65 results about "Right-hand rule" patented technology

New [GOD, I], [GOD, II], & [GOD, III] dual-plasma fuel cells provide the electric start systems to start their warm-up processes, automatically. After their warm-up processes done and the operation temperatures reached, the dual-plasma fuel cells will run independently by continuously supplying fuels and moisture into the units. In dual-plasma nuclear [fusion and / or fission] fuel cells' configuration, electrical power will be generated from the nuclear-thermal-plasmas reaction by exothermal heating from combustion & nuclear reactions. With conducting high-electrons' current, the cable, loads, and electrodes are connected among one another between two plasmas' ionizing chambers for civil utility purposes. In the [GOD, II] dual-plasma fusion fuel cell, heavy water [D2O] injection into the atomizing chambers increases the plasmas heating and electrical conductivities. And the un-like charges of the heavy water's [D2O+], & [D2O−] react with plasmas' [2H+& O=] combustion heating which will induce the fusion reaction and release much more nuclear heating power for initiation of the next plasmas-generation cycle much easily. For the [GOD, III] dual-plasma fission fuel cell, fission fuels located in the combustion & nuclear reaction space through robotic movements provide additional nuclear-thermal energy that allows for initiation of the plasmas-generation process for the next cycle. For [GerTh. I] dual-plasma jet thruster, the dual plasmas are ejected to an opening end of a ‘C’ shaped magnet, and linear thrust is generated, according to the right-hand rule as in a jet thruster of propulsion for space traveling.

The invention belongs to the technical field of navigation satellite precision orbit determination, and specifically relates to a navigation satellite orbit rapid recovery method based on short arc orbit determination and forecast. The navigation satellite orbit rapid recovery method based on short arc orbit determination and forecast includes the steps: through short arc orbit determination and short arc forecast, taking the distance from of the satellite at a reference epoch to the geocenter as the radial component, taking the distance from the satellite to the initial orbit plane as the secondary normal component, taking the third component defined according to the right hand rule of the coordinate system as the tangential component, taking the time rate of change of the radial component, the secondary normal component and the tangential component, and performing rapid recovery of the navigation satellite orbit through compatible user ephemeris calculation with an additional component correction value. The navigation satellite orbit rapid recovery method based on short arc orbit determination and forecast can realize seamless docking of the ephemeris solution method of the userbefore and after orbit control, can improve the accuracy of satellite orbit determination and forecast, can obtain the satellite precise orbit of the user application demand in a relatively short timeafter orbit control, and can make accurate forecast so as to enable the satellite to resume normal use and guarantee normal operation of the satellite system, and has important guiding significance for the technical field of navigation satellite orbit determination.

The invention discloses a three-freedom-degree parallel mechanism control method. The three-freedom-degree parallel mechanism control method is characterized by comprising the following steps that (1)a platform mechanism is built at first, wherein the platform mechanism comprises a static platform and a movable platform, a fixed coordinate system is built on the static platform, a movable coordinate system is built on the movable platform, the projection, on the static platform, of the movable coordinate system coincides with the fixed coordinate system in the original state, and coordinate axes meet the right hand rule; (2) according to mechanical parameters of the platforms and working requirements of users, the lengths of three electric cylinder rods corresponding to different poses are inversely solved through the kinematics; (3) the time corresponding to each rod length is worked out; and (4) the tree rod length variable quantities and time variable quantities are set to be arrays, and an electric cylinder is driven by a multi-axis motion controller to continually move, so that platform euler angle output is achieved, and motion simulation is achieved. The three-freedom-degree parallel mechanism control method has the advantages that the hardware structure is simple, intermediate links are decreased, the reliability is high, the control algorithm is easy to achieve, and the good popularization value is realized.

