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MIL-A-8860B
AIRPLANE STRENGTH AND RIGIDITY, GENERAL SPECIFICATION FOR
Year: 1987
Abstract: This specification contains general requirements, which, in combination with other applicable specifications, define the structural design, analysis, test, and data requirements for fixed wing piloted airplanes. These requirements include, but are not limited to, the following:
a. The strength and rigidity of the structure of the airplane including supporting and carry-through structures for fixed equipment and useful load items.
b. The strength and rigidity of control systems for operation of lateral, longitudinal, and directional control surfaces; dive or speed brakes; high lift devices; tabs; stabilizers; spoilers; certain other mechanisms; and their respective carry-through structures.
c. The shock-absorption characteristics and strength of landing-gear units and the strength and rigidity of their control systems and of their carry-through structures. Requirements for wheels, tires, and brakes are also included.
d. The strength of structures integral with the airplane provided for transmitting catapulting forces to the airplanes, and for engaging shipboard and shorebase arresting gear, and barricades. Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Naval Air Engineering Center, Systems Engineering and Standardization Department (Code 93), Lakehurst, NJ 08733-5100, by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document, or by letter.
e. The strength of anchor-line clamps, and the airplane strength for hoisting, jacking, towing, tie-down, and other ground- or deck-handling conditions.
f. Flutter and other aeroelastic instability prevention, and aeroacoustic and vibration characteristics.
g. Determination of special weapons effects.
h. Structural design, analysis, and test data.
i. Laboratory and flight tests performed to obtain information regarding strength rigidity and loads.
j. Definitions. Intended Use: The requirements of this specification are intended for use in the structural design and substantiation of airplanes.
a. The strength and rigidity of the structure of the airplane including supporting and carry-through structures for fixed equipment and useful load items.
b. The strength and rigidity of control systems for operation of lateral, longitudinal, and directional control surfaces; dive or speed brakes; high lift devices; tabs; stabilizers; spoilers; certain other mechanisms; and their respective carry-through structures.
c. The shock-absorption characteristics and strength of landing-gear units and the strength and rigidity of their control systems and of their carry-through structures. Requirements for wheels, tires, and brakes are also included.
d. The strength of structures integral with the airplane provided for transmitting catapulting forces to the airplanes, and for engaging shipboard and shorebase arresting gear, and barricades. Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Naval Air Engineering Center, Systems Engineering and Standardization Department (Code 93), Lakehurst, NJ 08733-5100, by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document, or by letter.
e. The strength of anchor-line clamps, and the airplane strength for hoisting, jacking, towing, tie-down, and other ground- or deck-handling conditions.
f. Flutter and other aeroelastic instability prevention, and aeroacoustic and vibration characteristics.
g. Determination of special weapons effects.
h. Structural design, analysis, and test data.
i. Laboratory and flight tests performed to obtain information regarding strength rigidity and loads.
j. Definitions. Intended Use: The requirements of this specification are intended for use in the structural design and substantiation of airplanes.
Subject: Aeroacoustics
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| contributor author | AIR FORCE - 71 - Air Force Sustainment Center - Oklahoma City | |
| date accessioned | 2017-09-04T16:12:08Z | |
| date available | 2017-09-04T16:12:08Z | |
| date copyright | 05/20/1987 | |
| date issued | 1987 | |
| identifier other | SOCJDAAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;query=autho162s7D83081DAC426159DD6E350F014A/handle/yse/75380 | |
| description abstract | This specification contains general requirements, which, in combination with other applicable specifications, define the structural design, analysis, test, and data requirements for fixed wing piloted airplanes. These requirements include, but are not limited to, the following: a. The strength and rigidity of the structure of the airplane including supporting and carry-through structures for fixed equipment and useful load items. b. The strength and rigidity of control systems for operation of lateral, longitudinal, and directional control surfaces; dive or speed brakes; high lift devices; tabs; stabilizers; spoilers; certain other mechanisms; and their respective carry-through structures. c. The shock-absorption characteristics and strength of landing-gear units and the strength and rigidity of their control systems and of their carry-through structures. Requirements for wheels, tires, and brakes are also included. d. The strength of structures integral with the airplane provided for transmitting catapulting forces to the airplanes, and for engaging shipboard and shorebase arresting gear, and barricades. Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Naval Air Engineering Center, Systems Engineering and Standardization Department (Code 93), Lakehurst, NJ 08733-5100, by using the self-addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document, or by letter. e. The strength of anchor-line clamps, and the airplane strength for hoisting, jacking, towing, tie-down, and other ground- or deck-handling conditions. f. Flutter and other aeroelastic instability prevention, and aeroacoustic and vibration characteristics. g. Determination of special weapons effects. h. Structural design, analysis, and test data. i. Laboratory and flight tests performed to obtain information regarding strength rigidity and loads. j. Definitions. Intended Use: The requirements of this specification are intended for use in the structural design and substantiation of airplanes. | |
| language | English | |
| title | MIL-A-8860B | num |
| title | AIRPLANE STRENGTH AND RIGIDITY, GENERAL SPECIFICATION FOR | en |
| type | standard | |
| page | 18 | |
| status | Active | |
| tree | AIR FORCE - 71 - Air Force Sustainment Center - Oklahoma City:;1987 | |
| contenttype | fulltext | |
| subject keywords | Aeroacoustics | |
| subject keywords | Aeroelastic | |
| subject keywords | Airplane | |
| subject keywords | Airplane configuration | |
| subject keywords | Airplane rigidity | |
| subject keywords | Airplane speeds | |
| subject keywords | Airplane strength | |
| subject keywords | Design weight | |
| subject keywords | Divergence | |
| subject keywords | Fail-safe | |
| subject keywords | Flight loads | |
| subject keywords | Flight tests | |
| subject keywords | Flutter | |
| subject keywords | Landing-gear | |
| subject keywords | Shock absorption (landing gear) | |
| subject keywords | Special weapons | |
| subject keywords | Structural design | |
| subject keywords | Takeoff | |
| subject keywords | Ultimate loads | |
| subject keywords | Vibration |