Design constraints in the payload-range diagram of ultrahigh capacity transport airplanes

Martínez‐Val, Rodrigo; Pérez, Emilio Ortega; Muñoz, Tomás García; Cuerno, Cristina

doi:10.2514/3.46646

Cited by 15 publications

(16 citation statements)

References 6 publications

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“…The quarter chord swept angle, , is directly linked to the design Mach number, relative thickness (17 per cent), and cruise lift coefficient (∼0.20) through equation (3).…”

Section: Optimization Processmentioning

confidence: 99%

“…As a consequence, the airliners are now about 100 per cent more efficient than 50 years ago, in terms of range parameter [2]. However, it seems that this configuration is approaching an asymptote around the size of A380 in its productivity and capacity characteristics [3,4], and this is happening in a period of increasing environmental concern about pollution and noise [5][6][7].…”

Section: Commercial Aviation Of the Jet Era Has Been Basedmentioning

confidence: 99%

See 1 more Smart Citation

Optimization of planform and cruise conditions of a transport flying wing

Martínez‐Val

Pérez

Puertas

et al. 2010

Proceedings of the Institution of Mechanical Engineers, Part G:

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The flying wing is a promising concept for the mid long-term commercial aviation. After the previously published conceptual design of a 300-seat class flying wing, the present article carries out a parametric analysis to optimize its planform and analyse the suitable cruise conditions to achieve the highest efficiency of such configuration. The figures of merit chosen for the optimization are the direct operating cost and the maximum take-off weight per passenger, for a specified constant range of 10 000 km. The design has to respect five relevant constraints: wingspan (limited to 80 m), cabin width, wing tip chord, number of passengers, and cruise lift coefficient. The optimum aircraft fulfilling all constraints cruises at 45 000-47 000 ft and M = 0.82, has an aspect ratio of 6.3 and taper ratio of 0.10, and carries about 280 passengers in three-class seating. This aircraft is about 20 per cent more efficient than conventional wide bodies of similar size, in terms of trip fuel.

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“…The quarter chord swept angle, , is directly linked to the design Mach number, relative thickness (17 per cent), and cruise lift coefficient (∼0.20) through equation (3).…”

Section: Optimization Processmentioning

confidence: 99%

Section: Commercial Aviation Of the Jet Era Has Been Basedmentioning

confidence: 99%

Optimization of planform and cruise conditions of a transport flying wing

Martínez‐Val

Pérez

Puertas

et al. 2010

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…For example, the drive towards a high speed civil transport (HSCT) has focused on advances in propulsion and materials. The threesurface aircraft described by (Martínez-Val, 1994) and (Birch, 1995) has been shown to improve aerodynamic performance. Another concept to improve aerodynamic performance is the blended wing-body (BWB).…”

Section: New Technologies and Conceptsmentioning

confidence: 99%

Systems Engineering for Commercial Aircraft

Jackson¹

1997

INCOSE International Symp

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The application of systems engineering (SE) to commercial aircraft presents a set of requirements and processes unique to the commercial aircraft industry. SE can be applied to new, derivative, and change‐based aircraft design. The concept of an aircraft system extends beyond the aircraft itself. The hierarchy of the aircraft architecture is embedded in present‐day processes. Aircraft life‐cycle functions follow the classical life‐cycle functions. The aircraft‐level functions can be flowed to aircraft and subsystem level functions and requirements. Requirements which receive more attention than others include performance, safety, cost, reliability, and weight, not necessarily in that order. Economic requirements include both market‐driven and particular customer requirements. Certification guidelines for the aircraft, including its software, incorporate SE principles. Strong SE management is required for the successful development of commercial aircraft. This paper is based on the author's book Systems Engineering for Commercial Aircraft (1997).

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“…Within DOC, major categories can be identified and used as design constraints. Although the components of DOC vary slightly from source to source, the major ones used both at DAC and by [Martínez, 1994] and [Aerospace Engineering, 1994] are shown in Table 1. All three major categories are, of course, of interest to both the developer and the customer.since they affect both system purchase cost and operating cost, and hence profitability of the customer and, therefore, sales by the developer.…”

Section: Table 1 Direct Operating Costsmentioning

confidence: 99%

2.2.1 Systems Engineering and the Bottom Line

Jackson¹

1995

INCOSE International Symp

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Systems Engineering (SE) cannot be viewed in isolation, but rather as a subset of, first, the Integrated Product Development process, and secondly, as part of a commercial or non‐governmental corporation's business enterprise. This paper discusses four ways in which the SE process directly affects the financial operations of a company and how SE can be employed to improve the financial performance. First, the design‐to‐cost process can be brought to bear to maintain predictable and affordable products. Second, the normal business cycle in commercial industries, presents cost and schedule constraints which can be treated by considering them as a natural part of the SE process. Next, the improved product quality through the SE process results in many direct and indirect financial benefits through reduced development cost, reduced unit cost, reduced operating cost, and improved sales. Finally, the SE process provides consistent methodology for obtaining superior products from suppliers, and hence enhances the business prospects for the product. Examples in this paper focus on the commercial aircraft industry, although the principles found in it may be applied to many industries.

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Design constraints in the payload-range diagram of ultrahigh capacity transport airplanes

Cited by 15 publications

References 6 publications

Optimization of planform and cruise conditions of a transport flying wing

Optimization of planform and cruise conditions of a transport flying wing

Systems Engineering for Commercial Aircraft

2.2.1 Systems Engineering and the Bottom Line

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