Hyper-X: Foundation for future hypersonic launch vehicles

McClinton, Charles R.; Rausch, Vincent L.; Shaw, R. J.; Metha, Unmeel; Naftel, Chris

doi:10.1016/j.actaastro.2005.03.061

Cited by 44 publications

(11 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Recent research on hypersonic flight has inspired the interest in developing ultra‐high‐temperature ceramics (UHTCs) . UHTCs can withstand extremely high temperatures in chemically aggressive environments and are commonly defined as Group IVB‐ and VB‐based transition metal boride, carbide, and nitride ceramics with melting temperature above 3000°C and chemical stability exceeding 2000°C .…”

Section: Introductionmentioning

confidence: 99%

Volatility diagram of ZrB₂‐SiC‐ZrC system and experimental validation

Zou

et al. 2018

J Am Ceram Soc

View full text Add to dashboard Cite

A volatility diagram of zirconium carbide (ZrC) at 1600, 1930, and 2200°C was calculated in this work. Combining it with the existing volatility diagrams of ZrB 2 and SiC, the volatility diagram of a ternary ZrB 2 -SiC-ZrC (ZSZ) system was constructed in order to interpret the oxidation behavior of ZSZ ceramics. Applying this diagram, the formation of ZrC-corroded and SiC-depleted layers and the oxidation sequence of each component in ZSZ during oxidation and ablation could be well understood. Most of the predictions from the diagrams are consistent with the experimental observations on the oxidation scale of dense ZrB 2 -SiC-ZrC ceramics/coatings after oxidation at 1600°C or ablation at 1930 and 2200°C. The reasons for the discrepancy are also briefly discussed. K E Y W O R D S microstructure, oxidation, volatility diagrams, ZrB 2 -SiC-ZrC

show abstract

Section: Introductionmentioning

confidence: 99%

Volatility diagram of ZrB₂‐SiC‐ZrC system and experimental validation

Zou

et al. 2018

J Am Ceram Soc

View full text Add to dashboard Cite

show abstract

“…A scramjet is favorable as the primary engine for a hypersonic aircraft at the cruise phase accounting for the cycle efficiency, thus increasing propulsion efficiency. The airframe shape would be a waverider design, considering the hypersonic flight operations to minimize wave drag [1][2][3][4][5][6][7]. The airframe and the propulsion system of a hypersonic aircraft that has a waverider shape equipped with a scramjet engine must be designed together, as parts of the airframe will be parts of the engine [1].…”

Section: Introductionmentioning

confidence: 99%

Thrust Augmentation by Airframe-Integrated Linear-Spike Nozzle Concept for High-Speed Aircraft

2018

View full text Add to dashboard Cite

Abstract:The airframe-integrated linear-spike nozzle concept applied to an external nozzle for high-speed aircraft was evaluated with regard to the thrust augmentation capability and the trim balance. The main focus was on the vehicle aftbody. The baseline airframe geometry was first premised to be a hypersonic waverider design. The baseline aftbody case had an external nozzle comprised of a simple divergent nozzle and was hypothetically replaced with linear-spike external nozzle configurations. Performance evaluation was mainly conducted by considering the nozzle thrust generated by the pressure distribution on the external nozzle surface at the aftbody portion calculated by computer simulation at a given cruise condition with zero angle of attack. The thrust performance of the proposed linear-spike external nozzle concept was nearly equivalent to that of the baseline geometry though the wall surface area can be significantly reduced. This is because the design of the proposed concept had a compression wall for the exhaust flow, which resulted in increasing the wall pressure. The configuration with the boattail exhibited a potential for further improvement in thrust performance. The trim balance evaluation showed that the aerodynamic center location appeared as acceptable. Thus, benefits were obtained by employing the airframe-integrated linear-spike external nozzle concept.

show abstract

“…Hypersonic vehicles (HSV) possess great meaning for aerospace applications, and have important potential values in various fields [1][2][3][4]. Reentry guidance of HSV is a critical technology for assuring the vehicle's arrival at a desired destination.…”

Section: Introductionmentioning

confidence: 99%

Hypersonic Vehicles Profile-Following Based on LQR Design Using Time-Varying Weighting Matrices

Chen¹,

Xiong²,

Liang³

et al. 2018

Advances in Some Hypersonic Vehicles Technologies

View full text Add to dashboard Cite

In the process of applying linear quadratic regulator (LQR) to solve aerial vehicle reentry reference trajectory guidance, to obtain better profile-following performance, the parameters of the aerial vehicle system can be used to calculate weighting matrices according to the Bryson principle. However, the traditional method is not applicable to various disturbances in hypersonic vehicles (HSV) which have particular dynamic characteristics. By calculating the weighting matrices constructed based on Bryson principle using time-varying parameters, a novel time-varying LQR design method is proposed to deal with the various disturbances in HSV reentry profile-following. Different from the previous approaches, the current states of the flight system are employed to calculate the parameters in weighting matrices. Simulation results are given to demonstrate that using the proposed approach in this chapter, performance of HSV profile-following can be improved significantly, and stronger robustness against different disturbances can be obtained.

show abstract

Hyper-X: Foundation for future hypersonic launch vehicles

Cited by 44 publications

References 2 publications

Volatility diagram of ZrB₂‐SiC‐ZrC system and experimental validation

Volatility diagram of ZrB₂‐SiC‐ZrC system and experimental validation

Thrust Augmentation by Airframe-Integrated Linear-Spike Nozzle Concept for High-Speed Aircraft

Hypersonic Vehicles Profile-Following Based on LQR Design Using Time-Varying Weighting Matrices

Contact Info

Product

Resources

About

Hyper-X: Foundation for future hypersonic launch vehicles

Cited by 44 publications

References 2 publications

Volatility diagram of ZrB2‐SiC‐ZrC system and experimental validation

Volatility diagram of ZrB2‐SiC‐ZrC system and experimental validation

Thrust Augmentation by Airframe-Integrated Linear-Spike Nozzle Concept for High-Speed Aircraft

Hypersonic Vehicles Profile-Following Based on LQR Design Using Time-Varying Weighting Matrices

Contact Info

Product

Resources

About

Volatility diagram of ZrB₂‐SiC‐ZrC system and experimental validation

Volatility diagram of ZrB₂‐SiC‐ZrC system and experimental validation