MIL-A-8870 Revision C:1993
Current
Airplane Strength and Rigidity Vibration, Flutter, and Divergence
25-03-1993
1. SCOPE
2. APPLICABLE DOCUMENTS
3. REQUIREMENTS
4. QUALITY ASSURANCE PROVISIONS
5. PACKAGING
6. NOTES
Provides criteria to preclude flutter, divergence, and other dynamic and static aeroelastic instabilities; control structural vibrations; limit vibration levels in crew and passenger stations and preclude fatigue cracking initiation.
| DevelopmentNote |
C NOTICE 1 - Notice of Validation. (08/2014)
|
| DocumentType |
Standard
|
| Pages |
56
|
| ProductNote |
NEW CHILD NOT 2 2019 NOW ADDED
|
| PublisherName |
US Military Specs/Standards/Handbooks
|
| Status |
Current
|
This specification contains the general and detail design
requirements and criteria in the design and construction of airplanes to:
a. Prevent flutter, divergence, and other dynamic and static
aeroelastic instabilities.
b. Control structural vibrations.
c. Prevent fatigue failure of the airframe structure or structural
components induced by vibrations, aeroacoustic and other oscillatory loads for the service life of the airplane.
d. Prescribe structural dynamic analyses, laboratory and ground tests, and structural dynamic flight tests required to demonstrate compliance with design requirements.
e. Apply to airplanes acquired by the Navy for all conditions of flight and surface operations for which the airplanes are required to operate.
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