JUH-1H Pneumatic Boot Deicing System Flight Test Evaluation
The concept of operation of the Pneumatic Boot Deicing System as a deice system is feasible under the conditions tested when installed on the test UH-1H helicopter. A cooperative effort between NASA and the B.F. Goodrich Company led to the development of a prototype pneumatic boot deicing system des...
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| creator | Haworth, Loran A Oliver, Randall G Woratschek, Ralph |
| description | The concept of operation of the Pneumatic Boot Deicing System as a deice system is feasible under the conditions tested when installed on the test UH-1H helicopter. A cooperative effort between NASA and the B.F. Goodrich Company led to the development of a prototype pneumatic boot deicing system designed for use on a helicopter main rotor system. Flight tests were conducted to establish an operational envelope and evaluate the feasibility of the pneumatic deicing concept. Phase I consisted of a ground and inflight structural loads survey which established an operational envelope. Phase II was a limited aircraft performance and handling qualities evaluation, and Phase III involved artificial icing tests. Thirteen problem areas were identified with the prototype Pneumatic Boot Deicing System installation, two of which were corrected during the evaluation. Major problem areas included excessive increases in power required for flight and deicer material erosion and breakdown. |
| format | Report |
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A cooperative effort between NASA and the B.F. Goodrich Company led to the development of a prototype pneumatic boot deicing system designed for use on a helicopter main rotor system. Flight tests were conducted to establish an operational envelope and evaluate the feasibility of the pneumatic deicing concept. Phase I consisted of a ground and inflight structural loads survey which established an operational envelope. Phase II was a limited aircraft performance and handling qualities evaluation, and Phase III involved artificial icing tests. Thirteen problem areas were identified with the prototype Pneumatic Boot Deicing System installation, two of which were corrected during the evaluation. Major problem areas included excessive increases in power required for flight and deicer material erosion and breakdown.</description><language>eng</language><subject>AVIATION SAFETY ; BOOTS ; DEICING MATERIALS ; DEICING SYSTEMS ; EROSION ; FLIGHT TESTING ; H-1 AIRCRAFT ; HANDLING ; HELICOPTER ROTORS ; Helicopters ; HOVERING ; Hydraulic and Pneumatic Equipment ; INFLATABLE STRUCTURES ; LEADING EDGES ; LEVEL FLIGHT ; LOAD DISTRIBUTION ; LPN-DA-A-83306B ; PBDS(PNEUMATIC BOOT DEICING SYSTEM) ; PRESSURE REGULATORS ; PROTOTYPES ; ROTOR BLADES(ROTARY WINGS) ; RUBBER ; SPRAYS ; STRUCTURAL LOADS ; STRUCTURAL PROPERTIES ; UH-1H AIRCRAFT ; VIBRATION</subject><creationdate>1983</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>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>230,780,885,27567,27568</link.rule.ids><linktorsrc>$$Uhttps://apps.dtic.mil/sti/citations/ADA140986$$EView_record_in_DTIC$$FView_record_in_$$GDTIC$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Haworth, Loran A</creatorcontrib><creatorcontrib>Oliver, Randall G</creatorcontrib><creatorcontrib>Woratschek, Ralph</creatorcontrib><creatorcontrib>ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA</creatorcontrib><title>JUH-1H Pneumatic Boot Deicing System Flight Test Evaluation</title><description>The concept of operation of the Pneumatic Boot Deicing System as a deice system is feasible under the conditions tested when installed on the test UH-1H helicopter. A cooperative effort between NASA and the B.F. Goodrich Company led to the development of a prototype pneumatic boot deicing system designed for use on a helicopter main rotor system. Flight tests were conducted to establish an operational envelope and evaluate the feasibility of the pneumatic deicing concept. Phase I consisted of a ground and inflight structural loads survey which established an operational envelope. Phase II was a limited aircraft performance and handling qualities evaluation, and Phase III involved artificial icing tests. Thirteen problem areas were identified with the prototype Pneumatic Boot Deicing System installation, two of which were corrected during the evaluation. Major problem areas included excessive increases in power required for flight and deicer material erosion and breakdown.