22 results about "Impact pressure" patented technology

The invention discloses an impact pressure loading device and a measuring method.The impact pressure loading device comprises a first pressure bearing surface (1), a second pressure bearing surface (2), a liquid injection pipe (4) and a pressure guiding pipe (7), and the first pressure bearing surface (1) and the second pressure bearing surface (2) are parallel to each other and arranged at an interval to form two opposite end faces of the impact pressure loading device; the first pressure bearing surface (1) and the second pressure bearing surface (2) form a cavity (6), the liquid injection pipe (4) and the pressure drawing pipe (7) are both communicated with the cavity (6) and extend to the outside of the impact pressure loading device, the impact pressure loading device is annularly installed on the periphery of an embedded structure of a test piece according to the embedded structure of the test piece, and the stress module and the impact pressure loading device are installed in an embedded mode. The device and the method are suitable for measurement of different annular belts such as the top, the bottom and the middle part of a reactor pit, meet the pressure measurement requirements of a complex structure at different positions, and provide reliable data support for comprehensive evaluation of structural response.

The invention discloses an excavator return control system which comprises a hydraulic oil tank, a main pump, a main valve, an electric proportional regulating valve, a rotary motor assembly, a controller, a handle operating valve, a pressure sensor A, a pressure sensor B and a pressure sensor C. The electric proportional regulating valve is used for controlling oil pressure between two steering working oil ports A3 and B3 of the rotary motor assembly. The pressure sensor A and the pressure sensor B are used for detecting oil pressure of two steering working oil ports A3 and B3 of the rotary motor assembly, and the pressure sensor C is arranged on a hydraulic pipeline between the handle operating valve and the main valve and used for detecting pilot pressure of a rotary system and transmitting the pilot pressure to the controller. According to the invention, the rotation mode can be selected autonomously according to the specific working condition of operation, the precise control requirement of rotation is met, the rotation starting impact pressure is reduced, and the rotation stopping backswing angle and impact are reduced.

The utility model provides gun bore radial impact load experiment equipment, which relates to the technical field of impact dynamic model devices, and comprises a support frame, a pneumatic loading assembly, an acceleration conduit, an impact rod, an energy collection assembly and an impact pressure reverser, the pneumatic loading assembly is connected with the top of the support frame; the acceleration conduit is connected below the pneumatic loading assembly and is located in the support frame; the impact rod is connected into the acceleration guide pipe in a sliding manner; the energy collecting assembly is connected with the bottom of the supporting frame, the energy collecting assembly and the pneumatic loading assembly are oppositely arranged, and the upper portion of the energy collecting assembly makes contact with a test piece; the impact pressure reverser is connected with a blast hole formed in the test piece and is opposite to the bottom end of the impact rod. The utility model solves the problems in the prior art that the loading of radial impact load is difficult to realize and the equipment is easy to damage or the experimental data is inaccurate.

The application discloses an integrated buffer seal engineering machinery oil cylinder and relates to the technical field of oil cylinders, which comprises a cylinder body, a piston and a piston rod, a buffer seal assembly is arranged outside the piston, the buffer seal assembly comprises a buffer column arranged at the front end and two lip-shaped sealing rings, a base is arranged at the bottom of the cylinder body, a buffer groove is formed in the base, and a throttle hole is formed in the base. The integrated design of the buffer and the sealing structure achieves multistage attenuation of impact load, dynamic adjustment of sealing force and self-adaptive control of oil flow, the cylinder hydraulic pressure dynamically adjusts the throttle hole diameter, cooperates with the multistage buffer structure, and reduces the impact pressure; meanwhile, the temperature self-adaptive flow control system can intelligently adjust the flow rate according to the change of the hydraulic oil viscosity, actively enhances the sealing tightness under high-temperature working conditions, effectively inhibits leakage, automatically optimizes the starting parameters in a low-temperature environment, and improves the equipment response speed.

The invention provides a water jet water column impact pressure intensity determination method. The method comprises the following steps: S1, constructing a water jet water column impact model; s2, the stress area of the impact force sensor is determined, and jet flow parameters are set; s3, a nozzle is controlled to output water jet to the impact force sensor according to the set jet flow parameters, and the current impact force value output by the impact force sensor is obtained; s4, determining the water jet impact pressure according to the impact force value and the stress area of the impact force sensor, and substituting the impact pressure into the water jet water column impact model to determine the coefficient of the water jet water column impact model; s5, determining flushing parameters of the to-be-flushed equipment, and substituting the flushing parameters into the water jet water column impact model to determine the impact pressure intensity of the water jet water column received by the to-be-flushed equipment, through the method, the flushing effect is ensured, meanwhile, no additional damage is caused to the to-be-flushed equipment, no additional test needs to be carried out on the to-be-flushed equipment on site, and the cost is reduced. And the efficiency is ensured.

