Abstract: A watercraft includes a pair of inflatable pontoons. Releasably affixed atop each of the pontoons and aligned therewith are inner and outer lengthwise frame members. Forward and aft beamwise frame members are affixed to the inner and outer lengthwise frame members. Primary arch members are affixed to the forward and aft beamwise frame members. A main fabric panel is stretched between the pair of primary arch frame members, the forward beamwise frame member, and the aft beamwise frame member. A motor mount is affixed centrally to the aft beamwise frame member, the motor mount being configured to removably support a motor assembly. Aft panel side members are rotatably-lockably affixed to the aft beamwise frame member and joined by an aft panel top member. An aft fabric panel is stretched between the aft panel side members, the aft beamwise frame member, and the aft panel top member.

Abstract: In a three row, roller bearing assembly coupling a vessel to a turret, the bearing assembly having a support row assembly disposed between an inner ring connected to the turret and outer rings connected to the vessel, a method and arrangement for in situ remediation of a damaged support row assembly. Couplers are secured to existing inner ring stud bolts. A continuous bearing ring below the couplers is assembled and a support bearing arrangement is installed between the couplers and the bearing ring. Reaction plates are mounted to the vessel. Each reaction plate has a jack screw which is positioned directly below the bearing ring. The jack screws are turned to elevate the bearing ring and form a flat surface for support of the support bearing arrangement. The turret axial load is transferred from the damaged support row assembly to the support bearing arrangement.

Abstract: A turret assembly for a vessel comprises a moonpool defined in the vessel and a turret structure rotatably mounted in said moonpool. The turret structure comprises a turret table which by means of a main bearing is rotatably mounted in said moonpool and a hollow turret shaft defined by a surrounding shaft wall, which turret shaft has an upper shaft end connected to the turret table, a substantially cylindrical shaft part that extends downwardly from the turret table and a lower shaft end provided with means intended for cooperation with a lower bearing. The shaft wall of the upper shaft end comprises a widened part surrounding the cylindrical shaft part and defines a circumferential crest, wherein the shaft wall of the upper shaft end, starting from said circumferential crest, extends downwardly towards a position where the upper shaft end is connected to the turret table.

Abstract: A lifeboat launch control system. The lifeboat launch control system has a wheel trunk that runs along the side of a ship. An axle box is vertically movable in the wheel trunk. The axle box has a pair of wheels on opposing sides of a bar. A shaft is removably inserted into the bar. The shaft is removable from the bar by a handle. When the shaft is removed from the bar, the lifeboat is released from the ship.

Abstract: The present invention relates to a method of providing an adjustable arm davit apparatus with height adjustable feature including, a base member, a shock absorber, a boom member, an adjustable arm, a winch assembly and a cylinder assembly. The boom member comprises a first member hingedly mounted on the base member and a second member mounted on the first member to adjust a height of the apparatus via the cylinder assembly disposed at the boom member. The adjustable arm is engaged to frontal ends of the boom member. The winch assembly positioned on the boom member for supplying a cable via a plurality of pulleys to attach the target object. The winch assembly is actuated to raise or lower the target object from the target location.

Abstract: The invention relates to a method for constructing habitable installations for floating structures, comprising the following steps: lowering a first adapted standard container (3) through at least one vertical prismatic cavity (25) of a carrying structure (2) until it is supported on support brackets (4) of the floor below; securing the first container (3) to said support brackets (4) of the floor below; and, for each subsequent floor, securing a number of subsequent support brackets (4) to the carrying structure (2) on each container (3) already in position; lowering a subsequent container (3) until it is supported on said subsequent support brackets (4); and securing said subsequent container (3) to subsequent support brackets (4) on which it is resting. The invention also includes a habitable installation (1) constructed according to said method, and a container (3) adapted for carrying out said method.

Abstract: A marine seat assembly is used in connection with a boat. The marine seat assembly comprises a hollow tubular metal frame with an upright portion and a seat portion. A plurality of polymer frame panels is disposed on the frame, using fasteners and adhesive to form a composite structure. A pair of armrests mounted on the frame pivot upward when not used. A bolster is pivotally mounted on bolster hinges for pivotal movement from in front of the seat, to above the seat. The bolster hinges are mounted sufficiently inboard of the bolster sides so as to preclude insertion of fingers in the bolster hinges, thereby avoiding injury.

