The technology herein relates to aircraft auxiliary power unit (APU) control systems, and more particularly to APU control methods and systems for defining steady state speed of an APU according to aircraft operating conditions. More particularly, in an aircraft comprising an auxiliary power unit, a control method comprising performing operations including the following with at least one processor: determining at least one aircraft operating condition; and controlling the steady state speed of the auxiliary power unit based on the at least one aircraft operating condition.
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p. ex. à la température, à la pression, à la vitesse du rotor
F02C 9/00 - Commande des ensembles fonctionnels de turbines à gazCommande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
2.
Systems and methods for defining APU steady state speed according to the aircraft operational conditions
B64D 31/00 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
3.
Quickly adjustable fail-safe link bar assemblies especially useful for connecting structural components of an aircraft
Link bar assemblies are provided to connect adjacent structural components (e.g., components of an aircraft such as connecting an underwing engine to the wing structure) having respective connection lugs. The link bar assemblies will include a link bar having opposed terminal ends which include circular bearings, bushings operatively received by the circular bearings of the link bar, and a bolt and pin assembly inserted through the bushings to connect the terminal ends of the link bar to the respective connection lugs of the adjacent structural components. At least one of the bushings includes a multi-faceted flange and defines an eccentric aperture (e.g., an elliptical aperture having major and minor axes) such that rotation of the bushing allows the eccentric aperture to become aligned with the mounting opening of a respective connection lug.
B64C 7/00 - Structures ou carénages non prévus ailleurs
F16M 13/02 - Autres supports ou appuis pour positionner les appareils ou les objetsMoyens pour maintenir en position les appareils ou objets tenus à la main pour être portés par un autre objet ou lui être fixé, p. ex. à un arbre, une grille, un châssis de fenêtre, une bicyclette
B64C 1/22 - Autres structures faisant corps avec le fuselage pour faciliter le chargement
An aircraft wing is provided with a positionally fixed closure fairing to close a cut-out opening in the leading edge of the wing associated with a wing leading edge slat so as to direct incident airflow to the wing leading edge from a lower surface of the aircraft wing to an upper surface of the aircraft wing.
An aircraft wing is provided with a shutter mechanism to close a cut-out opening in the leading edge of the wing when a leading edge wing slat associated with the wing leading edge is moved to a deployed condition.
B64C 3/50 - Variation de la courbure par volets de bord d'attaque ou de bord de fuite
B64C 9/22 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction formant des fentes à l'avant de l'aile
B64C 9/34 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction repliables ou escamotables contre ou à l'intérieur d'autres surfaces ou d'autres éléments
Coupling mechanisms for torque transmitting shafts are provided with sliding and fixed plates operably connectable to respective torque transmitting shafts, and a leaf spring having a preloaded spring force exerted on the sliding plate when the sliding and fixed plates are operably connected to one another. A hub is attached to the leaf spring and coaxially received within the sliding plate to allow the sliding plate to be capable of reciprocal axial movements relative to the hub between engaged and disengaged positions wherein the sliding and fixed plates are engaged and disengaged with one another so as to allow and prevent torque being transmitted from one to another of the shafts, respectively. An inner piston is coaxially received within the hub and moveable between a first position wherein the hub retains the sliding plate in the engaged position thereof, and a second position wherein the hub releases the sliding plate to allow movement of the sliding plate under bias force from the leaf spring into the disengaged position thereof.
F16D 11/14 - Embrayages dans lesquels les organes ont des parties qui se pénètrent mutuellement avec des organes d'embrayage mobiles selon l'axe uniquement
F16D 11/00 - Embrayages dans lesquels les organes ont des parties qui se pénètrent mutuellement
F16D 125/60 - Câbles ou chaînes, p. ex. câbles Bowden
An aircraft wing is provided having a wing leading edge, a wing leading edge slat positioned forwardly of the wing leading edge having an internal duct extending in a spanwise direction of the wing leading edge, a cut-out opening in the wing leading edge, a telescopic tube extending through the cut-out opening and connected to the internal duct of the wing leading edge to establish fluid communication with heated air associated with an aircraft anti-icing system, wherein the telescopic tube is moveable between retracted and extended conditions in response to the wing leading edge slat being moved between slat retraction and deployment positions, respectively, and a shuttering mechanism synchronously connected to the telescopic tube to close the cut-out opening in response to the telescopic tube being moved from the retracted condition to the extended condition thereof.
