460results about "Jet type power plants" patented technology

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine including an unducted fan defining a fan diameter; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a leading edge and including a first inflection point along the leading edge, the first inflection point defining a first radius of curvature that is less than 5 times the fan diameter and greater than 0.1 times the fan diameter.

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

Disclosed herein is an aircraft with engines positioned so as to avoid damage to other components of the aircraft. The aircraft may include a blended wing body aircraft. The engines may be positioned aft of a pressure vessel of the aircraft. The engines may be positioned aft of and / or above a fuel store of the aircraft. Such engine positioning may reduce the likelihood of damage to a pressure vessel and / or fuel store in the event of engine failure.

Aerodynamic lifting structures, such as aircraft wings, having embedded engines and associated methods and systems are disclosed herein. A wing assemblies configured in accordance with embodiments of the present technology can include, for example, an upper wing portion, a lower wing portion, and a plurality of independent ducts positioned between the upper wing portion and the lower wing portion. Each duct can extend between a corresponding inlet positioned toward a leading portion of the wing assembly and a corresponding outlet positioned toward a trailing portion of the wing assembly. The wing assembly can further include a plurality of fans and a plurality of electric motors operably coupled to the plurality of fans. The fans and electric motors are positioned in the corresponding individual ducts and the fan is rotatable to propel fluid received in the inlet through the duct to create lift.

A system for an aircraft includes a fan rotor, an engine core, a fan case, a core case, a bifurcation, an inner electrical system, an outer electrical system and multiple electrical lines electrically coupling the inner electrical system to the outer electrical system. The engine core is configured to drive rotation of the fan rotor about an axis. The fan case houses the fan rotor. The core case houses the engine core. The bifurcation radially crosses a bypass flowpath. The bypass flowpath is downstream of the fan rotor and located radially between the fan case and the core case. The inner electrical system is arranged with the engine core. The outer electrical system is mounted to the fan case. The electrical lines extend between and electrically couple the inner electrical system to the outer electrical system. The electrical lines run in parallel along one another radially through the bifurcation.

The invention provides an aircraft framework and an aircraft, the aircraft framework is used for the aircraft flying in the atmosphere, the aircraft framework comprises a cage serving as a framework main body, the cage bears the self weight and the flight load of the whole aircraft, at least two first turbojet engines can be contained in the cage, and the first turbojet engines are arranged in the cage; the cage is open at least in the lower portion and used for allowing the jet flow of the first turbojet engine to pass through. Through the arrangement of the cage which is a skeleton main body, a power source device of the aircraft is collected and gathered, so that the miniaturization of the whole aircraft is realized.

The invention provides a personal aircraft chassis and a personal aircraft. The chassis comprises a main framework and a chassis body, the personal aircraft comprises a main framework and a thrust array assembly, the thrust array assembly is fixed to the main framework, thrust of the thrust array assembly is achieved through a plurality of first turbojet engines, the geometric position relation between the thrust action point and the thrust direction of the thrust array assembly and the main framework is kept fixed, and when the personal aircraft stops on the ground, the thrust array assembly is fixed to the main framework. The thrust direction of the thrust array assembly is perpendicular to the ground. The vector nozzle assemblies are fixed to the main framework, thrust of the vector nozzle assemblies is achieved through the second turbojet engines, the central axes of the second turbojet engines are perpendicular to the central axis of the first turbojet engine, and vector nozzles of the vector nozzle assemblies at least have one degree of freedom relative to the main framework. And high-dynamic, high-fault-tolerance and reconfigurable flight control which cannot be realized by utilizing pure thrust difference control can be realized.

An aircraft assembly is disclosed having a wing and an engine mounting pylon. An aft end of the engine mounting pylon is connected to the wing by a spigot and at least one fastener. The aircraft assembly is configured such that, during operation of the aircraft assembly on an aircraft, the spigot transfers only lateral load between the engine mounting pylon and the wing and the at least one fastener transfers only vertical load between the engine mounting pylon and the wing.

A structure for linking and supporting a turbine engine on an aircraft pylon, the structure having a first longitudinal axis intended to extend parallel to a second longitudinal axis of the pylon, the structure including a first axial portion for fastening to the pylon, the first portion having an upper end that defines a substantially horizontal plane of interface with the pylon, and a lower end bearing suspension rods for suspending the turbine engine, which extend in a rear vertical plane; and a second axial portion that is intended to extend forward of the pylon and includes at least one suspension member of the turbine engine in a front vertical plane.

