Evolution of Aviation and Propulsion Systems: The Next Fifty Years

Allen, John E.; Armstrong, F. W.; Denning, R. M.

doi:10.1243/pime_proc_1995_209_267_02

Cited by 3 publications

(1 citation statement)

References 6 publications

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“…Compared to the mostwidely used conventional launch vehicle and the space shuttle, the suborbital spaceplane has the strengths of fastresponse and autonomous landing recovery, which reveals wider potential advantages. Many researches [1][2][3][4][5][6][7] have been conducted and developed for scientific researches, space explorations, and tourism. Currently, there are three major takeoff types of suborbital spaceplanes, including air launching (AL), horizontal takeoff horizontal landing (HTHL), and vertical takeoff and landing (VTVL).…”

Section: Introductionmentioning

confidence: 99%

Design optimization and analysis of HTHL suborbital spaceplanes propelled by hybrid rocket motors

Xiao

Zhu

Zhang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, a design optimization and parameter analysis of a horizontal takeoff horizontal landing (HTHL) suborbital spaceplane propelled by a hybrid rocket motor (HRM) is proposed. Referenced by a prototype, an integrated design model, including the mass and shape estimation, HRM design, aerodynamic calculation, and trajectory simulation, is established. A series of long burning experimental tests in the reference article is adopted to modify the influence of nozzle erosion on HRM. After modification, the results of HRM design are well fitted with the test ones, which verified the precision of the modified model and revealed the importance of erosion effect on HRM performance. Then, the integrated design process is built and optimized by the multi-island genetic algorithm. The results indicated that the designed HRM-propelled suborbital spaceplane could achieve the target flight height under all the constraints. The parameter analysis (PA) based on optimum result is adopted to analyze the influences of design variables on the performance parameters of the HTHL suborbital spaceplane, and it also gives theoretical reference to the design optimization of the similar aerospace vehicles.

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Section: Introductionmentioning

confidence: 99%

Design optimization and analysis of HTHL suborbital spaceplanes propelled by hybrid rocket motors

Xiao

Zhu

Zhang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Future large aircraft design — the delta with suction

Denning¹,

Allen²,

Armstrong³

1997

Aeronaut. j.

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Since the 1970s, large passenger aircraft design has evolved by modest, but commercially significant, incremental change following the underwing pod concept pioneered by the Boeing 707. In the 21st century, the market is likely to require greater passenger capacity to deal with air-side congestion and higher performance and operational efficiency to justify investment and conserve finite fossil fuel resources. Public opinion will require far greater emphasis on control of noise and engine exhaust pollution. There is likely to be much increased emphasis on pollution in the upper-atmosphere and its environmental impact. In such a situation, it is questionable whether the evolutionary design route can produce the necessary advances and this must stimulate the search for radical design alternatives.A revolutionary approach, involving the delta planform combined with wing laminar flow control and its impact on overall design, is given a preliminary study in this paper. This has been carried out by assuming that major improvements in drag can be obtained by extensive laminarisation. Using non-dimensional methods, the resulting broad interactive impacts on airframe and engine design and performance are derived. The effect of assuming varying quantities of low-energy air sucked from the foot of the boundary layer is studied and suction-system performance examined.In addition to the large potential improvements in range, a strong relationship between lower drag, lower cruising altitude and lower cruise engine size is identified. In the study, several factors emerge which may combine to drive large aircraft design towards low aspect ratio and the integrated delta wing planform. This paper is intended as a stimulus and a basis for further study and research.

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Numerical Investigation on a New Concept of Shock Vector Control Nozzle

Shi

Wang

et al. 2019

Journal of Engineering for Gas Turbines and Power

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Shock vector control (SVC) based on transverse jet injection is one of the fluidic thrust vectoring (FTV) technologies, and is considered as a promising candidate for the future exhaust system working at high nozzle pressure ratio (NPR). However, the low vector efficiency (η) of the SVC nozzle remains an important problem. In the paper, a new method, named as the improved SVC, was proposed to improve the vector efficiency (η) of a SVC nozzle, which enhances the vector control of primary supersonic flow by adopting a bypass injection. It needs less secondary flow from high pressure component of an aero-engine and has smaller influence on the working character of an aero-engine. The flow mechanism of the improved SVC nozzle was investigated by solving three-dimensional Reynolds-averaged Navier--Stokes with shear stress transport (SST) κ–ω turbulence model. The shock waves, jets-primary flow interactions, flow separation, and vector performance were analyzed. The influences of aerodynamic and geometric parameters, namely, NPR, secondary pressure ratio (SPR), and bypass injection position (Xj.ad.) on flow characteristics and vector performance were investigated. Based on the design of experiment (DOE), the response surface methodology (RSM) and the simulation model of an aero-engine, a method to estimate the coupling performance of the improved SVC nozzle and an aero-engine was studied, and a new balance relationship between the improved SVC nozzle and an aero-engine was established. Results shows that (1) with the assistance of bypass injection, the jet penetration and the capability of vector control are largely improved, resulting in a vector efficiency (η) of 1.98 deg/%-ω at the designed NPRD = 13.88; (2) in a wide range of operating conditions, larger vector angle (δp), higher thrust coefficient (Cfg), and higher vector efficiency (η) of the improved SVC nozzle were obtained, (3) in the coupling process of the improved SVC nozzle and an aero-engine, a δp of 18.1 deg was achieved at corrected secondary flow ratio of 10% and corrected bypass ratio of 6.98%, and the change of the thrust and the specific fuel consumption (SFC) were within 12%, which is better than the coupling performance of a SVC nozzle and an aero-engine.

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Evolution of Aviation and Propulsion Systems: The Next Fifty Years

Cited by 3 publications

References 6 publications

Design optimization and analysis of HTHL suborbital spaceplanes propelled by hybrid rocket motors

Design optimization and analysis of HTHL suborbital spaceplanes propelled by hybrid rocket motors

Future large aircraft design — the delta with suction

Numerical Investigation on a New Concept of Shock Vector Control Nozzle

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