AEROMETRIC METHOD AND DEVICE (SYSTEM) FOR MEASURING AIRCRAFT SPATIAL POSITION, YAW AND LATERAL VELOCITY
The proposed invention (method and device) is related to the measurement technology and is intended for measuring spatial position (roll and pitch), yawing and lateral speed of the aircraft. The objective of the invention is to expand the functionality and technical capabilities of aerometric method...
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| creator | PASHAYEV, Arif MirJalal KARIMLI, Vasif Isa HAZARKHANOV, Anvar Tapdig KARIMLI, Toghrul Isa NEYMATOV, Vasif Aydin |
| description | The proposed invention (method and device) is related to the measurement technology and is intended for measuring spatial position (roll and pitch), yawing and lateral speed of the aircraft. The objective of the invention is to expand the functionality and technical capabilities of aerometric method and device. For this purpose, in order to measure the additionally specified parameters by the air pressure probes installed in the left and right nose sections of the fuselage and additional air pressure probes installed in the left and right tail sections of the fuselage, as well as at both wingtips of the aircraft, useful data are generated as a result of the following: variation in aircraft roll angle, based on the difference in static air pressure values between left and right static air pressure probes additionally located at the wingtips of the aircraft; variation in aircraft pitch angle, based on the difference in static air pressure values between the air pressure probes located in the nose section and additional air pressure probes located in the tail section of the aircraft; during yawing and in the presence of the lateral speed of the aircraft, based on the difference in lateral static air pressure values between the additionally installed air pressure probes located in the nose and tail sections of the fuselage. This is achieved by the fact that the left-sided air pressure probes located in the front section of the fuselage, and those additionally installed in the tail section of the fuselage and at the left wingtip, are additionally provided with the horizontally located lateral openings for sensing left-sided lateral static air pressure; the right-sided air pressure probes located in the front section of the fuselage, and those additionally installed in the tail section of the fuselage and at the right wingtip, are additionally provided with the horizontally located lateral openings for sensing right-sided lateral static air pressure; and the air pressure probes additionally installed at the wingtips and in the tail section of the fuselage are provided by the vertically located openings for sensing static air pressure. When the roll angle of the aircraft changes, the vertical spatial movement of the static air pressure probes additionally installed at the wingtips causes the appearance of a difference in static pressure between such probes due to the difference in altitude of their relative positions. When the pitch angle of the aircraft changes, |
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| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_EP3450989A2</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>EP3450989A2</sourcerecordid><originalsourceid>FETCH-epo_espacenet_EP3450989A23</originalsourceid><addsrcrecordid>eNqNjMEKgkAQQL10iOof5lhQEFmQx2Edc0BdmZ0MTyKxdYkS7P9piT6g0zu8x5tGdySxJamwgYDcpoBVCik1bAiWrnVK5QoyK0GjOwtXJ0AWI5gpuBqVsYDaOla21RpavHwHBSpJMA0V1rC282hy6x-jX_w4iyAjNfnGD6_Oj0N_9U__7qiO94dtckxwF_-RfABgUjTO</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>AEROMETRIC METHOD AND DEVICE (SYSTEM) FOR MEASURING AIRCRAFT SPATIAL POSITION, YAW AND LATERAL VELOCITY</title><source>esp@cenet</source><creator>PASHAYEV, Arif MirJalal ; KARIMLI, Vasif Isa ; HAZARKHANOV, Anvar Tapdig ; KARIMLI, Toghrul Isa ; NEYMATOV, Vasif Aydin</creator><creatorcontrib>PASHAYEV, Arif MirJalal ; KARIMLI, Vasif Isa ; HAZARKHANOV, Anvar Tapdig ; KARIMLI, Toghrul Isa ; NEYMATOV, Vasif Aydin</creatorcontrib><description>The proposed invention (method and device) is related to the measurement technology and is intended for measuring spatial position (roll and pitch), yawing and lateral speed of the aircraft. The objective of the invention is to expand the functionality and technical capabilities of aerometric method and device. For this purpose, in order to measure the additionally specified parameters by the air pressure probes installed in the left and right nose sections of the fuselage and additional air pressure probes installed in the left and right tail sections of the fuselage, as well as at both wingtips of the aircraft, useful data are generated as a result of the following: variation in aircraft roll angle, based on the difference in static air pressure values between left and right static air pressure probes additionally located