1753results about "Engine testing" 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 relates to the technical field of torque motors, in particular to a torque performance detection system and method for a torque motor. The method comprises the following steps: evaluating the initial performance of the motor by acquiring object data of the torque motor and acquiring structural data; predicting a torque fluctuation dynamic overrun condition according to the initial performance of the motor, further evaluating an electromechanical coupling chain scission effect, and calculating a dynamic thermal load overload degree; evaluating the abnormal condition of the motor, analyzing the operation balance attenuation trend of the motor, and carrying out optimization processing based on the performance attenuation condition and the aging fault probability of the motor; according to the invention, the torque motor is optimized, so that the operation efficiency of the torque motor is higher.

The invention discloses a diversion cooling device and a rocket engine ignition test system, and belongs to the technical field of rocket launching tests. The flow guide cooling device comprises a spraying piece, a flow guide mechanism and a water supply mechanism. The spraying piece is arranged at the initial section of the tail flame of the rocket engine, a water curtain barrier can be arranged through spraying from top to bottom, cooling and noise reduction are achieved, fuel gas of the tail flame is prevented from burning other devices, and the temperature of the cooled tail flame cannot be too high when the cooled tail flame makes contact with the flow guide mechanism, and the flow guide mechanism cannot be damaged; in the flow guide mechanism, a flow guide groove water spraying panel which is in an arc shape and protrudes downwards in an inclined mode and flow guide groove bodies located on the two sides of the flow guide groove water spraying panel are used for conducting comprehensive spraying and flow guide on the high-impact-force and high-temperature tail flame, cooling and noise reduction are achieved, and water spraying areas with different spraying densities can conduct targeted spraying according to the temperature of the inner flame and the outer flame of the tail flame. And the arc plate and the second nozzle are detachable, so that the arc plate and the second nozzle are convenient to replace, assemble and disassemble after a certain part is damaged by high temperature, the cost is reduced, and the use economy is improved.

The invention relates to the technical field of engine testing, and discloses a reliability test method and system for a small general engine, and the method comprises the steps: collecting an engine vibration signal through a superconducting quantum interferometer, and collecting a temperature distribution parameter through a quantum dot temperature sensor; performing combined testing of cold and hot shock, high-load operation and random working conditions, and synchronously monitoring dynamic response characteristic data; constructing a Weibull probability model, and determining key influence factors through a global sensitivity analysis method; acquiring a surface roughness parameter by adopting a field emission scanning electron microscope, obtaining a material component parameter through energy spectrum analysis, and establishing a parameter mapping relation; establishing a vibration and temperature early warning system, executing a graded sweep frequency excitation and abrasive particle acceleration test, and recording a parameter degradation process; and generating a three-dimensional parameter cloud picture, and outputting a reliability test report. According to the method, the reliability of the small general engine can be comprehensively and efficiently evaluated, and a scientific basis is provided for design, maintenance and improvement of the engine.

The invention discloses an instantaneous torque measuring system and method based on the front end of an engine, and relates to the technical field of engine testing and signal processing, and the system comprises a signal acquisition module, a noise analysis module, a signal processing module and a signal processing module, the noise frequency distribution and noise amplitude range extraction module is used for extracting noise frequency distribution and a noise amplitude range from the smoothed torque data and determining filtered torque data containing low-frequency drift noise and periodic interference signals, and the parameter extraction module is used for analyzing the noise frequency distribution and the periodic interference signals by adopting fast Fourier transform according to the filtered torque data so as to obtain the low-frequency drift noise and the periodic interference signals. Acquiring noise duration time and a noise source identifier, and determining an amplitude compensation coefficient and a frequency suppression parameter; according to the instantaneous torque measuring system and method based on the engine front end, accurate acquisition and noise suppression of engine torque signals are achieved, the accuracy and reliability of torque data are improved, and effective support is provided for engine performance monitoring and fault diagnosis.

