10results about How to "Additional mass is small" patented technology

The invention relates to a dexterous lunar surface operation robot, which belongs to the technical field of aerospace / the field of lunar exploration, and comprises a specially designed mobile lifting system, a mechanical arm operation system, a navigation control system, a communication system, an energy system and a thermal control system, the mode that a foldable suspension supports local lifting of the additional platform is preferably adopted, meanwhile, the scheme that a large mechanical arm and a small mechanical arm are matched for cooperation and a tail end tool can be replaced is preferably adopted, the task operation space is expanded, the task operation height requirement is met, energy is saved, and the problem that in the prior art, the size and the weight cannot be considered at the same time is solved. And the method can adapt to different task scenes so as to solve the problem that in the prior art, the quality and the operation freedom degree cannot be considered at the same time, the operation freedom degree is met, meanwhile, the task reliability is considered, and most tasks can still be completed under the single-arm fault condition.

The invention discloses a large-scale low-speed wind tunnel flutter test full-model support device, comprising a model suspension frame and a plurality of steel cables, a position adjustment mechanism is installed on the model suspension frame, one end of two vertical steel cables is respectively connected to the position adjustment mechanism through a group of suspension springs, and the other end is connected to the model fuselage; the upper and lower ends of the two front steel cables are respectively fixedly connected to the upper and lower walls of the wind tunnel; the upper ends of the two rear steel cables are respectively fixedly connected to the upper wall of the wind tunnel, the lower end of each rear steel cable sequentially passes through the lower wall connection pulley on the corresponding side, the lower wall of the wind tunnel, the counterweight connection pulley and a group of counterweight groups, the two transverse steel cables are respectively fixedly connected to the left and right sides of the model fuselage, the two ends of each transverse steel cable are respectively connected to the front and rear steel cables, and the transverse steel cables are combined with the counterweights to tighten the front and rear steel cables toward the model direction, so that the model can move in multiple directions. The invention has small additional mass and small aerodynamic interference on the model, and is suitable for different models.

A sabot separating structure comprises a blocking cylinder, a sealing cylinder and a supporting assembly. The blocking barrel is connected to the end of the gun barrel, two symmetrically-arranged blocking blocks are arranged on the inner wall of the blocking barrel in the circumferential direction, and the blocking blocks are connected with the blocking barrel through shear pins. The sealing cylinder is matched in the gun barrel and is movably arranged in the axis direction of the gun barrel, a projectile body is arranged at the end, away from the bottom of the gun barrel, of the sealing cylinder, during application, the sealing cylinder enters the stopping cylinder, the end of the sealing cylinder abuts against the stopping block, the shear pin is cut off, and the projectile body is separated from the sealing cylinder; the supporting assembly comprises two supporting modules which are symmetrically arranged and connected to the end of the sealing cylinder, the supporting modules are located in the blocking cylinder, the supporting modules and the blocking blocks are arranged in a staggered mode at intervals, the supporting modules comprise a plurality of supporting rings arranged in the axis direction of the blocking cylinder at intervals, the supporting rings are arc-shaped, the angle between the two ends of each supporting ring is smaller than 180 degrees, and the supporting modules are used for limiting the peripheral side of the projectile body. The device not only can realize quick separation of the sabot, but also can reduce the additional mass of the sabot and reduce the influence on a projectile body during separation.

The invention relates to the technical field of vibration reduction, in particular to a parallel platform vibration suppression device and a vibration suppression method. The parallel platform vibration suppression method is applied to the parallel platform vibration suppression device, the parallel platform vibration suppression device is arranged on an upper platform of a parallel platform, and the upper platform is used for placing a load. The vibration suppression method includes determining an inherent frequency corresponding to a load placed on an upper platform. And according to the inherent frequency corresponding to the load, a virtual vibration absorber is designed. And acquiring the acceleration acquired by an acceleration sensor of the inertial mass actuator, and inputting the acceleration into the virtual vibration absorber to determine the control force generated by the virtual vibration absorber. According to the control force generated by the virtual vibration absorber, the force output by the inertial mass actuator is determined. Therefore, under the condition that the inherent frequency is changed due to the change of the load mass, the vibration suppression of the parallel platform at the inherent frequency can be realized without changing the mechanical structure.

