Evaluation of Fuel Flowmeter Instrumentation
Flight tests on the Flow Technology Inc. standard line turbine flow transducer were conducted between 5 August and 20 October 1970 to determine its acceptability as a test instrument. The evaluation was conducted at Edwards Air Force Base, California, by the US Army Aviation Systems Test Activity. G...
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| creator | Winn,Albert L Jefferis,Robert P |
| description | Flight tests on the Flow Technology Inc. standard line turbine flow transducer were conducted between 5 August and 20 October 1970 to determine its acceptability as a test instrument. The evaluation was conducted at Edwards Air Force Base, California, by the US Army Aviation Systems Test Activity. Ground calibrations showed that the sensor can be used with precision equal to present flow measurement methods. The testing consisted of 2.9 flight hours with the measurement systems mounted in a UH-1C helicopter. The Flow Technology sensor performance was compared to that obtained with standard Potter and Revere flight test systems. Results show that the sensor is acceptable as a flight test instrument. The indicator sensitivity is excellent and there was no degradation of meter performance with variations in engine power or flight conditions. Although the indicator scale range was suitable for this test, the range is not large enough to be operable on all Army aircraft. (Author) |
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The evaluation was conducted at Edwards Air Force Base, California, by the US Army Aviation Systems Test Activity. Ground calibrations showed that the sensor can be used with precision equal to present flow measurement methods. The testing consisted of 2.9 flight hours with the measurement systems mounted in a UH-1C helicopter. The Flow Technology sensor performance was compared to that obtained with standard Potter and Revere flight test systems. Results show that the sensor is acceptable as a flight test instrument. The indicator sensitivity is excellent and there was no degradation of meter performance with variations in engine power or flight conditions. Although the indicator scale range was suitable for this test, the range is not large enough to be operable on all Army aircraft. (Author)</description><language>eng</language><subject>AIRCRAFT ENGINES ; DETECTORS ; FLIGHT TESTING ; FLOWMETERS ; FUEL CONSUMPTION ; FUEL SYSTEMS ; H-1 AIRCRAFT ; Helicopters ; MEASUREMENT ; RELIABILITY ; TEST EQUIPMENT ; Test Facilities, Equipment and Methods ; TEST METHODS ; UH-1C AIRCRAFT</subject><creationdate>1971</creationdate><rights>APPROVED FOR PUBLIC RELEASE</rights><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>230,776,881,27544,27545</link.rule.ids><linktorsrc>$$Uhttps://apps.dtic.mil/sti/citations/AD0719280$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Winn,Albert L</creatorcontrib><creatorcontrib>Jefferis,Robert P</creatorcontrib><creatorcontrib>ARMY AVIATION SYSTEMS TEST ACTIVITY EDWARDS AFB CALIF</creatorcontrib><title>Evaluation of Fuel Flowmeter Instrumentation</title><description>Flight tests on the Flow Technology Inc. standard line turbine flow transducer were conducted between 5 August and 20 October 1970 to determine its acceptability as a test instrument. The evaluation was conducted at Edwards Air Force Base, California, by the US Army Aviation Systems Test Activity. Ground calibrations showed that the sensor can be used with precision equal to present flow measurement methods. The testing consisted of 2.9 flight hours with the measurement systems mounted in a UH-1C helicopter. The Flow Technology sensor performance was compared to that obtained with standard Potter and Revere flight test systems. Results show that the sensor is acceptable as a flight test instrument. The indicator sensitivity is excellent and there was no degradation of meter performance with variations in engine power or flight conditions. Although the indicator scale range was suitable for this test, the range is not large enough to be operable on all Army aircraft. (Author)</description><subject>AIRCRAFT ENGINES</subject><subject>DETECTORS</subject><subject>FLIGHT TESTING</subject><subject>FLOWMETERS</subject><subject>FUEL CONSUMPTION</subject><subject>FUEL SYSTEMS</subject><subject>H-1 AIRCRAFT</subject><subject>Helicopters</subject><subject>MEASUREMENT</subject><subject>RELIABILITY</subject><subject>TEST EQUIPMENT</subject><subject>Test Facilities, Equipment and Methods</subject><subject>TEST METHODS</subject><subject>UH-1C AIRCRAFT</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1971</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNrjZNBxLUvMKU0syczPU8hPU3ArTc1RcMvJL89NLUktUvDMKy4pKs1NzSsBq-BhYE1LzClO5YXS3Awybq4hzh66KSWZyfHFJZl5qSXxji4G5oaWRhYGxgSkAQsjJyU</recordid><startdate>197101</startdate><enddate>197101</enddate><creator>Winn,Albert L</creator><creator>Jefferis,Robert P</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>197101</creationdate><title>Evaluation of Fuel Flowmeter Instrumentation</title><author>Winn,Albert L ; Jefferis,Robert P</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_AD07192803</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1971</creationdate><topic>AIRCRAFT ENGINES</topic><topic>DETECTORS</topic><topic>FLIGHT TESTING</topic><topic>FLOWMETERS</topic><topic>FUEL CONSUMPTION</topic><topic>FUEL SYSTEMS</topic><topic>H-1 AIRCRAFT</topic><topic>Helicopters</topic><topic>MEASUREMENT</topic><topic>RELIABILITY</topic><topic>TEST EQUIPMENT</topic><topic>Test Facilities, Equipment and Methods</topic><topic>TEST METHODS</topic><topic>UH-1C AIRCRAFT</topic><toplevel>online_resources</toplevel><creatorcontrib>Winn,Albert L</creatorcontrib><creatorcontrib>Jefferis,Robert P</creatorcontrib><creatorcontrib>ARMY AVIATION SYSTEMS TEST ACTIVITY EDWARDS AFB CALIF</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Winn,Albert L</au><au>Jefferis,Robert P</au><aucorp>ARMY AVIATION SYSTEMS TEST ACTIVITY EDWARDS AFB CALIF</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>Evaluation of Fuel Flowmeter Instrumentation</btitle><date>1971-01</date><risdate>1971</risdate><abstract>Flight tests on the Flow Technology Inc. standard line turbine flow transducer were conducted between 5 August and 20 October 1970 to determine its acceptability as a test instrument. The evaluation was conducted at Edwards Air Force Base, California, by the US Army Aviation Systems Test Activity. Ground calibrations showed that the sensor can be used with precision equal to present flow measurement methods. The testing consisted of 2.9 flight hours with the measurement systems mounted in a UH-1C helicopter. The Flow Technology sensor performance was compared to that obtained with standard Potter and Revere flight test systems. Results show that the sensor is acceptable as a flight test instrument. The indicator sensitivity is excellent and there was no degradation of meter performance with variations in engine power or flight conditions. Although the indicator scale range was suitable for this test, the range is not large enough to be operable on all Army aircraft. (Author)</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AIRCRAFT ENGINES DETECTORS FLIGHT TESTING FLOWMETERS FUEL CONSUMPTION FUEL SYSTEMS H-1 AIRCRAFT Helicopters MEASUREMENT RELIABILITY TEST EQUIPMENT Test Facilities, Equipment and Methods TEST METHODS UH-1C AIRCRAFT |
| title | Evaluation of Fuel Flowmeter Instrumentation |
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