The invention relates to the technical field of data processing, in particular to an engine running state monitoring method and system, and the method comprises the steps: obtaining a vibration signal and a crankshaft rotating speed signal of an engine in real time, and converting the vibration signal from a time domain to an angle domain by taking the crankshaft rotating speed signal as a reference; performing order spectrum analysis on the vibration signal in the angle domain to generate a real-time order spectrum, and comparing the real-time order spectrum with a reference order spectrum to determine the energy deviation of each order; meanwhile, extracting waveform segments of each order in a plurality of continuous periodic vibration signals, and calculating the similarity between the waveform segments so as to evaluate the morphological dispersion degree and quantify the morphological stability degree; and finally, the energy deviation and the form stability degree are fused, the comprehensive fault risk index of each order is determined, and the operation state of the engine is monitored based on the comprehensive fault risk index of each order. The method improves the accuracy and reliability of engine state monitoring.

The invention belongs to the technical field of aero-engine vibration tests, and particularly relates to an aero-engine vibration assessment test method and system. Comprising the following steps: determining the worst vibration environment of accessories; determining the staying rotating speed of an engine rotor and the staying time of the staying rotating speed; according to the staying rotating speed of the engine rotor and the staying time of the staying rotating speed, a vibration assessment test run spectrum is formulated; based on the worst accessory vibration environment, carrying out an engine complete machine test by referring to the vibration assessment test run spectrum; generating an engine rotating speed and vibration curve graph according to the whole engine test measurement data, and making an accessory vibration limit value; an accessory vibration assessment test is carried out on a complete engine, and the complete engine used in the accessory vibration assessment test simulates the possible maximum vibration environment and test temperature of accessories in a full operation cycle and a full rotation speed range; and the installation and vibration environment is more in line with the engineering practical situation.

The invention discloses a voiceprint monitoring method, system, medium and equipment for rotation stall of an aero-engine compressor, and the method comprises the steps: determining the layout of a microphone array through the model parameters of the compressor of the aero-engine, and carrying out the synchronous collection of sound pressure time domain signals of multiple channels of the compressor of the aero-engine through the microphone array; arranging the multi-channel sound pressure time-domain signals in sequence to construct a time-domain signal matrix; performing spectral analysis on the sound pressure time-domain signals by adopting a fast Fourier transform algorithm to obtain a spectrogram of the sound pressure time-domain signals of each channel, monitoring whether an abnormal single-tone frequency peak value lower than one time of rotation frequency appears in the spectrogram or not, obtaining an acoustic mode spectrogram of the abnormal single-tone frequency peak value by adopting a single-frequency acoustic mode decomposition method, and obtaining an acoustic mode spectrum of the abnormal single-tone frequency peak value; and whether the rotating stall characteristic of the gas compressor occurs in the acoustic mode spectrogram is monitored to judge whether the rotating stall characteristic of the gas compressor occurs or not.

Embodiments of the present application disclose a fuel injection parameter adjustment method, device, equipment and storage medium. The fuel injection parameter adjustment method comprises: determining that a vehicle enters a series-parallel hybrid working condition; recording a set of initial fuel injection parameters of an engine; performing fuel injection parameter self-learning, obtaining a plurality of sets of test fuel injection parameters based on the set of initial fuel injection parameters; sequentially using the plurality of sets of test fuel injection parameters to run the engine, and calculating a plurality of test fuel consumptions of the vehicle; wherein each set of test fuel injection parameters corresponds to a test fuel consumption; the running time of each set of test fuel injection parameters is a first self-learning time; based on comparing the plurality of test fuel consumptions, determining an optimal self-learning result from the plurality of sets of test fuel injection parameters; and replacing the initial fuel injection parameters with the self-learning result.

