851 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.

A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, 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 gear train.

Embodiments of the present disclosure describe a snowmobile including an engine mounted on the chassis, a drive track in contact with the chassis, and a drive train, operatively interconnecting the engine with the drive track for delivering propulsive power to the drive track. The drive train includes a driveshaft, comprising a tubular driveshaft including two or more interior channels, the channels positioned in a substantially longitudinal orientation, two or more sprocket driving features on an exterior surface of the tubular driveshaft, and one or more fitting components, positioned at one or more distal ends of the driveshaft.

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.

An aircraft propulsion unit with an engine mount connecting a rigid casing, supporting a propeller, and a structure. First and second transverse link rods connect the casing and the structure with first and second joints each having an axis of pivoting substantially parallel to an axis of rotation of the propeller. First and second thrust rods connect the casing and the structure by first and second thrust rod connections. The first and second thrust rod connections separated from one another in the longitudinal direction. A longitudinal end stop is configured to limit the movement of the casing with respect to the structure in at least the longitudinal direction. An aircraft with at least one such propulsion unit.

The invention discloses a film covering, fixed-point film breaking and soil covering all-in-one machine, comprising: a moving unit comprising a frame, a first gasoline engine mounted on the frame, traveling wheels mounted on the frame, and a transmission part having a first transmission wheel; the film breaking unit comprises a second transmission wheel rotatably mounted on the frame, a crank rocker arm mechanism connected with the second transmission wheel, a film breaking rod mounted on the crank rocker arm mechanism and a drill bit mechanism mounted on the film breaking rod, and a transmission chain is mounted between the second transmission wheel and the first transmission wheel; the film mulching unit comprises a film cylinder frame, a film pressing wheel and a soil guiding wheel which are sequentially installed below the frame and in front of the drill bit mechanism from front to back, and the film pressing wheel and the soil guiding wheel are located on the two sides of the frame respectively; according to the equipment, two links of film mulching and fixed-point soil covering are seamlessly integrated, the soil filling and hole sealing operation procedure is moved forwards, the problem that labor is difficult to use in the links is effectively solved, and meanwhile convenience is provided for subsequent transplanting operation.

An aircraft hybrid motive power source system includes: a gas turbine engine mounted on an aircraft and including a low-pressure shaft and a high-pressure shaft as rotary shafts; a first motor generator drivingly connected to the high-pressure shaft; a second motor generator drivingly connected to the low-pressure shaft; a fuel cell to which a fuel gas and an oxidant gas are supplied; a fuel gas generator configured to generate the fuel gas from a raw material by heating using an exhaust gas from the gas turbine engine; and a controller configured to supply an electric power of the fuel cell obtained by a supply of the fuel gas to one of the first motor generator and the second motor generator, based on at least one of information indicating an operating status of the gas turbine engine and an electric power demand of the aircraft.

Embodiments relate to an outboard engine mount bracket that may be fastened to a transom and mount an outboard engine without requiring modification of the transom. The bracket comprises a first plate, a second plate, and at least one riser positioned between and secured to the first plate and the second plate. The bracket offsets the engine from the rear of the vessel while also providing built-in lift to accommodate larger engines. The bracket allows for adjustments by providing a number of different bracket fastening positions and engine mounting positions.

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.

An engine support assembly for operatively connecting an engine to an aircraft, the aircraft, the aircraft having a support frame surrounded by opposing first and second skins. The engine support assembly broadly comprises first and second support structures. The first support structure is secured to the support frame and extends away from the first skin. The second support structure is releasably connected to the first support structure and releasably connected to the engine.

An aircraft propulsion unit and an aircraft are disclosed, the aircraft propulsion unit comprising a main link for an engine cradle, and two safety links connected in parallel, the two safety links being connected to a front transverse reinforcement of a main structure of a pylon. The aircraft propulsion unit comprises an engine front bracket connecting the main structure of the pylon and the engine, the engine front bracket comprising: a main link positioned between the clevis of the front transverse reinforcement and the clevis of the engine; two safety links arranged on both sides of the main link and around which a clevis is arranged; and a reinforcement connection pin and an engine connection pin connecting the main link and the safety link to the front lateral reinforcement and to the engine. This propulsion unit makes it possible to minimize the number of backup interfaces and maintain the distribution of forces between the nominal configuration and the degraded configuration of the engine front cradle.

