38results about "Modular constructions" patented technology

The invention relates to the technical field of unmanned operation, and discloses an active deformation multi-aircraft integrated operation platform, which comprises a first aircraft, a second aircraft and a controller, one ends of the two fixed connecting rods are connected with the first aircraft, and steering engines are fixed to the other ends of the two fixed connecting rods; one ends of the two swing connecting rods are fixedly connected with the driving ends of the two steering engines respectively, a second aircraft and a third aircraft are connected to the two swing connecting rods respectively, the first aircraft, the second aircraft and the third aircraft are arranged in a triangular shape, and then a triangular collaborative architecture operation platform is formed; a first arc-shaped contact plate and a second arc-shaped contact plate are detachably arranged at the other ends of the two swing connecting rods respectively, a first clamping jaw is detachably arranged at one end of the first arc-shaped contact plate, and a second clamping jaw is detachably arranged at one end of the second arc-shaped contact plate. The platform can adapt to stable contact of diversified contact surfaces (flat / non-flat / corrugated wall surfaces, stand columns and the like), and the scene adaptation cost is reduced.

Disclosed are specialized airframe structures for mission-adaptable unmanned aerial vehicles (UAVs) that are fabricated by rapid, low-cost additive manufacturing techniques. In some embodiments, an integral fastening system for a mission-adaptable aerial vehicle includes a first airframe section, a second airframe section, and a bayonet mount system that comprises one or more passageways produced on a first end region of the first airframe section to include a first channel and second channel, and one or more protrusions produced on a second end region of the second airframe section, such that, when the first and second airframe sections being assembled, the one or more protrusions are first aligned with an entry region of the first channel to be translated and then aligned with the second channel of the one or more passageways to be rotated to securely connect the first and second airframe sections together.

A motor vehicle hub station configured to function as a terminal for an air motor vehicle, a ground motor vehicle, or a water motor vehicle, the motor vehicle hub station including a plurality of levels by a combination of a water surface level connected to a water surface and having an entrance for a water motor vehicle, a port level having a takeoff and landing field for an air motor vehicle, or a ground level configured to be connected to a ground and having an entrance for a ground motor vehicle, wherein a lift passage having an internal space extending in an up-down direction of the motor vehicle hub station is provided between the levels, the internal space is connected to each of the water surface level, the port level, and the ground level, and the air motor vehicle, the ground motor vehicle, or the water motor vehicle is lifted or lowered through the internal space.

A line assembly for installation in an aircraft fuselage comprises a first line section having a first diameter, at least one second line section having a second diameter, a set of first line brackets, and a set of second line brackets, wherein the first line brackets comprise a first receiving space designed for holding the first line section and a first support portion for attaching the first line brackets to a structural part of the fuselage, wherein the second line brackets comprise a second receiving space designed for holding the at least one second line section and a second support portion for attaching the second line brackets to the first line section, wherein at least one second line section comprises a higher flexibility than the first line section, and wherein the at least one second line section is attached to the first line section through a plurality of second line brackets that are arranged at a distance to and are independent from the first line brackets.

An unmanned aerial vehicle (UAV) includes a fuselage assembly, a further portion that attaches with the fuselage assembly, and a propulsion assembly coupled with the further portion. The propulsion assembly is constructed and arranged to provide propulsion for the UAV. The fuselage assembly includes a fuselage body constructed and arranged to operate as a forward portion of the UAV, lateral stringers coupled with the fuselage body and extending laterally along the fuselage body, and a set of interchangeable covers to cover at least a portion of a payload bay opening defined by the fuselage body. Utilizing such a fuselage assembly offers a highly configurable mounting architecture to accommodate a wide variety of payloads.

A modular aircraft system comprising a plurality of nacelles and a plurality of wing segments. The modular aircraft system is modularly configurable into a plurality of different configurations with pairs of the plurality of nacelles connected via respective wing segments of the plurality of wing segments to generate an annular wing that defines a wing cavity.