The invention provides a single-line excitation OH plane laser-induced fluorescence temperature measurement system and method, and belongs to the technical field of aero-engine special tests, the system comprises an Nd: YAG laser, a sheet light shaping lens group, two ICCD cameras and a data acquisition device, the laser outputs quadruplicated pulse laser, the sheet light shaping lens group is arranged at the output end of the laser, and the data acquisition device is arranged at the output end of the laser. Laser sheet light is output through the sheet light shaping lens group to illuminate a to-be-detected area in the flame and reacts with OH groups in the flame to generate fluorescent light; the cameras are respectively arranged opposite to flames, are respectively in communication connection with the data acquisition device, are respectively provided with a band-pass optical filter with different bandwidths, and are used for synchronously measuring fluorescence to obtain a bispectral fluorescence image, and the data acquisition device is used for carrying out data processing on the image to realize two-dimensional temperature distribution measurement. Through the processing scheme provided by the invention, the measurement system configuration and the data processing flow are remarkably simplified, and the light spot quality and the signal-to-noise ratio are improved.

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.

The invention discloses an axial force measuring device and an axial force measuring method.The axial force measuring device is arranged in a bearing seat and located between an axial limiting structure of the bearing seat and a bearing outer ring, the axial force measuring device comprises a first force measuring ring and a second force measuring ring, and the second force measuring ring is sleeved with the first force measuring ring; in the assembled state, the stress end of the second force measuring ring and the stress end of the first force measuring ring have a preset axial dimension difference so that the first force measuring ring can bear the axial force when the axial force is smaller than a preset value. And the first force measuring ring is also used for axially deforming to be matched with the axial size of the second force measuring ring after the axial force is greater than a preset value, so that the first force measuring ring and the second force measuring ring bear the axial force together.

The invention relates to the technical field of aero-engine tests, and discloses a temperature distortion test device and a design method thereof. An annular space between the inner casing and the inner casing forms a mixing space; the connecting assemblies are connected with the outer casing, and part of the connecting assemblies form a conveying assembly; a first input port is formed in one side wall surface of an injection part of the conveying assembly, and a second input port is formed in the other side wall surface; the gas conveying pipeline is connected with the connecting part; according to the invention, the response speed of the control valve is relatively high, so that the gas conveying pipeline can sensitively convey high-temperature gas flow, transient temperature distortion of the temperature distortion test device can be realized, and in addition, the comprehensive distortion effect can be greatly improved in a downstream and countercurrent combined mode; performance indexes of the temperature distortion test device meet test requirements of transient temperature distortion, so that the temperature distortion test device can realize transient temperature distortion by adopting a high-temperature airflow injection mode.

The utility model provides a high-enthalpy pure air heating device which is used for solving the technical problem that according to an existing heating mode, the attributes of incoming flow air and real air are different. The heating device comprises a gas inlet unit, a heating unit and a gas collecting unit, the air inlet unit is connected with the heating unit; the heating unit comprises a shell, and a heat transfer chamber and a combustion chamber which are arranged in the shell; the heat transfer chamber is coaxially installed in the shell, the radial section of the heat transfer chamber is of a circular ring structure, and the combustion chamber is axially installed in the center of the circular ring structure. A plurality of radial channels and axial channels which are mutually independent are arranged in the heat transfer chamber; the two ends of each radial channel communicate with the combustion chamber and the residual gas outlet correspondingly, and the radial channels are used for conveying high-temperature gas. The two ends of each axial channel communicate with the air inlet and the air outlet correspondingly, and the axial channels are used for conveying incoming flow air. And the gas collection unit is used for collecting the high-enthalpy air and transmitting the high-enthalpy air to external test equipment. The device is high in heating speed, and pure high-enthalpy air can be obtained.

The invention belongs to the technical field of engine fault diagnosis, and provides an engine test fault diagnosis method, system and device and a storage medium, and the method comprises the steps: collecting and analyzing engine data, and obtaining a fault data set; converting the fault data set into a target format; dynamically updating the target knowledge graph based on the fault data set in the target format; and inputting the query elements into the target knowledge graph, obtaining fault data of the corresponding engine, and obtaining a fault reason. According to the method, the dynamic target knowledge graph is adopted, after fault detection, the target knowledge graph can be updated according to the data of the engine, the node relation can be automatically expanded in real time, manual intervention is reduced, and more accurate diagnosis is provided for subsequent fault query; according to the method, nodes and fault data can be visualized during query, and an interactive fault diagnosis and learning interface can help a user to quickly position a fault source and accumulate fault detection experience.

