22results about How to "Improve pointing accuracy" patented technology

The invention relates to the technical field of optical systems, in particular to a light beam directivity deviation correction method and system. The method comprises the following steps: acquiring a light spot centroid position offset signal of a light source beam in the camera unit; according to the light spot centroid position offset signal, decoupling control is carried out through a target coupling matrix, and a driving voltage value of the fast steering mirror unit is obtained; the target coupling matrix is used for indicating a coupling coefficient relationship between the displacement change of the fast reflecting mirror unit and the position change of light spots in the camera unit; and based on the driving voltage value, controlling each fast reflecting mirror in the fast reflecting mirror unit to rotate around the respective axis so as to correct the directivity deviation of the light beam of the light source. According to the invention, by introducing the target coupling matrix, the coupling relation of light spot centroid change in the camera caused by angle change of the reflector in the horizontal and pitching directions is successfully eliminated, the problem that the other kind of error rises when a certain kind of error is adjusted is avoided, and accurate control is realized.

The invention discloses a laser orientation instrument which comprises an orientation instrument body, an adjusting ball is fixedly installed at the bottom of the orientation instrument body, the adjusting ball is matched with a mounting base in size, meanwhile, the adjusting ball is movably arranged in the mounting base, a base is fixedly installed at the bottom of the mounting base, and a handle is fixedly installed on the back face of the orientation instrument body. And a laser gun barrel is fixedly mounted on the front surface of the pointing instrument body. According to the laser orientation instrument, by means of friction force among four sets of limiting grooves, limiting strips, positioning columns and positioning holes, the stability of the isolation pipe connected to the outer side of the end of the laser gun barrel in a sleeving mode is guaranteed, loosening is avoided, and due to the arrangement of the isolation pipe, a large amount of external dust can be prevented from entering the inner side of the end of the laser gun barrel; the situation that dust particles enable laser to be scattered or refracted in the emission process, and consequently the direction of a laser beam deviates can be avoided, and the pointing precision of the laser pointing instrument is improved.

The invention provides an inertial navigation error correction method and device based on photoelectric equipment image target detection, and belongs to the technical field of photoelectricity, and the method comprises the following steps: obtaining a photoelectric image of a to-be-detected target based on a pre-correction attitude angle of photoelectric equipment; performing target detection on the photoelectric image to obtain a target deviation angle; obtaining a horizontal coordinate system deviation angle based on the target deviation angle and the image rotation angle; obtaining an inertial navigation correction angle of the photoelectric equipment based on the horizontal coordinate system deviation angle and the tracking turntable direction; and performing inertial navigation error correction on the photoelectric equipment based on the inertial navigation correction angle. According to the inertial navigation error correction method and device based on photoelectric equipment image target detection, the inertial navigation error can be effectively reduced, and the pointing precision of photoelectric equipment is improved.

The invention provides a gesture positioning method and device applied to an intelligent remote controller and electronic equipment, and relates to the field of data processing. According to the method, in the process that a user uses the intelligent remote controller, position change data and posture change data of the intelligent remote controller are obtained; inputting the position change data and the attitude change data into a preset LSTM model to obtain a dynamic pointing area; performing gesture intention reasoning on the dynamic pointing area, and determining a pointing probability corresponding to the dynamic pointing area; if it is determined that the pointing probability meets a preset condition, obtaining a target object from the dynamic pointing region; and sending the control instruction to the target object to control the target object to complete the control operation of the intelligent remote controller through the control instruction. By implementing the technical scheme provided by the invention, the positioning problem of the intelligent remote controller is solved, so that the intelligent remote controller realizes a control effect.

The present invention discloses an antenna optimal working surface fitting method and system based on Latin hypercube sampling, the method comprising: constructing a least squares conditional equation of the initial optimal working surface equation of the reflector antenna; calculating the partial derivative of the least squares conditional equation of the initial optimal working surface equation of the reflector antenna to obtain a normal equation group of the reflector antenna; sampling the panel of the reflector antenna by the Latin hypercube sampling method to construct a reflector antenna panel sampling point set; solving the normal equation group of the reflector antenna according to the reflector antenna panel sampling point set to obtain the optimal working surface equation of the reflector antenna and the optimal design variables of the reflector antenna. The present invention can effectively reduce the root mean square error of the reflector antenna surface and improve the pointing accuracy and antenna gain of the reflector antenna. As an antenna optimal working surface fitting method and system based on Latin hypercube sampling, the present invention can be widely used in the technical field of large-caliber reflector antennas.

