DI-SESS-82233A

Aircraft Store Loads Analysis Report

Describes the magnitudes and distributions of flight and ground loads imposed onto an aircraft store, used to evaluate the store's structural design against system performance requirements in the specified operational environment.

Approval DateJune 27, 2023

AMSC NumberN10399

Preparing ActivityAS

Project NumberSESS-2023-018

OPR—

DTIC Applicable—

GIDEP ApplicableNo

Limitation—

Applicable Forms—

Approval Limitation—

Form Version—

DID Formatfree_text

963C CompliantYes

DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited.

Supersedes

DI-SESS-82233

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Description & Purpose

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Application & Interrelationship

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Use & Relationship

This report describes the magnitudes and distributions of flight loads and ground loads imposed onto the aircraft store. The data will be used to evaluate the structural design of the store in order to verify the store has met the system performance requirements in the specified operational environment.

This Data Item Description (DID) contains the format, content, and intended use information for the data product resulting from the work task described by the contract SOW.

This DID supersedes DI-SESS-82233.

Preparation Instructions

1Reference documentsThe applicable issue of the documents cited herein, including their approval dates and dates of any applicable amendments, notices, and revisions, shall be as specified in the contract.

2FormatContractor format acceptable.

3ContentThe Aircraft Store Loads Analysis Report shall contain the following:

3.1Flight LoadsDescribe the aerodynamic data generated, including all data and analyses used to determine the magnitude and distribution of aerodynamic loads. Describe the data in correlation to initial loads estimates proposed using the methodology described in MIL-STD-8591. Describe how the loads estimates were augmented by the subsequent use of Computational Fluid Dynamics (CFD) analysis, wind tunnel test data, and captive carriage Six-Degree-of-Freedom (6DOF) analysis. Describe the correlation of analytical methods and assumptions with CFD, wind tunnel, and flight test data. Describe the following information:

3.1.1List of weights, speeds, altitudes, attitudes, load factors, variable geometry configurationsList of weights, speeds, altitudes, attitudes, load factors, variable geometry configurations, useful load distributions, and other pertinent conditions that were investigated with sufficient amplifying information to show that such investigations adequately covered all critical loads.

3.1.2The basis for selection of the design load conditionsThe basis for selection of the design load conditions, including discussion of design features affecting loads, parametric analyses, and loads trend data sufficient to provide a foundation for the validity of the selected conditions.

3.1.3Comparative tabulated values and curves of loads, shears, bending moments, and torsionsComparative tabulated values and curves of loads, shears, bending moments, and torsions showing the more critical nature of one condition versus another.

3.1.4Details of analyses methods with sample calculations, as appropriate

3.2Ground LoadsDescribe the loads resulting from all static and dynamic ground loading conditions. Describe all loads and structural responses determined by dynamic analyses for takeoff and landing conditions. Describe all other ground loads determined by static load analyses or by other rational methods. Describe how the loads analysis, augmented by captive carriage 6DOF analysis, was used to meet aircraft store ground loads performance requirements. Describe the following in the report:

3.2.1List each of the specified takeoff, landing impact, and ground handling conditionsList each of the specified takeoff, landing impact, and ground handling conditions with sufficient amplifying information to show that such an investigation adequately covers all critically applied external static and dynamic loads as well as airframe response loads.

3.2.2Results of parametric studies in graphical formResults of parametric studies in graphical form to show the variation on externally applied loads and airframe response loads caused by varying critical parameters, such as sinking speeds, airplane weight and weight distribution, attitudes and angular velocities, rough terrain contours, etc.

3.2.3Time histories of external loads, response loads, and motionsTime histories of external loads, response loads, and motions for all critical dynamic loading conditions and tabulation of maximum dynamic and static loads.

3.2.4Time histories of response loads, such as bending moments, shears, and torsionsTime histories of response loads, such as bending moments, shears, and torsions, with tabulation of maximum response loads.

3.2.5Amplifying information and discussion to substantiate the criticality of conditionsAmplifying information and discussion to substantiate the criticality of conditions in the ground loads analysis.

3.3Supporting Equations and DocumentationDescribe the equations used for determining static and dynamic loads. Describe the following data to support a dynamic loads analysis:

3.3.1The critical elastic modes of vibration

3.3.2The dynamic response characteristics of the store

3.3.3Aerodynamic and inertial loads

References

MIL-STD-8591 Airborne Stores, Suspension Equipment and Aircraft-Store Interface (Carriage Phase) https://quicksearch.dla.mil

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