A slat track roller assembly is provided so as to mount a slat track operatively associated with a wing leading edge slat for movements between retracted and deployed conditions relative to a leading edge of an aircraft wing. The slat track roller assembly may include at least forward and aft pairs of roller mechanisms connected to a respective one of opposed wing ribs of the wing leading edge in operatively rolling contact with a respective opposed lateral edge of the slat track. At least one of the roller mechanisms is positionally adjustable relative to the respectively opposed lateral edge of the slat track so as to compensate for mechanical tolerances that may be present.
Closure devices and methods are provided for closing a stringer penetration space defined between a stringer and a wing rib of an aircraft wing section. According to certain embodiments, the closure devices will integrally include a forward face plate positioned in covering relationship to at least a portion of the stringer penetration space, and a rearwardly projecting attachment arm rigidly adapted for rigid attachment to the stringer so as to positionally fix the forward face plate relative to the stringer penetration space.
This describes an aircraft control surface regulating device, comprising an elongated structural body formed of a base positioned at a first end and fixed to the structure of the aircraft and a regulation assembly arranged at a second end and positioned next to the control surfaces, the regulation assembly comprising at least one dial indicator positionable between a first measuring position and a second positioning position and at least one reference ruler arranged adjacent to at least one dial indicator and positionable between an initial position and a final position.
(iii) positioning the reference ruler in a final position and positioning the dial indicator in second positioning position to perform the positioning of the control surface regulated in relation to the wing of the aircraft.
B24B 19/26 - Machines ou dispositifs conçus spécialement pour une opération particulière de meulage non couverte par d'autres groupes principaux pour meuler des pièces à surfaces arquées, p. ex. parties de carrosserie de véhicules, pare-chocs ou têtes d'enregistrement magnétiques
B25J 5/04 - Manipulateurs montés sur roues ou sur support mobile se déplaçant le long d'un chemin de guidage dans lequel le chemin de guidage est aussi mobile, p. ex. du type pont roulant
B25J 21/00 - Enceintes à dispositifs de manipulation intégrés
B24D 9/08 - Plateaux circulaires servant de support au matériau souple
Lightweight passenger seats that are especially adapted for use in aircraft cabins. The seats will include a seat back and a seat bottom having a basin which defines a recessed central interior space, a plurality of straps having opposed ends connected to respective upper edge regions of the basin so as to be positioned under tension over the recessed central interior space; and a cover cushion covering the straps and connected to the basin. The seat back may be connected at opposed sides thereof to upright support members adjacent a lumbar region thereof so as to establish an upper region of the seat back above the lumbar region which is capable of being resiliently flexed between upright and rearwardly inclined positions.
B60N 2/24 - Sièges spécialement adaptés aux véhiculesAgencement ou montage des sièges dans les véhicules à des fins particulières ou pour des véhicules particuliers
Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box, wherein the upper pylon connection member and the lower pylon connection box respectively include multiple opposed pairs of connection lobes. At least one pair of the connection lobes includes a pin connection to restrict degrees of freedom thereat along an x-axis and a mutually perpendicular z-axis, while at least one other pair of connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis.
Inadvertent in-flight inflation of an inflatable slide associated with a non-co-located over-wing emergency door of an aircraft fuselage is prevented by a system having a source of compressed gas (e.g., a compress air cylinder) and a 3-way valve having an input port and a pair of output ports each being individually connectable to the input port. The 3-way valve is operable in response to a control signal so as to fluid-connect the source of compressed gas with either a vent line which vents the compress gas overboard or a supply line the inflatable slide. When the control signal fluid connects the gas source to the vent line, the system will be in a safe in-flight mode indicative of inflight operation of the aircraft in which case inadvertent inflation of the slide is prevented.
Methods are provided by which a treatment fluid (e.g., a liquid corrosion inhibitor) may be applied onto the interior surfaces of an aircraft fuselage. The methods include (a) deploying an automated guided vehicle (AGV) comprising a carriage assembly and a robotic spray system carried by the carriage assembly within the interior of the fuselage, (b) closing the cabin door opening of the fuselage with the AGV positioned therewithin, and (c) operating the AGV so as to move within the fuselage along a longitudinal axis thereof to spray the treatment fluid onto the surfaces thereof.
