EverySpec Standards
Home > Library > MIL-SPECS > MIL-SPECS-MIL-A > MIL-A-8870C

MIL-A-8870C, MILITARY SPECIFICATION: AIRPLANE STRENGTH AND RIGIDITY VIBRATION, FLUTTER, AND DIVERGENCE (25 MAR 1993)

MIL-A-8870C, MILITARY SPECIFICATION: AIRPLANE STRENGTH AND RIGIDITY VIBRATION, FLUTTER, AND DIVERGENCE (25 MAR 1993)., 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.

MIL-A-8870 Rev. C

    
 Status:
Active

 FSC Code:
 1510 - Aircraft, Fixed Wing

Version:
C03-19933.19 MB MIL-A-8870C
B05-19876.01 MB MIL-A-8870B
A05-198753.88 KB MIL-A-008870A

   Is this standard useful?
+6 -0
Simple Search
MilSpec Search



EverySpec Standards
About Us   |   Terms of Use   |   DMCA   |   Privacy   |   EverySpec LLC © 2009 - 2014   All rights reserved. new