A rotary element assembly structure in which a rotary element 53 is assembled to a tip side of a hollow shaft B1 provided upright on a pedestal 60. A cylindrical portion 53c for fitting with the hollow shaft is provided to a rotation center portion of the rotary element. In the cylindrical portion, a hook strut portion 53s that has a hook portion 53f overhanging in the radial direction at its tip side and that extends substantially in the fitting direction is arranged. A base end portion of the hook strut portion and a base end portion of the cylindrical portion are coupled with each other by a resin-made thin plate portion 53p. A small diameter portion B1s which is smaller in diameter than a hollow portion B1d of the hollow shaft is provided on the tip side of the hollow shaft. The radius of the overhang tip portion of the hook portion is set to be greater than the radius of the small diameter portion of the hollow shaft, and to be smaller than the radius of the hollow portion. By fitting the hollow shaft with the cylindrical portion of the rotary element, the hook portion on the tip side of the hook strut portion is pushed into the hollow portion via the small diameter portion on the tip side of the hollow shaft. Thereby, the hook portion engages with a stepped portion formed by the hollow portion and the small diameter portion.

A sensor for monitoring a plant population in front of a harvester and a transfer process of the crop from the harvester to a transport vehicle is arranged on an unmanned aircraft. The aircraft moves in the vicinity of the harvester in the harvesting mode and communicates in a wireless fashion with a control unit that controls an actuator for influencing an operating parameter of the harvester and/or the transport vehicle (in real time based on signals of the sensor in the harvesting mode.

Methods and system for presenting a plurality of attributes of a plurality of players from a plurality of teams that are part of a league includes obtaining a plurality of attributes of the plurality of players and the plurality of teams. The plurality of attributes of the plurality of the players and of the teams is populated in one or more databases along with any updates to these attributes. The databases are queried to retrieve updated plurality of attributes of the plurality of players and the plurality of teams. A roster grid is generated for the plurality of teams for rendering at a client in substantial real time. The roster grid displays the updated status of the plurality of attributes of the plurality of players and the plurality of teams simultaneously in a clean, concise and effective manner.

An air guide element (10) for an aircraft air conditioning system comprises a housing (12), which has an air inlet opening (14) and an air outlet opening (16). The air inlet opening (14) and the air outlet opening (16) are disposed in such a way and the housing (12) is shaped in such a way that air that is fed to the air guide element (10) through the air inlet opening (14), as it flows through the air guide element (10), is deflected at an angle of ca. 45° to 135° relative to the direction of the air flow through the air inlet opening (14). A cross-sectional area of flow of the housing (12) that is disposed at right angles to the direction of the air flow through the air outlet opening (16) is subdivided into at least two regions (18a, 18b, 18c). In each of said regions (18a, 18b, 18c) an easily accessible, removable and exchangeable calibrating element (20a, 20b, 20c) is disposed, which is designed to generate, in the air flow passing through a region (18a, 18b, 18c) that is associated with a respective calibrating element (20a, 20b, 20c), a pressure loss that is constant over said region (18a, 1b, 18c).

A system for ventilating an explosion hazard region of an aircraft includes a ram-air channel, which has an air inlet for feeding ambient air into the ram-air channel as well as an air outlet. The ram-air channel is devised to feed air to a device that is to be cooled on board the aircraft. A ventilation line has an air inlet for feeding air flowing through the ram-air channel into the ventilation line as well as an air outlet. The ventilation line is devised to feed air to a region of the aircraft that is to be ventilated. An accumulator is disposed between the ram-air channel and the air inlet of the ventilation line and is devised to convert the dynamic pressure of the air flow conveyed through the ram-air channel at least partially into static pressure for regulating flow through the explosion hazard region.

A system for air-conditioning an aircraft cabin includes an air conditioning unit connected to a central mixer, a first recirculation system designed to remove exhaust air from a first aircraft cabin region and connected to the central mixer, and a second recirculation system designed to remove exhaust air from a second aircraft cabin region and connected to a local mixer. A control device is designed to control the second recirculation system to reduce an air volume flow being removed from the second aircraft cabin region when shifting from a first operating state (e.g., normal operation) to a second operating state (e.g., defined operating situations such as when quick cooling is desired). The air volume being removed from the first aircraft cabin region may be increased accordingly in the second operating state.

