Estimation of the Unsteady Aerodynamic Load on Space Shuttle External Tank Protuberances from a Component Wind Tunnel Test

Panda, Jayatana; Martin, Fred W.; Sutliff, Daniel L.

doi:10.2514/6.2008-232

Cited by 8 publications

(6 citation statements)

References 5 publications

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“…Side forces have been observed not only as a result of axial asymmetric protuberances on the surface of slender-bodied objects, but of high angles of attack [9][10]. Therefore, in many development projects, aerodynamic loads induced by protuberances have been examined, such as the Epsilon Launch Vehicle in Japan, and Ares I and Ares V rockets in the United States [5][6][11][12]. However, these studies are considered to be limited in terms of the design of protuberance arrangement.…”

Section: Introductionmentioning

confidence: 99%

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Experimental and Numerical Investigations of Slender Body Side Force with Asymmetric Protuberances

Kawauchi

Harada

Kitamura

et al. 2019

Journal of Spacecraft and Rockets

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Typical space transportation vehicles have various asymmetric protuberant devices on their surfaces, such as cable ducts and side jet motors. Such protuberances, when arranged asymmetrically with respect to the vehicle axis, are known to cause asymmetric vortices that produce side force. In this study, to understand effects of side force and its associated flow fields, both wind tunnel tests and numerical calculations for a slender body with an asymmetric protuberance were conducted at a wind speed of Mach 1.5. The results of computed aerodynamic coefficients are in good agreement with the experimental results and detailed flow structures are provided. In particular, the results revealed that side force was generated by two factors. It linearly increased as vortices detached from the body and nonlinearly increased based on the effects of secondary vortex scale as the angle of attack increased. Additionally, the axial position and azimuthal angle (angle along the circumferential direction around the body axis) of the protuberance strongly influenced side force characteristics. First, the side force was significantly higher when the protuberance was installed in a forward axial position. Second, when the protuberance was installed on the leeward side of the slender body (upper side), the side force increased with the angle of attack. These results are not limited to the presented configuration and can be applied to other rocket designs for cost reduction and safety enhancement.

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Section: Introductionmentioning

confidence: 99%

“…Additionally, corresponding experiments were not conducted. As mentioned above, the authors of [5][6][7][8][9][10][11][12][13] only presented aerodynamic characteristics from either wind tunnel experiments or numerical calculations independently, or focused on a specific configuration.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Investigations of Slender Body Side Force with Asymmetric Protuberances

Kawauchi

Harada

Kitamura

et al. 2019

Journal of Spacecraft and Rockets

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“…Then, the demands of highly reliable space transportations are increasing. 1) In order to meet the demands, various studies [2][3][4] of rocket development such as aerodynamics are carried out. In the field of aerodynamics, researchers investigate aerodynamic characteristics of flight vehicles including rockets, and guarantee their flight feasibility.…”

Section: Introductionmentioning

confidence: 99%

“…For example, the aerodynamic characteristics of Epsilon rocket 7) and M-V rocket 5) with protuberant devices were investigated in references, but with their positions and sizes already determined. 4,8) In this study, on the other hand, we clarify the effect of changing the protuberance positions on flow fields and the roll moment of a supersonic flight vehicle using CFD. The present results will provide us with the in-depth insight concerning the protuberance-equipped vehicle aerodynamics from academic point of view, but also will serve as a fundamental yet useful guideline in future vehicle designs.…”

Section: Introductionmentioning

confidence: 99%

Roll Moment Characteristics of Supersonic Flight Vehicle Equipped with Asymmetric Protuberance

Harada

Kitamura

Nonaka

2019

AEROSPACE TECHNOLOGY JAPAN

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Most of flight vehicles have various protuberant devices on their surfaces, but asymmetry in their positioning with respect to the body axis can affect aerodynamic characteristics of vehicles, particularly roll moment. Thus, it is important in rocket development to clarify the effects of the protuberances on the vehicle aerodynamic characteristics. In this study, as a basic research, we systematically investigated such effects using CFD, by changing the positions of a protuberance. As a result, the roll moment increased nearly linearly with angle of attack (=α), but its trend was different in protuberance locations, particularly when arranged near the center-of-gravity. In positioning there at α = 20°, the wake vortex center moved farther away from protuberance compared with α = 15°, then the pressure decline at its wake side was suppressed, and thus, the pressure difference between its upstream and downstream sides became smaller. As a consequence, the roll moment did not arise linearly, but decreased at α = 20°.

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“…As shown in Figure 15, OVERFLOW also became an essential tool for the study of debris during launch 3536 , and was critical to the ET Bi-pod redesign after the loss of Columbia and the work that allowed the removal of the Protuberance Airload Ramp (PAL) foam after STS-114. 37 An excellent overview of the launch vehicle CFD support during the last 20 years is provided in Reference [38 ]. OVERFLOW was also used to study the unsteady flow dynamics in the 17 inch feedline, which led to cracks forming in the feedline flow liners.…”

Section: B Space Shuttle Launch Vehicle Aerodynamic Issuesmentioning

confidence: 99%

Legacy of the Space Shuttle From an Aerodynamic and Aerothermodynamic Perspective

Martin

2011

AIAA SPACE 2011 Conference &Amp; Exposition

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The development of the Space Shuttle Orbiter thermal protection system heating environment is described from a design stand point that began in the early 1970s. The desire for a light weight, reusable "heat shield" required the development of new technology, relative to previous manned spacecraft, and a systems approach to the design of the vehicle, entry guidance, and thermal protection system. Several unanticipated issues had to be resolved in both the entry and ascent phases of flight, which are discussed at a high level. During the life of the Program, significant improvements in computing power and numerical methods have been applied to Space Shuttle aerodynamic and aerothermodynamic issues, with the Shuttle Program often being the motivation, and or sponsor of the analysis development.

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Estimation of the Unsteady Aerodynamic Load on Space Shuttle External Tank Protuberances from a Component Wind Tunnel Test

Cited by 8 publications

References 5 publications

Experimental and Numerical Investigations of Slender Body Side Force with Asymmetric Protuberances

Experimental and Numerical Investigations of Slender Body Side Force with Asymmetric Protuberances

Roll Moment Characteristics of Supersonic Flight Vehicle Equipped with Asymmetric Protuberance

Legacy of the Space Shuttle From an Aerodynamic and Aerothermodynamic Perspective

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