Stability augmentation system for a forward swept wing aircraft

A stability augmentation system for a forward swept wing aircraft is disclosed that corrects a dynamic instability phenomenon which occurs when the whole vehicle (rigid body) motion couples with the wing structural motion. The sensors are positioned and their output signals combined such that wing s...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	MILLER, GERALD D, WYKES, JOHN H
Format:	Patent
Sprache:	eng
Schlagworte:	AEROPLANES AIRCRAFT AVIATION CONTROLLING COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS PHYSICS REGULATING SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES TRANSPORTING
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

container_end_page
container_issue
container_start_page
container_title
container_volume
creator	MILLER GERALD D WYKES JOHN H
description	A stability augmentation system for a forward swept wing aircraft is disclosed that corrects a dynamic instability phenomenon which occurs when the whole vehicle (rigid body) motion couples with the wing structural motion. The sensors are positioned and their output signals combined such that wing structural motion is isolated. Specifically positioned wing control surfaces are operated to suppress such motion with minimal resulting rigid body pitch motion inducing inputs.
format	Patent
fullrecord	<record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US4562546A</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US4562546A</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US4562546A3</originalsourceid><addsrcrecordid>eNrjZLAPLklMyszJLKlUSCxNz03NK0ksyczPUyiuLC5JzVVIyy9SSASR5YlFKQrF5akFJQrlmXnpComZRclFiWklPAysaYk5xam8UJqbQd7NNcTZQze1ID8-tbggMTk1L7UkPjTYxNTMyNTEzNGYsAoAFfowxw</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>Stability augmentation system for a forward swept wing aircraft</title><source>esp@cenet</source><creator>MILLER; GERALD D ; WYKES; JOHN H</creator><creatorcontrib>MILLER; GERALD D ; WYKES; JOHN H</creatorcontrib><description>A stability augmentation system for a forward swept wing aircraft is disclosed that corrects a dynamic instability phenomenon which occurs when the whole vehicle (rigid body) motion couples with the wing structural motion. The sensors are positioned and their output signals combined such that wing structural motion is isolated. Specifically positioned wing control surfaces are operated to suppress such motion with minimal resulting rigid body pitch motion inducing inputs.</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>1985</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=19851231&DB=EPODOC&CC=US&NR=4562546A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76290</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=19851231&DB=EPODOC&CC=US&NR=4562546A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MILLER; GERALD D</creatorcontrib><creatorcontrib>WYKES; JOHN H</creatorcontrib><title>Stability augmentation system for a forward swept wing aircraft</title><description>A stability augmentation system for a forward swept wing aircraft is disclosed that corrects a dynamic instability phenomenon which occurs when the whole vehicle (rigid body) motion couples with the wing structural motion. The sensors are positioned and their output signals combined such that wing structural motion is isolated. Specifically positioned wing control surfaces are operated to suppress such motion with minimal resulting rigid body pitch motion inducing inputs.</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>1985</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZLAPLklMyszJLKlUSCxNz03NK0ksyczPUyiuLC5JzVVIyy9SSASR5YlFKQrF5akFJQrlmXnpComZRclFiWklPAysaYk5xam8UJqbQd7NNcTZQze1ID8-tbggMTk1L7UkPjTYxNTMyNTEzNGYsAoAFfowxw</recordid><startdate>19851231</startdate><enddate>19851231</enddate><creator>MILLER; GERALD D</creator><creator>WYKES; JOHN H</creator><scope>EVB</scope></search><sort><creationdate>19851231</creationdate><title>Stability augmentation system for a forward swept wing aircraft</title><author>MILLER; GERALD D ; WYKES; JOHN H</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US4562546A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>1985</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>MILLER; GERALD D</creatorcontrib><creatorcontrib>WYKES; JOHN H</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>MILLER; GERALD D</au><au>WYKES; JOHN H</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Stability augmentation system for a forward swept wing aircraft</title><date>1985-12-31</date><risdate>1985</risdate><abstract>A stability augmentation system for a forward swept wing aircraft is disclosed that corrects a dynamic instability phenomenon which occurs when the whole vehicle (rigid body) motion couples with the wing structural motion. The sensors are positioned and their output signals combined such that wing structural motion is isolated. Specifically positioned wing control surfaces are operated to suppress such motion with minimal resulting rigid body pitch motion inducing inputs.</abstract><edition>4</edition><oa>free_for_read</oa></addata></record>
fulltext	fulltext_linktorsrc
identifier
ispartof
issn
language	eng
recordid	cdi_epo_espacenet_US4562546A
source	esp@cenet
subjects	AEROPLANES AIRCRAFT AVIATION CONTROLLING COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS PHYSICS REGULATING SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES TRANSPORTING
title	Stability augmentation system for a forward swept wing aircraft
url	https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-02-02T05%3A36%3A48IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=MILLER;%20GERALD%20D&rft.date=1985-12-31&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EUS4562546A%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true