The invention provides a diesel oil beam drop point position dynamic detection method and device and a medium, belongs to the technical field of internal combustion engine fuel injection detection, and aims at a petal-shaped combustion chamber, micro pressure sensors are reasonably arranged on the inner surface of the petal-shaped combustion chamber to form a detection grid, and the target oil beam drop point position is determined according to parameters of an oil injector. A pressure sensor signal is collected and preprocessed, an oil beam impact pressure field is constructed, and coordinates of a high-pressure area are extracted from the oil beam impact pressure field to calculate the actual oil beam drop point position. And comparing the actual drop point position with the target position to obtain a deviation, and finally averaging the deviation of the plurality of oil beam drop point positions to obtain an average oil beam deviation. By arranging the sensor, oil beam drop point information can be accurately obtained, and the deviation condition between the actual oil beam drop point and a target is mastered. Under the complex working condition of the engine, oil beam injection abnormity can be found in time, and reliable basis is provided for improving engine performance and stability.

The invention relates to the technical field of pressure test equipment, and provides pressure test equipment for automobile parts, which comprises a rack, a lifting plate, a pressure head and a locking mechanism, the pressure head has a static pressure state and an impact state; in a static pressure state, the pressure head is locked on the lifting plate by the locking mechanism, so that the pressure head can be driven by the lifting plate to descend and apply static pressure to a sample below; and in the impact state, the locking mechanism is unlocked, so that the pressure head can fall by virtue of self weight and apply impact pressure to the sample below. According to the scheme, two functions of a static pressure test and an impact pressure test can be achieved on one device, and the limitation that a traditional pressure testing machine is single in function is broken through. By means of the technical scheme, the technical problems that in the prior art, only one type of pressure test can be conducted through one pressure testing machine, and multiple devices need to be used for conducting multiple types of tests are solved.

A pitot system includes a body including an inlet port and a hermetically sealed chamber positioned in the body. The hermetically sealed chamber includes a movable barrier in fluid communication with the inlet port. The pitot system also includes one or more first sensors configured to provide first signals, to a computer, based on deflection of the movable barrier due to impact pressure exerted against the movable barrier by fluid in the body. The first signals correspond to a stagnation pressure of fluid that entered the body via the inlet port.

This invention discloses a method for calculating the impact pressure of an open cavity entering the water under wave conditions, relating to the field of marine engineering technology. It is used to predict the entry process of an open cavity into the water. The method includes constructing a geometric model of the open cavity, constructing a wave field, simulating the motion of the target cavity entering and within the wave field, constructing the time-domain motion equation of the target cavity, solving the time-domain motion equation of the target cavity using numerical integration, calculating the hydrostatic pressure component, the impact pressure component, the air wave pressure component, and the wave-induced pressure component of the target cavity, and decoupling the calculation of the impact pressure based on these four sub-components. This invention improves the accuracy of calculating the impact pressure distribution and time history characteristics of an open cylindrical cavity under wave conditions by establishing a coupled dynamic model of the wave field and the entry process of the open cavity through a multi-phase coupling mechanism.

This invention belongs to the field of automotive technology, specifically a device for testing the compressive strength of a car door limiter housing. The proposed solution includes a base with a support frame mounted on top. A limit bracket is fixedly mounted at one end of the top of the support frame, and a movable seat is slidably mounted in the middle of the limit bracket. A stepper motor for adjusting the movable seat's movement is mounted at the end of the limit bracket. A testing frame is mounted on the top of the movable seat, and a pressure-bearing mechanism is mounted on the top of the testing frame. This invention allows for rapid adjustment of the pressure applied to the door limiter's limiting box. When the driving mechanism drives the pressure adjustment mechanism in a free-fall motion from top to bottom, it applies pulsed impact pressure to the surface of the limiting box, causing deformation of the limiting box. The pressure change detected by the load seat is recorded, and the compressive strength test data of the limiting box is obtained. The test results are accurate and reliable.

A blockage detection system for detecting aircraft probe blockages includes a processor, a communication device, and computer-readable memory. The computer-readable memory encoded with instructions that, when executed by the processor, cause the system to execute a blockage detection algorithm. The processor receives a static pressure and an impact pressure from one or more aircraft probes. The processor converts the static pressure and the impact pressure to a correlating variable, via the blockage detection algorithm. The processor evaluates the correlating variable, via the blockage detection algorithm, to determine if a value of the correlating variable exceeds a threshold indicative of a blockage. The processor outputs a blockage indicator, to a receiving system in response to the correlating variable exceeding the first threshold indicative of a blockage. The processor is further able to determine if the blockage has cleared by reference to an external comparative pressure measurement.