An ultrasonic surgical instrument comprises a reusable housing including an internal transducer and an internal end effector rotation assembly. An exemplary rotation assembly is a ratchet and pawl assembly, which allows the transducer to rotate in a first direction but not in a second, opposite direction. The end effector, including an integral torque wrench, is attached to the transducer to form a single unit that is rotatable relative to the housing. The transducer attaches to a stationary cable via slip rings. The cable communicates with a generator, which provides electrical power to the transducer. The transducer converts the electrical power into ultrasonic vibrational energy, which is transmitted to the end effector.

The present invention relates to a bit for processing the inside diameter of a work material, the bit having on the outer surface of a shank a vibration preventing structure comprising a vibration absorption body made of a silicone material, and a hollow wire rod, thereby absorbing the vibration generated from a machine tool, preventing resonance generated between the work material and a tool, and thus, enabling the implementation of a slickenside from ultra-precision machining.

An unmanned aircraft, unmanned aviation system and method for collision avoidance during the flight operation of an unmanned aircraft are provided. The unmanned aircraft includes a lift and propulsion system and a flight control system having a flight control unit, a navigation system and an actuator system. The flight control unit has an autopilot unit. The flight control unit calculates control commands using data from the navigation system and/or the autopilot unit, which can be conveyed to the actuator system for actuating the lift and propulsion system. A collision warning system is connected with the flight control system, the collision warning system detects a collision situation and makes collision avoidance data available. A connection between the collision warning system and the autopilot unit is provided, in order to initiate an obstacle avoidance maneuver by the autopilot unit with the help of the collision avoidance data.

In some aspects, a master cylinder assembly for vertical lift aircraft is configured to move pressurized fluid through a conduit in response to applied movement of an input lever. A low pressure relief valve can be connected to a first conduit to limit pressure to a low level. An isolation valve can be connected to the first conduit and configured to isolate the low pressure relief valve from the conduit when engaged. A high pressure relief valve can be connected to a second fluid conduit to limit pressure to a high level. In some aspects, a rotor brake actuator is fluidly connected to the first conduit and the second conduit and configured to engage a rotor brake in response to hydraulic fluid pressure.

Disclosed is a method for the monitoring of a cabin region of a transport system located outside a field of view, wherein at least one light beam is emitted, passing through the cabin region in the longitudinal direction, and in the event of a disturbance of the at least one light beam path a message is generated. A monitoring device is also provided, with at least one emitter unit for purposes of emitting at least one light beam, with at least one receiver unit for purposes of receiving the emitted light beam, and with at least one messaging unit for purposes of generating a message in the event of a disturbance of the at least one light beam path; also disclosed is an aircraft cabin with at least one such monitoring system.

A system and method are described for receiving a NOTAM and storing information relating to the distance of a temporarily displaced threshold for a runway. When that runway is selected for approach and landing, the temporarily displaced threshold and new aiming point are automatically displayed. The change made to the display using NOTAM data can be indicated to the pilot by distinct symbology or particular color, or by using an icon or an annunciation.

A method of determining a turbulent condition in an aircraft with a handheld device where the handheld device has at least one of a gyroscope, seismometer, and an accelerometer where the method includes receiving an output from the at least one of the gyroscope, seismometer, and accelerometer while the handheld device is located within the aircraft and providing an indication of a turbulent condition.

A premium class passenger suite that includes a main seat positioned in the suite together with separate bed. The bed has a flexible mattress of predetermined dimensions and is movable between a stowed position to one side of the main seat and a deployed position above and separate from the main seat. A drive apparatus is provided for driving the bed between the stowed and deployed positions. The main seat is configured to be movable between a seating position when the bed is stowed, and a stowed position with a lowered seat back when the bed is deployed for use.

A seat cushion, in particular for an aircraft seat, the seat cushion comprising a seat part having a receiving surface adapted to receive a person and a reinforcing part supporting the seat part, wherein at least the reinforcing part contains expanded polypropylene (EPP), preferably comprising fire retardant properties. The invention further relates to a method for manufacturing such a seat cushion, a seat comprising such a seat cushion and a vehicle comprising such a seat.

An operating unit (1) for installation in an aircraft cabin comprises an operating unit front side (10) and an operating unit rear side (20), at least one operating element (12, 14) attached in the region of the operating unit front side (10) and accessible to a user, and a holding device (40) for attaching the operating unit (1) to a monument (30) accommodating the operating unit (1) in its state mounted in the aircraft cabin. The holding device (40) is designed to attach the operating unit (1) in its state mounted in the aircraft cabin to the monument (30), in a first position or in a second position, as desired, the operating element (12, 14) in the second position of the operating unit (1) being situated in a spatial position which is lowered with respect to the spatial position of the operating element (12, 14) in the first position of the operating unit (1) and/or is displaced in a direction parallel to an imaginary straight line connecting the operating unit rear side (20) to the operating unit front side (10).

