498 results about "Engine mount" patented technology

The invention relates to the technical field of mechanical vibration testing, in particular to a method for testing dynamic rigidity and damping characteristics of an engine support, which comprises the following steps of: 1, simulating a boundary; step 2, double-source excitation loading is carried out; step 3, dynamic response acquisition: arranging vibration measurement points in the main shaft direction of the rigidity of the support to acquire acceleration signals in three directions, synchronously acquiring excitation force signals, and recording all the signals at a set sampling rate after anti-aliasing filtering; 4, constructing a frequency response matrix: performing time-frequency transformation on the exciting force signal and the acceleration signal, and calculating a cross-point frequency response function matrix; 5, parameter decoupling calculation is carried out, wherein parameter decoupling is achieved through cross iterative optimization; and 6, outputting parameters. Through the decoupling calculation of the low frequency band and the high frequency band, the cross iteration optimization method can effectively reduce the calculation error, improves the parameter decoupling precision, and guarantees the reliability of the test result under different frequency bands.

The invention discloses a movable frame device for a high-power turboprop engine test bed and the engine test bed. The movable frame device comprises a movable frame framework, a front mounting seat and a counterweight system. The movable frame framework is arranged below the static frame device and used for being connected with the static frame device through a plurality of spring pieces arranged on the periphery of the movable frame framework, and then the rack system used for measuring the thrust of the turboprop engine is formed. The front mounting seat is used for being connected with an engine mounting rack for mounting a turboprop engine in a fast mounting manner so as to mount and support the turboprop engine to be measured. And the counterweight system is used for balancing the total weight of the turboprop engine and the engine mounting frame, so that the gravity center of the rack system is positioned in the center defined by the plurality of spring pieces. According to the movable frame device, the air inlet flow field of the propeller is not influenced by the size of the frame of the movable frame device, so that the engine performance is not influenced, the test result is high in accuracy, the test is safe and reliable, and the installation position of the propeller does not interfere with the structure of the movable frame device.

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.

The present invention provides a welding positioning device for an engine pipe body bracket of a drone, which includes a first positioning bracket, a second positioning bracket and a third positioning bracket, and is respectively used for accurately positioning the first pipe body, the second pipe body and the third pipe body of the engine pipe body bracket. Each pipe body penetrates into a pin column with holes to form an assembly base point of the engine. Bolts and nuts are used to penetrate into the pipe body pin column holes to position and fasten the pipe bodies, which can ensure the positioning accuracy of the engine assembly base point and the reliability of the positioning method. According to the correlation between the pipe bodies of the drone bracket, the engine bracket welding positioning device can combine the pipe bodies to form an accurate positioning of the bracket. By accurately positioning the engine bracket, the present invention enables the engine bracket to meet the accuracy requirements specified in the design drawings, meet the installation conditions for the assembly of the drone engine, ensure the stability of the engine function, and provide reliable power support for the drone.

A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, a geared architecture including a gear train, a compressor section and a turbine section. A static structure includes a first case and a second case. The first case includes a first engine mount location. The second case includes a second engine mount location. The first engine mount location is axially near the geared architecture.

A hydro engine mount for a vehicle may include a locking body including a plurality of locking portions; a body plate including a plurality of fastening grooves configured to be fastened to the plurality of locking portions, wherein a main rubber is mounted in the body plate; and a diaphragm stacked between the main rubber and the locking body.

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.

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle which comprises an engine, the engine is arranged on a fuselage frame plate in a fuselage through an engine mounting frame, a propeller is arranged on an output shaft of the engine, and the engine mounting frame comprises a main supporting plate, a double-layer isolation damping device and an anti-twisting device. The main supporting plate is arranged on a machine body frame plate in the machine body; a plurality of installation lugs are evenly distributed on the edge of the main supporting plate, plane normal lines of the four installation lugs are gathered at the gravity center position after an engine is installed, and the double-layer isolation vibration reduction device is arranged between each installation lug and the corresponding inner wall on the inner wall of the machine body. The vibration attenuation device is used for attenuating and isolating vibration of an engine and a propeller twice to achieve vibration attenuation. The anti-twisting device is arranged between the inner wall of the machine body and the two opposite edges of the main supporting plate and used for limiting twisting of the main supporting plate in the length direction of the machine body. According to the device, the damping effect is remarkably improved, and the safety and stability of power transmission are guaranteed.

