101. FLIGHT CONTROL LAWS FOR FULL ENVELOPE BANKED TURNS

申请号: EP11862586.2

申请日: 2011-03-29

公开（公告）号: EP2673720B1

公开（公告）日: 2016-05-11

发明人: CHRISTENSEN, Kevin, Thomas; SHUE, Shyhpyng, Jack; CAUDILL, Troy, Sheldon; LAPPOS, Nicholas, Dean

102. FLIGHT CONTROL LAWS FOR FULL ENVELOPE BANKED TURNS

申请号: EP11862586

申请日: 2011-03-29

公开（公告）号: EP2673720A4

公开（公告）日: 2014-05-21

发明人: CHRISTENSEN KEVIN THOMAS; SHUE SHYHPYNG JACK; CAUDILL TROY SHELDON; LAPPOS NICHOLAS DEAN

103. FLIGHT CONTROL LAWS FOR FULL ENVELOPE BANKED TURNS

申请号: EP11862586.2

申请日: 2011-03-29

公开（公告）号: EP2673720A2

公开（公告）日: 2013-12-18

发明人: CHRISTENSEN, Kevin, Thomas; SHUE, Shyhpyng, Jack; CAUDILL, Troy, Sheldon; LAPPOS, Nicholas, Dean

A flight control system and method for controlling full envelope banked turns of an aircraft, the flight control system including one or more of a control law architectures having one or more control laws adapted for controlling the flight of an aircraft for full envelope banked turns.

104. 비행체의 기동에 대응하는 회전 안테나 및 이를 구비하는 비행체

申请号: KR1020120136956

申请日: 2012-11-29

公开（公告）号: KR101318880B1

公开（公告）日: 2013-10-16

发明人: 박상혁

PURPOSE: A rotary antenna corresponding to the movement of a flying object and the flying object including the same are provided to improve signal reception performance by vertically maintaining the antenna even through the flying object suddenly moves in a roll direction. CONSTITUTION: An antenna (100) transmits or receives a signal for controlling a flying object and is attached to a rotator (200). The rotator rotates the antenna. A slip ring (300) is located on at least one area of the rotator. The slip ring transmits or receives the signal which is transmitted to or received from the antenna to or from the flying object.

105. 농업용 발사 기구를 포함하는 무인 비행 장치

申请号: KR1020150134978

申请日: 2015-09-23

公开（公告）号: KR101694636B1

公开（公告）日: 2017-01-23

发明人: 임완수; 스테판라이언앙산토; 양연모

본발명의다양한실시예는농업용발사기구를포함하는무인비행장치에관한것이다. 본발명의일 실시예에따르면, 농업용발사기구를포함하는무인비행장치에있어서, 농업용발사기구를포함하는무인비행장치의몸체일부에적어도둘 이상의회전익을포함하는비행인터페이스; 적어도하나의외부제어장치와통신하는통신인터페이스; 종자를포함하는종자보관함, 관으로형성되며, 상기관의일단에패킹이부착되고, 상기패킹으로부터지정된거리에서상기관의외주면으로적어도하나의제1 홀이형성되고, 상기관의측면에상기종자보관함과연결되는제2 홀이형성된발사관, 상기관의상기패킹이부착된일단이하부를관통하고, 상기패킹으로밀폐되는공기탱크, 상기발사관하부를감싸는플런저장치, 상기발사관과상기플런저장치를내부에포함하며, 상기플런저장치가고정되고, 상기공기탱크에연결되는발사부몸체, 및상기공기탱크에공기를압축하는압축기를포함하고상기농업용발사기구를포함하는무인비행장치의몸체하부에부착되는발사인터페이스; 및상기적어도하나의외부제어장치로부터수신하는제어신호에기반하여, 상기종자보관함으로부터지정된양의종자를상기제2 홀을통해서상기발사관내부의지정된위치로방출하고, 상기압축기를동작하여상기공기탱크에지정된수치의압력으로공기를압축하고, 상기플런저장치를동작하여상기발사관을상기공기탱크내부로밀어넣고, 상기제1 홀을통해서상기공기탱크로부터상기발사관으로유입되는압축된공기에기반하여상기발사관내부에위치한상기종자를상기발사관외부로발사하도록제어하는프로세서;를포함할수 있다.