B64C 1/14 - FenêtresPortesTrappes d'évacuation ou panneaux de visiteStructures de cadres environnantsVerrièresPare-brise
B05B 15/60 - Aménagements pour le montage, le maintien ou le soutien des appareils de pulvérisation
B05B 13/06 - Machines ou installations pour appliquer des liquides ou d'autres matériaux fluides sur des surfaces d'objets ou de matériaux par pulvérisation, non couverts par les groupes conçus spécialement pour traiter l'intérieur de corps creux
B05D 7/22 - Procédés, autres que le flocage, spécialement adaptés pour appliquer des liquides ou d'autres matériaux fluides, à des surfaces particulières, ou pour appliquer des liquides ou d'autres matériaux fluides particuliers à des surfaces internes, p. ex. à l'intérieur de tubes
B64C 1/22 - Autres structures faisant corps avec le fuselage pour faciliter le chargement
B64C 1/34 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés comprenant des composants structuraux gonflables
B05D 1/02 - Procédés pour appliquer des liquides ou d'autres matériaux fluides aux surfaces réalisés par pulvérisation
B05B 13/04 - Moyens pour supporter l'ouvrageDisposition ou assemblage des têtes de pulvérisationAdaptation ou disposition des moyens pour entraîner des pièces les têtes de pulvérisation étant déplacées au cours de l'opération
B05B 12/32 - Éléments d’écran, c.-à-d. éléments empêchant un excès de pulvérisation d’atteindre des aires autres que l’objet à pulvériser
B25J 5/00 - Manipulateurs montés sur roues ou sur support mobile
An automatic takeoff flight control system controls an aircraft to automatically follow a predetermined set of control parameters upon taking off from the ground using both longitudinal and lateral control laws. The control system provides takeoff speed reduction to thereby reduce the takeoff distance (TOD) and, as a consequence, increase the takeoff weight (TOW). The control system sets the horizontal stabilizer (HSTAB) in a non-trimmed condition—named “mistrim”; and provides beta for optimum climb at takeoff, through lateral-directional surfaces commands.
B64C 9/00 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction
B64C 13/18 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p. ex. répondant aux détecteurs de rafales utilisant un pilote automatique
G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
19.
Aircraft air conditioning system airflow regulation
An environmental control system for an aircraft uses engine bleed air for cabin environment control. The environment control system regulates the inlet airflow by assessing a plurality of parameters that provides, but not limited to, the aircraft operating conditions and external environment data, aiming at substantially reducing the extracted engine bleed air demand for cabin environment control and fuel consumption reduction and concurrently complying with aircraft pressurization, ventilation and thermal load requirements. The environmental control system airflow target is calculated based on the actual aircraft operating conditions, external environment data and a multi-dimensional airflow schedule map. Then, environmental control system airflow target is further trimmed based on the actual aircraft operating conditions and air conditioning system performance capabilities by fixing the air conditioning airflow outlet temperature and then regulating the air conditioning inlet mass airflow through the flow control valve. The first control method reduces and the second one trims the environmental control system airflow target comparing to conventional control methods. Thus, fuel consumption reduction is obtained when the environment control system airflow target (extracted bleed air demand) can be reduced and or trimmed depending on flight conditions.
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
B64D 13/02 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant pressurisé
20.
Variable angular compression seal assemblies for moveable aircraft components
Variable angular compression seal assemblies are disclosed that may usefully be employed to seal movable aircraft components, e.g., so as to seal a flap torque tube operating in a flap track cutout opening in a wing to fuselage fairing. The seal assembly may be provided so as to seal a component moveable between first and second positions within a cutout opening. The seal assembly includes a split seal having opposed seal members in non-compressive contact with one another along a split line between opposed ends of the seal members so as to allow the component to be moved along the split line between the first and second positions thereof. The seal members include opposed wall portions at one end thereof defining a recess for receiving the moveable component when in the first position thereof. The split line between the opposed seal members can be variably curved.
F16J 15/16 - Joints d'étanchéité entre deux surfaces mobiles l'une par rapport à l'autre
B64C 7/00 - Structures ou carénages non prévus ailleurs
F16J 15/10 - Joints d'étanchéité entre surfaces immobiles entre elles avec garniture solide comprimée entre les surfaces à joindre par garniture non métallique
21.