The invention provides a fatigue test loading device for an engine mounting bracket. The fatigue test loading device comprises a large bottom plate; the engine simulation part is mounted on the engine mounting bracket; the simulation part weight counteracting assembly is installed on the large bottom plate, and the simulation part weight counteracting assembly is used for eliminating the influence of the weight of the engine simulation part on the loading error; the X-direction loading executing mechanism is mounted on the large bottom plate; the Z-direction loading executing mechanism is mounted on the large bottom plate; the Y-direction loading executing mechanism is mounted on the large bottom plate; the bottom of the three-direction loading connector is fixedly connected to the engine simulation part, and the upper portion of the three-direction loading connector is connected with the X-direction loading execution mechanism, the Z-direction loading execution mechanism and the Y-direction loading execution mechanism; the torque loading executing mechanism is mounted on the large bottom plate; meanwhile, the invention also provides an engine mounting bracket fatigue test loading method.

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.

An apparatus for aircraft propulsion includes a propeller and a hybrid-cooled electric engine mounted to a support structure and configured to rotate the propeller. The electric engine is located in an enclosure, with a first heat transfer element thermally coupled to the electric engine via a fluid flow path, partially located outside the enclosure. A second heat transfer element, integral to or thermally coupled to the electric engine, provides air cooling. Both heat transfer elements are housed within the aircraft's support structure. At least one air inlet on the upper side of the support structure receives propeller downwash. A first cooling path directs a portion of the downwash from the air inlet to the first heat transfer element, and a first air outlet exhausts the downwash.

A front engine attachment system for an engine having an engine pylon with a nose having a main female clevis and a cylindrical housing, a main rod fastened to the engine by a secondary ball joint connection about a secondary axis, a main shaft realizing a main ball joint connection of the main rod in the main female clevis about a main axis, wherein the main axis and the secondary axis are in the same vertical plane, a hollow outer cylinder with a vertical axis, of which a first end is fastened in the cylindrical housing and of which a second end is mounted so as to be able to move, via an annular linear connection, with respect to the front casing and an inner cylinder threaded and fastened in the outer cylinder.

An apparatus for aircraft propulsion includes a propeller and an electric engine mounted to a support structure and configured to rotate the propeller. The electric engine is located in an enclosure, with a heat transfer element thermally coupled to the electric engine, An air inlet is located at an upper side of the support structure and the air inlet is configured to receive downwash from the propeller. An air outlet is located at the upper side of the support structure, and the air outlet is configured to exhaust the downwash from the heat transfer element.

A ride-on power trowel has first and second engines mounted to a rigid frame. Each of first and second drive loops have a hydraulic pump powered by such an engine and a drive motor powered by the hydraulic pump. Rotor assemblies are coupled to the drive motors and configured to contact a concrete surface beneath the frame. A feedback controller sets rotor speed in each assembly to a power limited speed based on loads sensed in the drive loops. The power limited speed is an estimated maximum rotor speed achievable for the highest sensed load, which may be affected by operating data received from the engine associated with the highest sensed load.

A fuel reforming system includes a reciprocating engine; a decomposer that decomposes a hydrocarbon fuel; and a hydrocarbon fuel supply device. The reciprocating engine includes an intake port, an exhaust port, and a third port that allows a cylinder and the decomposer to communicate and that is opened and closed by an on-off valve. The on-off valve opens in a stroke in which a combustion gas inside the cylinder is supplied to the decomposer with ascending of a piston. The on-off valve opens in a stroke in which a combustion gas, in which the carbon and the hydrogen gas has been removed, is introduced from the third port to the cylinder with descending of the piston. The hydrocarbon fuel supply device injects the hydrocarbon fuel into the third port between the on-off valve and the decomposer during a stroke in which the on-off valve is closed.

A tuning element that can be integrally formed with a resilient body of a bush and configured to reduce dynamic stiffness increases associated with eigenmodes of the resilient body within a predetermined operational vibration frequency range. The tuning element may resemble an upstanding wall or wing on an outer surface of the resilient body. The resilient body may comprise a plurality of radial arms having axial passageways therebetween. The tuning element may bridge the passageways. A bush configured in this way may be particular suitable for use in scenario where the operational vibration frequency range comprises high frequency, such as an engine mount for an electric vehicle.

