Figure 25 - uploaded by Charles Camarda
Content may be subject to copyright.
![– Space Shuttle thermal protection system (TPS) tile assemblage [22, 31].](profile/Charles-Camarda/publication/296652080/figure/fig16/AS:335275415883785@1456947296200/Space-Shuttle-thermal-protection-system-TPS-tile-assemblage-22-31.png)
Source publication
![Figure 9. – Global and local thermal stress issues [12]. The X-15A-2...](profile/Charles-Camarda/publication/296652080/figure/fig3/AS:335275411689476@1456947295217/Global-and-local-thermal-stress-issues-12-The-X-15A-2-was-designed-to-explore-flight_Q320.jpg)
The Space Shuttle was an amazing and unique spacecraft that transported crewmembers, supplies, equipment, experiments, and large payloads both to and from low Earth orbit (LEO). It served multiple functions to satisfy diverse military, civilian, industry, and scientific requirements including: facilitating satellite launch, servicing, and return to...
Citations
... Local amplification of heat fluxes by factors of 5 and up to 19 was observed in wind tunnel experiments at Mach 6 to 20 conditions. 31,32 The first in-flight confirmation of the severity of shock interference heating took place in October 1967 when the NASA X15A2 experimental rocket-driven aircraft suffered severe damage to one of its fins, 30,33,34 as illustrated in Fig. 7. However, most of the current re-entry configurations use highly swept wings, where shock interference is dominated by Type VI interactions 34 and the resulting amplification of surface heat loads is less severe. ...
This paper presents a review of current aerothermal design and analysis methodologies for spacecraft. It briefly introduces the most important system architectures, including rockets, gliders, and capsule-based configurations, and gives an overview of the specific aerothermal and thermo-chemical effects that are encountered during their different flight phases and trajectories. Numerical and experimental design tools of different fidelity levels are reviewed and discussed, with a specific focus placed on the present limitations and uncertainty sources of models for the wide range of physical phenomena that are encountered in the analyses. This includes high temperature thermodynamics, chemical effects, turbulence, radiation, and gasdynamic effects. This is followed by a summary of current predictive capabilities and research foci, with missing capabilities identified. Finally, a future strategy toward an efficient and predictive aerothermal design of re-useable space transportation systems is proposed.
... The skills required to identify critical failure mechanisms, to construct a building-block experiment/analysis approach to understand fundamental, physics-based behaviors, and to predict complex, system-level performance up to and including failure were carefully nurtured and mentored. Figure 6 illustrates schematically what is described in (Camarda, 2014a) how the everchanging design requirements and funding issues in phases A through C of the Shuttle Phased-Gated product development cycle resulted in the selection of the partially reusable Shuttle configuration shown in Phase C. The Shuttle was originally required to fly somewhere between 50 to 100 missions per year, turnaround from landing to launch to be less than 2 weeks, launch costs on the order of $1,000 per pound of payload, and airlinelike operations while on the ground and being readied for flight. By far, the most significant objectives of the program were to demonstrate a significant reduction in the cost of travel to low Earth orbit (LEO) and routine access to space. ...
... The large-area repair effort followed a free-flowing approach similar to the innovative conceptual engineering design (ICED) methodology described in (Camarda, 2014a). It began with a meeting of experts in high-temperature materials and structures, in the reentry environments, and in on-orbit operations (e.g., EVA-qualified astronauts), as well as a number of "free thinkers" who had technical backgrounds. ...
The classical way of developing products in industrial R&D is the so-called point-based or sequential method, where the design concepts for the project and all its constituent elements are decided up front and only these concepts are matured in the product development. In contrast to this traditional approach, in set-based concurrent engineering approach, several alternative solutions are being developed simultaneously. If the requirements change during the R&D process, there is still a possibility than one of the several possible solutions can meet the new requirements. In the set-based approach the requirements can also be adjusted during the later phases of the R&D process, when there is enough information to do so. In this manner, the set-based R&D differs significantly from classical sequential R&D that is typically time-consuming, and does not allow major changes during the process. The goal of this paper is to make a practically oriented presentation of set-based rapid concept development methods. The presentation in the paper is illustrated by industrial production and technology case examples from United States and Finland.
