Abstract: A retractable landing gear assembly for an aircraft includes a leg mounted to airframe structure for rotation about a pivot axis. A stay assembly is provided for maintaining the landing gear assembly in a deployed, for example down and unlocked, configuration. The stay assembly has a linkage mechanism including a first stay and a second stay movable between a folded state and an unfolded state. Room that would otherwise be occupied within a landing gear bay may be freed up above the landing gear leg when in a stowed configuration by the stay assembly being unfolded but generally aligned with the length of the landing gear leg, with the stay assembly being mostly positioned beneath the leg.

Abstract: A heat shield assembly is disclosed. In various embodiments, the heat shield assembly defines a first circumferential side and a second circumferential side and an inboard end and an outboard end and includes a first layer defining a first surface of the heat shield assembly and having a first tab member disposed proximate the inboard end at the first circumferential side and a second tab member disposed proximate the outboard end at the first circumferential side; and a second layer defining a second surface of the heat shield assembly and having one or more first crimped portions extending along the first circumferential side and configured to engage the first tab member and the second tab member.

Abstract: An anti-tail buffet device leverages existing rotorcraft components to attenuate a tailboom's lateral “ringing” from air buffeting. Anti-buffet masses are tuned to the tailboom's lateral-bending or torsional natural frequency such that when lateral motion occurs, the response at this frequency is cancelled by the anti-buffet system, preventing this vibration from entering into the tailboom structure. Motion stops prevent over-travel. The mass of the tail rotor actuator is soft-mounted, such that its natural frequency is equal to the tailboom's lateral-bending or torsional natural frequency. When lateral loading occurs on the tail rotor disk, the lateral response at this frequency is attenuated by the soft-mounted tail rotor actuator, thereby preventing the vibration in the tailboom structure.

Abstract: A vibration attenuator for a rotor of an aircraft has a track housing adapted for rotation relative to the rotor and configured for rotation at a second angular velocity greater than a first angular velocity of the rotor. A track is located within the track housing and has a reaction surface, a pair of weights being configured for movement within the track and in contact with the reaction surface. A stop assembly has a pair of stops spaced 180 degrees apart, the stops separating the weights from each other, and each weight being allowed to travel within the track between the stops. A motor rotates the track housing relative to the rotor. The weights are free to travel relative to each other between a minimum-force configuration, in which the weights are positioned 180 degrees apart, and a maximum-force configuration, in which both weights are adjacent one of the stops.

Abstract: There is disclosed an aircraft engine assembly including an engine having an engine shaft; an output shaft; a clutch in driving engagement between the engine shaft and the output shaft. The clutch has a first component in driving engagement with the engine shaft and a second component. The clutch is operable between first and second configurations. In the first configuration, the first component is rotatable relative to the second component and the engine shaft is rotatable relative to the output shaft. In the second configuration, the first and second components are engaged with one another and the engine shaft rotates with the output shaft. A mechanical lock is operable between first and second positions. In the first position, the mechanical lock is disengaged from the first component. In the second position, the first and second components are secured for joint rotation one relative to the other.

Abstract: A helicopter uses electric propeller torque arm as power source directly driving main rotor to rotate. The helicopter may be battery powered. The helicopter may be without an engine, a clutch, a reducer, a tail driver, a tail boom, a tail rotor and a fuel supply system. The main design goal is to have the output shaft of the high-energy motor being coaxial with the main rotor shaft or having output shafts of a plurality of motors as close as possible to the main rotor shaft. The centrifugal force of the motor(s) is negligible or minimized. The torque arm assembly includes a plurality of torque arms. Each of the torque arm of the plurality of torque arms includes a propeller and a driving system. In the case of a malfunction, the helicopter's main rotor will spin like a maple leaf and will facilitate the spin autorotation landing.