The invention relates to an anchor-node-free three-dimensional wireless sensor network physical positioning method. In the method, the concept of partially concentrating and global distributing is adopted to solve the common problem of reversal differences in distance measuring methods, and achieving precise physical positioning is achieved through low calculated amount and communication traffic. The method comprises the steps of: 1) initializing a WSN (Wireless Sensor Network) system, searching an adjacent node of each sensor node through each sensor node, and measuring the distance and relative angle information between each sensor mode and the adjacent node; 2) establishing each local space rectangular coordinate system of each node, wherein all rectangular coordinate systems meet a right-hand rule, and the axis z always points to the same half space; 3) calculating the local coordinate of each adjacent node; 4) solving a three-dimensional coordinate system transformational matrix based on homogeneous coordinates through the adjacent node, and transforming the transformational matrix to calculate a coordinate relative to another local coordinate system; and 5) selecting the origin of global coordinate system, and through the recursion transmission of the coordinate system transformational matrix, calculating the global physical coordinate of each node.

The invention discloses a method for determining a three-dimensional direction of a single crystal. The method comprises determination of a one-dimensional direction of the single crystal and determination of the three-dimensional direction of the single crystal. The method comprises the following steps: (1) determining the one-dimensional direction of the single crystal by an XRD sample platform provided by the utility model with a patent number being 200620079376.7; and (2) marking a two-dimensional coordinate system on a predetermined crystallography plane (h1k111) after the one-dimensional direction of the crystal is determined so as to determine the three-dimensional direction of the single crystal, namely, firstly determining an X axis of the two-dimensional coordinate system in the crystallography plane (h1k111), marking a straight line, which is a Y axis, perpendicular to the X axis in the crystallography plane (h1k111) according to a right-hand rule, and taking a normal direction [h1k111]of the crystallography plane (h1k111) as a Z axis of a three-dimensional coordinate system to determine the three-dimensional direction of the single crystal. Through the method for determining the three-dimensional direction of the single crystal, the three-dimensional direction of the crystal can be quickly determined by only carrying out a diffraction experiment on one crystal plane of the crystal, and thus the blindness and the waste of the crystal in the direction determining process are avoided.

The invention relates to a multi-rotor aircraft, which comprises four main rotor systems, two auxiliary rotor systems, a body and a flying integrated system arranged in the body, wherein an original point of a coordinate system of the body is the gravity center of the aircraft; a z axis is vertical upwards; an x axis is vertical to the z axis and points to the front part; a y axis is determined by a right-hand rule; the four main rotor systems are respectively distributed inside four quadrants of an x-y plane of the body coordinate system; each rotary axis of the four main rotor systems and the z axis of the body coordinate system form an included angle theta, and a projection of each rotary axis on an x-o-y plane of the body coordinate system is overlapped with the projection of a connection line from a rotation center to the original point of the body coordinate system on the x-o-y plane of the body coordinate system. According to the invention, movement and gesture change of the aircraft can be achieved by adjusting rotating speed of the four main rotor systems and the two auxiliary rotor systems; and the aircraft can achieve the actions such as vertical take-off and landing, forward flying, reverse flying, hovering, rolling and the like, and the stability and the controllabitity are good.

The invention discloses a bucket positioning method, which is applied to an excavator and comprises the following steps of: specifying a positive direction by adopting a right hand rule and establishing an excavator kinematics model; C; calculating a movable arm fulcrum coordinate according to the coordinate of the antenna phase center in the geographic coordinate system and the position vector ofthe antenna phase center measured by the RTK in the geographic coordinate system; C; calculating the rotating angle of the movable arm according to the excavator mechanical parameters and the movablearm inclination angle; C; calculating a bucket rod rotation angle according to the bucket rod inclination angle and the movable arm rotation angle; C; calculating the bucket rotation angle accordingto the bucket inclination angle, t, the movable arm rotation angle and the bucket rod rotation angle; A; and calculating the position of the shovel tip by establishing a DH matrix model according to the coordinates of the movable arm fulcrum. The method can solve the problem that the excavator is difficult to accurately calculate and position the bucket.