The present invention relates to a vertical take-off and landing module (200) for a fixed-wing aircraft (110), which includes at least one vertically-acting propulsion unit (240), actuator means (245) and support means (230), so as to be adapted to be operatively connected to said aircraft (110).The actuator means (245) can move the propulsion unit (240) from the inside of the module (200) towards the outside, and vice versa, so that the propulsion unit (240) is adapted to generate a substantially vertical propulsive force during the aircraft take-off and landing phases.

The invention relates to a drone system (2) for transporting a payload (4), comprising a fuselage (6) for receiving the payload (4) and a wing assembly (8) which is connected to the fuselage (6). The drone system (2) has a first aerodynamic configuration (A1) formed by at least one structural element (10). According to the invention, the drone system (2) can be transferred into a second aerodynamic configuration (A2), which differs from the first aerodynamic configuration (A1), by releasing the at least one structural element (10), in particular by ejecting same, the structural element (10) forming a first wing structure (18) in the first aerodynamic configuration (A1), in which the wing assembly (8) has a first aerodynamic profile (20), and the drone system (2) can be transferred into the second aerodynamic configuration (A2) by ejecting the first wing structure (18), the wing assembly (8) having, in the second aerodynamic configuration, a second aerodynamic profile (24) which is formed by a second wing structure (22) and differs from the first profile (20), and the first aerodynamic profile (20) at least partly enclosing the second aerodynamic profile (24) in the first aerodynamic configuration (A1). The invention also relates to a corresponding designing method (100), a corresponding production method (200), and a corresponding operating method (300).

This invention relates to a MRO cost effective, VTOL / CTOL capable advanced rotorcraft design that addresses key challenges in current helicopter technologies. It employs a Direct Drive electric motor for propulsion, eliminating the need for complex gearboxes and transmission systems, thereby reducing mechanical complexity and maintenance costs. The electric motor provides Direct Drive, high torque, and enhances reliability and manoeuvrability. The fuselage features a laminar, elongated, and sleek shape for low air resistance and highspeed horizontal flight. Its modular construction optimizes aerodynamic efficiency and enables easy maintenance through quick module replacement. The rotorcraft also incorporates front wings (canards) for improved lift and manoeuvrability, especially at low altitudes. These wings enhance handling and stability, allowing precise movements in confined environments. This combination of PMSM propulsion, a modular laminar fuselage, and front wings results in superior performance, reduced maintenance, and increased versatility, making the rotorcraft well-suited for modern combat scenarios, including urban and littoral operations.

Provided is a vehicle comprising a fuselage provided with at least one storage module each configured to accommodate therein unmanned aerial systems and at least one docking module each configured to detachably interact with at least one of the unmanned aerial systems so as to enable connection thereof to the fuselage for movement of the vehicle, and a control module configured to present control commands to at least one of the unmanned aerial systems so as to enable release thereof from the storage module for interaction with one of the docking modules. Furthermore, provided are variants of the transport system, each of which variants includes the subject vehicle, and a method of moving the subject vehicle.

This present invention relates to the field of aircraft and discloses an aircraft and a method for connecting a canard to an arm. The connection method is used to couple a canard and an arm. The canard comprises a coupling insertion portion, which comprises a plurality of fixing portions. The arm comprises an arm insertion cavity, and an insertion opening is provided at one end of the arm insertion cavity. The coupling insertion portion is configured to be inserted into the arm insertion cavity through the insertion opening and is fixed within the arm via the fixing portions. In the present invention a detachable structure is enabled between the canard and the arm, allowing the position of the center of lift to be adjusted by exchanging canards featuring different designs, thereby adapting to aircraft cabins with different centers of gravity.