Quick connection assemblies especially useful for coupling aircraft antenna fairings to airframe structures
Aircraft antenna fairing assemblies include a fairing shell and connection components for positionally fixing the fairing shell to airframe structure of an aircraft. The connection components may comprise a guide assembly having a guide head and a receiver defining a guide channel for receiving the guide head therewithin, and a latch assembly for latching the fairing shell to the airframe structure of the aircraft. The receiver of the guide assembly may define a generally C-shaped or generally U-shaped channel for receiving the guide head therewithin.
B64C 1/38 - Constructions adaptées pour réduire les effets de l'échauffement aérodynamique ou d'un échauffement externe d'autre nature
B64C 1/36 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés adaptés pour recevoir des antennes ou des radômes
H01Q 1/42 - Enveloppes non intimement mécaniquement associées avec les éléments rayonnants, p. ex. radome
B64C 7/00 - Structures ou carénages non prévus ailleurs
H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
Pylon fairings for an aircraft turbojet engine mounted below an aircraft wing are provided with inboard and outboard lateral faces which converge rearwardly to form a trailing edge of the pylon fairing and which are positioned so as to contact a portion of a cold flow exiting a fan duct of the turbojet engine, and a bottom face positioned above a hot exhaust flow exiting an exhaust nozzle of the turbojet engine. The trailing edge of the pylon fairing extends in an upward direction relative to an engine longitudinal axis of symmetry between a lower terminus at the bottom face and an upper terminus located at a lower surface of the aircraft wing. The lower terminus is coincident with a longitudinal midplane of the turbojet engine, and the upper terminus is offset in an inboard direction so that the trailing edge of the pylon fairing is cambered in the inboard direction between the lower terminus and the upper terminus.
Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box, wherein the upper pylon connection member and the lower pylon connection box respectively include multiple opposed pairs of connection lobes. At least one pair of the connection lobes includes a pin connection to restrict degrees of freedom thereat along an x-axis and a mutually perpendicular z-axis, while at least one other pair of connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis.
B64C 27/26 - Giravions complexes, c.-à-d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion caractérisé par le fait qu'il est doté d'ailes fixes
B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur
B64D 27/18 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction à l'intérieur des ailes ou fixés à celles-ci
24.
System and method to interchange flight control inceptors in an aircraft flight control system and cockpit
A flexible flight control system enables conversion from one architecture using one type of inceptor to another architecture using another type of inceptor, through the usage of modular software and hardware pieces with common interfaces among the different types of inceptors. Longitudinal and lateral directional control laws are adapted to be compatible with the specific aspects of the operation of each configuration/architecture, giving the option to the aircraft operator to choose any one of a number of inceptor architectures at time of manufacture.
B64D 43/00 - Aménagements ou adaptations des instruments
B64C 13/06 - Dispositifs amorçant la mise en œuvre actionnés par l'homme réglables pour s'adapter à la conformation de l'utilisateur
B64C 13/04 - Dispositifs amorçant la mise en œuvre actionnés par l'homme
B64C 27/56 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p. ex. mouvement de traînée caractérisés par les dispositifs de déclenchement de la commande, p. ex. à commande manuelle
B64D 11/06 - Aménagements ou adaptations des sièges
Stabilized wing rib components and methods for assembling such stabilized wing rib components with at least one other aircraft airfoil structural component
Devices and methods for stabilizing a structural component are provided. The devices may include a main body component, a pair of opposed stabilization feet engageable with opposed regions of the structural component, a pair of coaxially disposed and reciprocal rectilinearly movable support shafts coupling the stabilization feet to the main body component, and an actuator assembly for rectilinearly moving the support shafts opposite to one another which in turn moves the stabilization feet between retracted and extended positions relative to the main body component. In use, the device may be positioned between opposed flanges of a structural component so as to stabilize the component and facilitate automated assembly processes.
B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleursManipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
B25B 5/02 - Presses ou serre-joints à mâchoires coulissantes
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
30.
Force-balancing mechanisms especially useful for assisted lifting/lowering of aircraft stairs
The disclosed embodiments herein are generally directed toward force-balancing mechanisms for weighted members and/or loads. According to one embodiment, the force-balancing mechanism includes at least one gear rack, at least one spring assembly comprising a spring member operatively connected to the at least one gear rack, a pinion gear intermeshed with the at least one gear rack; and a variable radius cam. Rotation of the cam causes the pinion gear to rotate to thereby in turn linearly drive the at least one gear rack and accumulate spring force of the spring member. The spring member may be a compression or a tension spring. Preferably, the spring member is a compression spring.