A rear engine mounting structure 15, for connecting an engine system (fig.1,1) to an aircraft structure 2, has an elongate body 16 having a first end for connection to an aft side of a turbine exhaust case 6; and one or more mounting points 5 for connection to the aircraft structure. The mounting points are on the elongate body spaced apart from the first end in an axial direction, preferably on a surface of the elongate body. The first end may be connected to either an inner ring (fig.3,12) or an outer ring (fig.3,11) of the exhaust casing. The elongate body may have a polygonal cross-section (fig.8b), and include a lattice of beams (fig.10a). Alternatively, the mounting points are located on an annular body (fig.6c,17) with a number of radial struts (fig.6b,18) connecting it to the centrally located elongate body. The struts may be non-parallel and connect via an inner annular part (fig.6c,17b) of the elongate body, located between the elongate and annular bodies, the circumferential spacing of pairs of struts may be different. The struts may be hollow for conveying fluid. The annular portion may have a number of perforations.

The utility model discloses an integrated power assembly suspension system of an off-highway dumper, which is horizontally arranged and comprises an engine suspension structure, a pair of first connecting pieces, a pair of second connecting pieces, a pair of third connecting pieces, a pair of fourth connecting pieces and a pair of fourth connecting pieces, and the first connecting pieces are symmetrically arranged on two sides of a central surface of an engine flywheel casing in the width direction of a power assembly; the left side and the right side of the front end of the engine are connected with the left frame and the right frame respectively; the gearbox suspension structure comprises a pair of second connecting pieces which are symmetrically arranged on the two sides of the center face of the engine flywheel shell in the width direction of the power assembly, and the left side and the right side of the rear end of the engine and the left side and the right side of the rear end of the gearbox are connected and then connected with the left frame and the right frame. The four-point type suspension system has excellent vibration damping performance, simultaneously avoids stress damage of a flywheel casing caused by insufficient support of a traditional four-point type suspension system on the premise of a large-torque power assembly, thoroughly solves the problem of difficulty in assembly and maintenance, and realizes that a power assembly system can still keep away from an upper wing surface of a frame in a limited frame space. And integrated hoisting and dismounting are completed.

The invention discloses an attitude-controllable multi-rocket engine parallel connection structure which comprises a rack, and a first engine, a second engine, a third engine and a fourth engine which are mounted on the rack and are uniformly arranged along the periphery of a rocket center shaft, a center shaft of the first engine and a center shaft of the second engine are oppositely and obliquely arranged, and a center shaft of the third engine and a center shaft of the fourth engine are oppositely and obliquely arranged. Through the design that the four engines incline oppositely, the pitching, rolling and yawing functions are successfully integrated, and the problem of energy loss during rocket flight is effectively avoided. Meanwhile, a complex swing engine and a matched servo motor thereof in the prior art are abandoned, the system structure is greatly simplified, and the cost is remarkably reduced. According to the invention, the cost is obviously reduced, the performance of the rocket is not influenced, and the balance between cost control and performance expression is realized.

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.

A military vehicle including a chassis, a cab mounted to the chassis and defining a rear wall, an engine mounted to the chassis, a transfer case coupled to the engine and including a driven output providing mechanical power to the military vehicle and a generator output, and an electric machine positioned rearward of the rear wall of the cab and coupled to the generator output of the transfer case and generating electrical power.