A CRDS unlatching tool includes a support assembly and a latching assembly, wherein the support assembly is received within the latching assembly in a manner wherein the latching assembly is moveable relative to the support assembly. The support assembly has a plurality of latch fingers and at least one pin, each of the latch fingers being movable between a latched position wherein the latch finger is structured to engage and hold the CRDS an unlatched position wherein the latch finger is structured to not engage the CRDS. The latching assembly includes a first sleeve member and a second sleeve member, the second sleeve member having at least one slot, wherein the at least one pin is moveably received within the at least one slot. The latching assembly is movable from a latched state to an unlatched state wherein the latch fingers are actuated by the first sleeve member.

An apparatus for anchoring at least two graft ligaments within a longitudinal bone tunnel includes a longitudinal sleeve having at least two ligament-contacting surfaces located in lateral opposition to a sleeve inner lumen. The sleeve is configured for at least partial insertion into the bone tunnel with each graft ligament positioned laterally adjacent a different ligament-contacting surface and at least partially located between the bone tunnel and the sleeve. An actuating member has proximal and distal actuating member ends. An asymmetrically offset profile is defined by the sleeve and/or the actuating member. The asymmetrically offset profile has engagement thresholds. The actuating member is inserted into the sleeve to cause frictional engagement of each graft ligament with both the bone tunnel and at least one ligament-contacting surface, the frictional engagement of each graft ligament being temporally spaced apart from the frictional engagement of at least one other graft ligament.

A rotary joint device includes attachment grooves formed at positions in an outer peripheral surface of an outer cylinder, each attachment groove being formed so as to straddle a pair of adjacent cylindrical blocks and so as to be exposed from the outer peripheral surface of the outer cylinder, each attachment groove having a bottom surface that is machined to form a flat surface in a state in which the cylindrical blocks are combined, and positioning blocks corresponding to the attachment grooves on a one-to-one basis and each having an attachment phase that is uniquely set to a corresponding one of the attachment grooves in the axial direction and in a circumferential direction of the outer cylinder, each positioning block having an attachment surface corresponding to the bottom surface of a corresponding one of the attachment grooves, the attachment surface being machined so as to form a flat surface.

A method to develop a system for management of warnings and electronic procedures for an aircraft, comprising a database of parameters relating to the warnings and to logic and procedures, the aircraft comprising ATA equipment, comprises definition and calculation of maturity criteria for development of the system, which comprises, in order: A) verification of warnings in the database with respect to predefined lists of warnings and calculation of a maturity criterion, B) if the criterion of A>predetermined threshold, verification of the coherence of the logic for the warnings then definition and calculation of a maturity criterion, C) if the criterion of B>predetermined threshold, verification of the existence of the procedures and, for each warning, analysis of its logic with respect to its procedure, then definition and calculation of a maturity criterion, the system being fully set up when the latter criterion>predetermined threshold.

Guard elements (31) are provided for the corner connectors (16 through 19) of a heald shaft (10) of a shedding unit, the guard elements covering the open space formed between the two legs (26, 27) and thus providing a grip protection.

An implantable graft device is disclosed. The device comprises a graft body forming a lumen defining a longitudinal axis and comprising proximal and distal ends. The graft body comprises a woven fabric having warp yarns aligned in a first direction and weft yarns aligned in a second direction. The weft yarns are woven with the warp yarns. A portion of the warp yarns along the longitudinal axis of the graft body are not interwoven with the weft yarns, defining floating yarns having loops aligned in one of the first direction and the second direction. The device further comprises an expandable stent disposed circumferentially about the longitudinal axis and received through the loops of the floating yarns to attach the stent to the graft body.

An implantable graft device having treated yarn is disclosed. The device comprises a graft body forming a lumen defining a longitudinal axis and comprising proximal and distal ends. The graft body comprises a woven fabric having warp yarns aligned in a first direction and a weft yarns aligned in a second direction. At least one of the weft yarns and the warp yarns has an agent applied thereto defining treated yarns of the graft body.

