DI-SESS-82489
Dynamic Response Analysis and Test Report
Describes the ground and flight analyses and tests used to characterize a system's elastic response to dynamic load inputs, verifying the dynamic loads and fatigue loads spectrum, with results used to determine service life for operational usage.
Approval DateJuly 9, 2025
AMSC NumberF10575
Preparing Activity11 (AFLCMC/EZFS)
Project NumberSESS-2025-014
OPR—
DTIC ApplicableNo
GIDEP ApplicableNo
Limitation—
Applicable Forms—
Approval Limitation—
Form Version—
DID Formatfree_text
963C CompliantYes
DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited.
Application & Interrelationship
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Use & Relationship
The Dynamic Response Analysis and Test Report describes the ground and flight analyses and tests used to characterize the system elastic response to dynamic load inputs. It provides a means for verifying or improving the dynamic loads analysis and fatigue loads spectrum for the air vehicle, missile, or helicopter weapon system. Results are incorporated into the fatigue test program to determine service life for actual operational usage.
a. This Data Item Description (DID) is applicable to any contract for which a dynamic response test is required.
b. This DID contains the format, content, and intended use information for the data deliverable resulting from the work task described in section 5 of MIL-STD-1530, Aircraft Structural Integrity Program (ASIP) (copies of this document are available online at https://quicksearch.dla.mil).
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.
2FormatThe Dynamic Response Analysis and Test Report shall be in the contractor's format.
3ContentThe Dynamic Response Analysis and Test Report shall describe the contractor's analyses and testing activities associated with the design for dynamic load inputs. The report shall contain the results and findings used to validate or correct the initial dynamic response analyses.
3.1The report shall be based on the interpretationand evaluation of the dynamic response analyses and tests and shall contain the following, as applicable:
3.1.1Descriptions and photographs of the systemfixturing, rigging, ground equipment, instrumentation, component(s) under test, and the configurations including fuel states, store loadings, weights, centers-of-gravity, internal payloads, and simulated sling loads.
3.1.2Descriptions of the flight or ground handling conditionsthat result in significant dynamic responses of the structure, and the effects of these conditions on service life.
3.1.3Descriptions of the test procedurestest conditions, test methods, and data acquisition systems, including a copy of the final version of the test plan.
3.1.4Descriptions of the methodologies used for selectingtest instrumentation types, test instrumentation measurement capabilities, and test measurement locations.
3.1.5Specifications for all test instrumentation
3.1.6Description of the methods used for mounting instrumentation
3.1.7Descriptions of the methods used for the reduction and analysis of the test data
3.1.8Copy of the test matrix as planned to be executed
3.1.9Defined measurement units including axis labels of plots and figures
3.1.10Plots of the transfer functions versus frequency for vibration sensors
3.1.11Descriptions and time history plots of critical test load cases
3.1.12Copy of the test log as executed
3.1.13Results from both discrete and power spectral density methodsof analysis and a comparison of the load inputs, structural responses, and transfer functions with the dynamic loads analysis.
3.1.14The transfer functions between the internal structural loadsand accelerations at various locations throughout the airframe and the gust, landing, taxi, takeoff, towing, buffet, aerial refueling, catapult, arrestment, gun fire, and store ejection load inputs.
3.1.15The transfer functions between vertical center of gravityaccelerations and the load frequency distribution for the range of gross weights, system configurations, speeds, angles of attack, angles of sideslip, and altitudes being flown in service.
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