An abnormality diagnosis device performs determination for at least one of abnormality of an electric motor driven by an inverter driven at a predetermined operation frequency and abnormality of a motive power transmission mechanism which transmits motive power from the electric motor to a load, wherein spectrum peaks extracted through FFT analysis of detected current of the electric motor are analyzed, and frequencies of spectrum peaks due to noise of the inverter are acquired in advance using the operation frequency and the frequencies of sideband waves with respect to the operation frequency. In abnormality diagnosis, abnormality determination is performed after spectrum peaks due to noise of the inverter are extracted from spectrum peaks extracted through FFT analysis of detected current of the electric motor.

A system for mitigating backsputter to a thruster in a propulsion test facility includes a plate disposed in an output plume of the thruster and a magnetic field generator disposed about or at the plate and configured to generate a magnetic field between the thruster and the plate. The magnetic field generator is oriented such that a magnetic field is generated transverse to the output plume.

The invention discloses a spraying system for an aeroengine icing test and a high-altitude icing simulation test bed, the spraying system comprises a spraying device, the spraying device comprises a spraying support and a plurality of atomizing pipe groups, and the plurality of atomizing pipe groups are detachably arranged on the spraying support. Each atomizing pipe group comprises a heat insulation coating barrel, a plurality of atomizing nozzles sequentially arranged in the length direction of the heat insulation coating barrel, a water supply pipe and an air supply pipe which are arranged in the heat insulation coating barrel in the length direction of the heat insulation coating barrel, and a heat insulation material filled in the heat insulation coating barrel; the inner side end, located in the heat insulation wrapping barrel, of the atomizing nozzle communicates with a water supply pipe and an air supply pipe, the opposite outer side end of the atomizing nozzle extends out of the heat insulation wrapping barrel, and at least one end of the water supply pipe and at least one end of the air supply pipe extend out of the spraying support to correspondingly introduce water and compressed air. According to the invention, the atomization pipe group can be taken out as required for deep maintenance, and meanwhile, the anti-freezing and anti-blocking capabilities of the water supply pipe and the air supply pipe in the test process are improved, so that the long-time duration of the icing test of the aero-engine is ensured.

The invention discloses a solid rocket engine in-situ heat preservation ignition test run frame which comprises a fixing base, a movable fixing plate, a supporting assembly, a force bearing pier, a first force transmission piece, a second force transmission piece, a force measuring piece, a heat preservation bottom plate and a heat preservation cover. A solid rocket engine to be tested is movably arranged on the movable fixing plate through the two supporting assemblies, and the movable fixing plate is connected to the fixing base through the multiple plate springs. The heat preservation bottom plate is arranged on the lower side of the movable fixing plate, the heat preservation cover is buckled on the heat preservation bottom plate, cold air is conveyed into the heat preservation cover through the cold air connector, the solid rocket engine to be tested can be cooled, and when the temperature of the solid rocket engine to be tested reaches the temperature required by testing conditions, the movable door is opened, and the solid rocket engine to be tested is ignited. And the force measuring piece can obtain thrust data of the solid rocket engine. The solid rocket engine in-situ heat preservation ignition test run rack can accurately simulate the thrust test of the solid rocket engine in an ultralow-temperature working environment.

The invention relates to the technical field of rocket engine simulation tests, in particular to a tool and a process for installing an ejection system of a vertical high-altitude simulation test bed. Comprising a cabin bottom platform which is arranged on the ground and located above the plane of a fuel gas diversion trench; the mounting hole is formed in the cabin bottom platform, and a vacuum cabin flange located in the mounting hole is arranged at the bottom end of the vacuum cabin; and the ejection system flange is arranged on the ejection system in a sleeving manner and is suitable for being connected with the vacuum cabin flange. In the application, the plane of the fuel gas diversion trench can be used for placing an injection system, and a vacuum cabin flange can be arranged in the mounting hole and can be connected with an injection system flange. The lifting part is used for lifting the injection system, and lifting force in the vertical direction can be converted into lifting force in the horizontal direction, so that the lifting part can penetrate through the vacuum cabin door to be arranged on the inner side of the vacuum cabin, the requirement for the height of the lifting part is lowered, and interference between the lifting part and the upper space of the vacuum cabin is avoided.