Abstract: An exemplary rotorcraft includes a power train with an engine coupled to a gearbox, a main rotor blade having a mast coupled to the power train, a control input linkage in communication between a pilot input device and the main rotor blade configured to communicate a control input force from the pilot input device to the main rotor blade, and a counterweight system in connection with the control input linkage and the power train to apply a centrifugal force to the control input linkage.

Abstract: The present invention relates to a device for directly controlling a blade which comprises a stator (1), at least one blade carrier (7) composed of at least one curved magnet (6), the blade carrier (7) being secured to at least one blade (3) and pivotally coupled to the rotor (8) for varying the alpha angle of said blades with the excitation of the stator (1). The stator (1) is a partially spherical stator, the stator core (1) being the intersection of the blade axis (22) and the rotor axis (20), said stator being radially close to the magnets (3) to control the rotation of the blades (3) around the blade axis (22). A magnetic ring (5) holds the blades (3) in a neutral position, the system can be compared to a cyclically controlled mechanical oscillator, the frequency, phase and amplitude of the oscillation being controlled by said stator. Device providing a compact, lightweight and robust solution for controlling the direction of an aircraft.

Abstract: Neutral Axis Duct with Tandem Telescopic Thrust Vectoring Leading and Trailing Edge Propellers for Multi-Mode Spatial Vehicle [NADTVPMSV] is a single monocoque chassis frame for a multi-mode vehicle that can travel in all land, air, over water and under water as a perfect road vehicle, perfect flying machine, perfect speed boat and perfect submarine.

Abstract: A traffic control system, a controller and an associated method are provided to direct a vehicle to slow or, in some instances, stop at a defined spatial location along the roadway. In the context of a controller, the controller includes at least one processor and memory including computer program code with the memory and the computer program code configured to, with the at least one processor, cause the controller to receive information indicative of at least one characteristic of the behavior of the vehicle as the vehicle approaches a defined location. Based on the information, the controller is caused to compare the behavior of the vehicle to a defined criterion and, in response, to cause an unmanned air vehicle (UAV) to maintain a hovering position in which the UAV hovers above the roadway so as to be within the path of travel of the vehicle on the roadway.

Abstract: An apparatus, method and system utilize an unmanned air vehicle (UAV) in order to support the definition and use of routes by bicyclists, pedestrians or scooters. With respect to defining a bicycle route a map database is accessed that represents roads segments in a geographic area. The map database contains map data that indicates attributes of the road segments. The bicycle route is then defined from an origin to a destination based upon the map data indicative of attributes of the road segments. In this regard, the bicycle route is defined to include one or more road segments that allow bicycle traffic unaccompanied by a UAV and one or more road segments for which bicycle traffic is unauthorized unless accompanied by a UAV. The bicycle route is subsequently caused to be provided to the bicyclist or a device accessible to the bicyclist.

Abstract: A computer-implemented method includes generating, by a computer device, a plurality of clusters of unmanned aerial vehicles (UAVs) from a plurality of UAVs having different UAV characteristics, the clusters being generated based on the UAV characteristics of each of the UAVs; determining, by the computer device, task characteristics for a first task; selecting, by the computer device, one of the clusters based on the task characteristics of the first task; assigning to the first task, by the computer device, a first UAV of the plurality of UAVs from the selected cluster; receiving, by the computer device, task feedback regarding an attempt by the first UAV to complete the first task; and reassigning, by the computer device, and based on the task feedback, the first UAV to a determined one of the plurality of clusters.

Abstract: Systems and methods for transferring control of drones from one computing device to another during flight are disclosed. An example method may include accepting, by a drone control module of a computing device, a destination associated with a user. The method may further include establishing, by the drone control module, a channel of communication with a user device of the user. Thereafter, the drone control module may launch the drone from a first location. The method may further include transmitting, by the drone control module, control data for the drone to the user device via the channel of communication. The method may continue with transferring, by the drone control module, an operational control of the drone to the user device.