The invention provides a laser emission control system capable of monitoring and correcting a transmitting-receiving optical axis, and a light beam output by an emission light source sequentially passes through a transmitting-receiving optical axis monitoring assembly, an optical axis correcting mirror and a telescope and is finally emitted to a target. The same detector is adopted to detect an emission optical axis and a receiving optical axis, and the emission optical axis is adjusted by controlling the optical axis correction mirror, so that an emission light beam and a receiving light beam are coaxial or emitted to a target at a certain advance angle, and high-precision target pointing is realized. Compared with the prior art, the complexity is low, the receiving optical axis and the emission optical axis can be detected under the condition that emission light is not turned off, the emission control technology is not prone to being affected by factors such as receiving light spot intensity, temperature deformation and gravity deformation, and the pointing precision and reliability of a laser emission system can be improved.

The invention relates to a method for eliminating the influence of polarization grating rotation. The method comprises the following steps: firstly, providing a rotation model based on a liquid crystal polarization grating and analyzing a two-dimensional error caused by the rotation of a single grating; mat lab is adopted for simulation, the 10-degree liquid crystal polarization grating is analyzed, and an error value caused in the two-dimensional direction is obtained; secondly, adopting two liquid crystal grating groups through experiments, rotating 10-degree gratings to obtain error data, and comparing the error data with a simulation result to verify the simulation reliability; secondly, carrying out grating rotation error analysis on the two liquid crystal polarization gratings, and respectively fitting an error correction experimental formula and a theoretical formula in a two-dimensional direction; finally, the fitted correction formula is substituted into a system control program, errors caused by grating rotation are corrected, and the light beam pointing precision is improved. The method provided by the invention provides technical support for subsequent application in laser radars, laser weapons and laser communication.

The utility model discloses a small-tonnage forklift body point splicing tool, which belongs to the technical field of machining tools, and comprises a platform, and a limiting seat, a mudguard supporting seat, a connecting plate limiting seat, a plurality of first mudguard limiting seats, a plurality of second mudguard limiting seats and a plurality of oil tank supporting seats which are arranged on the platform, a plurality of first bearings are arranged on each oil tank supporting seat; a ball is arranged on the connecting plate limiting seat; and a second bearing and a roller are arranged on each first fender limiting seat. By means of the platform and the components arranged on the platform, point splicing operation is convenient and fast, point splicing precision and production efficiency are improved, labor intensity of workers is reduced, and welding quality is guaranteed; and meanwhile, through the arrangement of the bearings, the balls and the rollers, sliding friction is converted into rolling friction, manual pushing is facilitated, use of travelling cranes is reduced, scratches can be effectively avoided, and the appearance quality of products is guaranteed.

The invention discloses an antenna pointing correction method based on a theoretical trajectory and an improved genetic algorithm, and the method comprises the steps: constructing an antenna pointing error correction model, extracting correction parameters, carrying out the global optimization of the correction parameters through employing the improved genetic algorithm, and taking a residual matrix as a target value, taking error minimization between azimuth angle and pitch angle deviation predicted values output by the antenna pointing error correction model and a theoretical matrix as a fitness function, performing iterative solution through selection, intersection and mutation operation to obtain an optimal correction parameter group, and completing parameter calibration of the antenna pointing error model; the optimized parameters are fed back to the antenna pointing error correction model, and the antenna pointing error is corrected in real time. According to the method, the convergence speed of the algorithm is higher, a better solution can be found in a shorter time, the global search capability is enhanced, the pointing precision of the antenna is improved, and rapid tower-free calibration of the antenna is realized.

The invention relates to an instantaneous large overload resistant spacecraft structure, which comprises: a main body structure, which comprises a plurality of bearing columns, the outer surfaces of which define a revolution body and are configured to bear an overload impact force; the support beams are arranged between every two adjacent force bearing columns and are configured to provide mounting points for the single aircraft; the end connecting structures are located at the two ends of the main body structure and provided with first threads. The spacecraft structure adopts a gyration body configuration, the stability and strength of the structure are effectively improved, the transverse rigidity of the structure is increased through the gyration body structure, the pointing precision of the spacecraft is effectively improved, the critical yield load coefficient of the structure is increased, and the problem that the structure is damaged due to configuration instability when subjected to large overload impact is solved; and uniform stress of the structure is ensured when the structure bears instantaneous overload, and damage caused by stress concentration is avoided.

The application discloses a kind of virtual reality in cursor adaptive display and control method, it is related to interactive interface cursor adaptive display technical field, solve the technical problem that cursor control accuracy is not high in three-dimensional man-machine interface, visual feedback information is insufficient, its technical scheme main point is based on interactive target prediction technology, the final target control is predicted, and based on this, cursor form control, control pre-naked hand interaction of cursor adaptive display rendering and zoom cursor C / D ratio gain are carried out.Not only the pointing accuracy and efficiency are enhanced, but also the operation of user provides immediate visual feedback, significantly improves the user experience.Meanwhile, the method has high universality, can be well migrated to other three-dimensional man-machine interaction pointing technology.