Abstract: The present invention relates to a longitudinal vessel for production and/or storage of hydrocarbons. The vessel comprises a hull which extends along a longitudinal axis between a bow and a stern of the vessel. The hull is provided with a longitudinal well for a multiple riser arrangement. The longitudinal well is located on or adjacent to a centerline along the longitudinal axis of the hull and extends vertically through the hull.

Abstract: A personal riding board for aquatic sporting activities. The board includes multiple layers. At least two of the layers include a reinforcement member. The reinforcement members function together similar to a leaf spring to provide the board enhanced flexibility where needed while minimising the risk of breakage.

Abstract: Embodiments of the present disclosure relate generally to an improved surfboard or paddleboard leash or other cord system that raises the leash line away from the board or surface in order to prevent it from interfering with the user's freedom of movement.

Abstract: A board-type watercraft is adapted for selective disassembly into a plurality of separate sections for ease of transport and storage. Preferably, a selection of differently configured nose and tail sections can be releasably connected to a universal middle section to create a wide variety of distinctive board styles. With the watercraft in its assembled state, adjacent sections are releasably secured together using compressive-type fastening elements, such as spring-biased latch mechanisms. Pairs of fastening elements are preferably arranged on the top and bottom surfaces of the board in substantial vertical alignment to limit torque between sections and thereby ensure adequate stiffness through each joint. In its disassembled state, the sections can be stacked into a highly compact configuration suitable for packaging within a container that is compliant with maximum size standards for conventional ground courier services.

Abstract: A wake generating apparatus may include a frame. The frame may support at least one pair of fins. The frame may include a mounting apparatus. The mounting apparatus may allow for the frame to removably mount to a transom of a watercraft. The frame may support the fins such that the fins extend approximately below and behind a stern of the watercraft. The fins may be positioned to generate a wake when the watercraft is cruising in the water.

Abstract: The present disclosure provides a carrying device and an operation method thereof. The carrying device includes: a floating platform; and at least one flexible unit provided on a bottom side of the floating plate and having a cavity formed therein. The flexible unit is deformed under a stress to reduce the friction force between the flexible unit and the solid in the water, which allows the carrying device to break free from the solid without external help.

Abstract: The invention provides an object (10) that during use is at least partly submerged in water, the object (10) further comprising an anti-biofouling system (200) comprising an UV emitting element (210), wherein the UV emitting element (210) is configured to irradiate with UV radiation (221) during an irradiation stage one or more of (i) a part (111) of an external surface (11) of said object (10) and (ii) water adjacent to said part (111) of said external surface (11), wherein the light source (220) is at least controllable between a first UV radiation level and a second UV radiation level, wherein the first UV radiation level is larger than the second UV radiation level, wherein the object (10) is selected from the group consisting of a vessel (1) and an infrastructural object (15), wherein the object (10) further comprises a control system (300) configured to control said UV radiation (221) as function of input information comprising information of one or more of (i) a location of the object (10), (ii) moveme

Abstract: It is an object of the present invention to provide a means of constructing an Autonomous fully-Submersible Offshore Marine Platform (ASOMP) of considerable warfighting or commercial capability which is mobile and can autonomously transport to a hazardous operating area in a low-observable reduced vulnerability manner, fully submerge to avoid the military or environmental threat hazard, hibernate until needed, perform fully submerged mobility and mission operations, surface and provide Barge and SWATH surface ship mobility and mission operations, resubmerge if the hazardous threat appears and relocate to a new operating area. Another object of the present invention is to provide a fully autonomous and submersible low-cost “lily-pad” that surfaces when called and provides a main deck platform at appropriate freeboard and seakeeping motions to function as a refueling landing zone and pier to extend the range of aircraft and marine vehicles operating in a high-threat environment.

Abstract: The present invention is to provide a launcher for an underwater vehicle by which thrust force of a mover arranged movably in a water conducting tube can efficiently be obtained. The mover forms a plurality of magnetic circuits in which magnetic flux generated by a plurality of permanent magnets flows, and the plurality of magnetic circuits includes a first magnetic circuit in which the magnetic flux flows through one of a pair of circumferential magnets, a second magnetic circuit in which the magnetic flux flows through one of a pair of axial magnets, the second magnetic circuit being formed in parallel to the first magnetic circuit, and a third magnetic circuit in which the magnetic flux flows through a radial magnet, the third magnetic circuit being formed in parallel to the first magnetic circuit and the second magnetic circuit, respectively.