Abstract: A method for controlling an unmanned vehicle includes sensing a trigger event for updating a set of parameters of a remote neural network trained for a respective vehicle context of the unmanned vehicle, receiving from a remote server a set of updated parameters of the remote neural network that at least includes updated connection weights of the remote neural network, and transmitting the updated connection weights to the unmanned vehicle for the unmanned vehicle to operate according to a vehicle-based neural network applying the updated connection weights.

Abstract: A method of fire-fighting is provided based on unmanned aerial vehicles “UAV(s)” launched from transporter aircrafts to deliver water or fire-retardants or any other fire-fighting materials to a location selected by the fire-fighting personnel. A capability of putting-off high intensity forest fires is provided that stems from the precision and the quantity of material that can be delivered per unit surface per unit time. After releasing the fire-fighting material(s), the UAV reaches a safe altitude from which it flies on autopilot to intercept and then proceed on a pre-programmed route to land per pre-programmed instructions on an airfield from which fire-fighting transporter(s) operate, allowing a high efficiency along the line, from loading the transporter airplanes to maximizing the quantity of material that reach the target, to minimizing the remote-pilot time and up to the recovery system that minimizes the recovery cost and it maximizes UAVs' utilization by a quick turnaround.

Abstract: A discharge valve assembly for opening and closing the discharge opening of a collapsible, aerial fire-fighting bucket, the discharge valve assembly including an upper member and a lower member, wherein: a) the upper member is a disc-shaped closure with a peripheral seal-receiving channel and an annular seal seated in the channel; and b) the lower member is a bucket mounting assembly with a mounting frame and a central shaft, the mounting frame including a central hub and radially extending legs for mounting the central hub to the discharge opening of the bucket, the central shaft extending upwardly from the central hub; and wherein the upper member is mounted on the central shaft of the lower member for movement along the central shaft from a closed position, where the annular seal is in sealing engagement with a sealing rim of the discharge opening, to an open position allowing filling and emptying of the fire-fighting bucket through the discharge opening.

Abstract: Systems and methods are disclosed for package delivery using unmanned aerial vehicles. Example methods may include positioning a first component at a first elevation, and operatively connecting the first component to a winch; positioning a second component at a second elevation higher than the first elevation; and configuring cable of a lifting component to: operatively connect to the first component and the second component, connect to and disconnect from a vehicle, and lift the vehicle from the first component towards the second component using the winch.

Abstract: The present invention provides an unmanned aerial vehicle with non-lethal neuromuscular incapacitation system comprising a body, a plurality of rotary assemblies secured to the body and configured to provide lift, a control system disposed within the body, and a telescoping stinger assembly mounted on the body. The telescoping stinger assembly comprises an elongated projectile having a barb at a first end thereof, a wire having a first end attached to a second end of the elongated projectile, a high voltage pulse power supply attached to a second end of the wire, and firing mechanism for launching the projectile from the telescoping stinger assembly toward a target. A protective cage may be attached to and surround the body of the UAV.

Abstract: A projectile module is attached to a gun component which operates as a system to launch a projectile at a flying device. The gun component is configured to be removably and electro-mechanically attached to a flying vehicle. A cylindrical gas valve is part of the gun component and has a safety component configured on an exterior surface of the cylindrical gas valve to enable the gun component only to attach to the flying vehicle when the projectile module is locked into position. A splitter component configured on the gun component adjacent to the cylindrical gas valve and has an output opening for gas flow. The projectile module is removable and includes weights attached to a projectile, wherein the weights are positioned in channels on the projectile module. The projectile is fired when gas flow is initiated from a reservoir the cylindrical gas valve and splitter component to the channels containing the weights.

Abstract: A mounting system configured for coupling a device to a vehicle and providing for movement and remote operation of the device includes a first member for removably coupling the device to the mounting system, a second member rotatably coupled to the first member, a rotational actuator configured to rotate the first member relative to the second member about a first axis, a linear actuator configured to move the first and second members together, a device actuator configured to operate the device, and a deployment apparatus configured to move the device from a stored position to a deployed position.

