49results about How to "Flexible posture adjustment" patented technology

The invention discloses an aircraft and a control method of the aircraft. The aircraft comprises an aircraft body, multiple aircraft arms and a power device, wherein the multiple aircraft arms are arranged in the periphery direction of the aircraft body at intervals, the end of each aircraft arm is connected with the aircraft body, at least one aircraft arm comprises a first rotating portion, oneend of the first rotating portion is connected with the aircraft body in a rotating manner so that the first rotating portion can rotate around the center axis of the aircraft body, and the power device is connected with the other ends of the aircraft arms and used for providing power for the aircraft. According to the aircraft, at least one aircraft arm comprises the first rotating portion, one end of the first rotating portion is connected with the aircraft body in a rotating manner so that the first rotating portion can rotate around the center axis of the aircraft body, and the posture ofthe aircraft can be adjusted more flexibly. In addition, by means of combination with the power device, in the flying process of the aircraft, the aircraft body of the aircraft is ensured to be horizontal, the air resistance is reduced beneficially, the aircraft can fly more rapidly, and hang time is prolonged.

The invention provides a rocket launching platform applicable to rockets with different models and attitudes, and belongs to the technical field of rocket launching devices. The rocket launching platform applicable to rockets with different models and attitudes comprises a launching framework, a movable platform, a supporting platform, a fixed platform, supporting legs, and a first branch chain to a ninth branch chain, wherein the first branch chain, the second branch chain and the third branch chain are evenly distributed on the launching framework and fastened to the launching framework in a circumferential manner, the fourth branch chain and the fifth branch chain are connected between the launching framework and the supporting platform respectively, a space closed-loop mechanism is formed by the fourth branch chain, the fifth branch chain, the launching framework and the supporting platform, the sixth branch chain is connected between the supporting platform and the movable platform, the seventh branch chain, the eighth branch chain and the ninth branch chain are connected between the movable platform and the fixed platform respectively, a space closed-loop mechanism is formed by the seventh branch chain, the eighth branch chain, the ninth branch chain, the movable platform and the fixed platform, the three supporting legs are located at the bottom of the fixed platform and are distributed circumferentially, one end of each supporting leg is fastened to the fixed platform through a bolt, and the other end of each supporting leg is fastened to the launching ground through a ground nail. The rocket launching platform applicable to rockets with different models and attitudes has the advantages of being compact in structure, high in adaptability to different working conditions, flexible in attitude adjustment, relatively easier to control and the like, and rockets of different models can be launched.

A dual-axis swing mechanism based on a transmission gear ring structure belongs to the fields of electric control technology and aviation power technology, and in particular relates to a dual-axis swing mechanism based on a transmission gear ring structure. The invention provides a double-axis swing mechanism based on a transmission gear ring structure with high reliability and working performance. The present invention includes a first servo motor 1, a second servo motor, a first cylindrical gear 2, a first conical bevel gear, a second cylindrical gear 3 and a casing. The main points of the structure are a bevel gear ring 8 inside the casing, and a bevel gear ring 8 is arranged on the casing. There is a third bevel gear 18; the center of the first cylindrical gear 2 is connected with the rotating shaft of the first servo motor 1, the central axis of the second cylindrical gear 3 is fixedly connected with the housing, and the first cylindrical gear 2 and the second cylindrical gear 3 engage.

The invention relates to a waste filling supporting bracket. The waste filling supporting bracket comprises a protective side, a top beam, an upright post, a four-rod mechanism, a base, a scraper conveyer and tamping mechanisms, wherein the hydraulic support is provided with a rear top beam; the front end of the rear top beam, the rear end of the top beam and the upper end of an upper connecting rod are hinged through a hinge pin; a rear upright post is arranged between the middle part of the rear top beam and the base; the rear part of the rear top beam is provided with a chute along the traverse direction; a rear slipping way is arranged in the chute; the rear end of the base is hinged with a waste baffle seat; and the tamping mechanisms are hinged on the waste baffle seat. In the wastefilling supporting bracket, the front end of the rear top beam, the rear end of the top beam and the upper end of the upper connecting rod are hinged through the hinge pin to form a structure of which three hinging points are superposed; the upper connecting rod cannot be moved when the top beam or the rear top beam is swung, lifted or put down, the stable structure of the supporting bracket is ensured, and the problem of top plate caving or waste rock leakage is solved. The waste baffle seat at the rear end of the base is provided with the two tamping mechanisms, fillers are more compactly filled, the overall strength of the fillers is improved, and the deformation of the earth surface is effectively controlled.