A propulsion assembly for an aircraft, the propulsion assembly having a jet engine having a fan casing and a central casing around a longitudinal axis and having a vertical median plane passing through the longitudinal axis, an attachment pylon having a rigid structure that takes the form of a box that has a front wall and an upper spar extending forwardly in respect to the front wall, a front engine attachment fixed between an upper area of the central casing and a lower end of the front wall, and a complementary front engine attachment fixed between an upper area of the fan casing and a front end of the upper spar.

A system for attaching a front engine of an aircraft, having: a vertical median plane, an engine pylon with a nose having a main female clevis, and a cylindrical housing around a vertical axis, a main link fastened to a front casing of the engine by a secondary ball-joint connection about a secondary axis perpendicular to the median plane by a secondary shaft, a main shaft, perpendicular to the median plane and forming a main ball-joint connection of the main link in the main female clevis about a main axis, the main and secondary axes in the plane perpendicular to the median plane, and an outer cylinder, coaxial with the vertical axis and a first end of which fastened in the cylindrical housing and a second end of which mounted, via an annular linear connection, around the vertical axis with respect to the front casing.

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

An aircraft propulsion assembly including an engine assembly that includes front and rear parts offset along a longitudinal axis, a primary structure of a pylon, at least one supporting structure that extends along the longitudinal axis, separate from the rear part and connected to the front part of the engine assembly, an engine-attachment system that includes at least one front attachment directly connecting the engine assembly and the primary structure, and at least one rear attachment offset toward the rear relative to the front attachment connecting the primary structure and the supporting structure.

A strut assembly for coupling an engine to a wing of an aircraft, the strut assembly comprising a mid truss assembly comprising a fore portion and an aft portion; an engine mount member connected to the fore portion of the mid truss assembly; an aft truss assembly comprising a fore portion and an aft portion, the fore portion of the aft truss assembly being connected to the aft portion of the mid truss assembly; an aft strut bulkhead connected to the aft portion of the aft truss assembly; and a wing mounting feature operatively connected to, and located aft of, the aft strut bulkhead.

An aircraft may comprise propulsors. The propulsors may be integrated into an array of propulsors. An array of propulsors may be integrated in an airfoil of the aircraft. The aircraft may include a flow turning control system. The flow turning control system may include an end wall and one or more movable flaps. The flow turning control system may enable selective flow turning of the flow of propelled by the array of propulsors. The selective flow turning may include actuating the one or more movable flaps. The selective flow turning may achieve flow turning of over a trailing edge of a movable flap.

Truss-braced wing aircraft engine mounting and associated systems are disclosed. An example aircraft includes a fuselage including a central structural section, a wing extending from the fuselage, a truss extending from the central structural section and coupled to the wing, a pylon coupled to the central structural section, and an engine coupled to the pylon, wherein the pylon is positioned at an angle substantially 45 degrees from a horizontal plane and a vertical plane.

A propulsion system for an aircraft can include an electric power source and an propulsion assembly having a propulsor. An electric power bus can electrically connect the electric power source to the propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.

A propulsion assembly having an engine and an engine attachment which connects the engine and a primary structure of a pylon and which comprises a removable connection connecting a transverse beam and the primary structure. This removable connection has a first contact surface integral with the transverse beam, a second contact surface integral with the primary structure, at least one connection element keeping the first and second contact surfaces pressed against one another, at least one system for transmission of transverse forces between the engine and the primary structure and at least one waiting fail-safe connection distinct from each connection element and configured to generate an additional path for forces only in the event of malfunction of an element of the first removable connection.

A blended wing aircraft is provided, including a body having a fuselage and a pair of wings extending outward from the fuselage; and an aircraft engine defining an outlet and including a thrust reverser assembly, the thrust reverser assembly including a deployable structure extending less than 360 degrees around the outlet.

The invention relates to the technical field of aircrafts, and discloses a triphibian aircraft and a triphibian form switching method thereof. Comprising an aircraft main body, a left auxiliary body and a right auxiliary body, retractable wings are arranged between the aircraft main body and the left auxiliary body and the right auxiliary body, sliding wheel assemblies are arranged at the bottoms of the three bodies respectively, foldable rotor wing mechanisms are arranged at the tops of the left auxiliary body and the right auxiliary body, a propeller is arranged at the tail of the aircraft main body, and foldable small wings are arranged on the outer sides of the left auxiliary body and the right auxiliary body. During take-off, the wings and the winglets are unfolded, the rotor mechanisms are started, and rising is achieved; during air cruise, the sliding wheel assemblies and the rotor mechanisms are stored, the propellers are started, and smooth flight is ensured; when the unmanned aerial vehicle runs on land, the sliding wheel assemblies are opened, the rotor mechanisms are stored, the wings and the winglets are folded, wind resistance is reduced, and the propellers are started to run; when sailing on the water, the three-body structure ensures buoyancy, and the propeller is pushed to move forwards; through the three-body structure, seamless switching of air, land and water triphibian scenes is achieved, the system adapts to multiple environments, the use flexibility is improved, and the application range is widened.