The utility model provides a boss-shaped oil gas seal device which comprises an undercarriage body, the undercarriage body comprises an outer cylinder, a piston rod and a supporting ring, the outer cylinder is arranged on the peripheral side of the piston rod in a surrounding mode, the supporting ring is arranged between the outer cylinder and the piston rod in a clamping mode, and the piston rod is arranged on the supporting ring. The supporting ring is fixed to the end of the outer cylinder, and a rubber ring groove is formed in the side, close to the piston rod, of the supporting ring. The sealing ring assembly is installed in a rubber ring groove of the supporting ring in a nested mode and makes contact with the outer surface of the piston rod, the sealing ring assembly comprises a boss-shaped sealing ring, the boss-shaped sealing ring is provided with a main body part and a protruding part, the main body part is embedded in the rubber ring groove, and the protruding part is embedded in the rubber ring groove. And the lug boss is in contact with the outer surface of the piston rod. The boss-shaped oil-gas sealing device is suitable for oil-gas sealing of an aircraft landing gear buffer, meets the requirements of oil sealing and gas sealing under impact pressure, and improves the sealing effect and reliability of the boss-shaped oil-gas sealing device.

The invention relates to the field of safety engineering, in particular to an energetic material impact safety quantitative characterization device. Comprising a lifting mechanism which is installed on a main body frame and provides kinetic energy for impacting energetic materials; the hammer body is detachably connected with the movable end of the lifting mechanism and is used for impacting the energetic material; the impact supporting mechanism is mounted on the main body frame, is positioned below the hammer body and is used for supporting an energetic material; the monitoring device is mounted on the main body frame and is used for detecting the falling speed, the impact pressure and the sound decibel of the hammer body; and the heating device is mounted on the main body frame and is used for providing initial heat energy for the energetic material. According to the invention, the critical ignition time, impulse and acting of different energetic materials can be obtained as impact safety characterization quantities, and the visualization and quantification of the novel impact safety testing device are realized.

The present application relates to a kind of doing function power test system and test method, belong to doing function power test technical field, solve the problem that the impulse of metal particle composite charge is difficult to test in prior art.The doing function power test system of the present application, comprising: doing test device, dynamic data acquisition system, data processing system, pressure sensor and speed acquisition system;The doing test device is used to acquire the number of metal particles to the piston slide doing work and the motion acceleration of piston slide;The pressure sensor can be used to monitor shock wave pressure value;The speed acquisition system is used to monitor the motion speed when metal particle hits the piston slide;The dynamic data acquisition system can record the waveform and pressure data of test signal;The data processing system is used to process and calculate the data obtained by test.The present application realizes the coupling doing function power test of impact pressure and metal particle and the test result is high in reliability.

The invention discloses a pitot static instrument for determining the airspeed of an aircraft. The pitot system includes a body including an inlet port and a sealed chamber positioned in the body. The sealed chamber includes a movable barrier in fluid communication with the inlet port. The pitot system also includes one or more first sensors configured to provide a first signal based on a deflection of the movable barrier due to an impact pressure exerted on the movable barrier by a fluid in the body. The first signal corresponds to a stagnation pressure of fluid entering the body via the inlet port.

The present invention discloses a light gas gun flyer pressurization device and method, which relates to the fields of impact dynamics and shock wave physics. The device comprises a light gas gun, a detonation driver, flyers, and a target plate. The target plate is arranged at the right end of the detonation driver, and the detonation driver is arranged at the right end of the light gas gun. Flyers are arranged at the end of the light gas gun, between the detonation driver and the target plate. The flyers include a first-stage flyer, a gradient flyer, and a second-stage flyer. The centers of the second-stage flyer, the gradient flyer, and the first-stage flyer are located at the same horizontal height. The present invention adopts the above-mentioned light gas gun flyer pressurization device and method. Based on the impact loading platform of light gas guns such as first-stage gas guns, second-stage gas guns, and hydrogen-oxygen guns, the device and method can significantly increase the speed and impact pressure of the target by adding a detonation driver and gradient flyers to the tail section of the launch tube without changing the structure and launch process of the light gas gun. Compared with a three-stage gun, the experimental cost can be significantly reduced.