at the wingtips of the aircraft; variation in aircraft pitch angle, based on the difference in static air pressure values between the air pressure probes located in the nose section and additional air pressure probes located in the tail section of the aircraft; during yawing and in the presence of the lateral speed of the aircraft, based on the difference in lateral static air pressure values between the additionally installed air pressure probes located in the nose and tail sections of the fuselage. This is achieved by the fact that the left-sided air pressure probes located in the front section of the fuselage, and those additionally installed in the tail section of the fuselage and at the left wingtip, are additionally provided with the horizontally located lateral openings for sensing left-sided lateral static air pressure; the right-sided air pressure probes located in the front section of the fuselage, and those additionally installed in the tail section of the fuselage and at the right wingtip, are additionally provided with the horizontally located lateral openings for sensing right-sided lateral static air pressure; and the air pressure probes additionally installed at the wingtips and in the tail section of the fuselage are provided by the vertically located openings for sensing static air pressure. When the roll angle of the aircraft changes, the vertical spatial movement of the static air pressure probes additionally installed at the wingtips causes the appearance of a difference in static pressure between such probes due to the difference in altitude of their relative positions. When the pitch angle of the aircraft changes, the vertical movement of the static air pressure probes additionally installed on the opposite sides of the fuselage causes the appearance of a difference of static air pressure between such probes due to the difference in altitude of their relative positions. In the process of yawing of the aircraft, the lateral static air pressure increases at the additionally installed lateral static air pressure probes located on the opposite sides of the fuselage in the direction of the yaw turn, and decreases at the probes located against the direction of the yaw turn. Under the wind effect, if the aircraft experiences a leftward or rightward lateral speed (in the absence of yawing), the lateral static air pressure increases at the additionally installed lateral static air pressure probes located in the wind plane, and decreases on the opposite sides.</description><language>eng ; fre ; ger</language><subject>AIRCRAFT ; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT ; AVIATION ; CONTROLLING ; COSMONAUTICS ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FLYING SUITS ; GYROSCOPIC INSTRUMENTS ; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT ; MEASURING ; MEASURING DISTANCES, LEVELS OR BEARINGS ; MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION,OR SHOCK ; NAVIGATION ; PARACHUTES ; PERFORMING OPERATIONS ; PHOTOGRAMMETRY OR VIDEOGRAMMETRY ; PHYSICS ; REGULATING ; SURVEYING ; SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES ; TESTING ; TRANSPORTING</subject><creationdate>2019</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=20190306&DB=EPODOC&CC=EP&NR=3450989A2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76516</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20190306&DB=EPODOC&CC=EP&NR=3450989A2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>PASHAYEV, Arif MirJalal</creatorcontrib><creatorcontrib>KARIMLI, Vasif Isa</creatorcontrib><creatorcontrib>HAZARKHANOV, Anvar Tapdig</creatorcontrib><creatorcontrib>KARIMLI, Toghrul Isa</creatorcontrib><creatorcontrib>NEYMATOV, Vasif Aydin</creatorcontrib><title>AEROMETRIC METHOD AND DEVICE (SYSTEM) FOR MEASURING AIRCRAFT SPATIAL POSITION, YAW AND LATERAL VELOCITY</title><description>The proposed invention (method and device) is related to the measurement technology and is intended for measuring spatial position (roll and pitch), yawing and lateral speed of the aircraft. The objective of the invention is to expand the functionality and technical capabilities of aerometric method and device. For this purpose, in order to measure the additionally specified parameters by the air pressure probes installed in the left and right nose sections of the fuselage and additional air pressure probes installed in the left and right tail sections of the fuselage, as well as at both wingtips of the aircraft, useful data are generated as a result of the following: variation in aircraft roll angle, based on the difference in static air pressure values between left and right static air pressure probes additionally located at the wingtips of the aircraft; variation in aircraft pitch angle, based on the difference in static air pressure values between the air pressure probes located in the nose section and additional air pressure probes located