106. Aircraft display management system for flight envelope protection

申请号: US14819956

申请日: 2015-08-06

公开（公告）号: US09587961B2

公开（公告）日: 2017-03-07

发明人: Jean-Jacques Toumazet; Mélanie Vadillo

A display management system is provided for displaying a graphical representation of flight envelope information of an aircraft. Included in the display management system is a control module being coupled to the display management system and programmed to control the graphical representation including at least one flight envelope protection attribute. A signal detection module receives signals from a plurality of sensors of the aircraft, and the received signals include associated parameter values for the at least one flight envelope protection attribute. A protection selection module selects the at least one flight envelope protection attribute based on the received signals and parameter values. A display module displays the at least one flight envelope protection attribute on a display screen in relation to a flight control law state stored in a database using a display model of the aircraft from an elevational view based on the received signals and parameter values.

107. Automatic flight envelope protection for uninhabited air vehicles

申请号: US09844863

申请日: 2001-04-27

公开（公告）号: US06493609B2

公开（公告）日: 2002-12-10

发明人: Timothy L. Johnson

A method and system for automatic flight envelope protection to reduce damage and mishap rates of vehicles. The method and system generally include receiving a mission command from a mission management system that contains a predetermined flight mission; evaluating whether executing the command will maintain the vehicle within a flight envelope; modifying the command to one when executed will maintain the vehicle within the flight envelope, if otherwise; replanning and updating the mission pursuant to the command; sending the command to a flight control center; measuring the vehicle's state to determine if the command was executed as planned, and finally obtaining a next mission command.

108. Method for manufacturing multi-layer printed wiring board including flying tail

申请号: JP2006036812

申请日: 2006-02-14

公开（公告）号: JP2007220735A

公开（公告）日: 2007-08-30

发明人: MURAKAWA AKIRA; TSURUSAKI KOJI; NAKAO SATORU

PROBLEM TO BE SOLVED: To provide a method for manufacturing a multilayer printed wiring board for acquiring flexibility of a flying tail, by protecting the flying tail from a solution used in the intermediate steps such as plating step and etching step, etc. in the slit processing method. SOLUTION: The method comprises a step of adhering a bonding material 40 having an aperture 41 and an external layer substrate 30 including a slit 33, so that the slit 33 of the external layer substrate 30 is located at the external side of the aperture 41 of the bonding material 40 provided between both substrates 10, 30 in the substrate laminating step of the internal layer substrate 10 and the external layer substrate 30, and a distance (d) between a side surface 33a as an edge 34a of a part 34 to be removed on the flying tail 2 among both side surfaces 33a, 33b of the slit 33 and the edge 41a of the aperture 41 of the bonding agent becomes 0 mm or more and 0.2 mm or less. An etching resist 20 having resistivity to copper plating solution is formed to a part 14 corresponding to the flying tail 2 of the internal layer substrate 10 before the laminating step, and the etching resist 20 is peeled after the step of exposing the flying tail 2. COPYRIGHT: (C)2007,JPO&INPIT

109. On-line &mgr; method for robust flutter prediction in expanding a safe flight envelope for an aircraft model under flight test

申请号: US09074024

申请日: 1998-05-06

公开（公告）号: US06216063B1

公开（公告）日: 2001-04-10

发明人: Richard C. Lind; Martin J. Brenner

A structured singular value (&mgr;) analysis method of computing flutter margins has robust stability of a linear aeroelastic model with uncertainty operators (&Dgr;). Flight data is used to update the uncertainty operators to accurately account for errors in the computed model and the observed range of aircraft dynamics of the aircraft under test caused by time-varying aircraft parameters, nonlinearities, and flight anomalies, such as test nonrepeatability. This &mgr;-based approach computes predict flutter margins that are worst-case with respect to the modeling uncertainty for use in determining when the aircraft is approaching a flutter condition and defining an expanded safe flight envelope for the aircraft that is accepted with more confidence than traditional methods that do not update the analysis algorithm with flight data by introducing &mgr; as a flutter margin parameter that presents several advantages over tracking damping trends as a measure of a tendency to instability from available flight data.

110. Method for the protection of aircrafts against flying objects comprising UV-homing heads

申请号: US841725

申请日: 1992-02-26

公开（公告）号: US5158351A

公开（公告）日: 1992-10-27

发明人: Johannes Grundler

The present application describes a method for the protection of aircrafts against flying objects comprising UV-homing heads, this method being characterized in that the aircrafts are, at least temporarily, provided with an UV-emitting radiation source.