New [GerTh. I]& [DawShien. II] dual-plasma jet thrusters provide the electric start system to start their warm-up processes, automatically. After their warm-up processes done and the operation temperatures reached, the [GerTh. I]& [DawShien. II] dual-plasma jet thrusters will run through themselves, independently by continuously supplying fuels and moisture into the units. Electrical power will be generated from the only [GerTh. I] jet thruster's fuel cell ([GOD, I] fuel cell) by thermal-plasmas reaction and then, its [GOD, I] fuel cell's fuel supplies are transformed from molecular forms into atomized and ionized forms by plasmas combustion heating, stepwise. When dual plasmas are ejected through the ‘C’ shaped magnet's opening sides, linear thrust is generated according to the right hand rule. Thereafter, the combustion and neutralization are conducted also with the same electric thrust direction for propelling the object in the same linear guided motion.

The invention discloses a routing method for greedy geographical routing protocol tangent switching hole processing, and mainly solves the problems that a greedy geographical routing protocol adopts an edge recovery algorithm when meeting a routing hole and routing has blindness. The realization scheme is that if the greedy geographical routing protocol meets the routing hole when searching a target node, the left hand and right hand rules are simultaneously used when entering an edge recovery mode, three conditions of tangent judgment are added from the second hole node, a greedy forwarding mode is recovered if the conditions are met, and routing hops under the left and right hand rules are compared and the optimal path for data forwarding is selected. The routing hops are reduced in comparison with the greedy geographical routing protocol, and control overhead is reduced in comparison with a self-adaptive hole processing algorithm based on road sign distributed iterative extraction and elimination so that the routing method can be used for a mobile wireless sensor network.

The invention discloses a step counting method based on a micromechanical gyroscope. A reference coordinate system is established with the center of the human body as a coordinate original point, theZ axis points to the vertical direction, the X axis points to the forward direction of a person, the Y axis points to the left side, and the right-hand rule is accorded with; the micromechanical gyroscope is placed on the thigh of a pedestrian, and a sensitive shaft of the micromechanical gyroscope is parallel to the Y axis; the movement state of the pedestrian is determined by detecting whether or not the micromechanical gyroscope has periodic output, and the number of walking steps of the pedestrian is calculated. The step counting method based on the micromechanical gyroscope is complete infunction and easy to implement, has an obvious effect and can replace a commonly-used step counting method based on an accelerometer; the method is applied to a navigation positioning system, the accelerometer special for step counting can be omitted, and the method has a great significance on simplifying the system and saving the cost.

The invention discloses a modal parameter test method of a rigid body of a power assembly suspension system based on full-automobile states. According to the test method, a counter-weight based rubber soft hammerhead is used for force hammer excitation and a full-vehicle coordinate system is used as the reference; the X axis points to the back of the vehicle and is perpendicular to the front shaft; the Z axis is upwards vertical; the Y axis is determined according to the right hand rule; the six-degree-of-freedom rigid body modal including translational motions in three directions and rotation around three directions into three groups, and single modal parameter identification is performed on each group once; the specific steps are: selecting X-direction excitation FX of the power assembly, testing frequency response functions of response points and using the PolyMAX modal identification method to identify the X-direction transitional motion modal and rotation modal around the Y axis and the Z axis; selecting Y-direction excitation FY and identifying Y-direction transitional motion modal and rotation modal around the X axis and the Z axis; and selecting Z-direction excitation FZ and identifying Y-direction transitional motion modal and rotation modal around the X axis and the Y axis. According to the invention, the test method is simple to operate, high in identification accuracy and suitable for identification of six-degree-of-freedom modal parameters of the rigid body of any rubber support.

The invention provides an external stator magnetic pole parallel type hybrid excitation composite motor which relates to the technical field of hybrid excitation composite motors, with the object of solving the problem of small output torque of conventional hybrid excitation motors. In the motor, excitation windings are wound onto the iron core of an excitation external stator to make the motor free of brushes. The excitation windings are in a certain form of series connection to ensure that during direct current charging, the right hand rule is obeyed. The direction of the excitation flux linkage is corresponding to a permanent magnet magnetizing direction; by changing the direction of excitation current, the motor is made to work in a magnetism increased or a magnetism weakened state. By changing the direct current in excitation coils, the magnetic field of the motor can be widely adjusted. In addition to that, the motor enables the armature winding induction potential to be adjusted by adjusting the excitation current and can offset the magnetic field produced by a permanent magnet part through the adjustment of excitation current when the armature winding malfunctions for short circuit, therefore realizing high efficient demagnetization when the armature winding of a motor breaks down for short circuit.