A generator includes a permanent magnet generator, an exciter and a main generator mounted for rotation on a shaft. The main generator is configured to produce a voltage output. A generator control unit includes a circuit configured to provide current from the permanent magnet generator to the exciter. A switch is provided in the circuit and is configured to change between open and closed conditions. The switch is configured to flow current in the circuit in the closed condition and interrupt current flow in the open condition. An overvoltage limit controller is programmed to determine an amount of overvoltage of the output voltage exceeding a desired voltage. Either a fixed reference threshold is used or a reference threshold voltage is calculated based upon the duration in over voltage condition, and the switch is modulated between the open and closed conditions according to error between the actual output voltage and the reference threshold voltage to limit the output voltage to the desired reference threshold voltage.

Disclosed is a coupler comprising a first structure, a first shaft rotatably supported by the first structure, a second structure supporting the first structure, and a moving device configured to move the first structure relative to the second structure.

An exemplary embodiment of the present invention provides an induced-draft injection system comprising an injection line in fluid communication with a duct under negative pressure, a particulate storage containing particulate, and a feeder receiving the particulate from the particulate storage and feeding the particulate to the injection line. The negative pressure in the duct supports the transportation of at least a portion of the particulate through the injection line and into the duct. Inside the duct, a binding portion of the particulate is bound to a portion of mercury in a flue gas passing through the duct, thus enabling a portion of the mercury to be filtered out of the flue gas.

This invention consists of a coupling device by means of which the shafts of a sulky used in harness horse racing can be quickly and easily attached to or detached from the harness of the horse. It consists primarily of a metal framework, which is part of the harness, into which is inserted the end of each shaft wherein it is held by a spring loaded pin which passes through the framework and the free end of the shaft. The shaft is released simply by pulling the pin out of the shaft end; when released, the pin returns to the locking position until it is pulled up again to reinsert the shaft.

Hitch for securing a racing sulky to a harness or saddle of a horse. The hitch has an elongated, generally cylindrical body which includes a frustoconical tapered front portion, a generally cylindrical mid-portion and a cylindrical rear portion of slightly smaller diameter than that of the mid-portion so as to form a shoulder. The rear portion is adapted to be inserted into the open end of a tubular shaft, such as a shaft of a racing sulky. When so inserted, the hitch may be permanently secured to the shaft. The mid-portion of the hitch includes cylindrical front and rear end members which adjoin the front portion and the rear portion respectively of the hitch. The mid-portion of the hitch has one or more cutouts which define a longitudinally extending rigid strut and (when there is more than one such cutout) one or more transverse spacer discs, which are spaced from the end members and from each other. A rigid rod extends through the rear portion and the mid-portion of the hitch. The strut and the rigid rod (and the spacer discs when present) together define one or more slotted openings for receiving a strap or the like which is associated with a harness or saddle. Preferably the entire hitch except for the rigid rod is formed from a single piece of material; the rigid rod may be formed from a second piece of material and joined to the remaining structure. Either metal (such as steel or aluminum) or rigid plastic can be used for forming the hitch.

A railroad freight car multipiece spring seat assembly including a spring seat, a top plate, and a spring. The spring seat is adapted to operably engage one end of a spring assembly in a railroad freight car draft gear. The top plate is adapted to operably engage with each of a plurality of friction shoes arranged in the railroad freight car draft gear. The spring of the multipiece spring seat assembly is operably disposed between the spring seat and the top plate.

A draft sill with special rear draft lug for a railcar is disclosed. In some embodiments, a rear draft lug comprises a metallic body. The rear draft lug further comprises a boss extending along a transverse portion of the metallic body. The boss is configured to be coupled to a first vertical reinforcement plate. The rear draft lug also comprises an overhang portion extending from the boss along the transverse portion. The overhang portion configured to be coupled to the first vertical reinforcement plate. In some embodiments, the boss and the overhang portion are configured to be coupled to the first vertical reinforcement plate with a weld.

A draft gear assembly includes housing and an elastomeric spring stack disposed therewithin and including a plurality of compressible elastomeric springs disposed in series with each other. Each compressible elastomeric spring includes a compressible elastomeric pad, a rigid member positioned in direct contact with one end surface of the compressible elastomeric pad, a central aperture through a thickness of the rigid member, an abutment upstanding axially on the end surface of the compressible elastomeric pad, the abutment having a peripheral surface thereof sized to be received within the central aperture formed through the thickness of the rigid member, and an annular lip disposed on a distal end of the axial abutment in a plane being substantially transverse to the central axis, whereby an annular thickness portion of the rigid member is caged between the end surface of the compressible elastomeric pad and an inner surface of the annular lip.