The invention provides a solar panel driving device control method and device, equipment and a medium. The method comprises the following steps: acquiring a current track illumination state; based on the current track illumination state, corresponding working modes are selected and entered, and the working modes at least comprise a sunshine area working mode and a shadow area working mode; according to the entered working mode, a corresponding driving instruction is generated and output, and the driving instruction is used for controlling movement of a driving mechanism of the solar panel driving device so that the angular acceleration of the driving mechanism can change continuously in the movement process. The scheme is used for solving the problem that the periodic motion of a slip-ring-free swing type SADA in the related technology can influence the attitude stability and the pointing precision of a satellite platform.

This application discloses an automatic calibration method, apparatus, display device, and storage medium. The automatic calibration method obtains a first actual feature value of the current installation position of the transceiver device in the display device, determines target algorithm parameters matching the current installation position based on the first actual feature value and a preset database, and then automatically calibrates the transceiver device according to the target algorithm parameters. The automatic calibration method in this application compares the first actual feature value with multiple standard feature values ​​in the preset database, finds the standard feature value that best matches the current installation position, and loads the preset algorithm parameters corresponding to this standard feature value as the target algorithm parameters. Subsequently, the pointing calculation model can be updated according to the target algorithm parameters to correct angle, distance, and coordinate mapping errors caused by installation position deviations, thereby achieving automatic calibration of the transceiver device and improving pointing accuracy.

The invention provides a background noise determination method and a manufacturing method of a low-noise MHD angular velocity sensor. The background noise determination method comprises the steps that on the basis of appearance data of an upper electrode, a lower electrode, a conductive fluid ring, a magnetic core, a primary winding and a secondary winding in the MHD angular velocity sensor, parameter values of a plurality of equivalent devices included in an equivalent circuit model of the MHD angular velocity sensor are determined, and the appearance data comprise size data, material data and shape data; determining the noise voltage power spectral density of the MHD angular velocity sensor based on the respective parameter values of the plurality of equivalent devices and the turn ratio of the primary winding to the secondary winding; and determining the background noise of the MHD angular velocity sensor based on the noise voltage power spectral density of the MHD angular velocity sensor.

The application discloses a self-adaptive sleeve for hydraulic joint installation and an automatic positioning installation method, and relates to the technical field of hydraulic joint installation, in particular to a self-adaptive sleeve for hydraulic joint installation and an automatic positioning installation method. The self-adaptive sleeve for hydraulic joint installation comprises a stepped spring collet seat, the inside of the spring collet seat is sequentially provided with a first stepped square hole, a second stepped square hole, an inner cylindrical hole and an inner tapered hole from top to bottom along the vertical direction; the side length of the first stepped square hole is larger than that of the second stepped square hole, and the diameter of the outer circle of the second stepped square hole is larger than that of the inner cylindrical hole; a gas cylinder is arranged in the second stepped square hole and fixed on the top end face of the inner cylindrical hole; the spring collet is matched with the inner tapered hole of the spring collet seat, the spring collet is pulled upward and shrunk by the gas cylinder, and then the outer hexagonal size of different specifications of hydraulic joints is adapted, so that the auxiliary time caused by frequent replacement of the sleeve is avoided, and the technical problems that the existing automatic assembly unit of the hydraulic valve quick joint is complicated to install and needs manual assistance are solved.

The utility model discloses a foldable laser frame adjusting device which comprises a vertical frame and a transverse frame, the ends of the vertical frame and the transverse frame are connected in a hinged mode, the upper end of the vertical frame is connected with a first U-shaped frame in a hinged mode, a transversely-arranged connecting plate is fixedly connected to the upper portion of the middle of the first U-shaped frame, and a through hole is formed in the outer side of the connecting plate and used for being fixed to the lower end of a top plate anchor rod through a nut. The free end of the transverse frame is hinged to a second U-shaped frame, the middle of the second U-shaped frame is perpendicularly and fixedly connected with a fixing bolt, the fixing bolt is matched with a nut to be fixedly connected with a laser frame, the vertical frame and the transverse frame are each composed of two long-strip-shaped plates which are spaced by a certain distance, through holes are formed in the ends of the long-strip-shaped plates, and hinge shafts with damping are arranged in the through holes. The device is reasonable in design, compact in structure, flexible in adjustment, convenient to use and carry and not prone to damage, the laser frame does not need to be fixed to a certain anchor rod, the angle and the position are convenient to adjust, and the positioning efficiency and precision of the laser frame are improved.

