LAPCAT II : towards a Mach 8 civil aircraft concept, using advanced Rocket/Dual-mode ramjet propulsion system

Serre, Laurent; Defoort, Sébastien

doi:10.2514/6.2009-7328

Cited by 9 publications

(5 citation statements)

References 3 publications

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“…And coefficient ω is defined in (12). V e means the effective velocity of inner jet, which can be calculated in (13). M c means the convective Mach number, which is defined in (14).…”

Section: Engine Jet Noise Prediction Modelmentioning

confidence: 99%

“…A variety of new generation supersonic civil aircraft concepts have been put forward in some literatures [4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20][21], for example, the conceptual design of Mach 5 TBCC engine which is applied into the supersonic civil aircraft has been investigated [22]. However, for Mach 5 TBCC engine, the inlet adjustment is more complicated, and the total inlet temperature can reach around 1300 K. So, it is more challenging to solve the airframe thermal protection problem based on the existing material and technology, due to the high stagnant temperature due to extremely high Mach.…”

Section: Introductionmentioning

confidence: 99%

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Research on Simulation and Performance Optimization of Mach 4 Civil Aircraft Propulsion Concept

Chen

Jia

Tang

et al. 2019

International Journal of Aerospace Engineering

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Supersonic civil aircraft is of a promising area in the development of future civil transport, and aircraft propulsion system is one of the key issues which determine the success of the aircraft. To get a good conceptual design and performance investigation of the supersonic civil aircraft engine, in this article, a fast, versatile as well as trust-worthy numerical simulation platform was established to analyze the Mach 4 turbine-based combined cycle (TBCC) engine concept so as to be applied to the supersonic civil aircraft. First, a quick and accurate task requirement analysis module was newly established to analyze the mission requirement of the Mach 4 supersonic civil aircraft. Second, the TBCC engine performance simulation model was briefly presented and the number of engines on the supersonic civil aircraft was analyzed, considering single engine inoperative. Third, the Stone model and the DLR method were investigated to estimate the engine jet noise and the NOx emission of the Mach 4 supersonic civil aircraft. Finally, a multiobjective optimization tool made up of a response surface method and a genetic algorithm was developed to optimize the design parameters and the control law of the TBCC engine, in order to make the Mach 4 supersonic civil aircraft engine with better performance, lower noise, and lower emissions. The uniqueness of the developed analysis tool lies in that it affords a numerical simulation platform capable of investigating the task requirement analysis module of the supersonic civil aircraft, engine jet noise prediction model, and the NOx emission prediction model, as well as a multiobjective performance optimization tool, which is beneficial for the conceptual design and performance research of Mach 4 supersonic civil aircraft’s propulsion system.

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“…And coefficient ω is defined in (12). V e means the effective velocity of inner jet, which can be calculated in (13). M c means the convective Mach number, which is defined in (14).…”

Section: Engine Jet Noise Prediction Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Research on Simulation and Performance Optimization of Mach 4 Civil Aircraft Propulsion Concept

Chen

Jia

Tang

et al. 2019

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

show abstract

“…(1) LAPCAT concepts [37]- [39]: MR2.4/M4.5/M8/A2 scenarios. (2) Other hypersonic concepts: HyperSoar 2000 [40], [41], NASP X30 [42], NASA Ma6 Transport/Fighter [43], and recalculated Scale 1 PREPHA Vehicle [38]. (3) Demonstrated Hypersonic Vehicles: Lockheed HYCAT-1/1A/4 [43], ROCKWELL Vehicle [43], X-15 [37], and X-51A [44].…”

Section: B Subsystem 1: Structurementioning

confidence: 99%

“…LAPCAT II [38] is aimed to design a hypersonic airliner with a payload capacity of 60 × 10 3 kg and a range of 18.7 × performance should be satisfied. Besides, the gross weight of the vehicle is also desired to reduce, which means a high payload capacity is pursued.…”

Section: Case 2: From Prepha To a Lapcat Scenariomentioning

confidence: 99%

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Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

et al. 2019

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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.

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Overall performance design of paralleled heat release and compression system for hypersonic aeroengine

et al. 2018

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LAPCAT II : towards a Mach 8 civil aircraft concept, using advanced Rocket/Dual-mode ramjet propulsion system

Cited by 9 publications

References 3 publications

Research on Simulation and Performance Optimization of Mach 4 Civil Aircraft Propulsion Concept

Research on Simulation and Performance Optimization of Mach 4 Civil Aircraft Propulsion Concept

Lowest-Technical-Merit Design Methodology of Hypersonic Cruise Vehicle

Overall performance design of paralleled heat release and compression system for hypersonic aeroengine

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