To provide a control device for an EGR valve, which can properly control an EGR rate.SOLUTION: A control device is for an EGR valve that opens and closes an EGR pipe of an engine mounted on a vehicle. The EGR pipe is provided with a water cooling type EGR cooler, and the EGR pipe and EGR cooler are exposed to travel wind passing through a grill shutter of the vehicle. The control device for the EGR valve comprises an acquisition unit that acquires the temperature of cooling water introduced into the EGR cooler, a vehicle speed, and the opening degree of the grill shutter, and a correction unit that corrects the opening degree of the EGR valve on the basis of the cooling water temperature, the vehicle speed, and the opening degree of the grill shutter.SELECTED DRAWING: Figure 2

The invention belongs to the technical field of temperature field measurement, and discloses a three-dimensional temperature field sensing device and method. Wherein the three-dimensional temperature field sensing unit comprises a sensor mounting bracket (5), an ultrasonic sensor (6), a first steering engine mounting bracket (1-1), a first 180-degree steering engine (2-1), a first steering engine rotor wing (3-1), a second steering engine mounting bracket (1-2), a second 180-degree steering engine (2-2) and a second steering engine rotor wing (3-2), and the ultrasonic sensor is a transceiving integrated ultrasonic sensor. And the transmitting port and the receiving port are positioned on the same surface of the sensor mounting bracket. The mechanical structure based on the multi-axis holder is designed, the receiving and transmitting integrated ultrasonic sensor is carried, the orientation angle of the sensor is adjusted and fixed through the steering engine, and the three-dimensional temperature field sensing device is suitable for conducting three-dimensional temperature field sensing on a closed three-dimensional space. According to the transmitting-receiving integrated sensor and the multi-axis holder, the arrangement flexibility is greatly improved.

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.

The utility model relates to a testing fixture for an automobile engine mounting bracket. The testing fixture comprises a bedplate, and a normal position detection module and a side position detection module which are arranged on the bedplate, the normal position detection module comprises a first bottom plate transversely fixed to the top of the platen, a supporting plate transversely arranged above the first bottom plate, a plurality of stand columns fixed between the supporting plate and the first bottom plate, two alignment units arranged at the top of the first bottom plate, and a first pressing unit arranged at the top of the first bottom plate and matched with the two alignment units. According to the utility model, the size data of each important part on the engine mounting bracket can be checked, so that the detection result is comprehensive and complete, and the size precision of the engine mounting bracket is ensured; in addition, the working efficiency is improved, and the structure and operation are simplified.

A vibration dampening engine mount configured to mount an engine to a vehicle frame includes: a first bolt receiver having a first through hole configured to receive a first bolt; a second bolt receiver having a second through hole configured to receive a second bolt; and a mass damper connector integrally connecting the first bolt receiver and the second bolt receiver, wherein the vibration dampening engine mount has a predetermined mass.

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.

The utility model discloses a gear hobbing device for machining an engine support, which relates to the technical field of engine support machining and comprises a fixed plate welded on the outer wall of the upper part of one side of a box body, a position adjusting mechanism, a reciprocating machining mechanism and a rotary clamping mechanism, the position adjusting mechanism comprises a sliding groove formed in the top of the fixing plate, a threaded rod rotationally installed in the sliding groove and a T-shaped adjusting base in threaded connection to the threaded rod. Through cooperation of the rotary clamping mechanism and the reciprocating type machining mechanism, the engine support clamped by the three-jaw chuck rotates, and the electric hobbing cutter reciprocates on the surface of the engine support, the surface of the engine support can be subjected to sufficient and uniform hobbing treatment; the gear hobbing treatment effect can be improved; and the cooling assembly is arranged, so that the surface of the engine support in the rotating state can be uniformly cooled, and meanwhile, the reciprocating electric hobbing cutter can be cooled.

The invention relates to the technical field of engine complete machine external assembly quality detection, in particular to an AGV-based engine complete machine external assembly quality detection system, which comprises a vehicle body, a visual detection device and an electric control system which are separated and independent, and is characterized in that the vehicle body is used for fixing and supporting an engine and is provided with a plurality of fixing clamps; the fixing clamp comprises a stand column, a mounting pin and a pressing block, the bottom of the stand column is fixed to the vehicle body, the pressing block is fixed to the top of the stand column, and the mounting pin is detachably connected with the pressing block; during use, an engine shell is located between the stand columns, and the mounting pins are matched with the engine mounting joints to fix an engine. According to the invention, rapid, accurate and automatic detection of gap assembly quality of fasteners such as aero-engine bolts, nuts, insurance and locking plates and three-dimensional pipelines can be realized.