A tubular vibration-damping device for a motor mount including: a first molded article including: an inner shaft member; an intermediate sleeve receiving the inner shaft member being inserted therein; and an inner rubber elastic body connecting the inner shaft member and the intermediate sleeve elastically in a radial direction; and a second molded article including: an outer tube member; and an outer peripheral rubber elastic body being bonded to an inner surface of the outer tube member, wherein the intermediate sleeve of the first molded article is fitted radially into the outer peripheral rubber elastic body of the second molded article so as to combine the first molded article and the second molded article in a non-adhesive manner.

The utility model discloses a crop cultivation machine tool, a power traction mechanism takes a tractor as traction power, the tractor comprises a front frame and engine mounting frame welding group, a front wheel and steering group, a rear axle frame gearbox rotary cultivator general assembly, a rear frame, a positive and negative thread connecting rod, an oil cylinder and an engine, and the rear frame comprises a sliding outer square tube; the front frame and engine installation frame welding set comprises a front frame, an engine installation frame and a sliding inner square pipe, the engine is installed on the engine installation frame, the engine installation frame is installed on a sliding outer square pipe, and the sliding inner square pipe is sleeved with the sliding outer square pipe. The rear axle frame gearbox rotary cultivator assembly comprises a rear wheel set, a gearbox, a cultivation operation machine tool, a fixing square pipe and a height adjusting connecting device, the gearbox is hinged to a rear frame, the gearbox is in transmission connection with an engine through a V-shaped belt, the gearbox and the engine move synchronously, and the rear axle frame gearbox rotary cultivator assembly is simple in structure, small in size, flexible in operation and diversified in function.

An aircraft comprising at least one engine mounting system which connects a propulsion unit and a wing and which comprises a primary structure, engine mounts connecting the primary structure and the propulsion unit, as well as at least first, second and third wing mounts connecting the primary structure and the wing structure, the first and second wing mounts being offset height-wise with respect to one another, the third wing mount being offset in the longitudinal direction toward the rear with respect to the first and second wing mounts.

Provided is an engine control device that suppresses the occurrence of a torque shock at the time of resuming from a fuel cut and suppresses deterioration of a combustion state. A control device for an engine mounted on a vehicle, the control device being provided with: an acquisition unit that acquires an engine speed and atmospheric pressure when there is a request to restore from a fuel cut; a recovery control unit that delays the ignition timing at the time of recovering from the fuel cut from the MBT ignition timing by a predetermined retardation amount and executes a recovery process for recovering from the fuel cut; and a retardation amount control unit that reduces the retardation amount as the engine rotation speed is higher, and increases the retardation amount as the atmospheric pressure is lower. The retardation amount control unit increases a reduction rate, which is a reduction amount of the retardation amount with respect to an increase in the engine rotation speed, as the atmospheric pressure is lower.

The utility model relates to the field of all-terrain vehicles, and particularly discloses a UTV vehicle engine mounting structure which comprises a vehicle frame. The engine system is arranged on the frame; the engine system is provided with a motor and a gearbox, the gearbox is installed on the frame through a fixing piece, the frame completely wraps the gearbox, the motor is located at one end of the gearbox, the end, away from the gearbox, of the motor is located outside the frame, and the end, located outside the frame, of the motor is connected to the frame through a supporting piece so that the two ends of the frame can be kept stable. The method has the effect of improving the transverse stability of the vehicle.

The present invention discloses an engine mount durability test equivalence method and system. The method comprises: obtaining load data of the engine mount under a vehicle durability test condition, the load data including at least the maximum, minimum, and root mean square (RMS) values ​​of the acceleration load of the engine mount in a preset direction; sorting the test conditions in sequence according to preset rules based on the maximum, minimum, and RMS values ​​of the acceleration load of the engine mount in the preset direction, and obtaining a sorted table of the test conditions in the preset direction; obtaining multiple target conditions arranged at preset positions from the sorted table, and determining a target test condition based on the multiple target conditions; and using the target test condition for the durability test of the engine mount. The present invention solves the problem of low efficiency of engine mount durability testing in the prior art.