The invention relates to a multi-rotor aircraft. The multi-rotor aircraft comprises four main rotor systems, two auxiliary rotor systems, an aircraft body and an integrated flight system which is arranged in the aircraft body, wherein an original point of a coordinate system of the aircraft body is the center of gravity of the aircraft, a z axis is vertical upwards, an x axis is vertical to the z axis and points forward, and a y axis is determined by a right-hand rule; the four main rotor systems are respectively distributed in four quadrants of an xy plane of the coordinate system of the aircraft body; an included angle theta is formed between each rotary axis of the four main rotor systems and the z axis of the coordinate system of the aircraft body; and the projection of each rotary axis to an xoy plane of the coordinate system of the aircraft body is coincided with the projection of a connecting line of a rotary center and the original point of the coordinate system of the aircraft body to the xoy plane of the coordinate system of the aircraft body. By regulating the rotary speed of the four main rotor systems and the two auxiliary rotor systems, the movement and attitude of the aircraft can be changed, the aircraft can vertically take off and land, fly forwards, fly backwards, hover and roll, and the multi-rotor aircraft is high in stability and controllability.

The invention discloses a method for positioning radio self-organized network nodes based on a homogeneous coordinate. The method comprises the following steps of: initializing a radio self-organized network system, wherein each node finds out an adjacent node and measures the distance and angle information of the adjacent node; constructing a local plane rectangular coordinate system of each node, wherein when viewed from above, all coordinate systems always conform to right-hand rule; calculating the local coordinates of the adjacent node; solving a coordinate system transformational matrix based on the homogeneous coordinate by the adjacent node, so that the node relative to a local coordinate system can calculate the coordinate relative to another local coordinate system through the transformation of the transformational matrix; and selecting an original point of a global coordinate system, wherein each node calculates a global physical coordinate through the recursion transmission of the coordinate system transformational matrix. The method disclosed by the invention takes full advantage of self distance and angle measurement capacities of the radio nodes, and can determine the physical position of each unknown node in the radio self-organized network where beacon nodes are not suitable for being deployed.

The present invention belongs to the technical field of physics teaching demonstration experiment devices, and especially relates to an experiment device for demonstration of electromagnetism induction phenomenon in physics teaching. The device comprises a demonstration rack and an electromagnetic induction mechanism arranged on the demonstration rack; the electromagnetic induction mechanism comprises permanent magnets, demonstration channels arranged below the permanent magnets, induction coils winded at the outer surfaces of the demonstration channels and an indication bulb. One ends of thepermanent magnets are movably connected with the demonstration rack, two ends of the induction coils are provided with binding posts, and the indication bulb is connected with the binding posts through wires. Through comparison experiment, the electromagnetic induction demonstration experiment device for physics teaching allows students to clearly understand the Lenz's law, the right hand rule andthe relation of currents and forces so as to effectively improve the students' learning motility, train the students' initiative for problem thinking and problem solution and improve the learning efficiency.

The invention discloses an all-optical information acquiring device and method based on a four-zone phase delay array. The all-optical information acquiring device comprises a front telescoping system, a four-zone phase delayer assembly, a polarizer, a four-face pyramid prism, a Savart polariscope, a polarization analyzer, an image-forming mirror and a CCD detector. The front telescoping system, the four-zone phase delayer assembly, the polarizer, the four-face pyramid prism, the Savart polariscope, the polarization analyzer, the image-forming mirror and the CCD detector are sequentially arranged in the direction of a main light axis of incident light. An xyz coordinate system meeting the right-hand rule is established, and the main light axis is the Z axis. A first set of delayers is located between a second set of delayers and the front telescoping system, the included angle between the fast-axis direction of the first set of delayers and the x axis is 0 degree, and the included angle between the fast-axis direction of the second set of delayers and the forward direction of the x axis is 45 degrees. The all-optical information acquiring device can realize all-Stokes vector polarization information detection without causing reduction of the resolution, and has no special requirement for an incident spectrum.