Method (66) for installing system components (2, 52, 60) in a section of an aircraft fuselage (4), comprising the steps: - Providing (68) at least one planar structural arrangement (8, 18, 20, 22, 24, 50, 56) to be attached to or within the fuselage of the aircraft, - Attaching (70) system components (2, 52, 60) to the structural arrangement (8, 18, 20, 22, 24, 50, 56), - Coupling (72) of system lines (46) with the system components (2, 52, 60) and arranging (74) the system lines (46) on the structural arrangement (8, 18, 20, 22, 24, 50, 56), - Positioning (72) the structural assembly (8, 18, 20, 22, 24, 50, 56) with the system components (2, 52, 60) and system lines (46) arranged thereon at a designated installation location of the structural assembly (8, 18, 20, 22, 24, 50, 56), and - mechanical coupling (78) of the structural assembly (8, 18, 20, 22, 24, 50, 56) with the aircraft fuselage (4); wherein the mechanical coupling (78) comprises connecting structural support elements (14, 62) to the aircraft fuselage (4) and the at least one structural arrangement (8, 18, 20, 22, 24, 50, 56); wherein the connection of the supporting structure elements (14, 62) to the aircraft fuselage (4) and the at least one structural arrangement (8, 18, 20, 22, 24, 50, 56) includes compensating for manufacturing tolerances by adjusting connection positions, wherein the adjustment of the connection positions is carried out by means of tolerance-compensating screw connections (36) between the supporting structure elements (14, 62) and the at least one structural arrangement (8, 18, 20, 22, 24, 50, 56).

Apparatus for removably suspending a propulsion system externally from a fuselage body of a modular aircraft and along a centre-line of the aircraft, the propulsion system comprising an engine. The apparatus comprises: a support structure; a fuselage mounting arrangement configured to removably suspend the support structure externally from the fuselage body, wherein the support structure is arranged to extend longitudinally below a section of the fuselage body; and an engine mounting arrangement for suspending the engine from the support structure. Also provided is a modular aircraft assembly kit comprising: a plurality of interchangeable support structures arranged to be removably suspended from a fuselage body of a modular aircraft, each support structure being arranged to suspend a respective propulsion system externally from the fuselage body and along a centre-line of the aircraft, and each support structure comprising an engine mounting arrangement for suspending an engine of the respective propulsion system from the support structure. The plurality of support structures comprises: a first support structure from which a first propulsion system is suspended or suspendable, thereby to removably suspend the first propulsion system from the fuselage body; and a second support structure from which a second propulsion system is suspended or suspendable, thereby to removably suspend the second propulsion system from the fuselage body.

Additive manufactured airframe structure having a plurality of additive manufactured airframe segments operable to be linked together in an assembled direction. Each of the plurality of additive manufactured airframe segments are separate from one another in an unassembled configuration. Plurality of reinforcement elements operable to be received in a receiving portion of the plurality of airframe segments and extending through the plurality of airframe segments in a normal direction. Receiving portion is located on the interior of a respective one of the plurality of airframe segments.

An aerial vehicle includes a housing having an accommodation space. The aerial vehicle is configured to access a first communication network through a first communication apparatus, and / or access a second communication network different from the first communication network through a second communication apparatus. An aerial vehicle system includes the aerial vehicle and the first communication apparatus.

An apparatus 100 has a support frame 102 and an engine mounting arrangement. In use, the support structure may be suspended externally below a modular aircraft’s fuselage 16, extending longitudinally, using a fuselage mounting arrangement. A modular aircraft may have different sets of support frames and propulsion systems 10 with an engine 32, a respective set can be removed, and swapped for a different set, when installed the engine is suspended from the respective support frame. Preferably, the support frame is located above, and rearward of, a central wing structure 20 of the aircraft; stiffness of the support frame relative to part of the fuselage configured to reduce force transmission between the fuselage and engine. The engine mounting arrangement may have vibration isolation mounts, and U-shaped front 144, and rear 146, engine mounts. Preferably, the fuselage mounting arrangement includes frame members 104,106 which are secured to fuselage clevis brackets 108,110. Frame members are spaced apart near lateral sides of the support frame, and include a number of front 104a,104b, and rear 106a,106b, frame members, near to the respective engine mounts. Figures 1 & 4B

Additive manufactured airframe (10) structure having a plurality of additive manufactured airframe segments (30) operable to be linked together in an assembled direction (40). Each of the plurality of additive manufactured airframe segments (30) are separate from one another in an unassembled configuration (50). Plurality of reinforcement elements (70) operable to be received in a receiving portion (80) of the plurality of airframe segments (30) and extending through the plurality of airframe segments (30) in a normal direction (90). Receiving portion (80) is located on the interior (100) of a respective one of the plurality of airframe segments (30).