A snake-arm robot and a servicing device are mechanically coupled. The mechanical coupling is accomplished by a longitudinal insertion of the snake-arm robot into the servicing device or the servicing device into the snake-arm robot. An actuator moves the snake-arm robot through a passage within an engine until the snake-arm robot reaches a desired location. The movement of the snake-arm robot concurrently moves the servicing device through the passage. Subsequently, the snake-arm robot is de-coupled from the servicing device and the snake-arm robot is removed from the engine while leaving the servicing device in place within the engine.

The invention belongs to the technical field of aero-engines, and particularly relates to an array type energy absorption target plate. Comprising a support frame; the multiple knife-shaped columns are fixed to the supporting frame at intervals, and cutting edges of the knife-shaped columns face the throwing direction of an impact object; the energy absorption turning plates are hung between the adjacent knife-shaped columns in a turnover mode through rotating shafts and arranged into a multi-layer array in the vertical direction, and the energy absorption turning plates are configured to turn over when being impacted so as to allow an impacted object to pass through and absorb kinetic energy of the impacted object; the inclined back plate is obliquely arranged on the side, opposite to an impact object, of the array type energy absorption turning plate, and the projectile body collecting box is located below the inclined back plate and used for collecting the impact object penetrating through the energy absorption turning plate array.

The invention belongs to the technical field of aero-engine component test environment construction, and provides a dynamic variable speed air inlet channel test method and system under continuous air supply and exhaust conditions, and the method comprises the steps: constructing a spray pipe profile, a tester spray pipe inlet and outlet pressure ratio, air supply and exhaust pressure and a sub-model which is continuously adjusted along with the speed and is used for balancing the flow; inputting a dynamic change requirement of a target speed along with time in a continuous variable speed test under the condition of not stopping air supply into each control sub-model, and establishing a variable speed regulation model of a spray pipe profile, a pressure ratio of an inlet and an outlet of a tester spray pipe, air supply and exhaust pressure balance, a test piece posture and the like along with time in combination with a control rule of each execution mechanism; and a continuous variable-speed flow field meeting variable-speed and time requirements under the condition of uninterrupted air supply and extraction is carried out. According to the method, the blowing test with the speed continuously and dynamically changing can be carried out under the conditions of not stopping air supply and not interrupting operation of a tester, and reliable test data support is provided for design and optimization of an air inlet channel of an advanced aircraft.

The invention relates to a testing device (10) for electric drive units, comprising a receptacle (12a, b) for an electric drive unit (14) and two output shafts (16) which can be coupled to an electric drive unit (14) at either end, wherein the two output shafts (16) are each coupled to a separate output motor (20) which can drive the electric drive unit (14) in motor operation and / or load it in generator operation, characterized in that each output motor (20) is coupled to the associated output shaft (16) via a gear (22).

The invention discloses an optical measurement device for an engine flow field, and relates to the technical field of optical measurement. The transmitting end module and the receiving end module are arranged on two walls of an engine to be tested and are provided with opposite lens type end caps; the transmitting end module comprises a built-in metal coating high-temperature single-mode optical fiber; one end of the single-mode optical fiber is connected with a lens type end cap of the transmitting end module to form an integrated laser transmitting probe; the receiving end module comprises a built-in metal coating high-temperature multimode optical fiber and a detector; one end of the multimode optical fiber is connected with a lens type end cap of the receiving end module to form an integrated laser coupling probe; and a receiving and transmitting light path pair penetrating through an engine combustion area is formed between the lens type end caps of the transmitting end module and the receiving end module. Water vapor between a window sheet and an optical probe collimating lens and between the collimating lens and an optical fiber core in a traditional measurement module is eliminated, and the measurement precision of an engine flow field combustion area is improved.