in the tail section of the aircraft; during yawing and in the presence of the lateral speed of the aircraft, based on the difference in lateral static air pressure values between the additionally installed air pressure probes located in the nose and tail sections of the fuselage. This is achieved by the fact that the left-sided air pressure probes located in the front section of the fuselage, and those additionally installed in the tail section of the fuselage and at the left wingtip, are additionally provided with the horizontally located lateral openings for sensing left-sided lateral static air pressure; the right-sided air pressure probes located in the front section of the fuselage, and those additionally installed in the tail section of the fuselage and at the right wingtip, are additionally provided with the horizontally located lateral openings for sensing right-sided lateral static air pressure; and the air pressure probes additionally installed at the wingtips and in the tail section of the fuselage are provided by the vertically located openings for sensing static air pressure. When the roll angle of the aircraft changes, the vertical spatial movement of the static air pressure probes additionally installed at the wingtips causes the appearance of a difference in static pressure between such probes due to the difference in altitude of their relative positions. When the pitch angle of the aircraft changes, the vertical movement of the static air pressure probes additionally installed on the opposite sides of the fuselage causes the appearance of a difference of static air pressure between such probes due to the difference in altitude of their relative positions. In the process of yawing of the aircraft, the lateral static air pressure increases at the additionally installed lateral static air pressure probes located on the opposite sides of the fuselage in the direction of the yaw turn, and decreases at the probes located against the direction of the yaw turn. Under the wind effect, if the aircraft experiences a leftward or rightward lateral speed (in the absence of yawing), the lateral static air pressure increases at the additionally installed lateral static air pressure probes located in the wind plane, and decreases on the opposite sides.</description><subject>AIRCRAFT</subject><subject>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</subject><subject>AVIATION</subject><subject>CONTROLLING</subject><subject>COSMONAUTICS</subject><subject>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</subject><subject>FLYING SUITS</subject><subject>GYROSCOPIC INSTRUMENTS</subject><subject>INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT</subject><subject>MEASURING</subject><subject>MEASURING DISTANCES, LEVELS OR BEARINGS</subject><subject>MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION,OR SHOCK</subject><subject>NAVIGATION</subject><subject>PARACHUTES</subject><subject>PERFORMING OPERATIONS</subject><subject>PHOTOGRAMMETRY OR VIDEOGRAMMETRY</subject><subject>PHYSICS</subject><subject>REGULATING</subject><subject>SURVEYING</subject><subject>SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES</subject><subject>TESTING</subject><subject>TRANSPORTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2019</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNjMEKgkAQQL10iOof5lhQEFmQx2Edc0BdmZ0MTyKxdYkS7P9piT6g0zu8x5tGdySxJamwgYDcpoBVCik1bAiWrnVK5QoyK0GjOwtXJ0AWI5gpuBqVsYDaOla21RpavHwHBSpJMA0V1rC282hy6x-jX_w4iyAjNfnGD6_Oj0N_9U__7qiO94dtckxwF_-RfABgUjTO</recordid><startdate>20190306</startdate><enddate>20190306</enddate><creator>PASHAYEV, Arif MirJalal</creator><creator>KARIMLI, Vasif Isa</creator><creator>HAZARKHANOV, Anvar Tapdig</creator><creator>KARIMLI, Toghrul Isa</creator><creator>NEYMATOV, Vasif Aydin</creator><scope>EVB</scope></search><sort><creationdate>20190306</creationdate><title>AEROMETRIC METHOD AND DEVICE (SYSTEM) FOR MEASURING AIRCRAFT SPATIAL POSITION, YAW AND LATERAL VELOCITY</title><author>PASHAYEV, Arif MirJalal ; KARIMLI, Vasif Isa ; HAZARKHANOV, Anvar Tapdig ; KARIMLI, Toghrul Isa ; NEYMATOV, Vasif Aydin</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP3450989A23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2019</creationdate><topic>AIRCRAFT</topic><topic>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</topic><topic>AVIATION</topic><topic>CONTROLLING</topic><topic>COSMONAUTICS</topic><topic>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</topic><topic>FLYING SUITS</topic><topic>GYROSCOPIC INSTRUMENTS</topic><topic>INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT</topic><topic>MEASURING</topic><topic>MEASURING DISTANCES, LEVELS OR BEARINGS</topic><topic>MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION,OR SHOCK</topic><topic>NAVIGATION</topic><topic>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>PHOTOGRAMMETRY OR