The present application discloses an aircraft. The aircraft comprises a fuselage mount coupled to a first wing and a second wing via a first hinge and a second hinge via a second hinge, a fuselage detachably mounted on the fuselage mount, a first engine nacelle detachably mounted on an end of the first wing distal from the fuselage, and a second engine nacelle detachably mounted on an end of the second wing distal from the fuselage.

A modular unmanned aerial vehicle (UAV) that consists of a fuselage (2), wing panels (3), a stabilizer (4) and two booms (5), and each of the boom (5) is equipped with an adapter (6). The wing panels (3) are configured so as the adapters (6) of the boom (5) are connectable thereto to form a lock connection. A spar (7) is passed through the fuselage (2), and the wing panels (3) are provided with holders (8) for the spar (7). Ends of the spar (7) are equipped with adapters (9) formed as tabs. The lock connection is formed by a simultaneous connection of a turn bushing (10), having a transverse notch (11) and a spring-loaded fastener (12) that is positioned in each of the wing panels (3), to the spar (7) adapter (9) and to the adapter (6) of the boom (5) that is hook-shaped, while being fixable by an external lever (13) that is rigidly coupled to the turn bushing (10). Each wing panel (3) is equipped with a torque pin (21) that is coupled to a corresponding fuselage (2) hole (22) that is displaced along a fuselage (2) axis relative to the spar (7).

A Lynchpin structure may be combined with one or more additional Lynchpin structures to form a compound Lynchpin propulsion structure. Each Lynchpin structure may include six pentangular areas, and one or more of the pentangular areas may include a propulsion device. The propulsion may be used to propel the compound Lynchpin propulsion structure through or over various media, such as through air, across ground, on or underwater, or through or over other media. The propulsion may include avionic propulsion, ground propulsion, hydrodynamic propulsion, or other types of propulsion. A single type of propulsion device may be used within one or more of the pentangular areas, or diverse types of propulsion may be used to provide various navigational performance or multi-mode operation. Each propulsion device may also include a device to direct the propulsion, such as a single or multi-axis gimble or adjustable aerodynamic control surface.

A modular UAV comprising a fuselage, wing panels, a stabilizer, and two booms with vertical stabilizer, each of the booms equipped with an adapter. The wing panels are configured so the adapters of the boom are connectable thereto to form a lock connection. A spar passes through the fuselage, and the wing panels include holders for the spar. Ends of the spar comprise adapters formed as tabs. The lock connection is formed by connection of a turn bushing having a transverse notch to a spring-loaded fastener positioned in each of the wing panels, and of each spar adapter to a respective boom adapter that is hook-shaped, while being fixable by an external lever rigidly coupled to the turn bushing. Each wing panel includes a torque pin coupled to a corresponding fuselage hole displaced along a fuselage axis relative to the spar.

Disclosed herein is a drone docking station for depositing drone-delivered items / goods into a secure receptacle. Packages can be delivered from curbside, mailbox, postbox, porch, basement safe, or window receptacle to a multi-compartment receptacle with a specific residential or commercial address and including heated and cooled sections. Optional features include: a communication system between the station and the drone, pre- and post-delivery temperature and storage, a battery charging and replacement station, a collector for identifying explosives and anthrax, an ultraviolet system for eliminating pathogens, viruses, and harmful substances, an ozone applicator for eliminating pathogens, viruses, and harmful substances, weather monitoring, vehicle and package tagging and tracking, a facial recognition camera and software for pets and humans, and floodlights.

The application relates to the field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle, which comprises a machine body, a fixed-wing component and a rotor component which are alternatively connected to the machine body; wherein the fixed-wing component is connected to the machine body to form a vertical take-off and landing fixed-wing unmanned aerial vehicle, and the rotor component is connected to the machine body to form a multi-rotor unmanned aerial vehicle, so as to realize an unmanned aerial vehicle which can be switched between a vertical take-off and landing fixed-wing unmanned aerial vehicle and a multi-rotor unmanned aerial vehicle.

A propulsion module of an aerial vehicle can include a door portion disposed in a housing and opening or closing an open portion of the housing by sliding movement of the door portion, a propeller for providing propulsion to the aerial vehicle, a linkage assembly having a first end portion connected to the housing and a second end portion connected to the propeller to pull the propeller through the open portion into an interior space of the housing or pull the propeller through the open portion outside the interior space, and a portion opening and closing the door portion coupled to the door portion and configured to provide an opening force or a closing force to the door portion according to the inward pulling movement or the outward pulling movement of the propeller, respectively.

