Studies of Engine-Airframe Integration on Hypersonic Aircraft

Johnston, Patrick; Cubbage, J. M.; Weidner, J. P.

doi:10.2514/3.59129

Cited by 12 publications

(3 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…With the continuous development of aircraft, the integration of flight and engine has become a major challenge that cannot be ignored, and a large number of related studies have been conducted [1][2][3][4][5]. As a key component of the engine, the integrated design of the nozzle and the aircraft afterbody has become the core focus of the research on the integration of flight and engine.…”

Section: Introductionmentioning

confidence: 99%

Optimal Design of Ejector Nozzle Profile with Internal and External Integrated Flow

He,

Shi,

2024

Aerospace

View full text Add to dashboard Cite

Based on the orthogonal experimental method, a simulation case of the flow field of the ejector nozzle was designed to investigate the influence of the structural parameters of the ejector nozzle on the internal and external flow. This study explored the effects of throat area, outlet area, throat position, and ejector nozzle length on the ejector flow rate ratio, thrust coefficient, and net thrust coefficient. Subsequently, flow path geometry optimization was conducted to maximize the thrust coefficient or net thrust coefficient. The results revealed that the throat area ratio and the outlet area of the ejector nozzle are the primary factors affecting the aerodynamic performance. Compared to the baseline ejector nozzle model, the optimal model for thrust coefficient exhibited a 16.333% improvement, while the optimal model for net thrust coefficient demonstrated a significant enhancement of 46.674%.

show abstract

Section: Introductionmentioning

confidence: 99%

Optimal Design of Ejector Nozzle Profile with Internal and External Integrated Flow

He,

Shi,

2024

Aerospace

View full text Add to dashboard Cite

show abstract

“…In conventional aircraft design, the design and analysis is subdivided into separate technical disciplines to be optimised individually, and the final product is a compilation of the optimised components (Johnston et al, 1971). Unfortunately this is not the case for HAAVs as the technical disciplines of aerothermodynamics, propulsion, vehicle dynamics and control have complex nonlinear relationships.…”

Section: Haav Design Methodologymentioning

confidence: 99%

Multidisciplinary design and optimisation of a pitch trimmed hypersonic airbreathing accelerating vehicle

Preller¹

View full text Add to dashboard Cite

The global economic environment combined with the rapid pace of technology advancement is placing importance on reducing the size and cost of access to space systems. Based on decades of practical experience with rocket-only launch vehicles, current technology is operated close to theoretical limits and only marginal further improvement is possible. A possible solution is to include an airbreathing stage into the launch system architecture. Performance wise, airbreathing hypersonic engines such as scramjets have an advantage over rocket propulsion in terms of a significantly higher specific impulse in the hypersonic flight regime. A reusable airbreathing stage could contribute to an increase in payload mass-fraction by using scramjet propulsion over a meaningful proportion of the launch trajectory and provides the flexibility of aircraft-like operations while being inherently reusable.Researchers at the University of Queensland investigated the use of a three stage to orbit rocket-scramjet-rocket system for transporting small payloads into LEO. The second stage scramjet powered accelerator of this system was the subject of a series of Multi-Disciplinary Optimisations (MDO) which involved flying complete trajectories. Promising results were achieved however this work did not include the requirement for the vehicle to be pitch trimmed, which is an important aspect which must be addressed.The purpose of the investigation described in this thesis was to gain a better understanding of the impact that the second stage vehicle's planform has on the pitch trim of the vehicle. This was addressed through a numerical study utilising and expanding on the capabilities of the MDO system developed by Jazra (2010) by: i) Defining a more realistic mission of delivering small satellites up to 500 kg into a Sun Synchronous Orbit of 566.89 km altitude suitable for several earth science missions.ii) Increasing the fidelity of the MDO system to enable an accurate estimate of the trim drag. This included refining the vehicle mass model and aerodynamic module updates such as introducing a 2-D aft body exhaust expansion model plus elevon force and pitching moment inclusions.

show abstract

“…one that allows for longitudinal stability while efficiently producing positive net thrust, requires compromise in between the individual optima. Johnston et al (1971) and Perrier et al (1996) emphasise the importance of factoring in trim penalties when evaluating nozzle performance. It is estimated that losses from trim can reduce the engine performance by as much as 10 %.…”

Section: General Analyses Of Nozzle and Vehicle Performancementioning

confidence: 99%

Design of a 3D shape transitioning nozzle and experimental thrust measurements of an airframe integrated scramjet

Kunze¹

View full text Add to dashboard Cite

show abstract

Studies of Engine-Airframe Integration on Hypersonic Aircraft

Cited by 12 publications

References 2 publications

Optimal Design of Ejector Nozzle Profile with Internal and External Integrated Flow

Optimal Design of Ejector Nozzle Profile with Internal and External Integrated Flow

Multidisciplinary design and optimisation of a pitch trimmed hypersonic airbreathing accelerating vehicle

Design of a 3D shape transitioning nozzle and experimental thrust measurements of an airframe integrated scramjet

Contact Info

Product

Resources

About