MIL-A-8870 Revision C:1993
Current
The latest, up-to-date edition.
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.
| MIL A 8893 : 0 | AIRPLANE STRENGTH AND RIGIDITY, SONIC FATIGUE |
| MIL-A-8860 Revision B:1987 | Airplane Strength and Rigidity, General Specification for |
| MIL-STD-8591 Base Document:2005 | Airborne Stores, Suspension Equipment and Aircraft-Store Interface (Carriage Phase) |
| MIL-A-8866 Revision C:1987 | Airplane Strength and Rigidity Reliability Requirements, Repeated Loads, Fatigue and Damage Tolerance |
| MIL-D-8684 Revision B:1959 | Data and Tests, Engineering, Contact Requirements for Air Launched Guided Missile Systems (No S/S Document) |
| MIL F 9490 : D | FLIGHT CONTROL SYSTEMS - DESIGN, INSTALLATION AND TEST OF PILOTED AIRCRAFT, GENERAL SPECIFICATION FOR |
| MIL-HDBK-244 Revision A:1990 | Guide to Aircraft/Stores Compatibility |
| MIL STD 1763 : A | AIRCRAFT STORES CERTIFICATION PROCEDURES |
| MIL-A-8591 Revision H:1990 | Airborne Stores, Suspension Equipment and Aircraft-Store Interface (Carriage Phase); General Design Criteria for (S/S by MIL-STD-8591) |
| MIL-D-8685 Revision B:1967 | Data and Tests, Engineering, Contract Requirements for Guided Missile Target Systems (No S/S Document) |
| SAE ARP94910 | Aerospace - Vehicle Management Systems - Flight Control Design, Installation and Test of, Military Unmanned Aircraft, Specification Guide For |
| SAE AS94900 | Aerospace - Flight Control Systems - Design, Installation and Test of Piloted Military Aircraft, General Specification For |
| MIL-HDBK-516 Revision C:2014 | Airworthiness Certification Criteria |
| MIL-A-8868 Revision B:1987 | Airplane Strength and Rigidity Data and Reports (No S/S Document) |
| MIL-DTL-9490 Revision E:2008 | Flight Control Systems - Design, Installation and Test of Piloted Aircraft, General Specification for |
| JSSG-2006 Base Document:1998 | Aircraft Structures |
| MIL-HDBK-1763 Base Document:1998 | Aircraft/Stores Compatibility: Systems Engineering Data Requirements and Test Procedures |
| MIL-T-18232 Revision B:1968 | Targets, Aerial, Powered, Design and Construction of General Specification for (No S/S Document) |
| MIL A 8892 : 0 | AIRPLANE STRENGTH AND RIGIDITY, VIBRATION |
| MIL-D-8708 Revision C:1991 | Demonstration: Aircraft Weapon Systems, General Specification for |
| SAE AS8860 | Landing Gear Structural Requirements as Listed in the MIL-886X Series of Specifications |
| SAE AIR4922A | Primary Flight Control Hydraulic Actuation System Interface Definition |
| MIL-A-8863 Revision C:1993 | Airplane Strength and Rigidity Ground Loads for Navy Acquired Airplanes |
| MIL-A-8861 Revision B:1986 | Airplane Strength and Rigidity Flight Loads |
| MIL-A-8866 Revision C:1987 | Airplane Strength and Rigidity Reliability Requirements, Repeated Loads, Fatigue and Damage Tolerance |
| MIL-A-8860 Revision B:1987 | Airplane Strength and Rigidity, General Specification for |
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