111. AILE D'AERONEF COMPRENANT UN VOLET MOBILE DE BORD DE FUITE ENTRAINE PAR UN MOTEUR ELECTRIQUE LINEAIRE

申请号: PCT/EP2017/078003

申请日: 2017-11-02

公开（公告）号: WO2018083145A1

公开（公告）日: 2018-05-11

发明人: LANGER, Hugues; SCIARRABONE, Steve; DEBAISIEUX, Stéphane

L'invention concerne une aile d'aéronef comprenant un volet mobile de bord de fuite (16), l'aile comprenant un dispositif (50) de mise en mouvement de ce volet, le dispositif étant équipé : - d'une poutre (51) portant un rail de guidage; - d'un chariot (52a) monté mobile sur le rail (20); - d'une liaison articulée (40a) entre le chariot (52a) et une ferrure (30) solidaire du volet; - d'un organe de basculement (29) du volet mobile; - d'une liaison articulée (40b) entre la ferrure (30) et l'organe de basculement (29); et - d'une liaison articulée (40c) entre l'organe de basculement (29) et la poutre (51). Selon l'invention, le dispositif (50) comprend un moteur électrique linéaire (22) comportant un ensemble primaire (52) équipé du chariot (52a) qui intègre des bobines (55), et un ensemble secondaire (54) comportant une voie magnétique agencée sur le rail (20).

112. Supply system for an aircraft, use of a shielded supply line in an aircraft and an aircraft with a supply system

申请号: EP12188172.6

申请日: 2012-10-11

公开（公告）号: EP2720334A1

公开（公告）日: 2014-04-16

发明人: Schult, Jens; Stengel, Torsten; Fouquet, Nicolas

A supply system (2) for supplying energy in an aircraft comprises at least one electrical line (8) connectable to a current source (4), an electrically conductive shield (18), and a detection unit (20) having at least two electrical inputs. The at least one electrical line (8) comprises at least one core (6) connectable to a pole (14, 16) of the current source (4), wherein the shield (18) surrounds the at least one core (6) under a distance and creates an intermediate space between the at least one core (6) and the shield (18). At least one port of the detection unit (20) is connected to the at least one core (6) and wherein at least another port of the detection unit (20) is connected to at least one of the shield (18) and the at least one first core (6). The detection unit (20) is adapted for detecting a differential current over the at least one core (6) or an absolute current between the shield (18) and a ground potential. The detection unit (20) is further adapted for generating a warning signal if a predetermined threshold value for the detected current value is exceeded. Thereby an improved level of safety is reached in the electrical supply of an aircraft, especially in the vicinity of fluid lines transferring flammable or oxidizing fluids.

113. METHOD OF ANALYZING IONS IN AN APPARATUS INCLUDING A TIME OF FLIGHT MASS SPECTROMETER AND A LINEAR ION TRAP

申请号: PCT/CA1998/001106

申请日: 1998-12-03

公开（公告）号: WO99030350A1

公开（公告）日: 1999-06-17

发明人:

A method of analyzing ions is carried out in a mass spectrometer apparatus comprising an ion source, a linear RF quadrupole and a time of flight mass spectrometer. Ions are generated from the ion source and passed into the linear RF quadrupole. To retain ions within the linear RF quadrupole, potentials are applied to either end of it and it is then operated as an ion trap. Ions of interest are selected in the linear RF quadrupole and unwanted ions are caused to be ejected. Selected ions are then excited and caused to collide with a neutral gas, to cause collision induced dissociation thereof, thereby forming fragment ions for analysis in the time of flight mass spectrometer. The potential of one end of the linear RF quadrupole is then adjusted to pass selected and fragment ions through to the time of flight mass spectrometer. This enables a spectrum of the selected and the fragment ions to be obtained from the time of flight mass spectrometer.

114. AUTOMATED DISTRIBUTION OF LOGON CREDENTIALS FOR ESTABLISHING WIRELESS CONNECTIVITY OF ELECTRONIC FLIGHT BAG(EFB)

申请号: EP16150505

申请日: 2016-01-07

公开（公告）号: EP3046305B1

公开（公告）日: 2017-06-07

发明人: HENZL MARTIN; GOTTHARD PETR

Automated distribution of wireless logon credentials for an electronic flight bag (EFB) is provided. In one embodiment, a method for secured aircraft wireless network access comprises: establishing a NFC link between an EFB and an NFC node, wherein the node is hardwired to a wireless access point coupled to EFB service applications via an aircraft network. The access point provides a plurality of wireless channels for accessing the network, each are single user wireless channels. In response to a request from the EFB, determining whether a first wireless channel is available; if the first wireless channel is available, generating a logon credential associated with the first wireless channel and transmitting the credential to the EFB with the NFC node; establishing a second link between the EFB and the wireless access point using the credential; and transferring data between the EFB and EFB server applications over the second link.