The present invention discloses a noise-reducing engine base and a method thereof, relating to the technical field of engine bases. The present invention includes two engine mount rubber bodies. Each engine mount rubber body includes an alloy upper housing. Inside the alloy upper housing, a rubber shock absorber is fixedly installed. The bottom of the rubber shock absorber extends downward outside the alloy upper housing. A plug-in member is provided at the top of the alloy upper housing. By providing a detection assembly, when the automobile engine emits obvious noise or the vehicle body has abnormal vibration, the external detection electric push rod will drive the external pressure sensing head to squeeze the rubber shock absorber, judge the elasticity and toughness of the pressure-bearing area of the rubber shock absorber, obtain the current hardness and aging degree of the rubber shock absorber, directly detect the condition of the engine mount rubber body, investigate the causes of abnormal engine noise and vehicle body vibration, the process is simple and fast, and at the same time, reference data can be provided for the replacement and maintenance of the engine mount rubber body.

A vehicle diagnostic device for diagnosing a pressure sensor, which is used in a vehicle including: an engine mounted on an exhaust pipe with a filter for collecting particulate matter; a pressure piping branching from an upstream side of the filter of the exhaust pipe and bypassing the filter and connecting to a downstream side of the filter; and a pressure sensor mounted on the pressure piping and detecting a pressure of air in the pressure piping, wherein the execution of the diagnosis of the vehicle using the pressure sensor is prohibited, and in a case where freezing of water in the pressure piping is estimated, the execution of the diagnosis of the vehicle using the pressure sensor is permitted when the integrated value of the time traveled at a low speed exceeds the time determination value after the warm-up of the exhaust pipe is completed.

This invention provides a helicopter-mounted seeding device based on a novel broadcasting technology, relating to the field of broadcasting technology. The helicopter-mounted seeding device includes three outriggers with isosceles triangular endpoints and a hopper fixed between the three outriggers. Two of the outriggers running longitudinally are each fixedly equipped with stabilizing rudders to increase balance. On opposite sides of the three outriggers, from top to bottom, are an upper beam, a connecting beam, and a lower beam. The connecting beam is triangular and includes a left connecting beam, a rear connecting beam, and a right connecting beam. A power supply is mounted at the midpoint of the upper end of the rear connecting beam via a power mounting plate. Gasoline engine mounting plates are mounted on the upper ends of the left and right connecting beams via No. 4 bolts, and a gasoline engine is mounted on the gasoline engine mounting plates. This invention not only meets the requirements for aerial seeding of various crops but also reduces the impact of cylindrical circulation and increases the balance of the hopper by adding a stabilizing rudder structure.

The invention provides a generator set test run quick-mounting device and a working method, relates to the field of test run devices, and aims to solve the problems of poor applicability and low test run efficiency of a current generator set, the distance between a generator mounting position and an engine mounting position of a base can be adjusted according to different equipment sizes to adapt to different types of generators and engines; the connecting assembly adapts to interfaces of different devices through the adapter flange and the flywheel connecting disc, and spline fit can be compatible with shaft diameter differences within a certain range. Meanwhile, axial dimensional deviations of different devices can be compensated through stretching and retracting of the elastic pieces and sliding of the spline sleeves, racks do not need to be customized for specific devices, the applicability is improved, transmission connection of the connecting assemblies is achieved through tooth-shaped matching of the spline shafts and the spline sleeves, bolts are not needed, preliminary connection can be completed only by aligning the spline sleeves with the two spline shafts in the butt joint process, and the butt joint efficiency is improved. And the assembly steps are greatly simplified.

The invention provides an engine support and a carrier rocket. The engine support is applied to a carrier rocket and comprises a support body and a mounting frame, the support body is in a table shape with a closed first end and an open second end, and the diameter of the first end of the support body is smaller than that of the second end; the first end of the support body is provided with an engine installation face used for being connected with a two-stage rocket engine, the second end of the support body is used for being connected with the bottom of a propellant storage box, and the outer wall face of the support body is used for installing engine equipment. The mounting frame is arranged on the outer wall face of the support body and used for being detachably connected with a servo swing mechanism of the two-stage rocket engine. The support body is arranged to be table-shaped and arranged at the bottom of the propellant storage box, the size and weight of the engine support can be reduced, and the weight of a carrier rocket can be reduced.

Methods and systems are provided for an engine. In one example, a method includes adjusting a stiffness of an engine suspension unit in response to outputs from the engine and the electric motor. The stiffness increases as an engine power output decreases.

1. Name of the design product: Left engine mount support assembly (TA60-1001500BJ). 2. Use of the design product: Left engine mount support for vehicles. 3. Design key points of the design product: Lies in the shape. 4. Picture or photo that best shows the design key points: Perspective view.