16results about How to "Improve postural stability" patented technology

An attitude dynamic compensation control method for a multi-stage satellite platform with a motion load comprises the following steps: establishing a kinetic model of a scanning accessory, analyzing transmission characteristics of disturbance in the multi-stage satellite platform by combining a motion law of the kinetic model, and designing a feed-forward torque compensation method of an upper platform secondary system; calculating disturbance values of the scanning accessory in the upper platform secondary control period and the lower platform primary control period, and designing an angular momentum attitude compensation method of the lower platform; based on a kinetic model of a multistage satellite, designing a multi-step forecasting algorithm, determining the gain of an observer, and reducing the measurement time delay of the sensor; and calculating the control reaction torque of the upper platform, and dynamically correcting the feed-forward compensation value of the lower platform in real time. The attitude control method provided by the invention can be applied to attitude control of a multi-stage satellite platform and a traditional single-stage satellite platform, and high-precision and high-stability attitude control of a multi-stage satellite can be realized.

This invention belongs to the field of molten salt energy storage technology, specifically relating to a molten salt cryogenic tank with a liquid level-following annular cavity. The molten salt cryogenic tank includes a tank body and a stirrer. The stirrer includes a motor mounted on the top of the tank body, a drive shaft extending into the tank body, and a flow impeller mounted on the lower end of the drive shaft. An inlet and an outlet are provided on the side wall of the tank body. An annular cavity is provided at the molten salt surface. The annular cavity has a hollow structure, and its overall density is less than that of the molten salt, allowing it to float on the molten salt surface and move up and down with changes in the molten salt level. A central opening in the annular cavity allows the drive shaft and flow impeller to pass through. This invention, through continuous regulation of the molten salt near the liquid surface by the annular cavity, weakens the liquid surface temperature stratification and flow stagnation phenomena, raises the minimum temperature inside the cryogenic tank, reduces the risk of molten salt crystallization in the liquid surface area, and improves the safety and reliability of the cryogenic tank operation.

This utility model provides a pneumatic lifting device for electronic trays, including a tray positioning assembly, a drive assembly, and a handling robot. The tray positioning assembly inserts a central positioning cone into the center hole of the tray, and, in conjunction with a pressure plate, clamps the tray to achieve precise vertical positioning. The drive assembly uses a downward-pressing cylinder to drive the limit plate to rise and fall, with linear bearings ensuring stability. The handling robot uses a rotary cylinder, a gripper cylinder, and a synchronous belt mechanism to achieve 45-degree rotation and extend / retract the fork, completing the tray gripping and handling. This device has a compact structure, high positioning accuracy, and strong adaptability, significantly improving the efficiency and stability of automated production, and is suitable for various electronic trays.

The invention relates to the technical field of air inlet grilles, in particular to a sliding type active air inlet grille which comprises a frame, a motor, a driving shaft and blades, the frame is provided with a motor mounting area, a driving shaft mounting area and a blade mounting area, the motor mounting area is located at the end of the frame, the driving shaft mounting area is located above the blade mounting area, and the blade mounting area is located above the driving shaft mounting area. A sliding rail is arranged on the side wall of the blade mounting area; the motor is arranged in the motor mounting area and is used for providing power output; the driving shaft is arranged in the driving shaft mounting area, extends out of the driving shaft mounting area, is connected with an output shaft of the motor and is used for receiving power of the motor and driving the blades to move; the blades are arranged in the blade installation areas and connected with the driving shaft through connecting rod matching pieces, and the ends of the blades are movably connected with the sliding rails through guide shafts. In the using process, the trend of the blades can be adjusted only by adjusting the sliding rails, and the design cost and the manufacturing cost of adjustment can be reduced.

The present disclosure provides a kind of unmanned aerial vehicle control method, device, electronic equipment and storage medium, the method includes: the control execution component of unmanned aerial vehicle is divided, obtains tilting rotor group, fixed rotor group and aerodynamic rudder group;Based on the dynamics characteristics of tilting rotor group and fixed rotor group, obtain low-speed stage control efficiency matrix;Based on the dynamics characteristics of tilting rotor group and aerodynamic rudder group, obtain high-speed stage control efficiency matrix;Through adaptive weight factor, the low-speed stage control efficiency matrix and the high-speed stage control efficiency matrix are weighted and fused, and target control efficiency matrix is obtained.The control energy efficiency matrix obtained by the present scheme can effectively improve the control continuity, attitude stability and working condition adaptation robustness of unmanned aerial vehicle in global flight state.