Abstract: An azimuth thruster system includes a pod configured to rotate relative the hull of the ship about an azimuthal axis of the pod, a propeller shaft extending from the pod and being configured to rotate relative to the pod about a central axis of the propeller shaft, an outer shaft disposed at least partially in the pod and configured to be driven by a first primary prime mover, an inner shaft disposed at least partially within the outer shaft and configured to be driven by a second primary prime mover, and a pod gear unit disposed within the pod and coupled to the outer shaft, the inner shaft, and the propeller shaft. The outer and inner shafts are configured to rotate at least one of the pod and the propeller shaft based on directions and magnitudes of the torques generated by the first and second primary prime movers.

Abstract: An outboard motor includes an upper case, a lower case including an oil reservoir chamber, an oil flow passage, and an oil flow passage shutoff valve. When the lower case is detached from the upper case, the oil flow passage is separated into an upper oil flow passage in the upper case and a lower oil flow passage in the lower case and connected to the oil reservoir chamber. The oil flow passage shutoff valve opens the lower oil flow passage in a state in which the lower case has been attached to the upper case. The oil flow passage shutoff valve closes the lower oil flow passage in a state in which the lower case has been detached from the upper case.

Abstract: There is provided a mounting assembly for a marine vessel having a pair of stern-mounted propulsion units. The assembly includes a pair of angle-setting members which forwardly angle the propulsion units towards a bow of the marine vessel when each propulsion unit is at the center of its total steering range. Each propulsion unit has a line of action of its propulsion force. The lines of action of the propulsion units intersect each other between a center of rotation of the marine vessel and a stern of the marine vessel when the propulsion units are steered forwardly towards each other.

Abstract: A marine propulsion unit includes a propeller that rotates around a rotation axis of a propeller shaft, a case in which the propeller shaft is disposed, and a skeg that extends downward from the case. The skeg includes a reinforcer with a mechanical strength greater than that of a base material of the skeg.

Abstract: A clamp assembly for connecting a rudder to an aquatic device having a body with a first end, a second end, a top and a bottom. A slot, having more than one section extends into the body from the first end. A clamp having a screw connected to a pivot pin disposed within a clamp head is removably connected to the top of the body for selectively applying a clamping force within the slot.

Abstract: An energy dispersion plug for use in an unmanned aerial vehicle (UAV) includes a blunt head section, a wedge section, and a rim section. The blunt head section has an outer side for receiving an impact force and an inner side opposite the outer side. The wedge section has a base end and a distal end opposite the base end. The wedge section extends at the base end from the inner side of the blunt head section towards the distal end and the distal end has a smaller cross-sectional area than the base end. The wedge section is shaped and sized to fit into an open end of a hollow structural member of the UAV and to transfer impact energy incident upon the blunt head section into the hollow structural member to shatter the hollow structural member into fragments.

Abstract: A door assembly includes a door panel having a first pair of bearings secured to a top portion of the door panel and a second pair of bearings secured to a bottom portion of the door panel. A wall having an opening which extends through the wall wherein a first rail track extends along a first end portion of the opening having a first opening and a second rail track extends along a second end portion of the opening having a second opening. At least one hinge blocking assembly includes a first bracket connected to the wall and a second bracket wherein the second bracket is rotatably mounted to the first bracket about a fixed axis of rotation defined by the at least one hinge blocking assembly wherein with the second bracket in a first position the second bracket extends away from the first bracket.

Abstract: A floor assembly for an aircraft comprising a multiplicity of supports configured to be fastened in pairs to opposite sides of a frame of the aircraft, and a monolithic self-supporting floor element comprising at least two longitudinal members, a floor plate arranged on the longitudinal members and a respective connecting element arranged at each end of each of the longitudinal members. The floor element can be fastened to the frame by fastening of each connecting element to a corresponding support, and the floor plate can extend in the direction of the longitudinal members at least between two supports fastened in pairs. Furthermore, an aircraft region comprises such a floor assembly, an aircraft comprises such an aircraft region.

Abstract: An aircraft operable between a deployed position and a stowed position is disclosed. The aircraft includes a fuselage, a pair of wing segments, and a translation and rotation mechanism for attaching the wing segments to the fuselage. The mechanism includes an upper assembly having an outer shaft and an inner shaft. A first wing segment is attached to the outer shaft and a second wing segment is attached to the inner shaft. The outer shaft translates downward with respect to the inner shaft. Thereafter, the outer and inner shafts rotate in opposite directions in order to rotate the wing segments on top of one another, parallel to a long axis of the fuselage, and into the stowed position. The operation of the outer and inner shafts is reversed in order to return the wing segments to the deployed position.

