Design Study of Structural Concepts for an Arrow-Wing Supersonic Cruise Aircraft

Sakata, Isao; Davis, Gregory W.; Robinson, J. C.; Yates, E. C.

doi:10.2514/3.58726

Cited by 12 publications

(12 citation statements)

References 4 publications

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“…The reason for this limitation is twofold: It is believed that this configuration will be applied for many decades, and even for alternative configurations, such as blended wings [7][8][9][10] and high speed aircraft [11,12], many structural and material aspects discussed for the conventional configuration will remain applicable.…”

Section: Structural Considerationsmentioning

confidence: 99%

Fiber/Metal Composite Technology for Future Primary Aircraft Structures

Alderliesten

Benedictus

2008

Journal of Aircraft

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This paper discusses the structural and material considerations for fiber/metal composite technology for future primary and secondary aircraft structures. Based on these considerations and the experience obtained so far with fiber/metal laminates in primary aircraft structures, the potential field of further development of fiber/metal composite technology will be explained. It is concluded that a composite technology approach, in which both metals and fibers are combined to form a tailored structural material, can lead to significant weight reduction in future structural applications.

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Section: Structural Considerationsmentioning

confidence: 99%

Fiber/Metal Composite Technology for Future Primary Aircraft Structures

Alderliesten

Benedictus

2008

Journal of Aircraft

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“…First, it involved the acquisition/development of a body of manufacturing knowledge. This was based on several previous supersonic transport studies, [18][19][20][21][22][23][24][25][26][27][28] as well as studies of candidate materials and processes to be used for the HSCT. 24,[29][30][31][32] The most relevant knowledge was embodied in a Knowledge-Based System, CLIPS, 33 (C Language Integrated Production System) which was used for this research.…”

Section: Implementation Of Design Justificationmentioning

confidence: 99%

“…The Lockheed SST concept carried 234 passengers, had a cruise Mach of 2.7, and a baseline wing area of 10,900 square feet. The SST studies [18][19][20][21][22] resulted in a large amount of published data. Much information exists in the reports from the various disciplines, including performance and weights.…”

Section: Summary Of the Lockheed Sst Evaluation Processmentioning

confidence: 99%

Effects of alternative wing structural concepts on high speed civil transport life cycle costs

Marx

Mavris

Schrage

1996

37th Structure, Structural Dynamics and Materials Conference

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An integrated design and manufacturing approach allows economic decisions to be made that reflect the entire system design as a whole. In order to achieve this objective, integrated cost and engineering models were developed and utilized within a focused design perspective. A framework for the integrated product and process design of an aircraft system with a combined performance and economic perspective is described in this paper. This framework is based on the concept of Design Justification using a Design for Economics approach. A production cost model is developed that is sensitive to material and product/process selections for the wing structure. The use of cost/time analyses is described and applied for evaluation of process trades at the sub-component level of design. Results of an Integrated Product/Process Development (IPPD) case study are presented for potential High Speed Civil Transport (HSCT) wing structural concepts. Cost versus performance studies indicate that an aircraft with a hybrid wing structural concept, though more expensive to manufacture than some homogeneous concepts, can have lower direct operating costs due to a lower takeoff gross weight and less mission fuel required.

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“…Collier et al (2010) also suggested that Hat stiffened panels were the most efficient for carrying axial compressive loads, being up to 20 % lighter than sandwich based alternatives. Hence, both Collier et al (2010) and Sakata and Davis (1977) came to a similar conclusion regarding the optimal stringer geometry, despite having different vehicles being analysed. This suggested that Hat based stringers may also be the most efficient stringer stiffening cross section for the SPARTAN third stage aeroshell.…”

Section: Design and Optimisation Of Stringer Stiffened Structuresmentioning

confidence: 73%

“…According to work by Sakata and Davis (1977) on the structural design of a supersonic cruise aircraft fuselage, Zee and Hat stringer profiles were found to offer the maximum mass savings.…”

Section: Design and Optimisation Of Stringer Stiffened Structuresmentioning

confidence: 99%

Analysis of aerodynamic loading on a rocket and design

Yarrow¹

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The University of Queensland's Centre for Hypersonics are investigating the viability of a reusable three-stage, rocket-scramjet-rocket based access to space system, aimed at reducing the cost to orbit for small satellites (Preller & Smart, 2015). The final stage of this system is a conventional liquid fuelled rocket, designed to carry the satellite into its final orbit after being released from the second stage scramjet (Preller & Smart, 2015). Previously, the third stage vehicle was designed for exo-atmospheric operations, but new trajectories place the separation point well within the atmosphere, exposing the vehicle to high dynamic pressures (up to 50 kPa), at large angles of attack (10 degrees) (Forbes-Spyratos, Kearney, Smart, & Jahn, 2017;Preller & Smart, 2015). The large angle of attack on the vehicle resulted in lift dominating the aerodynamic forces, as opposed to in a conventional rocket where drag dominates. As such, it was hypothesised that conventional rocket design literature may not be applicable for the design of the third stage vehicle (Benson, 2014). The purpose of this thesis was to evaluate this hypothesis, to determine if rocket based design and optimisation literature could be adapted to a lift dominated, rocket like structure, in particular, the third stage vehicle.Phase One of this thesis involved reviewing available rocket design and optimisation literature and adapting it to develop a parametric CAD model of the third stage vehicle. The CAD model consisted of two main assemblies, an external aeroshell and the internal structure. Due to the atmospheric release point of the vehicle, the protective aeroshell needed to resist all aerodynamic loads, making it a critical component of the current design which needed to be validated.Phase Two then involved undertaking finite element analysis on the third stage to evaluate the applicability of using conventional rocket optimisation literature in the design of the third stage vehicle. To achieve this goal, static and buckling simulations of the third stage aeroshell were undertaken in ANSYS for freestream dynamic pressures ranging from 30 to 50 kPa (to simulate different release altitudes). For the dynamic pressures tested the aeroshell was statically 3.6 to 6.0 times stronger than necessary. Buckling was also not a critical failure mode. It was concluded that the restrictions imposed on the stringer and backing thicknesses of the aeroshell, due to the literature optimisation techniques implemented, resulted in the vehicle being heavily overdesigned for the applied loads. This suggested that the adaption of conventional rocket optimisation methods for the vehicle in this thesis was not the most effective method to optimise the load bearing structure. The final optimised configuration of the aeroshell weighed 281 kg, but to further reduce the safety factors and vehicle mass, evidence suggested that the backing and stringer thicknesses of the third stage vehicle needed to be reduced.ii

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Design Study of Structural Concepts for an Arrow-Wing Supersonic Cruise Aircraft

Cited by 12 publications

References 4 publications

Fiber/Metal Composite Technology for Future Primary Aircraft Structures

Fiber/Metal Composite Technology for Future Primary Aircraft Structures

Effects of alternative wing structural concepts on high speed civil transport life cycle costs

Analysis of aerodynamic loading on a rocket and design

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