This invention discloses a tilt-lift short takeoff and landing (STOVL) aircraft and its control method, comprising a fuselage, wing assembly, multi-layered distributed propulsion system, tilt drive assembly, and control unit. The wing is hinged to the fuselage via a pivot in the mid-rear section of the chord, and the tilt drive assembly drives the wing to rotate and adjust the angle of attack. The multi-layered distributed propulsion system includes a first rotor assembly located in the mid-rear section to the wingtip region of the wing and a second rotor assembly located on the lower surface of the wing near the fuselage. During cruise, the first rotor assembly is stopped and feathered, and the propulsion system tilts synchronously with the wing. This invention, through a layered distributed propulsion layout and synchronous wing tilting for synergistic lift enhancement, solves the problems of insufficient control torque at low speeds and high cruise energy consumption, achieving a balance between STOVL performance and cruise economy.

The utility model relates to a connecting piece, a joint structure and a robot, the connecting piece is used for connecting a joint actuator and a base body and comprises a first connecting body and a second connecting body, the first connecting body comprises an actuator connecting part and a brake connecting part, the actuator connecting part is used for connecting the joint actuator, and the brake connecting part is used for connecting the joint actuator. The brake connecting part is adjacent to the actuator connecting part and is used for being connected with a brake for braking the joint actuator; the second connecting body is connected with the first connecting body and used for being connected with the base body. According to the technical scheme, the connecting part used for installing the brake is designed on the connecting piece, the joint actuator is braked through the installed brake, the possibility of redundant motion of the joint is reduced, and when the connecting piece is applied to the humanoid robot exemplarily, the posture stability of the humanoid robot can be improved.

The application discloses a kind of measuring device and method of satellite load active array, belong to satellite internet and 6G non-ground network test technical field.Device includes microwave darkroom, rotary table, multiple probe scanning frame and amplitude and phase controllable synthetic array.Satellite load active array to be measured is placed on rotary table, and radiation aperture is towards upwards;Multiple probe scanning frame is located above rotary table, and multiple antenna probes simultaneously collect near-field signal, and far-field pattern is obtained by near-far field conversion;Amplitude and phase controllable synthetic array is composed of amplitude and phase independently adjustable antenna unit, can be moved into above rotary table, and the electromagnetic wave of setting wave front is synthesized in the quiet zone covering the aperture of array to be measured, or each unit received signal is weighted and synthesized, to complete receiving directional diagram, transmit-receive frequency index, dynamic scene and system level performance measurement.The application shortens measurement distance, and measurement efficiency is improved by one to two orders of magnitude compared with single probe scanning, and flat installation reduces engineering difficulty, supports active array air interface measurement of no feed interface.

The application discloses a head structure for stabilizing the oblique-in-water attitude of a navigation body and the navigation body, and relates to the technical field of navigation body structures, and solves the problem of attitude disturbance caused by complex transient hydrodynamic action, uneven load distribution and transmission during the cross-medium water entry process of the navigation body. The head structure comprises a spherical head, an axial transition section and two execution components, the spherical head is arranged at one end of the axial transition section, and the execution components are arranged on the side surface of the other end of the axial transition section; one side of the spherical head is provided with a spherical surface, the spherical center of the spherical surface is collinear with the axis of the axial transition section; the axial transition section is telescopically arranged at the head of the main body of the navigation body; the execution components are matched with the main body of the navigation body to drive the head structure to move. Through the comprehensive design of the front shape of the navigation body and the structure form between the front shape and the main body, the hydrodynamic load characteristics suffered by the navigation body during the water surface penetration process are improved, so that the sensitivity of the attitude response of the navigation body during the water entry stage is reduced.

The application discloses a curtain wall unit anti-wind swing hoisting device for super high-rise buildings, which is applied to the field of building curtain wall construction and comprises a main hoisting base frame, a limiting top frame mechanism and a protective side frame which are arranged on the main hoisting base frame in sliding cooperation. A top bracing locking assembly is arranged on the protective side frame, a bottom locking assembly is arranged on the main hoisting base frame, and a three-dimensional constraint space is defined through cooperation of the assemblies. A damping extrusion structure is arranged in the space, and a ring-shaped binding mechanism is arranged on the main hoisting base frame in cooperation. In addition, a damping main hoisting assembly is arranged at the top end of the device, damping control assemblies with gravity center control functions are arranged at the bottom ends of the device, and the device is characterized by the following advantages. Through the multi-dimensional adjustment constraint frame and the integrated energy dissipation and damping system, the curtain wall unit swing under the wind field environment of the super high-rise building is effectively inhibited, the posture balance and the structural safety in the hoisting process are ensured, the precision and the efficiency of the curtain wall installation are remarkably improved, and the device has extremely high practical value.