</description><subject>AVIATION SAFETY</subject><subject>BOOTS</subject><subject>DEICING MATERIALS</subject><subject>DEICING SYSTEMS</subject><subject>EROSION</subject><subject>FLIGHT TESTING</subject><subject>H-1 AIRCRAFT</subject><subject>HANDLING</subject><subject>HELICOPTER ROTORS</subject><subject>Helicopters</subject><subject>HOVERING</subject><subject>Hydraulic and Pneumatic Equipment</subject><subject>INFLATABLE STRUCTURES</subject><subject>LEADING EDGES</subject><subject>LEVEL FLIGHT</subject><subject>LOAD DISTRIBUTION</subject><subject>LPN-DA-A-83306B</subject><subject>PBDS(PNEUMATIC BOOT DEICING SYSTEM)</subject><subject>PRESSURE REGULATORS</subject><subject>PROTOTYPES</subject><subject>ROTOR BLADES(ROTARY WINGS)</subject><subject>RUBBER</subject><subject>SPRAYS</subject><subject>STRUCTURAL LOADS</subject><subject>STRUCTURAL PROPERTIES</subject><subject>UH-1H AIRCRAFT</subject><subject>VIBRATION</subject><fulltext>true</fulltext><rsrctype>report</rsrctype><creationdate>1983</creationdate><recordtype>report</recordtype><sourceid>1RU</sourceid><recordid>eNrjZLD2CvXQNfRQCMhLLc1NLMlMVnDKzy9RcEnNTM7MS1cIriwuSc1VcMvJTM8oUQhJLS5RcC1LzCkFqszP42FgTUvMKU7lhdLcDDJuriHOHropQHPii0sy81JL4h1dHA1NDCwtzIwJSAMAMUkrSw</recordid><startdate>198305</startdate><enddate>198305</enddate><creator>Haworth, Loran A</creator><creator>Oliver, Randall G</creator><creator>Woratschek, Ralph</creator><scope>1RU</scope><scope>BHM</scope></search><sort><creationdate>198305</creationdate><title>JUH-1H Pneumatic Boot Deicing System Flight Test Evaluation</title><author>Haworth, Loran A ; Oliver, Randall G ; Woratschek, Ralph</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-dtic_stinet_ADA1409863</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1983</creationdate><topic>AVIATION SAFETY</topic><topic>BOOTS</topic><topic>DEICING MATERIALS</topic><topic>DEICING SYSTEMS</topic><topic>EROSION</topic><topic>FLIGHT TESTING</topic><topic>H-1 AIRCRAFT</topic><topic>HANDLING</topic><topic>HELICOPTER ROTORS</topic><topic>Helicopters</topic><topic>HOVERING</topic><topic>Hydraulic and Pneumatic Equipment</topic><topic>INFLATABLE STRUCTURES</topic><topic>LEADING EDGES</topic><topic>LEVEL FLIGHT</topic><topic>LOAD DISTRIBUTION</topic><topic>LPN-DA-A-83306B</topic><topic>PBDS(PNEUMATIC BOOT DEICING SYSTEM)</topic><topic>PRESSURE REGULATORS</topic><topic>PROTOTYPES</topic><topic>ROTOR BLADES(ROTARY WINGS)</topic><topic>RUBBER</topic><topic>SPRAYS</topic><topic>STRUCTURAL LOADS</topic><topic>STRUCTURAL PROPERTIES</topic><topic>UH-1H AIRCRAFT</topic><topic>VIBRATION</topic><toplevel>online_resources</toplevel><creatorcontrib>Haworth, Loran A</creatorcontrib><creatorcontrib>Oliver, Randall G</creatorcontrib><creatorcontrib>Woratschek, Ralph</creatorcontrib><creatorcontrib>ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA</creatorcontrib><collection>DTIC Technical Reports</collection><collection>DTIC STINET</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Haworth, Loran A</au><au>Oliver, Randall G</au><au>Woratschek, Ralph</au><aucorp>ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA</aucorp><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>JUH-1H Pneumatic Boot Deicing System Flight Test Evaluation</btitle><date>1983-05</date><risdate>1983</risdate><abstract>The concept of operation of the Pneumatic Boot Deicing System as a deice system is feasible under the conditions tested when installed on the test UH-1H helicopter. A cooperative effort between NASA and the B.F. Goodrich Company led to the development of a prototype pneumatic boot deicing system designed for use on a helicopter main rotor system. Flight tests were conducted to establish an operational envelope and evaluate the feasibility of the pneumatic deicing concept. Phase I consisted of a ground and inflight structural loads survey which established an operational envelope. Phase II was a limited aircraft performance and handling qualities evaluation, and Phase III involved artificial icing tests. Thirteen problem areas were identified with the prototype Pneumatic Boot Deicing System installation, two of which were corrected during the evaluation. Major problem areas included excessive increases in power required for flight and deicer material erosion and breakdown.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AVIATION SAFETY BOOTS DEICING MATERIALS DEICING SYSTEMS EROSION FLIGHT TESTING H-1 AIRCRAFT HANDLING HELICOPTER ROTORS Helicopters HOVERING Hydraulic and Pneumatic Equipment INFLATABLE STRUCTURES LEADING EDGES LEVEL FLIGHT LOAD DISTRIBUTION LPN-DA-A-83306B PBDS(PNEUMATIC BOOT DEICING SYSTEM) PRESSURE REGULATORS PROTOTYPES ROTOR BLADES(ROTARY WINGS) RUBBER SPRAYS STRUCTURAL LOADS STRUCTURAL PROPERTIES UH-1H AIRCRAFT VIBRATION |
| title | JUH-1H Pneumatic Boot Deicing System Flight Test Evaluation |
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