The invention discloses a position and configuration parameter measuring method of a digital denture. The method comprises the following steps: introducing a denture model; adjusting a coordinate system of the denture model, so that a coordinate direction dir of the denture model, wherein the coordinate direction dir satisfies the following relations that an z axle is parallel to the direction ofa long axis, an x axle is parallel to a far-middle-near direction, a y axle is parallel to a buccolingual or labiolingual direction, and the directions of the x axle, the y axle and the z axle conforms to a right-hand rule; in accordance with the coordinate direction dir, recognizing five appearance high points of a denture within an h height range in a mode of calculating coordinate extreme values, wherein the h is a preset height threshold and the h is used for predicting a distance from a dental cusp to a gingival margin; and in accordance with the five appearance high points of the denture, calculating two appearance dimensions and three datum planes. According to the method provided by the invent, by adding the height threshold h, the method not only has the property of being strong in operability but also guarantees the reliability of a recognition result; the method, which calculates the two appearance dimensions and the three datum planes in accordance with the five appearancehigh points of the denture, is more convenient. The method provided by the invention can be widely applied to the denture repair field.

The invention discloses a method for realizing three-dimensional pie chart dynamic presentation. The method comprises the following steps of: calculating point coordinates on the circumference according to a central angle; adjusting the point coordinates according to the actual direction relative to the origin position; obtaining points on the circumference with indexes from 1 to n, wherein n is a natural number; sequentially connecting adjacent points on the circumference according to the indexes based on the right-hand rule to generate a triangle; generating the top surface and bottom surface of a three-dimensional pie chart in the mode; and generating the side surface of the three-dimensional pie chart according to the thickness. Through the technical scheme, the pie chart can be dynamically represented in a three-dimensional mode so as to provide a better visual effect and a unique user experience.

The invention discloses an electromagnetic thruster based on circular polarization distribution and a cavity of the electromagnetic thruster. The cavity is a microwave resonant cavity, electromagneticfield distribution of the resonant cavity has the circular polarization characteristic, and under a Cartesian right-angled coordinate system, the section of the microwave resonant cavity is defined to be in a circular shape; an X axis and a Y axis are located in the plane where the section is located, the X axis and the Y axis are orthogonal, and a Z axis is determined through a right hand rule;and an origin O is at the center of the circular section, an electromagnetic field is distributed unevenly in at least one of the X-axis, Y-axis and Z-axis directions. The cavity is provided with twoor more coupling ports; and the resonant cavity having the circular polarization characteristic is applied to the field of electromagnetic thrusters for the first time, the effect that at present, thethruster works stably is achieved, by introducing the design of the circular polarization electromagnetic field, the electromagnetic field resonance mode can be effectively controlled, and the stability of thrust is improved.

The invention discloses a parameter optimization method for a suspension system of a power assembly. The parameter optimization method comprises the step of formation of an optimization function, the step of calculation of inherent frequency and decoupling rate of the suspension system of the power assembly, the step of selection of an objective function and design variable, and the step of rearrangement output of an analysis result; the power assembly is regarded as a rigid body with six degrees of freedom and is characterized by comprising a power assembly position and a power assembly mass parameter, a coordinate system is established in a center of mass, an x axis points to the rear portion of an automobile, the y direction points to the front end of an engine through the center of mass, the z direction is determined through the x direction and the y direction according to the right hand rule, and the suspension system is simplified as a spring at a certain position in the coordinate system of the power assembly, wherein the spring has three-dimensional translational motion rigidity and damping. By means of the parameter optimization method for the suspension system of the power assembly, the manual debugging time can be saved, the decoupling calculation result of the system can be automatically, intelligently and efficiently calculated, the suspension rigidity can be optimized, the calculation efficiency can be improved, and the suspension decoupling result quality of the power assembly is guaranteed.