VIDEOGRAMMETRY</topic><topic>PHYSICS</topic><topic>REGULATING</topic><topic>SURVEYING</topic><topic>SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES</topic><topic>TESTING</topic><topic>TRANSPORTING</topic><toplevel>online_resources</toplevel><creatorcontrib>PASHAYEV, Arif MirJalal</creatorcontrib><creatorcontrib>KARIMLI, Vasif Isa</creatorcontrib><creatorcontrib>HAZARKHANOV, Anvar Tapdig</creatorcontrib><creatorcontrib>KARIMLI, Toghrul Isa</creatorcontrib><creatorcontrib>NEYMATOV, Vasif Aydin</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>PASHAYEV, Arif MirJalal</au><au>KARIMLI, Vasif Isa</au><au>HAZARKHANOV, Anvar Tapdig</au><au>KARIMLI, Toghrul Isa</au><au>NEYMATOV, Vasif Aydin</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>AEROMETRIC METHOD AND DEVICE (SYSTEM) FOR MEASURING AIRCRAFT SPATIAL POSITION, YAW AND LATERAL VELOCITY</title><date>2019-03-06</date><risdate>2019</risdate><abstract>The proposed invention (method and device) is related to the measurement technology and is intended for measuring spatial position (roll and pitch), yawing and lateral speed of the aircraft. The objective of the invention is to expand the functionality and technical capabilities of aerometric method and device. For this purpose, in order to measure the additionally specified parameters by the air pressure probes installed in the left and right nose sections of the fuselage and additional air pressure probes installed in the left and right tail sections of the fuselage, as well as at both wingtips of the aircraft, useful data are generated as a result of the following: variation in aircraft roll angle, based on the difference in static air pressure values between left and right static air pressure probes additionally located at the wingtips of the aircraft; variation in aircraft pitch angle, based on the difference in static air pressure values between the air pressure probes located in the nose section and additional air pressure probes located in the tail section of the aircraft; during yawing and in the presence of the lateral speed of the aircraft, based on the difference in lateral static air pressure values between the additionally installed air pressure probes located in the nose and tail sections of the fuselage. This is achieved by the fact that the left-sided air pressure probes located in the front section of the fuselage, and those additionally installed in the tail section of the fuselage and at the left wingtip, are additionally provided with the horizontally located lateral openings for sensing left-sided lateral static air pressure; the right-sided air pressure probes located in the front section of the fuselage, and those additionally installed in the tail section of the fuselage and at the right wingtip, are additionally provided with the horizontally located lateral openings for sensing right-sided lateral static air pressure; and the air pressure probes additionally installed at the wingtips and in the tail section of the fuselage are provided by the vertically located openings for sensing static air pressure. When the roll angle of the aircraft changes, the vertical spatial movement of the static air pressure probes additionally installed at the wingtips causes the appearance of a difference in static pressure between such probes due to the difference in altitude of their relative positions. When the pitch angle of the aircraft changes, the vertical movement of the static air pressure probes additionally installed on the opposite sides of the fuselage causes the appearance of a difference of static air pressure between such probes due to the difference in altitude of their relative positions. In the process of yawing of the aircraft, the lateral static air pressure increases at the additionally installed lateral static air pressure probes located on the opposite sides of the fuselage in the direction of the yaw turn, and decreases at the probes located against the direction of the yaw turn. Under the wind effect, if the aircraft experiences a leftward or rightward lateral speed (in the absence of yawing), the lateral static air pressure increases at the additionally installed lateral static air pressure probes located in the wind plane, and decreases on the opposite sides.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION CONTROLLING COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GYROSCOPIC INSTRUMENTS INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT MEASURING MEASURING DISTANCES, LEVELS OR BEARINGS MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION,OR SHOCK NAVIGATION PARACHUTES PERFORMING OPERATIONS PHOTOGRAMMETRY OR VIDEOGRAMMETRY PHYSICS REGULATING SURVEYING SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES TESTING TRANSPORTING |
| title | AEROMETRIC METHOD AND DEVICE (SYSTEM) FOR MEASURING AIRCRAFT SPATIAL POSITION, YAW AND LATERAL VELOCITY |
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