11 results about "Mass system" patented technology

The application discloses a kind of high impact load under spring mass system dynamic response polarized optical measurement system and method, belong to optical measurement technical field, for analog launch load and service load etc. High impact load working condition of spring mass system, by constructing birefringent interference color feature unit on the surface of the base and mass block of spring mass system, using polarization dark field to filter background stray light, cooperate with high-speed camera, so that mass block presents as high-contrast color spot, through HSV color segmentation and relative displacement calculation based on motion coordinate system, the non-contact, clear and continuous measurement of millisecond transient displacement response of mass block is realized.The application effectively fills the experimental measurement blank of high overload dynamics, eliminates the interference of the increased mass caused by the introduction of sensor in contact measurement, and provides high-fidelity visual data support for the dynamic response research of spring mass system in high dynamic environment.

This invention belongs to the field of servo system load trajectory tracking technology, and relates to a command-filtered tracking control based on an extended state observer. The method includes the following steps: establishing a dynamic model and state equations for a two-mass servo system, initializing the system state and system parameters; estimating the load-side information, motor-side information, and total disturbance using an extended state observer; introducing a command-filtered control algorithm to approximate the derivative of the virtual control law, suppressing the differential explosion problem present in the backstepping method, and designing a virtual control function and a load tracking controller. This method achieves effective estimation of the system state and uncertain models, giving the system speed, stability, and accuracy, strong anti-interference capability, and excellent load tracking performance.

The application relates to the technical field of landing gear load calculation, and discloses a landing gear landing load calculation method and device, which comprises the following steps: simplifying a buffer of a landing gear into a two-mass system to obtain an upper mass of an outer cylinder of the buffer and a lower mass of a piston rod, and constructing a target landing relationship function of the buffer according to the upper mass of the outer cylinder and the lower mass of the piston rod; constructing a motion state load function of the buffer, substituting the motion state load function into the target landing relationship function to solve, and obtaining a maximum vertical load parameter of the buffer; determining other load parameters of the buffer according to the maximum vertical load parameter, and determining landing load parameters of the landing gear according to the maximum vertical load parameter and the other load parameters. In this way, the reliability and accuracy of landing gear landing load calculation are improved through the two-mass system model of the landing gear; meanwhile, the landing gear landing load calculation process is simplified, so that the landing load calculation efficiency is improved.

The application provides a kind of rigid-flexible coupling spacecraft nonlinear stiffness softening effect prediction method based on improved multiscale method, the core is to improve the solution format of traditional multiscale method, for accurately predicting the nonlinear dynamic response of rigid-flexible coupling spacecraft, especially reveal the stiffness softening effect caused by coupling nonlinear inertial force and its influence on system stability.The method first establishes the dynamic model of the central rigid body-flexible beam-additional mass system, then obtains the accurate analytical expression through the reconstruction of multiscale method perturbation solution format, not only can clearly reveal that nonlinear coupling inertial force (Coriolis force, tangential inertial force, centrifugal inertial force) is the physical root of the overall stiffness softening of the system, and can quantitatively analyze the contribution of each inertial force, while having the advantages of strong applicability and comprehensive prediction ability.

The invention discloses a control system for water pressure of a strip steel aerial fog cooling nozzle. The method specifically comprises the following steps: respectively setting target water pressure values for two shunting headers on the upper and lower surfaces of cooling strip steel; the actual water pressure is monitored in real time through a water pressure gauge installed on the collecting pipe; water pressure deviation is calculated, and control signals are generated through control algorithms such as PID; the opening degree of the electric flow regulating valve installed on the header overflow pipe is regulated according to the control signal, and the water pressure of the header is accurately controlled by changing the overflow quantity and is stabilized at a set value. The strip steel cooling uniformity and the product quality can be effectively improved, the system response is fast, and the control precision is high.