The invention relates to the field of aircraft, and discloses an aircraft and its multi-rotor aerial platform. The multi-rotor aerial platform of the present invention comprises at least one pair of rotor arms, which are symmetrically arranged about a central axis and each of which is provided with a plurality of vertical take-off and landing (VTOL) power units; a main wing, which is symmetrically arranged about the central axis and connected to the at least one pair of rotor arms; and a canard and a central avionics bay, which are respectively structurally integrated with a pair of rotor arms closest to the central axis and form a monolithic closed-loop structure with this pair of rotor arms. By forming the canard, the rotor arms, and the central avionics bay into a monolithic closed-loop structure, the present disclosure significantly enhances the structural rigidity of the motor installation on the rotor arms.

A modular and reconfigurable aircraft including a first aircraft module, a second aircraft module, a plurality of connectors, and a coupler. The first aircraft module can include a polyhedral cage structure, a propeller disposed in an interior of the polyhedral cage structure, and a motor disposed in the interior of the polyhedral cage structure and configured to drive the propeller. The second aircraft module can include a polyhedral cage structure, a propeller disposed in the interior of the polyhedral cage structure, and a motor disposed in the interior of the polyhedral cage structure and configured to drive the propeller. A plurality of connectors can be configured to couple the polyhedral cage structure of the first aircraft module to the polyhedral cage structure of the second aircraft module. A coupler can be configured to attach a payload to the polyhedral cage structure of the first aircraft module.

The present disclosure discloses an aerial vehicle, an aerial vehicle system, a battery, and a movable platform. The aerial vehicle can communicate with an external device through a first communication apparatus and / or a second communication apparatus. The aerial vehicle can access a first communication network through the first communication apparatus and access a second communication network through the second communication apparatus. The first communication network is different from the second communication network. The aerial vehicle includes an accommodation space arranged at the housing of the aerial vehicle. At least a part of the first communication apparatus is quickly arranged into and removed from the accommodation space. Thus, the first communication apparatus does not have a greater impact on the shape of the aerial vehicle. The aesthetic of the appearance of the aerial vehicle can be ensured, and the impact of the first communication apparatus on the flight performance of the aerial vehicle can be reduced.

The invention relates to a drone system (2) for transporting a payload (4), comprising a fuselage (6) for receiving the payload (4), and a wing arrangement (8) which is connected to the fuselage (6), wherein the drone system (2) has a first aerodynamic configuration (A1) formed by at least one structural element (10). According to the invention, it is proposed that the drone system (2) can be transformed into a second aerodynamic configuration (A2) by releasing, in particular by jettisoning, the at least one structural element (10), which differs from the first aerodynamic configuration (A1). The invention further relates to a design method (100), a manufacturing method (200), and an operating method (300).

An aircraft data collection system comprising a set of removable data collection units and a computer system. The set of removable data collection units is loadable into a compartment in a commercial aircraft. The computer system is configured to control operation of the set of removable data collection units to collect data during a flight of the commercial aircraft on a flight path. A third party can use a smart phone or other electronic device to control the data collection unit during a commercial aircraft flight. The third party is different from the airline operating the commercial aircraft.

A modular wing, adapted to be used on a flying device such as a toy airplane, drone, or other small fixed wing flying device, or form a part of a wind turbine or any other apparatus that requires a wing or blade, that is compatible with all block-based toy systems such as LEGO®, DECOOL® or KAZI®. The modular wing is comprised of a series of modular aerodynamic surfaces that may be suitable for manufacture by a low-cost method such as molding or additive manufacturing such as 3D printing, typically but not necessarily from plastic, to form wing sub elements which, when assembled together, form a wing or blade such as an airplane wing or turbine blade. The modular wing may comprise cambered or symmetric wing shapes. The modular wing may be used in a static display model fully flying aerodynamic aircraft, sailing hydrodynamic boat, or aerodynamic functioning turbine.