Abstract: The invention relates to a device and to a method for the open and closed control of n actuators An, n=1, 2, . . . , N, where N?1, which drive aerodynamic control surfaces of an aircraft.

Abstract: Methods and apparatus for controlling landing gear shrink are described. A controller is to determine an on-ground status of a left main landing gear. The controller is also to determine an on-ground status of a right main landing gear. The controller is also to generate a control signal to shrink the left main landing gear and the right main landing gear based on the on-ground status of the left main landing gear and the on-ground status of the right main landing gear.

Abstract: A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to apply torque to a pinion so the pinion rotates and moved from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to a rotating wheel of an aircraft landing gear. After the initial contact time the pinion is moved further to a meshing position where the pinion meshes with the driven gear. A centre-to-centre distance between the pinion and the driven gear reduces as the pinion moves to the contact position and to the meshing position. The driven gear contacts the pinion in a series of impacts as the pinion moves from the contact position to the meshing position, each impact induces a spike in electromotive force or angular velocity at the motor.

Abstract: Methods of moving an aircraft undercarriage that is movable between a retracted position and a deployed position generally include: using a rotary electromechanical type drive actuator coupled to a portion of the aircraft undercarriage to raise it from the deployed position to the retracted position; disengaging the drive actuator during a descent of the undercarriage from the retracted position to the deployed position and using a hydraulic linear shock absorber coupled to a portion of the undercarriage to regulate the rate of descent and to absorb shock on arrival of the undercarriage in the deployed position; and neutralizing the shock absorber while raising the undercarriage.

Abstract: A center biased actuator having an outer cylinder, a slave cylinder linearly transposed within the outer cylinder, a rod assembly with a piston linearly transposed within the slave cylinder and a rod extending from the outer cylinder, one or more first dynamic seals arranged to act on a sidewall of the rod to inhibit hydraulic fluid leaking from the outer cylinder, one or more second dynamic seals arranged to act on a sidewall of the slave cylinder or an inner surface of the outer cylinder to inhibit hydraulic fluid leaking from the outer cylinder, and a gas chamber comprising a sealed expandable chamber containing gas. The expandable chamber is arranged to act on hydraulic fluid within the center biased actuator to bias the center biased actuator to assume an intermediate condition which lies between a compressed condition and an extended condition.

Abstract: A bearing assembly is for movably coupling first and second members, one being movable relative to the other. A plain bearing section includes an inner ring connectable with the first member and an outer convex bearing surface. An outer ring is disposed about the inner ring and has an inner concave bearing surface disposed against the inner ring bearing surface. The two bearing surfaces are formed such that one bearing surfaces slides against the other when the movable member displaces about a first axis and two bearing surfaces engage to prevent displacement between the two rings when the movable member displaces about a second axis. An elastomeric bearing section is disposed about the plain bearing section, is connected with the second member and formed such that at least a portion of the elastomeric bearing section flexes when the movable member angularly displaces about the second axis.

Abstract: A tiltrotor assembly has a central hub with a plurality of rotor blades extending therefrom and is configured to rotate about a mast axis to generate lift in a hover position. The central hub is configured to rotate about a tilt axis between the hover position and a forward-flight position such that rotation about the mast axis generates forward thrust. The central hub is surrounded by a segmented duct that includes a thin rotatable inner ring and a wide fixed outer ring. The inner ring is configured to rotate with the central hub about the tilt axis leaving the wide outer ring in a generally horizontal position.

Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons coupled therebetween. The airframe has a longitudinal axis and a lateral axis in hover. A two-dimensional distributed thrust array is coupled to the airframe. The thrust array includes a plurality of propulsion assemblies each operable for variable speed and omnidirectional thrust vectoring. A flight control system is operable to independently control the speed and thrust vector of each of the propulsion assemblies such that in an inclined flight attitude with at least one of the longitudinal axis and the lateral axis extending out of a horizontal plane, the flight control system is operable to maintain hover stability responsive to controlling the speed and the thrust vector of the propulsion assemblies.