This invention discloses a vibration reduction method for constant stiffness railway tracks. This method, while ensuring the absolute constancy of the track stiffness, utilizes the resonance principle to achieve effective vibration reduction through vibration absorbers, completely changing the traditional vibration reduction method that reduces track stiffness through a mass-spring system. In this method, vibration absorbers are pre-embedded in the track bed and foundation. Precise resonance tuning achieves the absorption and dissipation of vibration energy in specific frequency bands. The spring stiffness of the vibration absorber is calculated based on its own mass and the frequency band requiring vibration reduction, according to the formula for a single-degree-of-freedom undamped spring-mass system. A precise track-vibration absorber system model is established using a computer for dynamic simulation calculations to predict the system's vibration reduction performance. Based on the feedback information from the calculation results, the vibration absorber parameters and arrangement scheme are readjusted, and simulation calculations are performed again. Through iterative optimization, the vibration reduction requirements are met.

Test bench with torque transducers for measuring torques and a test bench control system, characterized in that the test bench control system is configured to execute a method for calculating the longitudinal acceleration of a motor vehicle with the following features: - The drivetrain, body and axles of the motor vehicle are modeled as a spring-mass system, - the body, axles and drivetrain components are represented as the massed bodies of the system, and the bearings of the components and subframe of the motor vehicle are represented as the springs connecting the bodies, - On the test bench, torques are measured at the wheels of at least one axle of the drivetrain, - a force exerted on the axle at the measured torques along the length of the motor vehicle is calculated and - The longitudinal acceleration of the body resulting from excitation of the system with the force is determined.

The application provides a zero-order horizontal shear wave control method and device and application thereof, and relates to the technical field of metamaterials, and comprises the following steps: based on the anti-resonance principle, a single superstructure unit and a plate structure are divided into unit cells, an equivalent mass is constructed by dividing the unit cells, and a spring mass system is formed; based on Newton's law of motion, a simple harmonic excitation force is applied to the spring mass system, a mass motion control equation is established, the mass motion control equation is solved through an anti-resonance mechanism, and an anti-resonance geometric configuration is obtained; according to the shear deformation characteristics of the zero-order horizontal shear wave, the anti-resonance geometric configuration is derived by combining a cylindrical approximation method and a preset anti-resonance boundary condition, and a superstructure unit geometric parameter scheme is obtained; and based on the optimal size superstructure unit in the superstructure unit geometric parameter scheme, the propagation of the zero-order horizontal shear wave is controlled through superstructure units in different arrangement modes. The application solves the problem that the zero-order horizontal shear wave cannot be accurately and non-destructively controlled effectively.

A method of controlling a gyroscopically-stabilized projectile, comprising a control system producing a control signal, a rotating aerodynamic shell, and a reaction mass system responsive to the control signal, the method comprising: imparting rotational and translational kinetic energy to induce gyroscopic stabilization of the projectile about a gyroscopic axis and a movement of the projectile along a flight path; interacting the shell with surrounding air while moving, to induce aerodynamic forces; generating the control signal from the control system; and altering a state of the reaction wheel system selectively in dependence on the control signal, to alter the flight path.

A method of controlling a gyroscopically-stabilized projectile, comprising a control system producing a control signal, a rotating aerodynamic shell, and a reaction mass system responsive to the control signal, the method comprising: imparting rotational and translational kinetic energy to induce gyroscopic stabilization of the projectile about a gyroscopic axis and a movement of the projectile along a flight path; interacting the shell with surrounding air while moving, to induce aerodynamic forces; generating the control signal from the control system; and altering a state of the reaction wheel system selectively in dependence on the control signal, to alter the flight path.

A clutch torque estimation and control method for vehicle hybrid powertrain includes, in response to detecting a mode transition of the hybrid powertrain that involves a state change of a disconnect clutch arranged between two torque generating systems, initializing a Kalman filter based on a state space model for dynamics of the disconnect clutch, utilizing the Kalman filter to predict estimated speeds and torques for the state change of the disconnect clutch, determining a set of constraints for the state change of the disconnect clutch based on a sign of a slip speed across the disconnect clutch, applying the set of constraints to the predicted estimated speeds and torques to obtain final estimated speeds and torques for the state change of the disconnect clutch, and controlling the disconnect clutch based on the final estimated speeds and torques to improve the mode transition of the hybrid powertrain.