MANEUVER-FORCE GRADIENT SYSTEM

A maneuver force gradient system causes a helicopter, that otherwise tends to pitch up in a banked turn, to pitch nose-down. A command signal (25) is provided as a function of the roll angle to operate the longitudinal trim actuator (27) which automatically moves the cyclic control (50) resiliently...

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Hauptverfasser:	DOUGLAS HAROLD CLELFORD, RICHARD DENNIS MURPHY
Format:	Patent
Sprache:	eng
Schlagworte:	AEROPLANES AIRCRAFT AVIATION CONTROLLING COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS PHYSICS REGULATING SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES TRANSPORTING
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creator	DOUGLAS HAROLD CLELFORD RICHARD DENNIS MURPHY
description	A maneuver force gradient system causes a helicopter, that otherwise tends to pitch up in a banked turn, to pitch nose-down. A command signal (25) is provided as a function of the roll angle to operate the longitudinal trim actuator (27) which automatically moves the cyclic control (50) resiliently (28) forward to push the nose down. The pilot must consequently pull back on the cyclic control (50) to achieve a desired pitch attitude, thereby establishing a longitudinal positive maneuver-force gradient. The system is operable only when the pilot initiates a roll (33, 38, 50, 51) and the roll angle equals or exceeds 30 DEG (30, 33, 36, 37). Both analog (FIG. 1) and digital (FIG. 2) embodiments are disclosed, and the invention may be practiced in association with an AFCS (101) having the longitudinal trim actuator (27) and resilient linkage (28).
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A command signal (25) is provided as a function of the roll angle to operate the longitudinal trim actuator (27) which automatically moves the cyclic control (50) resiliently (28) forward to push the nose down. The pilot must consequently pull back on the cyclic control (50) to achieve a desired pitch attitude, thereby establishing a longitudinal positive maneuver-force gradient. The system is operable only when the pilot initiates a roll (33, 38, 50, 51) and the roll angle equals or exceeds 30 DEG (30, 33, 36, 37). Both analog (FIG. 1) and digital (FIG. 2) embodiments are disclosed, and the invention may be practiced in association with an AFCS (101) having the longitudinal trim actuator (27) and resilient linkage (28).</description><edition>4</edition><language>eng</language><subject>AEROPLANES ; AIRCRAFT ; AVIATION ; CONTROLLING ; COSMONAUTICS ; HELICOPTERS ; PERFORMING OPERATIONS ; PHYSICS ; REGULATING ; SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES ; TRANSPORTING</subject><creationdate>1987</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=19870311&DB=EPODOC&CC=GB&NR=2135479B$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=19870311&DB=EPODOC&CC=GB&NR=2135479B$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>DOUGLAS HAROLD CLELFORD</creatorcontrib><creatorcontrib>RICHARD DENNIS MURPHY</creatorcontrib><title>MANEUVER-FORCE GRADIENT SYSTEM</title><description>A maneuver force gradient system causes a helicopter, that otherwise tends to pitch up in a banked turn, to pitch nose-down. A command signal (25) is provided as a function of the roll angle to operate the longitudinal trim actuator (27) which automatically moves the cyclic control (50) resiliently (28) forward to push the nose down. The pilot must consequently pull back on the cyclic control (50) to achieve a desired pitch attitude, thereby establishing a longitudinal positive maneuver-force gradient. The system is operable only when the pilot initiates a roll (33, 38, 50, 51) and the roll angle equals or exceeds 30 DEG (30, 33, 36, 37). Both analog (FIG. 1) and digital (FIG. 2) embodiments are disclosed, and the invention may be practiced in association with an AFCS (101) having the longitudinal trim actuator (27) and resilient linkage (28).</description><subject>AEROPLANES</subject><subject>AIRCRAFT</subject><subject>AVIATION</subject><subject>CONTROLLING</subject><subject>COSMONAUTICS</subject><subject>HELICOPTERS</subject><subject>PERFORMING OPERATIONS</subject><subject>PHYSICS</subject><subject>REGULATING</subject><subject>SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES</subject><subject>TRANSPORTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>1987</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZJDzdfRzDQ1zDdJ18w9ydlVwD3J08XT1C1EIjgwOcfXlYWBNS8wpTuWF0twM8m6uIc4euqkF-fGpxQWJyal5qSXx7k5GhsamJuaWTsaEVQAAP7cgow</recordid><startdate>19870311</startdate><enddate>19870311</enddate><creator>DOUGLAS HAROLD CLELFORD</creator><creator>RICHARD DENNIS MURPHY</creator><scope>EVB</scope></search><sort><creationdate>19870311</creationdate><title>MANEUVER-FORCE GRADIENT SYSTEM</title><author>DOUGLAS HAROLD CLELFORD ; RICHARD DENNIS MURPHY</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_GB2135479B3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>1987</creationdate><topic>AEROPLANES</topic><topic>AIRCRAFT</topic><topic>AVIATION</topic><topic>CONTROLLING</topic><topic>COSMONAUTICS</topic><topic>HELICOPTERS</topic><topic>PERFORMING OPERATIONS</topic><topic>PHYSICS</topic><topic>REGULATING</topic><topic>SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES</topic><topic>TRANSPORTING</topic><toplevel>online_resources</toplevel><creatorcontrib>DOUGLAS HAROLD CLELFORD</creatorcontrib><creatorcontrib>RICHARD DENNIS MURPHY</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>DOUGLAS HAROLD CLELFORD</au><au>RICHARD DENNIS MURPHY</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>MANEUVER-FORCE GRADIENT SYSTEM</title><date>1987-03-11</date><risdate>1987</risdate><abstract>A maneuver force gradient system causes a helicopter, that otherwise tends to pitch up in a banked turn, to pitch nose-down. A command signal (25) is provided as a function of the roll angle to operate the longitudinal trim actuator (27) which automatically moves the cyclic control (50) resiliently (28) forward to push the nose down. The pilot must consequently pull back on the cyclic control (50) to achieve a desired pitch attitude, thereby establishing a longitudinal positive maneuver-force gradient. The system is operable only when the pilot initiates a roll (33, 38, 50, 51) and the roll angle equals or exceeds 30 DEG (30, 33, 36, 37). Both analog (FIG. 1) and digital (FIG. 2) embodiments are disclosed, and the invention may be practiced in association with an AFCS (101) having the longitudinal trim actuator (27) and resilient linkage (28).</abstract><edition>4</edition><oa>free_for_read</oa></addata></record>
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subjects	AEROPLANES AIRCRAFT AVIATION CONTROLLING COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS PHYSICS REGULATING SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES TRANSPORTING
title	MANEUVER-FORCE GRADIENT SYSTEM
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