The invention provides a half carcass posture adjusting device on a slaughtering production line. Half carcasses are hung on carrying hooks running along the slaughtering production line. The device comprises an auxiliary guide rail, a fusiform guide frame and a release link, wherein the auxiliary guide rail is arranged below a main guide rail; the fusiform guide frame is arranged on the rear side of the auxiliary guide rail; and the release link is arranged on the rear side of the fusiform guide frame. The device can flexibly adjust the postures of the half carcasses on the slaughtering production line, and meets the operational requirements that the half carcasses running on the slaughtering production line are turned from a posture A to a posture B in the proceeding direction, and are released and turned to the posture A from the posture B after stably running at the posture B.

The invention designs a quadruped robot that can realize attitude adjustment in the air, which can be used in the attitude adjustment process of robots and spacecraft. The present invention mainly includes two parts, the trunk and the limbs. The trunk and the limbs are connected by hinges and the movement mode is controlled by the hinges. A flywheel with a large moment of inertia is respectively installed at the end of each limb of the robot, which has a relatively large moment of inertia. (Compared with the limbs, it cannot be ignored) and the emergency stop effect. The direction of the flywheel axis is the same as that of the centerline of the limbs. The overall posture of the robot can be fine-tuned by swinging the limbs of the robot and pointing to different rotation directions; the limbs can also point in the same direction. , to rotate the robot around a specific axis. This design reduces the quality of the flywheel required by the robot and spacecraft; it does not need to add too much space, reducing the size of the robot and spacecraft; it can also put all the flywheels into work and improve the utilization of the flywheel Rate.

The patent of the present invention relates to the technical field of near-field melt electrospinning direct writing, and in particular relates to an unsupported melt electrospinning direct writing device with a tiny three-dimensional structure. The setting of the platform and the Z-axis rotary insulating platform enables the part receiving plate to move horizontally in the X and Y axes, and the rotation of the X and Z axes has 4 degrees of freedom, which can flexibly adjust the posture of the prepared parts, and cooperate with one in the vertical direction. A 3-DOF robotic arm that can be rotated in the direction to adjust the posture of the electrospinning nozzle in the vertical plane. In the process of electrospinning, the present invention can cut the 3D model of the supporting part into smaller parts according to a plane, and each divided part is self-supporting when printed in the normal direction of the standard plane that divides it. Subsequent processing is carried out in sequence, and finally complete parts are printed through continuous unsupported electrospinning direct writing with the previous segment as the base, without adding additional supports, which improves production efficiency.

The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a flight array system with autonomous flight capability. It provides an autonomous flight array module that occupies a small space, has a high load capacity, and has flexible attitude adjustment, and can take off in a stacked manner in a small space.

An optical waveguide chip coupling test fixture, comprising a wafer table and a supporting structure for supporting the wafer table, a chip holder is arranged on the wafer table, and the chip holder includes a plurality of chip fixing adjustment knobs and connecting Chip fixing clips on each of the chip fixing adjustment knobs, a plurality of the chip fixing clips are arranged in a form that surrounds the chip to be fixed in the central area, and the chip fixing clips can be adjusted by each chip fixing adjustment knob The fixed position and fixed angle of the chip. The invention can be used for the clamping and fixing of the optical waveguide chip and the adjustment of the fixing angle of the optical waveguide chip for the end face coupling of the optical fiber and the optical waveguide, and is suitable for optical waveguide chips of various shapes and sizes. It has the advantages of flexible posture adjustment, easy disassembly and replacement of the chip held, simple and convenient operation, and wide application range.

The invention belongs to the field of aerotechnics and the electromechanical control technology, and particularly relates to a distributive vectored thrust system capable of achieving taking off, landing and hovering with any posture. The distributive vectored thrust system comprises free thrust units and a flight controller. Each free thrust unit comprises a first servo mechanism rack provided with a first steering engine, wherein a first steering engine shaft is connected with a second servo mechanism rack; the second servo mechanism rack is provided with a second steering engine, and a second steering engine shaft is connected with a power duct frame and is perpendicular to the first steering engine shaft. The flight controller controls the input of the rotating angle of the first steering engines and the rotating angle of the second steering engines and the rotating speed of power ducts.

The invention relates to the field of aircrafts, in particular to a small airborne floating balloon with a zero-breeze layer. The floating balloon includes a delivery system, a lifting system, a recovery system, a main control system, and a load system. The delivery system, the lifting system, the recovery system, the main control system and the load system are all sector structures, and the delivery system, the lifting system, the recovery system, the main control system and the load system are all drawer cage structures provided with a plurality of functional boards, and a plurality of functional boards are sequentially connected from the top to the bottom. The floating balloon is specially designed for an air ejection delivery mode. The floating balloon has the characteristics of flexible delivery location, small volume, long dwell time, stable dwell position, flexible attitude adjustment, easy recovery and the like; meanwhile, the floating balloon can be used for ejection deliveryof aircraft such as aircraft and unmanned aerial vehicles in the air. The volume of the airship is greatly reduced compared with a tethered balloon, and the power device and the ground towing equipment are not required.