A device and a method for predicting exhaust emissions of a gasoline engine (10) with an exhaust gas aftertreatment system (22) are proposed, which has a first lambda probe arranged downstream of combustion chambers (15) of the gasoline engine (10) and upstream of a first three-way catalyst (26) arranged closest to the combustion chambers (15) of the gasoline engine (10), and which has a second lambda probe arranged downstream of the first three-way catalyst (26), downstream or upstream of a first gasoline particulate filter (30) and upstream of a second three-way catalyst (32), and which has an engine control unit (36) in which an emissions model (42) is integrated, which has a combustion raw emissions model (44) via which raw emissions are calculated from the operating data of the gasoline engine (10), and has an exhaust gas aftertreatment model (46),via which the emissions at the outlet of the exhaust aftertreatment system (22) are calculated from the raw emission data. A first combustion air ratio in the exhaust stream is measured by means of the first lambda probe (24) to determine a first injected fuel mass, and an injected fuel mass is calculated as a function of the measured values of the first lambda probe (24), which serves as the input value of the emissions model (42). From this, the exhaust emissions at the outlet of the exhaust aftertreatment system (22) are subsequently calculated.

The invention discloses a steam turbine efficiency measurement method and system, and relates to the technical field of steam turbine efficiency measurement, and the method comprises the following steps: correcting a plurality of groups of measurement data of a steam turbine under different steady-state working conditions, and obtaining corresponding measurement data correction values; the uncertainty of the corresponding steam turbine efficiency is obtained by measuring a covariance matrix between the data correction values; inputting the multiple groups of measurement data and the standard steam turbine efficiency under the dynamic working condition into an extended Kalman filter as a system state to obtain the corrected steam turbine efficiency and the corresponding uncertainty under the dynamic working condition; and fusing the steam turbine efficiency and the uncertainty of the steam turbine efficiency under any steady-state working condition with the steam turbine efficiency and the uncertainty of the steam turbine efficiency under the corresponding working condition in the dynamic working conditions to obtain an optimal estimation value of the steam turbine efficiency. According to the method, more accurate measurement data are obtained by combining the steady-state measurement data and the dynamic measurement data, and the accuracy of steam turbine efficiency estimation is improved.

The utility model discloses a special parameter measuring device for an engine, which relates to the field of engine parameter measurement and comprises a main body platform and a C-shaped tool frame, a measuring platform is arranged on the main body platform, and weighing sensors are arranged at four corners of the bottom of the measuring platform. The measuring platform is symmetrically provided with two groups of mass center measuring mechanisms along the axial direction of the C-shaped tool frame, each mass center measuring mechanism comprises a measuring seat and two roller supports, the measuring seat is slidably mounted on the measuring platform, the top of the measuring seat is open, and the two roller supports are mounted in the opening of the measuring seat and are arranged at intervals along the radial direction of the C-shaped tool frame; the C-shaped tool frame comprises two C-shaped pieces, the two C-shaped pieces are located in the openings of the two measuring bases respectively and supported through the roller supports, the two C-shaped pieces are connected together through the connecting rods, the mass center, the rotational inertia and the mass of the engine can be measured without disassembling each part of the engine, the measuring operation is simplified, and the measuring precision is improved.

The utility model relates to the technical field of engine detection tools, in particular to an automobile engine skirt frame detection tool which comprises a bottom plate, a placement mechanism is arranged on the bottom plate, a clamping mechanism is arranged on the placement mechanism, a flow guide mechanism is arranged on the bottom plate, and the flow guide mechanism comprises a connecting shaft and a flow guide plate. A flow guide plate is rotationally connected to the bottom plate through a connecting shaft, a clamping groove is formed in one end of the connecting shaft, a clamping pin is inserted into the bottom plate, an inserting hole is formed in the position, on one side of the clamping pin, of the bottom plate, a collecting mechanism is arranged on the bottom plate and comprises a collecting frame, and one side of the bottom plate is fixedly connected with the collecting frame. A push plate is slidably connected into the collecting frame. According to actual conditions, oil stains flowing out of an engine skirt frame can be conveniently collected and treated in a centralized mode, pollution of the oil stains to a detection tool is reduced, and meanwhile follow-up detection work is facilitated.