Abstract: An aircraft that includes a body that defines a cabin interior, front and back rows of seats positioned in the passenger zone, a forward door that is pivotable between a closed position and an open position, and an aft door that is pivotable between a closed position and an open position. The cabin interior includes a pilot zone, a passenger zone positioned aft of the pilot zone, and a cargo zone positioned aft of the passenger zone. The pilot zone and the front row of seats are accessible and the back row and cargo zone are inaccessible from an exterior of the body when the aft door is in the closed position and the forward door is in the open position. The back row and cargo zone are accessible and the pilot zone and the front row of seats are inaccessible from the exterior of the body when the aft door is in the open position and the forward door is in the closed position.

Abstract: A system for providing a passenger interface for a passenger in a seat including at least one sensor adapted to generate a signal representative of the position, the configuration, and/or the direction of movement of hand of the passenger; a controller, and a projector for projecting a passenger interface, placement of which is determined based at least on the signal. A method includes receiving a first signal indicative of a position and/or an arm of the passenger; projecting, by a projector, a passenger interface onto a predetermined surface, the passenger interface location on the predetermined surface being based on the first signal, receiving a second signal indicative of the position, configuration, and/or direction of movement of the passenger's hand of with respect to the passenger interface; and adjusting at least one of a passenger controllable feature, and projection of at least one media display by a second projector.

Abstract: A panelling part for a cabin of a means of transportation is proposed, which includes at least one display unit and at least one control unit, which are produced by printing and equipping at least one film, which is applied to a panelling element. The control unit can communicate wirelessly with an external electronics unit, so that the panelling part only requires a power terminal to implement electronic functions. Functions can be retrofitted easily by replacing the at least one film.

Abstract: A multi-panel privacy screen assembly adapted to be deployed between laterally-adjacent passenger seats. The assembly includes an overhead beam having a plurality of tracks, a plurality of hanging panels, a plurality of coupling members suspending each of the plurality of hanging panels from the overhead beam, each coupling member coupled to one of the plurality of hanging panels, to one of a plurality of driven cables, and having rollers rollable along at least one of the plurality of tracks, and a drive mechanism including an intermittent gear assembly operable for driving the plurality of driven cables to move the plurality of hanging panels along at least one of the plurality of tracks according to predetermined deployment sequence.

Abstract: A modular faucet system for an aircraft comprising a faucet outlet, a flow valve, and an actuator. The faucet outlet is configured to be installed on the aircraft. The flow valve is configured to be installed on the aircraft separately from the faucet outlet, to be connected by a first water line to a water supply comprising a water tank on the aircraft, and to be connected by a second water line to the faucet outlet. The actuator is configured to be installed on the aircraft separately from the faucet outlet and the flow valve. The actuator comprises a touchless sensor that is configured to detect a user of the modular faucet system. The actuator is configured to generate a control signal to open the flow valve to provide water from the water supply to the faucet outlet in response to detection of the user by the touchless sensor.

Abstract: An aircraft including a lavatory monument. The lavatory monument includes an outboard wall and a shell wall removably connected to the outboard wall, both walls extending radially inwardly relative to a fuselage of the aircraft. The lavatory monument also includes a floor panel connected to and between the outboard wall and the shell wall. The lavatory monument also includes a toilet connected to the floor panel. The lavatory monument also includes a plurality of lavatory fixtures individually removably attached to at least one of: the outboard wall, the shell wall, the floor panel, or the toilet. Each of the plurality of lavatory fixtures is individually removable. Common interface points on each of the plurality of lavatory fixtures are unchangeable with respect to the lavatory monument.

Abstract: An aircraft comprises a fuselage and an aft wall of a lavatory monument within the fuselage and extending radially inwardly relative to the fuselage. The aft wall is removably connected to an outboard wall, a ceiling, and a floor of the lavatory monument.