115. AUTOMATED DISTRIBUTION OF LOGON CREDENTIALS FOR ESTABLISHING WIRELESS CONNECTIVITY OF ELECTRONIC FLIGHT BAG(EFB)

申请号: EP16150505.2

申请日: 2016-01-07

公开（公告）号: EP3046305A1

公开（公告）日: 2016-07-20

发明人: HENZL, Martin; GOTTHARD, Petr

Automated distribution of wireless logon credentials for an electronic flight bag (EFB) is provided. In one embodiment, a method for secured aircraft wireless network access comprises: establishing a NFC link between an EFB and an NFC node, wherein the node is hardwired to a wireless access point coupled to EFB service applications via an aircraft network. The access point provides a plurality of wireless channels for accessing the network, each are single user wireless channels. In response to a request from the EFB, determining whether a first wireless channel is available; if the first wireless channel is available, generating a logon credential associated with the first wireless channel and transmitting the credential to the EFB with the NFC node; establishing a second link between the EFB and the wireless access point using the credential; and transferring data between the EFB and EFB server applications over the second link.

116. Aircraft in-flight entertainment system including a distributed digital radio service and associated methods

申请号: US11023728

申请日: 2004-12-28

公开（公告）号: US08776146B2

公开（公告）日: 2014-07-08

发明人: Jason Funderburk; Scott D. Easterling; Robert M. Keen

An aircraft in-flight entertainment (IFE) system includes an antenna for receiving digital satellite radio signals, and an intermediate frequency (IF) down converter is connected to the antenna for down converting the digital satellite radio signals. A plurality of seat electronic boxes (SEBs) are spaced throughout the aircraft. Each SEB includes at least one IF tuner in communications with the IF down converter.

117. Disc drive actuator incorporating injection molding, flying leads, and locking flanges

申请号: US622616

申请日: 1996-03-26

公开（公告）号: US5734528A

公开（公告）日: 1998-03-31

发明人: Iraj Jabbari; Brian L. Phillips; Brian T. Bonn; Chul Soo Kim; Michael A. Maiers; Mark E. Gauger

The present invention provides an improved actuator arm assembly including scalloped locking flanges with indentations for longitudinal, perpendicular, and torsional support, an injection molding for precisely locating and fixing a motor coil bobbin, motor coil wires, magnetic latch striker plate, and a crash stop to an actuator arm. Apertures on the actuator arm allow the plastic molding to pass through and lock the actuator arm to the motor coil bobbin together. The magnetic latch striker plate fixably parks the actuator arm in the disc drive assembly. Locating apertures of various shapes in the motor coil bobbin adds further stability and aids in interlocking the plastic molds around the motor coil bobbin. Furthermore, to reduce the height of the disc drive, protect the lead wires from being unduly stressed during the formation of the mold, and increase wire strength to tolerate stresses during testing and assembly, another embodiment of the invention utilizes insulating sleeves around the lead wires. Thus, after forming the lead coils from a molded coil mounted at the rear of an actuator arm, the two lead wires from either end of the coil are led out from the end of the coil, and plastic tubes are slid over the wires up to a point closely adjacent the wound coil. The wound coil is then molded, fixing its shape and holding it in place on the rear of the actuator arm.

118. 飛球方向とフェースの開き具合を示すラインとスウィング軌道を示すラインをフェース上に印したアプローチウエッジ

申请号: JP2016018389

申请日: 2016-01-15

公开（公告）号: JP2016105808A

公开（公告）日: 2016-06-16

发明人: 水戸 貞夫

【課題】飛球方向より約20°でカット打ちにできるようテイクバックの目印となるガイドラインをフェース面上に印したアプローチウエッジを提供する。
【解決手段】フェース面の一番下のスコアラインの溝を刻んで加工した部分とフェース面上のトゥ側の加工していないクラウン部分を含む部分との境目の線を0°としてトゥ側に約10°の線を印し、その線がフェースを約10°開くガイドラインでもあり、飛球方向を示すラインになるものであり、また飛球方向を示すラインを基本線としてクラウン部分より最下部のスコアライン方向へ、フェース面のスコアラインの数本ある溝を斜め方向へ横切る約20°のラインを印し、再下部のスコアラインの左右の中心より少し外側にガイドラインがいくようにしてシャンクを押さえる役目を果たせ、スタンスも約20°開くのでカット打ちする感覚を持つことなくスタンスと平行にスウィングできるように導いてくれるようにしたもの。
【選択図】図1