MIL-STD-202H.pdf - 第58页

MI L - S TD - 202 - 10 9 CO NT E N T S PARAGRAPH PAG E FOREW ORD … ………………………………………………………. ii 1. SCOPE 1 1.1 Purpose …… ………………… …………………. …… .. …………. 1 2. APPLICABLE D O C U M EN T S 1 3. DEFINTIONS 1 4. GENERAL RE Q UI R …

MIL-STD-202-109

FOREWORD

1. This standard is approved for use by all Departments and Agencies of the Department of Defense.

2. This entire standard has been revised. This revision has resulted in many changes to the format, but the most

significant one is the splitting the document into test methods. See MIL-STD-202 for the change summary.

3. Comments, suggestions, or questions on this document should be emailed to std202@dla.mil or addressed to:

Commander, Defense Logistics Agency, DLA Land and Maritime, ATTN: VAT, P.O. Box 3990, Columbus, OH

43218–3990. Since contact information can change, you may want to verify the currency of this address

information using the ASSIST Online database at https://assist.dla.mil.

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MIL-STD-202-109

CONTENTS

PARAGRAPH PAGE

FOREWORD…………………………………………………………. ii

1. SCOPE 1

1.1 Purpose………………………………………….……..…………. 1

2. APPLICABLE DOCUMENTS 1

3. DEFINTIONS 1

4. GENERAL REQUIREMENTS 1

4.1 Apparatus ……………………………………………..…………. 1

4.1.1 Test facility……………………………………………………….. 1

4.1.1.1 Test facility performance requirements. …………………….. 1

4.1.1.1.1 Chamber design pressure…………………………………..….. 1

4.1.1.1.2 Pressure altitude. ………………………………..…………..….. 1

4.1.1.1.3 Chamber air temperature. …………………………………..….. 1

4.1.2 Fuel…..…………………………..….…………….………………. 2

4.1.3 Fuel vapor mixture. …………..….…………….……………….. 2

4.1.3.1 Effect of humidity on flammable atmosphere………………… 2

4.1.4 Altitude simulation. ……..….…………….…………….……….. 2

4.2. Procedure……..………………..….…………….………………. 3

4.2.1 Test preparation ………………………..……………………..… 3

4.2.1.1 Controls..……………………..………………………….……..… 3

4.2.1.1.2 Mounting..…………………..……………………..…….……..… 3

4.2.1.2 Loading. …………………..………..……………..…….……..… 3

4.2.2 Test execution..…………..………..……………..…….……..… 4

4.2.3 Test altitudes….…………..………..……………..…….……..… 4

5. DETAILED REQUIREMENTS 4

5.1 Summary……………..…………………………..………………. 4

6. NOTES 5

6.1 Supersession data………………………………………………. 5

FIGURE PAGE

1 Specific gravity of n-hexane…………………………………………..…… 3

iii

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MIL-STD-202-109

METHOD 109

EXPLOSION

1. SCOPE

1.1 Purpose. The purpose of this method is to determine if a part, while operating, will ignite an ambient explosive

atmosphere. This environment is prevalent in aircraft; therefore, the test is conducted at ground level and various

reduced barometric pressures. The parts subjected to this type of test are not enclosed in casings designed to

prevent flame or explosion propagation.

2. APPLICABLE DOCUMENTS

This section not applicable to this standard.

3. DEFINTIONS

This section not applicable to this standard.

4. GENERAL REQUIREMENTS

4.1. Apparatus.

4.1.1 Test facility. The test apparatus consists of a test chamber or cabinet together with associated equipment,

safety provisions, and auxiliary instrumentation necessary to establish, maintain, and monitor the specified test

conditions. The chamber should be equipped with a system for mixing and circulation of the explosive air-fuel

mixture, a means to ignite the air-fuel mixture such as a spark-gap device, as well as a means to collect and

determine the explosiveness of a sample of the mixture such as a spark gap or glow plug ignition source with

sufficient energy to ignite a 3.82 percent hexane mixture. An alternative method of determining the explosive

characteristics of the vapor is use of a calibrated explosive gas meter that verifies the degree of explosiveness and

the concentration of the air-fuel mixture. The chamber or cabinet should include provisions for the electrical and

mechanical operation of the specimen under test.

4.1.1.1 Test facility performance requirements.

4.1.1.1.1 Chamber design pressure. The test chamber shall be capable of withstanding any explosion pressure up

to and including 300 pounds per square inch (2 megapascals).

4.1.1.1.2 Pressure altitude. The test chamber shall be capable of maintaining any desired pressure altitude from

sea level to 60,000 feet (18,250 meters) ± 2 percent.

4.1.1.1.3 Chamber air temperature. The air temperature within the test chamber shall be uniform and shall be

controllable between 20°C ± 3°C and 240°C ± 3°C.

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