DI-MISC-81387A
Airframe Rigidity Test Report
This DID specifies the Airframe Rigidity Test Report, providing data to evaluate air vehicle modal vibration characteristics and rigidity properties against calculated analytical results.
Approval DateSeptember 27, 2007
AMSC NumberF9003
Preparing Activity—
Project Number—
OPR11 (ASC/ENFS)
DTIC ApplicableNo
GIDEP ApplicableNo
Limitation—
Applicable Forms—
Approval Limitation—
Form Version—
DID Formatdd_form_1664
963C CompliantNo
DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited.
Application & Interrelationship
—
Use & Relationship
This report on Airframe Rigidity Testing will provide data for the detailed evaluation of the air vehicle modal vibration characteristics and rigidity properties and comparison with calculated results. The principal use is to validate or update analytical models.
a. This Data Item Description (DID) is applicable to any contract for which a ground vibration test or other airframe rigidity 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 the contract.
c. DI-MISC-81387A supersedes DI-MISC-81387.
Preparation Instructions
1Reference Documents.The 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.
2Format.The Airframe Rigidity Test Report shall be in the contractor's format.
3Content.The Airframe Rigidity Test Report shall contain:
3.1The Air vehicle Vibration Test.When applicable, this section shall contain the following:
3.1.1Descriptions and photographs of the air vehicle suspension system, the instrumentation, and the air vehicle configurations.
3.1.2Description of test procedures, data acquisition, and methods of data reduction analysis.
3.1.4Mode shape measurement locations.
3.1.5Plots of the transfer function versus frequency for strategically located vibration pickups.
3.1.6The natural frequency, mode shapes, structural damping, and node line locations for all obtained structural modes of vibration that may be important with respect to flutter and other dynamic analyses.
3.1.7A comparison of the measured air vehicle modal data (frequencies, mode shapes, and node lines) with those as predicted by the analytical model.
3.2Aeroservoelastic ground test.When applicable, this section shall contain the following:
3.2.2Comparison of the test results with corresponding analysis.
3.3Component test.When applicable, this section shall contain results of the following tests:
3.3.1Component ground vibration tests on control surfaces, pylons, flaps, horizontal stabilizers, canards, control surface actuators, control surface dampers, racks for supporting stores, weapons bay doors, landing gear doors, and landing gear.
3.3.2Component stiffness tests.
3.3.3Control surface, tab, and actuator rigidity, free play, and wear tests.
3.3.4Balance weight attachment verification tests.
3.3.5Mass property measurements of control surfaces, tabs, and external stores.
3.3.6Flutter damper qualification and wear tests.
Schema v3.0Community-maintained · Verify against ASSIST 