The invention discloses a damping device, a rigid frame bridge and a damping method of the rigid frame bridge, and relates to the technical field of bridge damping. The damping device comprises a mass block, a connecting arm, a damping element, an inerter and a spring; the mass block is movably arranged in a box girder in the bridge direction, the top of the connecting arm is fixedly connected with a top plate of the box girder, the bottom of the connecting arm extends downwards, the mass block is located on one side of the connecting arm, and the two ends of the spring are connected with the connecting arm and the mass block respectively. The two ends of the damping element are connected with the connecting arm and the mass block respectively, and the two ends of the inerter are connected with the connecting arm and the mass block respectively. The anti-seismic capacity of the existing rigid frame bridge and the newly-built bridge can be improved.

The invention discloses a frequency-adjustable bandwidth micro flexible surface acoustic wave sensor and a design and preparation method thereof. Structural design parameters and a structural design range are selected according to structural characteristics of an SAW sensor; structural design parameters, a substrate material and an electrode material are used as optimization objects, eigenvalue quality factors corresponding to all step length nodes of to-be-optimized parameters are obtained through finite element simulation calculation, a proper function fitting method is selected, function fitting is conducted on quality factors corresponding to the to-be-optimized parameters, and the quality factors corresponding to the to-be-optimized parameters are obtained; obtaining a fitting function of the to-be-optimized parameters; and optimizing the fitting function of the plurality of to-be-optimized parameters based on a multi-parameter particle swarm optimization algorithm to obtain optimized structural design parameters of the SAW sensor. A flexible substrate structure is prepared by adopting a high-precision electric field driven spray deposition 3D printing technology, and the whole SAW sensor structure is prepared by utilizing a high-precision photoetching technology. The problems that an existing SAW sensor is narrow in signal resonant frequency, large in size and poor in flexibility are solved, the stability of the SAW sensor in a complex environment is improved, and the measurement range of the SAW sensor in the complex environment is widened.

This utility model discloses a lightweight winding structure for a coreless motor, relating to the field of coil windings. The lightweight winding structure includes a coreless winding in the shape of a sleeve. One end of the coreless winding has a front end cover. On the side of the front end cover near the coreless winding, multiple connecting pieces are distributed at equal angular intervals around the axis of the front end cover. This lightweight winding structure achieves precise weight reduction of the front end cover by opening a first lightweight slot at the position directly opposite the end of the coreless winding and a second lightweight slot on the outer edge. This reduces the added mass of the rotor, thereby reducing rotational inertia, decreasing energy consumption during high-frequency start-stop and high-speed rotation, and improving the motor's response speed and power density.

An elastic wing pulsating pressure test model and a manufacturing method, the test model includes an elastic model body, at least one cover plate and at least one pressure sensor, the model body is provided with a plurality of strip grooves, each groove extends along the length direction of the model body, and is sequentially arranged along the width direction of the model body; each groove is filled with a hard filling material, at least one pressure sensor is arranged in the hard filling material filled in a groove by fixing the filler, the surface of each pressure sensor is covered by a cover plate, the cover plate is provided with a through hole, and the head of the pressure sensor is exposed through the through hole. The elastic wing pulsating pressure test model of the present invention uses an elastic model to measure the pulsating pressure, considering the influence of the fluid-solid coupling effect, and the obtained result is closer to the real flight environment; the additional mass and additional stiffness provided by the hard filling material filled in the model body, the small sensor, and the cover plate are very small, which can make the test result more accurate.

The present application discloses an intelligent health monitoring system for a space solar power station, including a satellite network and a sensor network, wherein the satellite network monitors the overall structure of the space solar power station, and the sensor network monitors the key parts of the space solar power station. The present invention proposes an intelligent health monitoring system for ultra-large-scale flexible structures in space, such as space solar power stations, for monitoring the overall structure and health status of key parts of space solar power stations, and providing protection and guidance for the safe operation and maintenance of power stations on orbit.

The present invention discloses a testing device, a testing method and a system for a farmland pavement spectrum, and belongs to the field of agricultural field soil pavement spectrum testing. The farmland pavement spectrum testing device includes: a laser displacement sensor, a sensor protection device, a multi-channel data acquisition system and acquisition software and a host computer. The testing method includes: using a non-contact measurement laser displacement sensor to measure the elevation (displacement) changes of the four wheel positions and the vertical elevation changes of the center of mass of the whole machine, using MATLAB to calculate the average value and standard deviation of the elevation data, and obtaining the weight coefficients of each wheel and the center of mass through the coefficient of variation method, and taking the weighted average value as the elevation result of the whole machine, and performing a discrete Fourier transform on the weighted elevation data to obtain the farmland pavement spectrum. The above technical scheme has no additional mass for the test system, has little effect on the stiffness and damping of the system, is suitable for the harsh environment of complex farmland opening, has high test accuracy and efficiency, and is easy to operate.