Abstract: An electrical connecting system for a seat, in particular a passenger seat in a means of transportation, including an elongated carrier foil that is provided at least in regions with conductor tracks, the carrier foil having a first section so as to be arranged on a seat frame, a second section so as to be arranged on a backrest that may pivot and a transition section that lies between said first section and second section, wherein the transition section is embodied as V-shaped. As a consequence, an electrical connection may be achieved between an electronic unit that is arranged on a passenger seat and components that are arranged on the passenger seat.

Abstract: An aircraft that includes a body that defines a cabin interior and a longitudinal axis, and a front row positioned in the cabin interior. The front row includes a first front seat and a second front seat. The first and second front seats are angled away from one another. The first front seat is angled outwardly such that it forms a first acute angle with the longitudinal axis and the second front seat is angled outwardly such that it forms a second acute angle with the longitudinal axis. The first and second acute angles are approximately the same.

Abstract: A dynamic electro-mechanical ottoman may include a rail assembly with one or more actuatable tracks coupled to one or more rails. The dynamic electro-mechanical ottoman may include a cushion assembly translatable via the one or more actuatable tracks between a first translation position and a second translation position. The cushion assembly may include one or more cross plates coupled to a pivot shaft and the one or more actuatable tracks, and a cushion sub-assembly. The cushion sub-assembly may include one or more support plates coupled to a cushion and the pivot shaft, and may be rotatable about an axis through the pivot shaft between a first rotation position and a second rotation position. A top surface of the cushion may at least partially face an aircraft seat when the cushion sub-assembly is in the second rotation position.

Abstract: Described are passenger support assemblies for a passenger seat, including an expandable inner frame that attaches the passenger support assembly with a seat frame and an expansion mechanism that allows the expandable inner frame to change in width, and an outer frame that includes two side frame elements connected with the expandable inner frame and extending beyond the expandable inner frame, the outer frame configured to change in width in response to a change in width of the expandable inner frame. A diaphragm can held in tension by the two side frame elements of the outer frame to define a seating surface.

Abstract: A safety seat for an occupant includes a front shell secured to a bulkhead. The front shell has an outer edge and an inner edge. The inner edge defines an opening. The safety seat includes a seat base having a first side and a second side opposite the first side. The seat base has a first position and a second position. In the first position, the first side is flush with the inner edge and in the second position; the second side supports the occupant.

Abstract: An aircraft refrigeration system comprises an ambient air line, through which ambient air flows and which is connected to conduct ambient air to an aircraft, an ambient air compressor, arranged in the ambient air line, for compressing the ambient air in the ambient air line, a cabin exhaust air turbine, connected to a cabin exhaust air line and coupled to the ambient air compressor in the ambient air line and configured to expand cabin exhaust air flowing through the cabin exhaust air line and to drive the ambient air compressor, a transmission, configured to couple the cabin exhaust air turbine to the ambient air compressor and to set a speed of the ambient air compressor, and a motor, coupled to the transmission and configured to drive the ambient air compressor.

Abstract: We describe an ice protection system used for removing ice and/or other accretions from a structure. An actuator, coupled to a structure, is driven to generate vibrations in the structure. A controller drives the actuator using a signal that comprises a frequency chirp over a first period of time, and the controller controls the frequency chirp and the first period such that vibrations generated in the structure by the actuator propagate through the structure to coincide at a desired area of the structure remote from the actuator to remove ice and/or other accretions from the desired area of the structure.

Abstract: Systems and methods to facilitate a steep final approach phase of flight of an aircraft are disclosed. In one embodiment, a method for operating an aircraft during a steep approach phase of flight of the aircraft comprises operating an engine of the aircraft at an idle speed associated with the steep approach type that is lower than an idle speed associated with a non-steep approach type capable of being executed by the aircraft. The method also comprises operating an ice protection system of the aircraft during the steep approach phase of flight of the aircraft.