The invention discloses a light-gas gun flyer supercharging device and method, and relates to the technical field of impact dynamics and shock wave physics, the light-gas gun flyer supercharging device comprises a light-gas gun, a detonation driver, a flyer and a target plate, the target plate is arranged at the right end of the detonation driver, the detonation driver is arranged at the right end of the light-gas gun, and the flyer is arranged at the right end of the light-gas gun. Flyers are arranged at the end of the light-gas gun and between the detonation driver and the target plate, the flyers comprise a first-stage flyer, a gradient flyer and a second-stage flyer, and the centers of the second-stage flyer, the gradient flyer and the first-stage flyer are located at the same horizontal height. According to the light-gas gun flyer supercharging device and method, on the basis of light-gas gun impact loading platforms such as a first-stage gas gun, a second-stage gas gun and an oxyhydrogen gun, the structure and the launching process of the light-gas gun do not need to be changed, the detonation driver and the gradient flyer are additionally arranged at the tail section of the launching tube, and the target hitting speed and the target hitting impact pressure can be greatly increased; and compared with a three-stage gun, the experiment cost can be obviously reduced.

A blockage detection system for detecting aircraft probe blockages includes a processor, a communication device, and computer-readable memory. The computer-readable memory encoded with instructions that, when executed by the processor, cause the system to execute a blockage detection algorithm. The processor receives a static pressure and an impact pressure from one or more aircraft probes. The processor converts the static pressure and the impact pressure to a correlating variable, via the blockage detection algorithm. The processor evaluates the correlating variable, via the blockage detection algorithm, to determine if a value of the correlating variable exceeds a threshold indicative of a blockage. The processor outputs a blockage indicator, to a receiving system in response to the correlating variable exceeding the first threshold indicative of a blockage. The processor is further able to determine if the blockage has cleared by reference to an external comparative pressure measurement.

The application discloses a kind of real-time autonomous deforming actuators.Executed for receiving external impact pressure in turn delivery, executor includes shell, shortening adjustment structure in shell, lengthening adjustment structure and respectively located transmission rod, adjusting plate etc.at the front and rear end of shell;Transmission rod is pressed into drive pressure change and is transmitted to shortening adjustment structure, lengthening adjustment structure to carry out height support adjustment by adjusting cavity.This application can automatically shorten and adjust the length of executor by the ingenious design and cooperation of mechanical structure, cavity, gas and fluid, and automatically realize without manual intervention, without external power source.

The utility model provides an anti -impact pressure structure and static level gauge, including protection case, is seted up protection cavity on the protection case, four corner places of protection cavity inside all are equipped with angle plate guide rail, install static level gauge body between four angle plate guide rails, the corner side of static level gauge body and be located between angle plate guide rail protection cavity inner wall are connected fixed through connecting piece, connecting piece will static level gauge body limit in protection cavity, the top of the side of protection case is equipped with the installation cavity, install the board in the inside of installation cavity, the top of install the board with a plurality of impact -resistant seat is connected, the utility model has the beneficial effect as follows, the utility model can be installed in the construction site operation, exempts from the destruction of high altitude falling object, can when being impacted by high altitude falling object, can buffer the impact force, can still change the damaged part when the damaged part of the impact -resistant part happens damage.

The invention belongs to the technical field of aviation ground tests, and particularly relates to a system and method for measuring an impact pressure peak value in an oil receiving process, and the system comprises a constant-pressure oil source system, an oil receiving assembly, an impact pressure sensor, a dynamic measuring instrument, a test oil tank, and a test controller. The impact pressure sensor is connected with the constant-pressure oil source system, one end of the oil receiving assembly is connected with the impact pressure sensor, and the other end is connected with the test oil tank. One end of the dynamic measuring instrument is electrically connected with the impact pressure sensor, and the other end is electrically connected with the test controller. The test controller is electrically connected with the constant-pressure oil source system, and the test controller can control the output pressure of the constant-pressure oil source system. Through organic combination of'accurate measurement 'and'flexible simulation', a complete closed-loop test solution is formed. The technical bottleneck that real simulation and measurement cannot be achieved in the prior art is overcome, and qualitative leap is brought to test efficiency, safety and data value.

The invention provides a water jet load reduction device applied to water entry of a navigation body, and relates to the technical field of cross-medium water entry load reduction of the navigation body, the water jet load reduction device comprises a navigation body main body component, a navigation body auxiliary connecting component and a navigation body auxiliary component, the navigation body main body component comprises a water passing bullet, a front water chamber, a piston I, a valve control system and a rear high-pressure air chamber, water is stored in the front water chamber, a piston I is arranged in the front water chamber, high-pressure gas is filled in the rear high-pressure gas chamber, and the valve control system is connected between the front water chamber and the rear high-pressure gas chamber and used for achieving internal communication of the front water chamber and the rear high-pressure gas chamber. The piston I is pushed by high-pressure gas to do rigid motion in the front water chamber, so that water flow is pushed to be ejected at a high speed through the water passing bullet. The controllable water jet is formed by actively releasing the liquid in the front water chamber, inlet water impact pressure is counteracted, meanwhile, structural weight increment and cavitation instability are avoided, and the problems that a traditional passive load reduction technology is low in efficiency and depends on environmental conditions can be solved.