A coupler yoke and a coupler draft gear are used in the field of carriages of a railway and aim at solving the problems of lower strength, low safety and reliability and the like in the prior art. The coupler yoke comprises a hollow yoke body with the cross section being in a long concentric-square shape, the inner side surface of the one end of the hollow yoke body is a bearing surface, and at least part of the heavy loading area of the bearing surface protrudes outwards relatively to the end surface of the light loading area. The coupler yoke is used for connecting couplers between the carriages of a train, so that the carriages are connected to form the train for transmitting the tractive force in the transportation; the distribution pattern of the existing bearing surface is changed due to the arrangement of a middle groove.

A mechanical coupling, particularly in a draftgear in rail vehicles, includes a central plate (5) turnably mounted in a coupler head and having a link (7) pivoted in the same, and including a hooking mechanism for detachable hooking up of the central plate and the link in the non coupled position of the coupling, and a releasing device (10) for the automatic detachment of the hooking mechanism upon coupling. The hooking mechanism includes a hooking rod (12) pivotally connected with the central plate, which rod, by a lug (16), clutches a collar (11) arranged in the coupler head and, upon activation of the releasing device, detaches from the collar. A leaf spring (13) is arranged in the coupler head in order to, in abutment against the hooking rod, force the same, under the bias from the spring, to be pressed against the collar in the hooked up and disengaged positions.

A railcar draft gear assembly having an axially elongated spring assembly comprised of an axially stacked array of individual spring units and further including cooperating instrumentalities for maintaining the spring assembly generally axially aligned with a longitudinal axis of the railcar draft gear assembly during operation of the draft gear assembly while maintaining the individual spring units in generally aligned relation relative to each other.

A friction/elastomeric draft gear having a housing, a spring assembly arranged within the housing, and a friction clutch assembly having a wedge member and defining first sliding friction surface disposed at an angle θ relative to a longitudinal axis of the draft gear and a second friction surface disposed at an angle β relative to a longitudinal axis of the draft gear. The spring assembly is designed in combination with the angles θ and β of the first and second friction sliding surfaces relative to the longitudinal axis such that the draft gear consistently and repeatedly withstands between about 100 KJ and 130 KJ of energy imparted at less than three meganewtons over a range of travel of the wedge member in an inward axial direction relative to the draft gear housing not exceeding 120 mm.

A railcar draft gear assembly including a housing, a spring sea, a spring and a friction clutch assembly in operable combination relative to each other within the housing. The spring includes a series of axially stacked elastomeric pads arranged between a closed end of the housing and the spring seat. An axially elongated guide rod is endwise passed through the spring seat and elastomeric pads for aligning the pads relative to a longitudinal axis of the draft gear assembly. The guide rod is operably inhibited from axial shifting movements during operation of the draft gear assembly. A related method for assembling the draft gear is also disclosed.

A counterbalance mechanism for counterbalancing weight of a bottom-hinged door (such as a clamshell-type airstair door of an aircraft) includes an operator handle, a hoist rod pivotally connected at one end to the operator handle and at an opposite end thereof to the door near a bottom region thereof. A force accumulator assembly is provided which includes a force biasing member which accumulates and dissipates a bias force when opening and closing the door, respectively, to provide mechanical counterbalance to the weight of the door. A bellcrank assembly operatively connects the operator handle to the force accumulator. In such a manner, weight counterbalancing of the door is achieved.

Baggage compartment 1 for an aircraft, wherein the baggage compartment 1 comprises a housing 2 and a baggage holder 3, wherein the baggage holder 3 is swivel-mounted about a swivel axis A in the housing 2, wherein, the swivel axis A intersects, in its longitudinal extent, a holder side wall 32 of the baggage holder 3 and/or a housing side wall 21 of the housing 2, wherein the baggage holder 3 can be moved from a closed position G into an open position Ö with a first swivel movement S1 and the baggage compartment 1 is opened and wherein the baggage holder 3 can be moved from the open position Ö into the closed position G with a second swivel movement S2 and the baggage compartment 1 is closed, wherein the baggage compartment 1 comprises a drive device 6 having at least one drive motor 9, wherein the drive device 6 is designed to drive the baggage holder 3 during the first and/or second swivel movement S1; S2 and to open or close the baggage compartment 1, wherein the drive device 6 is connected to the holder side wall 32 on one side and to the housing side wall 21 on the other side.

A spacecraft carrier is disclosed. The carrier has a large internal volume for housing at least one spacecraft. The carrier can be used as a repair and maintenance facility in space for spacecraft. Manned and unmanned devices can be stored, repaired and resupplied. The carrier can also transport a number of spacecraft to other locations allowing for an efficient coordinated movement of many spacecraft.

