flight Vehicle

Unsteady test technique of jet control with multi-parameter coupling

Contact Info

Product

Resources

About