Elongate passenger service unit (PSU) assemblies are comprised of a plurality of modular passenger service units, and a plurality of variable-length modular spacer units. The modular spacer units are positioned between the modular passenger service units in an end-to-end manner so as to provide a desired lengthwise array of the passenger service units along the PSU assembly. Transport category vehicles, e.g., aircraft, may thus be provided with inboard and outboard PSU assemblies. The passenger seats may be arranged in a latitudinally side-by-side arrangement and/or may be arranged in a longitudinally staggered arrangement. By providing variable length modular spacer units, therefore, the individual passenger service units may be arranged directly overhead of each passenger seat.
B64D 11/00 - Arrangements pour passagers ou équipageInstallations de postes de pilotage non prévues ailleurs
A62B 7/14 - Appareils respiratoires pour vol à haute altitude
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret
Overhead bin assembly for transport vehicles (e.g., transport category aircraft) are provided with a generally U-shaped bin shell having a bottom wall, an outboard end wall and an upper wall defining an interior stowage space having an inboard opening opposite the end wall. A pair of separated transverse bin supports defining a bin space therebetween may be provided along with a bin door for closing the inboard opening. A cantilever hinge may be provided so as to connect the bin door to the transverse bin support in a cantilever manner to allow for pivotal movement of the bin door between closed and open positions relative to the inboard opening. An arcuate recessed wall may be positioned inboard relative to the upper wall of the bin shell (e.g., as a unitary (one-piece) extension thereof) such that the bin door is received within the recessed wall when in the open position thereof.
Diverter assemblies for aircraft air inlets include a diverter structure at least substantially surrounding the air inlet, and a fairing mounted to an upper edge of the diverter structure forwardly of the air inlet.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
The Climb-Optimized Takeoff System is an aircraft functionality aimed at improving the takeoff performance. The improvement is obtained by allowing the airplane to rotate to an optimized pitch attitude at and after VR, while ensuring that the minimum required takeoff climb gradients and the geometric limitations of the airplane are being respected. The optimum takeoff performance is obtained by granting that the airplane pitch attitude, instead of being limited by a single takeoff constraint (such as a given pitch to avoid tail strike) is being tracked to its instantaneous, most constraining limit during the air transition phase (d2).
G05D 1/06 - Régime de modification de l'altitude ou de la profondeur
G05D 1/12 - Commande pour la recherche d'un objectif
G06G 7/70 - Calculateurs analogiques pour des procédés, des systèmes ou des dispositifs spécifiques, p. ex. simulateurs de véhicules, p. ex. pour la détermination du chargement admissible de navires
G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
36.
Aircraft provided with aerodynamic seal for reduction of noise generated by aircraft control surfaces
Aircraft are provided with a perforated blade seal at the lower and/or upper side edges of a control surface contour, such as a flap, with the purpose of acting as a vortex generator, thereby making it difficult for the lower vortex system to move upwards and merge with the upper vortex system. The perforated blade seals are preferably arranged on the inboard and outboard edges of high lift flaps.
Aircraft wings are provided with aerodynamic devices that improve the wing's low airspeed aerodynamics. In preferred embodiments, the aircraft wings include a slat operatively positioned at the wing's leading edge for movement between a retracted position for relatively high airspeed aircraft operations, and a deployed position for relatively low airspeed aircraft operations. An aerodynamic device is positionally fixed to the wing laterally adjacent the leading edge slat, the device having a forward end extending forwardly of the wing leading edge. The device is operable in response to movement of the slat into the deployed position thereof so as to improve the aerodynamics of the wing at low airspeed aircraft operations, but provides substantially no aerodynamic improvement when the slat is in the retracted position thereof during high airspeed aircraft operations.
The Tail Load Monitoring System detects faulty low frequency (e.g. those in the range from 0.1 to 1 Hz) oscillatory conditions caused by Flight Control System malfunctions while the aircraft is in air by means of a continuous assessment of the estimated tail load behavior and data processing. Both estimation and data processing activities are provided by a dedicated architecture featuring a tail load estimation module, a band-pass filter and three independent paths that continuously monitor nuisance fault detection events avoidance, catastrophic events avoidance (addressing a limit load criterion), and structural damage avoidance (addressing fatigue life criteria).
brevets