The invention belongs to the field of aircraft strength calculation and relates to a finite element model-based aircraft motion surface deflection method. The method comprises the following steps of 1, building a motion surface finite element model of a neutral position in a basic coordinate system; 2, establishing a reference deflection coordinate system in the motion surface finite element model of the neutral position, wherein an original point of the coordinate system is a lug hole center of a suspension support, an X axis is perpendicular to a front beam plane of a motion surface, a front edge direction is positive, a Z axis is a rotary axis of the motion surface, a wing tip direction is positive, and a Y axis is determined by a right-hand rule; 3, defining coordinates of all nodes of the motion surface finite element model of the neutral position in the reference deflection coordinate system; and 4, generating a deflection coordinate system by enabling the reference deflection coordinate system to deflect around the Z axis of the reference deflection coordinate system for a required angle, thereby realizing the deflection of the motion surface of an aircraft. The finite element model-based aircraft motion surface deflection method is provided.

The invention provides a method for setting the directions of principal axes of a 3D object is provided. The method comprises: for each of any two principal axes, setting the direction of the principal axis according to at least one predefined function, with which the result calculated of the 3D object for the vertices in the positive half space of the principal axis is smaller than or equal to the result for the vertices in the negative half space of the principal axis, wherein a vertex in the positive half space of the principal axis means the one with a coordinate of the principal axis larger than 0, and a vertex in the negative half space of the principal axis means the one with a coordinate of the axis smaller than 0; setting the direction of the third principal axis of to follow the right-hand rule with said two principal axes, wherein the vector for the third axis is the cross product of the vectors for said two principal axes; and displaying a signal of the 3D object with the directions of the principal axes set according to the above steps.

New [GerTh-DawShien. V] dual-plasma flying object and [GerTh-DawShien. VI] dual-plasma-fusion flying object provide the electric start system to start their warm-up process to their steady-states, automatically. After their warm-up processes done and the operation conditions reached, the [Thruster V]& [Thruster VI] will run themselves, independently by continuously supplying fuel, oxygen, and moisture into the units. Their electrical power will be generated from the [ShihHwa. V] DC turbo-contacting generator by different material-made surfaces and rollers contacting reaction and then, its electricity supplies transform gases from their molecular forms into ionized forms by electrifying reaction. When dual plasmas are fast ejected from nozzles into the ‘C’ shaped magnet's opening, their current will be increasing and plasmas will be bent downward, according to the right hand rule. The linear upward reaction thrust is generated. Thereafter, the plasmas combustion, neutralization, and fusion reactions are conducted also to the action direction and their reaction force for propelling the flying object in the opposite linear guided motion, upward and forward.

The invention discloses a form-given mesh antenna pretension calculation method. The method is used for calculating net unit pretension of a spatial form-given mesh antenna unfolded structure or a spatial form-given mesh antenna folded structure and comprises the steps that the right-hand rule is utilized to establish an x-y-z-axis space rectangular coordinate system with the center of a truss being a benchmark, the axial direction of the truss being a z axis and the radial direction of the truss being an x axis, and net pretension of a middle cable net is calculated according to preset average pretension; according to the net pretension of the middle cable net, net pretension of an upper cable net is calculated; and according to the net pretension of the middle cable net and the net pretension of the upper cable net, net pretension of a lower cable net is calculated. According to the method, through tension calculation on the three-layer form-given mesh antenna, different areas of anelectromagnetic wave reflection net have certain concave-convex performance, and the defect of a traditional pretension calculation method is overcome.