Abstract: A chute-deployment-seat-release system for an ejection seat may be configured to deploy a parachute from the ejection seat and release an occupant restraint of the ejection seat. The chute-deployment-seat-release system may comprise an auto-deployment assembly, including a first power supply, and a manual deployment assembly, including a second power supply and a handle. The first power supply may be configured to activate in response to expulsion of the ejection seat from an aircraft. The second power supply may be configured to activate in response to an actuation of the handle.

Abstract: An example hybrid propulsion system is described that includes a plurality of propulsors, a first drive shaft, a second drive shaft, a gas turbine engine, a motor-generator, and a clutch. The gas turbine engine includes a first turbine stage operatively coupled to the first drive shaft and a second turbine stage operatively coupled to the second drive shaft. The motor-generator is operatively coupled to the second drive shaft and is configured to generate electrical power to drive at least one propulsor of the plurality of propulsors and selectively drive the second shaft. The clutch is configured to operatively couple the second drive shaft to the first drive shaft.

Abstract: A surface liner member includes an external wall which is provided with multiple holes, a spacer structure, and tubes which are respectively associated with the holes in the external wall. The surface liner member is intended to be applied to a base surface in order to reduce, by acoustic absorption, an acoustic wave reflected on this base surface. The acoustic absorption efficiency is improved, particularly for frequencies below 500 Hz, by varying the shape of the holes in the external wall such that the ratio of the hole perimeter to the hole area varies. Such a surface liner member may be adapted to form a surface portion of an aircraft engine nacelle, or of a leading edge of an aircraft wing.

Abstract: Herein provided are methods and systems for a method for controlling autothrottle of an engine. A digital power request is obtained from an autothrottle controller, the digital power request based on an autothrottle input to the autothrottle controller. A manual input mode for the engine is terminated, the manual input mode based on a second power request obtained from a manual input associated with the engine. An autothrottle mode for the engine is engaged to control the engine based on the digital power request.

Abstract: An inlet for a nacelle and an AM system and method for manufacturing the inlet having fewer discontinuities on the exterior surface to achieve a smoother flow over the inlet. The inlet includes an annular lip-cowl and a supporting framework. The AM system includes a support structure providing a form, and AM heads for depositing materials onto the form, with the materials subsequently hardening to become the lip-cowl. The support structure may have an upright or inverted orientation, is rotatable, and may be tiltable. Components may protrude from the form to be incorporated into the lip-cowl. The AM heads are mounted on moveable arms and are computer-controlled to deposit the material onto the form, and may be moveable along a radial axis to accommodate an asymmetrical portion of the form. The AM system may further include one or more machining heads for subtractively machining the deposited material.

Abstract: A turboprop engine system for an aircraft includes an engine, a propeller, and a gear train coupled to and configured to provide power from the engine to the propeller at a predetermined gear reduction. The engine system also includes a gearbox that houses at least part of the gear train. The gearbox includes a gearbox flow structure and an inlet flow structure that is removably attached to the gearbox. The inlet flow structure and the gearbox flow structure cooperate to define an inlet flow passage to the engine. The inlet flow passage has an upstream end and a downstream end that are cooperatively defined by the inlet flow structure and the gearbox flow structure. The upstream end is configured to receive an airstream that is directed along the inlet flow passage to the downstream end and toward the engine.

Abstract: A method of cooling an auxiliary power unit (APU) of an aircraft having prime mover engines fed with aircraft fuel, comprises: using the aircraft fuel as a heat sink to absorb the heat generated by the APU.

Abstract: A vehicle comprising: a fuel store (104) configured to store a fuel, the fuel comprising a hydrocarbon; a fuel reformer (108) coupled to the fuel store (104) and configured to: receive an input comprising the hydrocarbon; and process the received input to produce an output comprising hydrogen; and a fuel cell (112) coupled to the fuel reformer (108) and configured to: receive the hydrogen from the fuel reformer (108); and produce, using the received hydrogen, electricity for use on the vehicle.

