Design and verification of launch and space vehicle structures

Kabe, Alvar M.

doi:10.2514/6.1998-1718

Cited by 28 publications

(14 citation statements)

References 22 publications

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“…The wavenumber, f, determined from ri(/) = o.5 (8) is taken to be the boundary which spectrally separates the slowly-varying and turbulent wind features.…”

Section: Methodsmentioning

confidence: 99%

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Identifying Slowly-Varying and Turbulent Wind Features for Flight Loads Analyses

Spiekermann¹,

Sako²,

Kabe³

1999

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Washington Headquarters Services, Directorate for Information Operations and Reports. 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302, and A methodology developed to determine the spectral boundary between the slowly-varying components and the more rapidly varying, or turbulent components, of measured wind profiles is presented. Pairs of measured wind velocity versus altitude profiles from the Eastern and Western launch ranges of the United States were used to establish the vertical wavelengths which could no longer be considered slowly varying over discrete time intervals. Analyses were performed for wind pairs that were 30, 60, 90, and 120 minutes apart. The wavelength boundary between slowly-varying and turbulent wind features as a function of time interval is presented. The results of this work make it now possible to identify and extract the slowly-varying and/or turbulent wind features, as needed for a specific day-of-launch flight loads analysis, for these two launch facilities. SUBJECT TERMS AbstractA methodology is developed to determine the spectral boundary between wind features that can be considered slowly varying, and the more rapidly-varying, or turbulent, features of measured wind profiles. Pairs of measured wind velocity versus altitude profiles from the Eastern and Western launch ranges of the United States were used to establish the vertical wavelengths which could no longer be considered slowly varying over discrete time intervals. Analyses were performed for wind pairs that were 30, 60, 90 and 120 minutes apart. The wavelength boundary between slowly-varying and turbulent wind features as a function of time interval is presented. The results of this work make it possible to identify and extract the slowly-varying and turbulent wind features at a particular launch site.

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“…The wavenumber, f, determined from ri(/) = o.5 (8) is taken to be the boundary which spectrally separates the slowly-varying and turbulent wind features.…”

Section: Methodsmentioning

confidence: 99%

“…3 " 5 Loads analyses are typically divided into those that can be performed just prior to launch and those that have to be completed prior to the day of launch. 7,8 Both sets of loads are then combined statistically just prior to launch to estimate the total vehicle loads that are then compared to the allowable values. '…”

Section: Introductionmentioning

confidence: 99%

Identifying Slowly-Varying and Turbulent Wind Features for Flight Loads Analyses

Spiekermann¹,

Sako²,

Kabe³

1999

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show abstract

“…[5][6][7][8]. In addition, other analyses are performed to estimate loads due to items such as wind measurement error and vehicle dispersions from the nominal parameters used in the analyses.…”

Section: Other Load Contributorsmentioning

confidence: 99%

A refined and less conservative day-of-launch atmospheric flight loads analysis approach

Kabe

Spiekermann

Kim

et al. 1999

40th Structures, Structural Dynamics, and Materials Conference and Exhibit

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources gathering and mahtainino the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for redudng this burden, A day-of-launch atmospheric flight loads analysis approach that reduces conservatism by better defining the components of flight loads that have to be treated statistically and those that can be established with measured wind profiles just prior to launch is described. The approach introduces the concept of removing from measured day-oflaunch winds the rapidly varying features, and only using the more slowly changing components in day-of-launch, placard calculations. The proposed approach takes advantage of a recently-developed methodology that defines the spectral boundary, as a function of time, between wind components that can be considered slowly varying and those that change rapidly and, hence, have to be addressed statistically. SUBJECT TERMSAtmospheric flight loads, launch vehicles, turbulence, day-of-launch placards AbstractA day-of-launch atmospheric flight loads analysis approach that reduces conservatism by better defining the components of flight loads that have to be treated statistically and those that can be established with measured wind profiles just prior to launch is described. The approach introduces the concept of removing from measured day-of-launch winds the rapidly-varying features, and only using the more slowly-changing components in the load calculations performed just prior to launch. The proposed approach takes advantage of two recent developments. The first development defines the spectral boundary, as a function of time, between wind components that can be considered slowly varying and those that change rapidly and, hence, have to be addressed statistically. The second development provides an approach for calculating gust loads due only to the turbulent component of the winds, and thus, eliminates the need to include these wind components in the load calculations performed just prior to launch.

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“…These loads provide an important criterion for the principal structural design of the launch vehicle. Critical events responsible for the dynamic loads induced in the launch vehicle include the following: lift-off, atmospheric flight (e.g., static aeroelastic, gust, buffet), engine ignition, shutdown, and separating events [1].…”

Section: Introductionmentioning

confidence: 99%

Vibratory loads and response prediction for a high-speed flight vehicle during launch events

Kim¹,

Park²,

Eun³

et al. 2016

International Journal of Aeronautical and Space Sciences

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High-speed flight vehicles (HSFVs) such as space launch vehicles and missiles undergo severe dynamic loads which are generated during the launch and in in-flight environments. A typical vehicle is composed of thin plate skin structures with high-performance electronic units sensitive to such vibratory loads. Such lightweight structures are then exposed to external dynamic loads which consist of random vibration, shock, and acoustic loads created under the operating environment. Three types of dynamic loads (acoustic loads, rocket motor self-induced excitation loads and aerodynamic fluctuating pressure loads) are considered as major components in this study. The estimation results are compared to the design specification (MIL-STD-810) to check the appropriateness. The objective of this paper is to study an estimation methodology which helps to establish design specification for the dynamic loads acting on both vehicle and electronic units at arbitrary locations inside the vehicle.

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Design and verification of launch and space vehicle structures

Cited by 28 publications

References 22 publications

Identifying Slowly-Varying and Turbulent Wind Features for Flight Loads Analyses

Identifying Slowly-Varying and Turbulent Wind Features for Flight Loads Analyses

A refined and less conservative day-of-launch atmospheric flight loads analysis approach

Vibratory loads and response prediction for a high-speed flight vehicle during launch events

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