MIL-STD-1822A(USAF)
5.2.1.6 Environmental fly-around and data (see 4.3.1.8).
Support for environmental fly-around tests will be provided. These tests will be conducted by the appropriate Air Force test organization and will provide the basic data to demonstrate the warhead compatibility with the carriage/launch environments (thermal, vibration, and acoustic) for all aircraft weapon carriage locations. Vibration analyses will be conducted to identify the important frequencies and modes for the various arrangements of weapons on the launcher or pylon. Ground vibration tests of selected configurations may be performed to substantiate the vibration analysis results. In-flight measurements of the thermal, vibration, and acoustic environments will be made for selected configurations and flight conditions. Vibration of the weapon bay doors will be measured to demonstrate that the weapon bay door motion is not such that it could cause less than the required weapon-to-door clearance for ejection. Tests will be conducted with a vibrational fly-around assembly to simulate the structure and dynamic response of the actual warhead/bomb. Other environmental data will be gathered by sensors in the weapon bays or external pylons.
5.2.1.7 Separation tests (in-flight) (see 4.3.1.10).
Separation tests to assure compatibility of the aircraft with required nuclear weapons will be conducted. The tests will verify proper separation within the aircraft flight envelope to determine the nuclear weapon launch or delivery envelope. Detailed requirements and instrumentation will be jointly determined by the SPO, DoE laboratories, AFNWC/NCS, and contractors. The flight parameters of the drop tests will include all of the aircraft flight envelope with conditions tailored to the expected carrier flight and delivery envelopes. The number of tests required will be a function of the completeness of the 6 DOF model dynamic analysis and wind tunnel testing. Tests will at least verify the results predicted by wind tunnel tests and analytical modes in the extremes of the flight envelope.
5.2.1.8 Mechanical fit and electrical function tests (see 4.3.1.7, 4.3.1.16, 4.3.1.17).
The following tests will be performed by AFNWC/NCS and the DoE laboratories. MICDs and
EICDs will be delivered in sufficient time to support these tests.
a. A mechanical fit test will be performed for all configurations of the aircraft and for applicable transportation equipment. The test will include uploading and downloading (mating/de-mating) of compatibility test unit(s) at all stations using production or production-equivalent hardware and appropriate support equipment.
b. An electrical function test will be performed to verify compliance with the applicable portion of the AMAC POG System 1 or System 2 interface specification/standard and interoperability with other nuclear weapons carried on the aircraft. The test will include a flight test to verify the interface during flight conditions.
5.2.1.9 ACCD (see 4.3.1.19).
The ACCD is a control drawing prepared and maintained by SNL which establishes the extent of compatibility and restrictions between a nuclear bomb and an aircraft. It is released after the compatibility tasks defined in the CRP have been successfully completed. A similar document, the Compatibility Certification (CC) Drawing is used for cruise missile warheads. The ACCD and CC are maintained by SNL.
5.2.1.10 MAR.
The compatibility analyses and tests between aircraft/missile/warhead/bomb culminate in the issuance by the DoE of a compatibility statement contained in a document called the Major
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