The present invention relates to the technical field of longitudinal unmanned helicopters, and discloses an anti-static and anti-vibration fuel tank for helicopters. A plurality of groups of inner baffles are equidistantly installed in the fuel tank body in a segmented shape through bonding perforated plates. The folding direction of the inner baffles is perpendicular to the blocking surface of the adjacent inner baffles, which can effectively reduce the oil ripples in the front and rear and up and down directions, and weaken the influence of the oil ripples on the attitude of the aircraft. The segmented inner baffles are connected by conductive connecting pieces arranged on the upper part, so that the upper ends of the inner baffles are connected into a whole, which can quickly and effectively release static electricity. The fuel tank body is installed by means of an installation box seat, which not only provides a stable support but also effectively improves the impact protection of the fuel tank. A blowing heating component is arranged on the side of the installation box seat, which can realize rapid preheating and heating of the aircraft oil circuit in severe cold weather, and the heating structure has no direct contact with the fuel tank body, which greatly improves the working safety of the device.

The present application relates to the technical field of adaptive stiffness adjustment. The present application relates to a multi-cavity air spring electromagnetic valve intelligent control adaptive stiffness adjustment system. It comprises a data acquisition module, a data matching module, a standard setting module, an operation prediction module and a stiffness adjustment module; the data acquisition module acquires stiffness adjustment data, driving operation data and driving position data, simultaneously acquires map data, and divides the road section in combination with the driving position data; a correction coefficient is set based on the time proportion of the driving operation type, and the target coefficient is screened in combination with the reference list of the real-time road section, and then the switching rate of the operation type is predicted, so that the stiffness adjustment is changed from the traditional passive triggering to the active prediction, the upcoming working condition change is adapted in advance, the defects that the traditional adjustment technology lags behind the working condition change are effectively solved, the timeliness and accuracy of the stiffness adjustment are improved, and the steering stability of the vehicle under dynamic operations such as steering, braking and acceleration is ensured.

The invention belongs to the technical field of steel pipe machining, and particularly relates to rectangular steel pipe bending equipment which comprises a supporting platform, a positioning mechanism and a bending mechanism. A protection box is arranged on the front side of the middle of the upper end face of the supporting platform, avoiding holes are formed in the middle of the upper end face of the protection box in a bilateral symmetry mode, the positioning mechanism is used for positioning the bent position of a to-be-bent rectangular steel pipe and adjusting the bending radius of the rectangular steel pipe, and the bending mechanism is used for bending the two sides of the rectangular steel pipe at the same time in the bilateral clamping state. According to the rectangular steel pipe bending equipment disclosed by the invention, bending and rolling clamping positioning are synchronously carried out on the two sides, so that the situation that the rectangular steel pipe is crushed due to non-uniform bending moment distribution or excessive concentration in the bending process of the rectangular steel pipe is greatly reduced, and the forming yield of bending of the rectangular steel pipe is improved.

The invention discloses a pneumatic cold ejection device of an extraterrestrial celestial body ascender, and belongs to the field of deep space exploration. The device comprises a heat preservation box body, a heat preservation box cover, a pneumatic piston assembly, an air source assembly, a pressing assembly and a launching guiding and adjusting assembly. The pneumatic piston assembly is composed of a second-stage piston, a first-stage piston, a sealing ring, an inflation connector, a first-stage piston blanking cap, a first-stage piston cylinder, a buffering cushion, an exhaust guide cap and a first-stage piston end cover. The pressing assembly is composed of a bullet lifting beam, a bearing beam, a firer unlocking device and an ascender pressing piece. The launching guiding and adjusting assembly is composed of a guiding support, a guiding wheel and a pressure adjusting valve. The ascender is conveyed to a preset height in a pneumatic cold ejection mode, and ignition take-off conditions are provided; the compression problem of the launching section is solved based on a compression-heat preservation integrated device; based on an adjustable pneumatic piston assembly and an air source assembly, power is provided for launching, and adaptation to the terrain is achieved; the ejection device is prevented from rolling based on the guide assembly, and pneumatic cold ejection of the ascender is achieved.

The invention belongs to the technical field of guidance control, and discloses a solid carrier rocket atmosphere external guidance control method and system, and the method comprises the steps: designing a dual-redundancy navigation system; a new attitude control algorithm; optimizing a track correction module; the performance of the thrust vector control system is further improved through optimization of the thrust vector control TVC system, stable control over the complex attitude outside the atmospheric layer is achieved through the hybrid control technology of the liquid micro-thruster and the solid rocket engine, the attitude regulation and control capacity of the rocket is enhanced through configuration of the multi-redundancy thruster, and the performance of the rocket is improved. And it is ensured that enough control torque and correction capacity are provided in the track transfer process. According to the invention, the navigation precision is improved: through the design of the dual-redundancy navigation system, the precision drift of inertial navigation is greatly reduced, especially in a long-time flight process, high-precision orbit control can be maintained, and the hit rate of a target orbit is improved.