Abstract: A quad tiltrotor aircraft has a longitudinally extending fuselage with forward and aft stations. A forward wing having first and second outboard ends extends laterally from the forward station. An aft wing having first and second outboard ends extends laterally from the aft station. First and second forward rotors are respectively coupled proximate the first and second outboard ends of the forward wing and are tiltable relative to the forward wing between vertical lift and forward thrust orientations. First and second aft rotors are respectively coupled proximate the first and second outboard ends of the aft wing and are tiltable relative to the aft wing between vertical lift and forward thrust orientations. The forward rotors are higher disk-loading rotors than the aft rotors. The aft rotors are foldable in the forward flight mode to provide extended range for the quad tiltrotor aircraft.

Abstract: To eliminate stability issues in forward flight due to oncoming flow interfering with the flows produced inside the rotor, rotor shielding or enclosure are used giving it the ability to operate steadily at various forward speeds. Furthermore to improve performance and flows cycloidal rotor/propeller has blades travelling along generally non-circular and elongated track and is able to transition to a variety of other track shapes having corresponding blade orbit shapes. Track shape variation designs similar to such track designs for blade trajectory determination are used for the purpose of changing the blades pitch and their cross-sectional shape. One embodiment uses fixed elliptic shape track upon which run carriages connected to blade shafts. Said track can be inclined about its major axis thereby changing its shape projection onto the plane in which blades travel thus changing the elliptic shape of their orbit.

Abstract: A portable unmanned aerial vehicle approach and departure zone protection platform comprises a base, an active monitoring sensor connected to the base, a processor connected to the base, and a communication device connected to the base. The processor is configured to determine whether an object is present within an approach funnel.

Abstract: Methods and an apparatus are presented. A method of monitoring utilities is presented. A rechargeable battery of an unmanned aerial vehicle is charged using an electromagnetic field of a high voltage power line within a right-of-way and a recharging system of the unmanned aerial vehicle. The unmanned aerial vehicle is flown a specified distance from the high voltage power line during the charging. Utilities are inspected using a sensor of the unmanned aerial vehicle while flying the unmanned aerial vehicle the specified distance from the high voltage power line.

Abstract: Systems and methods are disclosed for determining a position of a camera affixed to a UAV in flight when the camera captures a digital aerial image. In particular, in one or more embodiments, the disclosed systems and methods utilize real time kinematic satellite navigation techniques to identify a position of a UAV. Moreover, the disclosed systems and methods precisely determine the time that a camera captures a digital aerial image together with an attitude of the UAV at the time of capture to calculate a location of a camera at the time of capture. In one or more embodiments, the disclosed systems and methods can utilize the determined position of the camera together with the captured digital aerial image to generate a three-dimensional representation of a site.

Abstract: A method for supporting application development in a movable object environment includes receiving a request to register one or more behavioral indicators for a movable object via a movable object controller, associating the one or more behavioral indicators with one or more indicator codes, and directing the movable object to behave based on an association between the one or more behavioral indicators and the one or more indicator codes.

Abstract: A method for operating a vehicle chassis includes providing the vehicle chassis including a main body and at least one compartment arranged on the vehicle chassis, selectively receiving one or more components in the compartment, and effecting an operational state of a vehicle comprising the vehicle chassis based on a type of at least one of the one or more components that are selectively received in the compartment. The one or more components is selected from a plurality of components of different types.

Abstract: Systems and methods are provided for multi-orientation flight. An unmanned aerial vehicle (UAV) may be capable of flight in a first orientation and a second orientation that may be different from the first orientation. For example, a UAV may include one or more electronic speed control (ESC) units that may control direction of rotation of one or more propulsion units depending on the orientation of the UAV, to generate lift for the UAV. The one or more propulsion units may include protective covers that may protect one or more rotating components of the propulsion units when the UAV is on a landing surface in the first orientation or the second orientation. The UAV may change orientation on the landing surface or while in flight, in response to a sensed condition and/or instructions from a remote user.

Abstract: A cart for restocking provisions includes a body having one or more exterior surfaces. The one or more exterior surfaces include a top surface facing a first direction and a bottom surfacing facing a second direction that is away from the first direction and parallel to the first direction. The cart also includes a handle fixedly attached to the body. The cart further includes one or more wheels coupled to the bottom surface. In addition, the cart includes one or more hoppers each including a hollow space having a length that extends from an aperture located on the top surface and through at least a portion of an interior of the body. The hollow space includes at least one curved surface that extends from the aperture along at least a portion of the length to allow the provisions to be stored within the one or more hoppers.