This invention provides a light-transmitting housing for a lidar and the lidar itself. The light-transmitting housing has a rotationally symmetric structure about the lidar's axis of rotation. The inner surface of the housing is parabolic, and its cross-section along the axis of rotation forms a parabola. The outer surface of the housing, on the cross-section along the axis of rotation, is an even-order aspherical shape corresponding to the parabola. The coordinate system used in the equation of the even-order aspherical shape has its z-axis parallel to the axis of rotation, and the planes containing the x-axis and y-axis of the coordinate system are parallel to the lidar scanning plane. The even-order aspherical shape ensures that a light beam emitted from any height parallel to the x-axis within the xz-cross-section along the axis of rotation is emitted parallel to the x-axis. The defocusing position of the lidar's light source ensures that the absolute value of the difference between the first divergence angle and the second divergence angle is less than a preset threshold. This invention solves the problem of beam deflection and divergence affecting beam transmission characteristics, thus improving the overall performance of the lidar.

The present application relates to a kind of space solar panel servo motor system rigid-flexible coupling modal modeling method, belong to spacecraft dynamics modeling technical field.This method aims to solve the failure of existing analytical model under single-axis large angle rotation and the problem that finite element model lacks explicit mathematical equation and is difficult to be directly used for control system design.The technical scheme is:establishing system geometry model and coordinate system;Adopting characteristic orthogonal polynomial to construct solar panel vibration displacement function;System kinetic energy, strain energy and hinge potential energy function are constructed;Based on Rayleigh-Ritz method, the system modal characteristic equation is established and the natural frequency and vibration mode are solved numerically.This method can realize the accurate modeling of single-axis large range rotation, and directly obtain low-dimensional high-precision explicit mathematical model, which is convenient for docking and co-simulation with control software.

The invention relates to the field of data processing, in particular to a sensing equipment distribution method and device based on clustering, a medium and equipment.The method comprises the steps that according to intersection scores corresponding to all initial intersections, the intersection aggregation degree corresponding to a target area is obtained, and the clustering number N is obtained in combination with shape scores and area areas; the method comprises the following steps: acquiring position coordinates of initial intersections, performing clustering in combination with the position coordinates of the initial intersections to obtain N first clustering sets, acquiring a clustering score according to the number of the initial intersections in each first clustering set to represent the clustering effect of the N first clustering sets, and if the clustering score is smaller than a preset clustering score threshold, determining that the clustering effect of the N first clustering sets is good or bad. If yes, updating the clustering number to W and replacing the clustering number N, repeatedly executing clustering operation until the clustering score is greater than or equal to the clustering score threshold value, obtaining a second clustering set, and arranging preset sensing equipment according to the second clustering set, thereby improving the clustering effect of the initial intersection, and improving the distribution accuracy of the sensing equipment.

The point location device at least comprises a horizontally-arranged workbench, a point location hole vertically penetrating through the workbench, a first point location mechanism and a second point location mechanism, wherein the first point location mechanism conducts point location marking on the position of the point location hole from the upper portion of the workbench, and the second point location mechanism conducts point location marking on the position of the point location hole from the lower portion of the workbench. The device has the advantages of being simple in structure, low in manufacturing cost, high in point location precision and capable of conducting point location marking on the two sides of the clothes cloth at the same time.

The invention provides a load-centered satellite platform cooperative control method, which comprises the following steps of: performing pointing control on a magnetic suspension joint according to attitude deviation and attitude angular velocity deviation of a load platform relative to a load platform rotating coordinate system under a load platform coordinate system; calculating the measurement data of the eddy current sensor of the magnetic suspension joint to obtain the displacement of the magnetic suspension joint so as to control the relative position of the load platform and the satellite platform; according to the expected control moment and the expected control force of the load platform, the output control moment and the output control force of the magnetic suspension joints at different installation positions are determined; calculating an attitude error of the satellite platform relative to the load platform according to the attitude deviation; and controlling the satellite platform according to the attitude deviation, the attitude angular velocity deviation, the displacement, the output control torque, the output control force and the attitude error. According to the scheme, the control precision and the control stability of the load platform are improved, and the control stability of the satellite platform is further improved.

The present invention discloses an ultra-wide spectrum three-pulse LIBS detection system and method for target component detection, which belongs to the field of laser detection technology. The system is mainly composed of a laser component; a primary laser beam expansion and beam combining optical component; a large dynamic adaptive transceiver multiplexing optical component; a spectrum-full waveform detection optoelectronic component; and an acquisition and industrial control component. In the present invention, a three-pulse output design of a high-energy single-wavelength pulse laser and a wide-spectrum tunable OPO laser combined light source is adopted. The plasma is excited by a single-wavelength high-energy laser pulse, and the plasma is synchronously heated by a double pulse output by a wide-spectrum tunable OPO light source. The output wavelength is more flexible, and while heating a wider LIBS spectrum line, the stability of the LIBS spectrum within a larger dynamic distance can be improved, thereby increasing the signal-to-noise ratio of longer-distance detection.