An aircraft designed to provide sustained G forces, with a relatively high steady angle of attack maneuverability using less thrust by balancing thrust and drag to sustain a high turn rate with dual low thrust engines using novel wing and fuselage designs. The aircraft includes a wing oriented laterally relative to the fuselage, at least one horizontal tail surface extending laterally from the fuselage and positioned rearward of the fixed wing, and at least one vertical tail surface extending upward from the fuselage. The first and second engines are mounted to the fuselage at locations positioned vertically below the fixed wing.

An assembly for an aircraft having an upper fitting fastened to a structure of the wing of the aircraft, a lower fitting fastened to a pressure-side panel of the wing, an engine pylon with two lateral panels mounted so as to articulate on the lower fitting, a starboard-side link rod and a port-side link rod mounted so as to articulate between the lateral panel that is on the same side and the upper fitting, and a stud having a proximal end secured to a rear rib of the engine pylon and a distal end mounted in an aperture of the lower fitting through an annular linear connection.

The invention relates to the technical field of unmanned aerial vehicles, in particular to a turbojet power system of a multi-rotor unmanned aerial vehicle, which comprises a turbojet engine, a fuel supply module, an electronic control unit, an air inlet flow guide structure, an exhaust flow guide structure, a cooling module, a damping bracket, a quick disassembly and assembly interface, a redundant backup system and an energy recovery module, according to the multi-rotor unmanned aerial vehicle, the power performance of the multi-rotor unmanned aerial vehicle is improved by replacing a traditional motor with the micro turbojet engine, so that the unmanned aerial vehicle can obtain longer endurance time under the condition of carrying the same load, and particularly, the unmanned aerial vehicle can still keep stable power output in extreme environments such as high altitude or high temperature; the problem of power attenuation caused by thin air or poor heat dissipation of the motor is solved, multi-degree-of-freedom thrust direction adjustment is achieved through the design of the deflectable nozzles, and the unmanned aerial vehicle can still keep accurate flight attitude control under severe environment conditions such as strong wind.

An aircraft may comprise propulsors. The propulsors may be integrated into an array of propulsors. An array of propulsors may be integrated in an airfoil of the aircraft. The aircraft may include a flow turning control system. The flow turning control system may include an end wall and one or more movable flaps. The flow turning control system may enable selective flow turning of the flow of propelled by the array of propulsors. The selective flow turning may include actuating the one or more movable flaps. The selective flow turning may achieve flow turning of over a trailing edge of a movable flap.

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

According to an embodiment, a control device controls a user-wearable flight device and includes a processing unit configured to acquire state data related to a state of the flight device and manipulation data related to a manipulation of the flight device, input the acquired state data and the acquired manipulation data to a model trained using deep reinforcement learning, and control the flight device on the basis of an output result of the model to which the state data and the manipulation data are input.

An assembly comprising a longitudinal member of an aircraft wing, where the longitudinal member has a contact wall which is penetrated by first bores, each passing through the contact wall parallel to a longitudinal direction, an engine pylon which is arranged at the end of the longitudinal member in the longitudinal direction and having an upper longitudinal member which, for each first bore, is penetrated by a second bore which is aligned with the first bore, and a nut and a screw for each pair of a first bore and a second bore, which are aligned, where the screw is screwed into the nut successively via the first bore and the second bore, sandwiching the upper longitudinal member and the contact wall.

The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.

The present invention provides an infrared enhancer with controllable radiant power, which relates to the field of unmanned aerial vehicles, and solves the problem that it is difficult to control the radiant power of the infrared enhancer; the device comprises a support component, a turbojet engine, which is fixed inside the support component; an installing adapter, which is used to connect the product to be installed, which is provided at one end of the support component, and is located on the side of the flame erupted from an exhaust nozzle of the turbojet engine; a heating cone, which is fixed to one end of the installing adapter and toward the exhaust nozzle of the turbojet engine, wherein infrared enhanced coating is coated outside the heating cone, and a heat insulation device is provided inside the heating cone; the present invention uses the flame at the exhaust nozzle of the turbojet engine to heat the heating cone, the flame temperature at the exhaust nozzle can be controlled by controlling the size of the operating state of the engine, and the heating cone is heated to form a stable infrared radiation source to enhance the infrared characteristics of the target; the infrared point source characteristics of an aviation jet engine can be simulated, and the present invention is suitable for a larger flight speed domain and an altitude domain.