Abstract: A cooling arrangement for a kitchen provided for installation in a means of transport comprises a cooling circuit which can have a cooling medium flowing through it and in which a condenser and an evaporator are arranged. The condenser is accommodated in a condenser housing and is arranged in a first installation space which is intended to form a first sub-region of the kitchen. The evaporator is accommodated in an evaporator housing formed separately from the condenser housing, and is arranged in a second installation space which is intended to form a second sub-region of the kitchen.

Abstract: A system including a base provided with the means in the form of clamping and locking jaws for clamping and locking of the system into position in the rail, the means in the form of clamping jaws being movable between a first position and a second position by making use of maneuvering means that are operable by an operator between an unlocking position and a locking position, wherein the maneuvering means includes a clamping screw engaged in a hole and adapted so as to cooperate with a threaded hole and in that it has a smooth section in order to allow the screwing thereof into the threaded hole only when the base and the means in the form of clamping jaws are in the correct position of fastening in the rail.

Abstract: A system for securing a seat, including a base provided with the means in the form of clamping and locking jaws for clamping and locking of the system into position in a rail, the means in the form of clamping jaws being movable relative to the base between a first position and a second drawn-together position for locking the system by clamping around the rail by making use of maneuvering means that are operable by an operator between an unlocking position and a locking position, wherein the hard spot crossing means are provided between the base and the means in the form of clamping jaws in order to maintain these means in the form of clamping jaws in their first drawn-apart position for mounting/dismounting of the system.

Abstract: A system for increasing passenger safety within an airplane (10) includes a forward seat (16) having a back surface (17) that faces an occupant seat (14). A tray table holder (22) is secured to or formed integrally with the back of the forward seat (16). A tray table (20) is rotatably connected to the tray table holder via a hinge (40) and is rotatable relative to the tray table holder. The tray table defines a cavity (32) inside the tray table. An airbag (54) is within the cavity. An inlet device (42) is coupled to the airbag and is rotatable about the hinge (40) such that the inflator inlet can rotate as the tray table rotates relative to the tray table holder. An inflator (52) is connected to the inlet device and is configured to deliver gas to the airbag through the inflator inlet.

Abstract: Methods and systems for providing self-lubricating icephobic elastomer coatings (SLICs) can include forming the coatings from a three-component composition of a silicon elastomer, silicone oil, and a solvent, such as xylene. The coatings can provide ultra-low ice adhesion and high durability levels for a variety of applications operating in harsh icing environments, such as in aviation. In an example, the coatings or SLICs can be used in combination with a localized heating component to provide a Coating Heating Ice Protection (CHIP) system to minimize ice adhesion on the surface of an aircraft component, such as an airfoil or fan blades. Methods and systems for evaluating the ice release performance of the coatings can include high speed impaction of supercooled droplets on rotating fan blades to evaluate the coatings under conditions more representative of in-flight ice conditions, as compared to traditional testing methods.

Abstract: A back pack with parachute that includes: a main compartment; and a chute compartment, wherein the chute compartment includes a releasable parachute. An air sensor is provided within the back pack, wherein the air sensor is adapted to enable the release of the parachute. Other features of the present invention include shoulder straps; a connection ring on the inside surface of the backpack; a waist strap extending from the connection ring; and leg straps extending from the connection ring. The air sensor includes an altimeter, wherein the altimeter enables the release of the parachute. The altimeter activates the release of the parachute after a predetermined distance alternatively a user may use a pull cord available on the back pack for manual activation.

Abstract: Aircraft isolator devices, systems, and methods for isolating a structural component within an aircraft can include an engine interface, airframe, and one or more (e.g., a plurality of) isolator devices attached to the engine interface and the airframe. In some aspects, the isolator devices have a housing, which has a first surface and a second surface that together at least partially define a perimeter of the housing and is configured for attachment to the airframe; an engine attachment component configured for attachment to the engine interface and disposed at least partially inside of the housing; and a plurality of elastomeric elements disposed on or over each of the first and second surfaces of the housing The plurality of elastomeric elements are spaced apart from the engine attachment component via the housing for improved heat dissipation from the engine, reducing operational temperatures of the elastomeric elements to prolong their use.

Abstract: An aircraft which comprises a fuselage and at least one propulsion assembly linked to the fuselage by at least two connecting rods positioned at least partially in an inner zone of the air inlet of the nacelle of the propulsion assembly. Thus, the connecting rods do not interfere with the secondary flow flowing inside the nacelle and do not affect the aerodynamic performance levels of the propulsion assembly.