Abstract: A method for integrating an application into a flight deck includes receiving, by the flight deck, an identification of the application for integrating into the flight deck, wherein the application is running on a portable electronic device (PED) separate from the flight deck. The method also includes transmitting, by the flight deck, the identification of the application to the PED. The method additionally includes locating an application window corresponding to the application on a display of the PED and reading pixel data corresponding to the application window on the display of the PED. The method further includes transmitting the pixel data from the PED to the flight deck and integrating the application into the flight deck using the pixel data.

Abstract: A gimbal rotation method includes controlling a driving assembly based on an angle command indicating a target angle to drive a gimbal to rotate to the target angle in a first time period having a pre-set length, determining whether a new angle command is received within the first time period, and, if not, estimating an estimated target angle based on gimbal rotation angles indicated by a plurality of previously-received angle commands and controlling the driving assembly to drive the gimbal to rotate from the target angle to the estimated target angle in a second time period having the pre-set length.

Abstract: A control apparatus, a camera apparatus, a flying object, a control method and a program are provided. The control apparatus is configured to control a driving of a focus lens included in a camera apparatus. The control apparatus includes a memory, storing a program; and a processor, configured to execute the program to set a drive range of the focus lens based on a height of the camera apparatus away from a reference position, and control the driving of the focus lens in the drive range.

Abstract: A ground handling facility (1) for passenger-transporting aircraft (100), in particular vertical takeoff and landing multicopters, including: at least one first platform (2) which is designed as a landing platform (2) for a passenger-transporting aircraft (100), wherein a) the at least one first platform is simultaneously designed as a takeoff platform for a passenger-transporting aircraft (100), or b) wherein a second platform (3) is provided which is designed as a takeoff platform (3) for a passenger-transporting aircraft (100); at least one region (4) which is designed as weather protection for the passengers and the aircraft (100), in particular by provision of a canopy; and at least one conveying device (5.1; 5.2; 5.3) for the aircraft (100) that is designed to move the aircraft (100) from the landing platform (2) through the region (4) to the takeoff platform (3), in which region there is provided at least one station (6.1-6.4) which is configured for a predetermined interaction with the aircraft (100).

Abstract: A method and system provide the ability to autonomously operate an unmanned aerial system (UAS) over long durations of time. The UAS vehicle autonomously takes off from a take-off landing-charging station and autonomously executes a mission. The mission includes data acquisition instructions in a defined observation area. Upon mission completion, the UAS autonomously travels to a target landing-charging station and performs an autonomous precision landing on the target landing-charging station. The UAS autonomously re-charges via the target landing-charging station. Once re-charged, the UAS is ready to execute a next sortie. When landed, the UAS autonomously transmits mission data to the landing-charging station for in situ or cloud-based data processing.

Abstract: A method for aligning and joining a first structure to a second structure in an aircraft is provided. A spacer system having a shape memory alloy is positioned in a gap between the first structure and the second structure. The shape memory alloy is initially in a cooled state. A temperature of the shape memory alloy is increased such that the shape memory alloy changes from the cooled shape to a heated shape to fill the gap and apply a load to hold the first structure in place relative to the second structure. Additional processes may then be performed to join the first structure to the second structure.

Abstract: A method for monitoring service load on airborne vehicle components is provided. The method includes: extracting, from an airborne vehicle after completing a mission, the start and end time of each of a plurality of flight regimes and flight parameters of interest for each of the plurality of flight regimes; generating, for each regime, a time domain spectrum of the stress spectrum for each regime/events/maneuvers actually encountered in the mission from the extracted flight parameters; determining flight conditions experienced during the planned mission; determining a stress per G spectrum corresponding to the experienced flight conditions, wherein the stress per G spectrum identifies an amount of stress experienced by the airborne vehicle at fatigue critical locations per G of air load experienced at the fatigue critical locations; and determining an air load stress spectrum for the airborne vehicle by multiplying the time domain spectrum data with corresponding stress per G spectrum data.