The invention provides labyrinth pipeline robot autonomous patrolling algorithm, which comprises the following steps of step 1, recording an advancing direction of the robot passing by each intersection, recording the left turning of the robot at a corresponding intersection with a letter L, recording the right turning of the robot with a letter R, recording the direct movement of the robot with a letter S, recording the U turn with a letter U, and utilizing the recorded letters to form a first path array according to the traveling sequence of the robot; step 2, substituting the letter combination SUL or the LUS in the first path array with a letter R and substituting the letter combination LUL in the first path array with the letter S when the control strategy is a left-hand rule; and substituting the letter combination SUR or RUS in the first path array with the letter L and substituting the letter combination RUR in the first path array with the letter S when the control strategy is a right-hand rule, and forming a second path array; and step 3, controlling the robot to perform a next patrol in a labyrinth pipeline according to the second path array. Due to the adoption of the algorithm and the robot, the patrolling efficiency of the robot is effectively improved.

The invention discloses a fruit body outer contour deformity detection method which comprises the following steps: S1, collecting a color image of a fruit outer contour, and converting the color imageinto a grayscale image; S2, performing image segmentation processing on the grayscale image, and extracting a boundary region of a fruit body in the image by adopting a canny algorithm; S3, pixel point coordinates of the fruit body boundary are obtained clockwise by adopting a pixel tracking method for the fruit body boundary; S4, judging the concavity and convexity of the outer contour of the fruit body by adopting a right-hand rule; and S5, comparing the number of concave property points of the outer contour of the fruit body with a preset threshold value to judge whether the fruit body isrejected or reserved. According to the method, the degree of concave-convex defects on the surface of the fruit body is detected by using software based on a computer, so that the abnormal fruit bodyis removed at a certain precision and speed, a good foundation is laid for subsequent classification, and the classification quality of the fruit body is improved.

The invention provides a new right hand rule for replacing Fleming left hand rule and Fleming right hand rule, and the rule is characterized in that right hand flat extends so that the thumb is perpendicular to the other four fingers; the four fingers point to the orientation of magnetic field*; the thumb points to the orientation of known vector (*or *); and the orientation which is pointed by the four fingers which are bent to be perpendicular to the palm is the orientation of the required vector (*or *). The Fleming left hand rule and Fleming right hand rule which are learned in the high school are easily confused and difficult to be applied, in order to be convenient for memory and orientation decision for the students, the new right hand rule is designed, which can judge the acting force of magnetic field applied to electric current and the orientation of the electric current produced by lead in the magnetic field simultaneously, is easy to be memorized and operated, and has strong practicability.

The invention relates to a demonstration device of the left-hand rule and the right-hand rule. The demonstration device of the left-hand rule and the right-hand rule includes a base, a transmission component, a magnetic pole rotating component and at least one wire component; the transmission component includes a handle and a gear transmission structure; the gear transmission structure is connected to the handle; the magnetic pole rotating component includes a rotating disk and two magnetic strips; the rotating disk is connected to the gear transmission structure; the two magnetic strips are detachably inserted on the rotating disk; the two magnetic strips are arranged symmetrically; and the magnetic poles on the surfaces of the two magnetic strips facing each other are different. The demonstration device of the left-hand rule and the right-hand rule is convenient for teaching.

The invention relates to a teaching aid, in particular to an electrical left-right hand rule demonstrator. The electrical left-right hand rule demonstrator comprises a magnetic north pole, a magneticsouth pole and a palm. The magnetic north pole and the magnetic south pole are connected into a whole through supports. The palm is arranged between a front support and a rear support through a rotating shaft. One side of the palm is a left palm, and the other side of the palm is a right palm. Sliding grooves are formed in the front end and the rear end of the palm. A conductor is arranged betweenthe two sliding grooves. An oblique groove is formed in the left palm center. A long hole is formed in the conductor. An external current arrow is inserted into the joint of the oblique groove and the long hole. A stress arrow is arranged on the left side of the conductor. The external current arrow is pushed upwards, and the conductor moves in the direction pointed by the stress arrow. The oblique groove is also formed in the center of the right palm, while the long hole is also formed in the conductor. The induced current arrow is inserted into the joint of the oblique groove and the long hole. A moving arrow is arranged on the right side of the conductor. When the conductor is pushed rightwards, the induced current arrow moves in the direction pointed by the arrow. The electrical left-right hand rule demonstrator can be used for demonstration at any time. The learned knowledge is consolidated through repeated operation.