A method of creating at least one flight plan of an aircraft includes entering a creation objective which illustrates a type and general characteristics of the flight plan to be created, automatically generating a flight plan outline, automatically generating a targeted request for information relating to missing parameters, entering the requested information relating to the missing parameters, and supplementing automatically the flight plan outline and automatically deleting any discontinuities to create, in a definitive manner, the flight plan.

A method of controlling a group (2) of engines developing a necessary power (Wnec) for driving a rotor (3), said group (2) of engines having at least one electrical member (4), electrical energy storage means (5), and a first number n of engines (6) that is greater than or equal to two. A processor unit (10) executes instructions for evaluating a main condition as to whether the group of engines can develop the necessary power while resting one engine, and if so for resting one engine and accelerating a second number engines not at rest, and for causing the electrical member to operate in motor mode, if necessary, the electrical member operating temporarily in electricity generator mode when the storage means are discharged.

An integrated aircraft galley structure includes a service module having a plurality of galley inserts including at least one oven and at least one refrigeration unit. The service module is formed with a plurality of bays sized to receive the plurality of galley inserts, along with a human machine interface for controlling all of the galley inserts. The service module further includes a plurality of galley insert modules for controlling each galley insert, and an insert power and control unit for each galley insert for controlling power to said insert. The entire system is controlled by a galley power and control unit for controlling each of the insert galley power and control units, and an AC distribution unit for distributing power to the insert power and control units.

A space efficient lavatory module for commercial aircraft includes an aft facing concave wall recess that provides a greater distance from an upper, forward facing portion of a cabin structure, such as an aircraft passenger seat to avoid having a passenger's head impact the aft facing lavatory or enclosure wall in a sudden aircraft deceleration. The aft facing concave wall recess also provides space for mounting of a protective cushion, in order to reduce a passenger's risk of head trauma in a sudden deceleration, as well as other items, such as a video monitor, a bassinet or infant bed, without inhibiting passenger movement.

In conventional aircraft cargo compartments panels or similar flat floor elements are fastened to floor beams or similar supporting elements that are installed in the body of the aircraft. Subsequently functional units such as roller elements, latches or PDUs are mounted and connected to one another by way of appropriate control conductors. It is proposed to fasten the floor elements permanently to the supporting beams so as to form prefabricated floor modules and to install these floor modules in the aircraft.

An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced.

According to one embodiment, a windshield attachment device for coupling a windshield to a body includes a fastener portion, a bolt, and an elastomeric load isolator. The fastener portion has an opening therethrough. The bolt is configured to extend through the opening of the fastener portion and couple the fastener portion to the body. The elastomeric load isolator surrounds at least a portion of the fastener portion and separating the fastener portion from the windshield.

Methods and apparatus are presented for spacecraft operation using non-Eigen axis attitude transitions via control momentum gyroscopes (CMGs) to avoid or mitigate singularities by providing a time-varying attitude command vector including a plurality of time-varying attitude command signals or values representing a plurality of spacecraft states and control trajectories as a guidance command input to an attitude controller of the spacecraft without modifying the spacecraft feedback control law.

A system and method for mitigating an aircraft incident is provided. The invention includes an aircraft panic component coupled to a terminal component. The aircraft panic component facilitates identification of a panic situation and communicates information associated with the panic situation to the terminal component. The aircraft panic component is further operative to at least partially disable a navigation system and/or operational system of an aircraft. The aircraft can then be sent to a safe zone, navigated remotely and/or a course of action for the aircraft can be determined. A safe zone component is adapted to facilitate identification of a course of action for the aircraft based at least in part upon aircraft positional information, aircraft condition information and/or aircraft resource(s). Further, aircraft navigational information and/or aircraft operational information can be sent via an aircraft communication component to a remote system having a remote communication component and a remote analyzing component facilitating transfer of information related to navigational and/or operational system(s) of the aircraft.

A harness is provided comprising a body having a series of electrical conductors embedded therein and substantially running along the length thereof. The body may be part of a structural component such as stringer.

The present invention relates to landing gear (5) having at least one undercarriage (10) comprising a landing gear leg (11) carrying at least one wheel (12). The undercarriage (10) includes a retraction actuator (20) having an electric motor (23), blocking means (30) for blocking the actuator in the retraction position and for enabling the retraction actuator to be positioned in the “landing gear extended” position by gravity, first monitoring means (35) for monitoring the operation of the retraction actuator (20), first control means (65) for controlling the refraction actuator (20), and second control means (75) for controlling the blocking means (30).