369 results about "Astronomical telescopes" patented technology

The invention discloses a follow-up tracking dynamic and static isolation type dual-super satellite platform and a working mode implementation method thereof. The follow-up tracking dynamic and static isolation type dual-super satellite platform is suitable for sensitive load spacecrafts with the ultra-precision and ultra-stability requirement. Dynamic and static isolation is used as the means, a satellite is divided into a load cabin and a service cabin, the load cabin can ensure that the effective load meets the expected ultra-precision and ultra-stability control requirement through a high-performance magnetic levitation flywheel arranged on the load cabin, the service cabin can resist environmental disturbance and track the load cabin in a follow-up mode through an external actuator mounted on the service cabin, and accordingly the two cabins can meet the expected relative pose requirement. The load cabin is connected with the service cabin through a suspension device in a non-contact mode, vibration disturbance of the service cabin can be effectively isolated, and the vibration isolation effect cannot be affected by the sensor performance. The satellite based on the dual-super satellite platform at least has the launching, ultra-precision and ultra-stability, anti-collision or mobility working mode. The dual-super satellite platform can be applied to high resolution sensitivity effective load spacecrafts such as a high resolution remote sensing satellite and a deep space exploration astronomical telescope.

An arc-driven large-bore astronomical telescope is driven by a RE permanent-magnet synchronized arc motor. A control mechanism includes an upper machine and a lower machine; the upper machine is connected with the lower machine through serial communication; the lower machine carries out the real-time control; a motor stator is composed of 15 blocks, each block consists of 9 complete silicon steel plates and two silicon steel plates for reducing the edge effect; an armature winding is arranged according to UVWUVWUVW from right to left; a rotor is composed of 4 blocks and has 120 magnetic steel plates in total, the rotor adopts the torque design for reducing tooth space and is provided with a fastening device; an absolute coder and an incremental coder are simultaneously arranged in the control mechanism signal collecting and comparing links, the former is used for the turnover of a servo motor and the latter is used for testing the position of the servo motor; the signal of the coder is transferred to the DSP module of the lower machine through a singlechip; a drive circuit adopts a digital-driven intelligent power module. The present invention can achieve the needs of long-time, high-precision tracing and observing various celestial bodies and meet the requirements of precision and wide speed regulation in astronomic observation.

This invention discloses a curve movement control system of large-bore astronomical telescope's azimuth axis. It includes an epistatic computer system and a hypogynous computer system. The epistatic one is connected with the hypogynous one through serial communication. The hypogynous one is made up of a DSP module, an executive electric engine, a signal collection, comparison link and a position data processing SCM. It is characterized in that the telescope's executive electric engine is a circular electric engine; the engine is connected with the drive circuit and protective circuit; the signal reversing collection and comparison link are both set with the absolute coder used for the inverting of circular electric engine and the incremental coder used for position detecting of circular electric engine; coder's signal is exported to the DSP module through the position data processing SCM; drive circuit adopts digitized intelligent drive power module; the PWM of DSP module is exported to it to control the circular electric engine's revolution. This invention can meet the need of long-time and high-precision tracing and observing all kinds of celestial bodies, and also can meet the need of precise and board-timing parameter.

The invention relates to an automatic focusing method for an astronomical telescope and belongs to the technical field of spatial object detection of the astronomical telescope. The method comprises the following steps: acquiring a corresponding unimodal and monotonic image gray gradient evaluation function on a time domain according to energy distribution, which is accordant with a target image, of the frequency-domain characteristic of a point spread function for an optical system of the astronomical telescope and the Rayleigh energy conservation law; performing low-pass filtering on the evaluation function to obtain an ideal target energy concentration ratio evaluation function; and continuously adjusting the step length and the direction of a driving motor and searching a global maximum of the evaluation function to complete an entire automatic focusing process by using an optimized hill-climbing method. The method has the advantages of simpleness, easy realization and generality.

The invention provides an eight-rod-connecting type non-contact satellite platform configuration and an assembling method. The eight-rod-connecting type non-contact satellite platform configuration comprises an upper connecting plate, a lower connecting plate, four same vertical mounting force actuators and four same horizontal mounting force actuators; both the vertical mounting force actuators and the horizontal mounting force actuators are connected between the upper connecting plate and the lower connecting plate and are arranged in a circumference manner; the vertical mounting force actuators and the horizontal mounting force actuators are arranged along the same circumference in a staggered and orthorhombic manner; the vertical mounting force actuators are vertical to the horizontal mounting force actuators. The eight-rod-connecting type non-contact satellite platform configuration implements complete isolation of an effective load on platform vibration and interference response, can be applied to spacecrafts with high-resolution sensitive effective load, such as a very-high accuracy remote sensing satellite, a deep space exploration astronomical telescope and the like, and can greatly improve exploration performance of spacecrafts.

The invention provides an air cooling heat dissipation thermoelectric cooler (TEC) electric refrigeration charge coupled device (CCD) Dewar which comprises a vacuum Dewar (1), a CCD detector (3), a TEC, an air cooling heat dissipation system (7) and a molecular sieve (5), wherein the CCD detector (3), the TEC and the molecular sieve (5) are arranged inside the vacuum Dewar (1), a cold end of the TEC is in heat conductance with the CCD detector (3), a hot end of the TEC is in heat conductance with the air cooling heat dissipation system (7), and the air cooling heat dissipation system (7) is connected with a vacuum Dewar cavity body (1) in a sealed mode. Due to the fact that the TEC and the molecular sieve are used for maintaining the technologies such as vacuum and air cooling heat dissipation in a long term to ensure low temperature requirements of a CCD in operation of the system, the air cooling heat dissipation TEC electric refrigeration CCD Dewar has the advantages of being large in a heat sink heat dissipation surface area, fast in temperature cooling speed, low in absolute refrigeration temperature, long in vacuum maintaining time, small in size, less in quality, convenient to install and control, capable of observing at any angle, simple in operation and maintenance and capable of being directly used for imaging and photometry of a astronomical telescope CCD lens.

The invention relates to a measuring method for the real-time accurate direction of an astronomical telescope, and a control system works according to the following steps: (1) acquiring the observation time and the directing data; (2) acquiring images; (3) generating theoretical star atlases; (4) carrying out the full-frame scanning of the images; (5) carrying out the matching distribution of the theoretical star atlases and actually-measured star atlases; (6) measuring the direction of the telescope; and (7) giving out the accurate direction of the telescope in real time by a computer system according to the input data, and guiding the telescope to carry out the observation and the tracking of space debris. In the invention, the accurate direction of the telescope can be measured in real time according to an acquired CCD (Charge Coupled Device) image as well as the moment corresponding to the image and the direction with an error, the measured direction precision of the telescope is superior to one half of the image-element resolution of the CCD image, the differing degree of the error of the telescope is measured in time, and the actual direction of the telescope can also be accurately measured. The processing effect is good, and the measuring method can be widely applied to the fields of scientific researches and projects and is particularly favorable to the direction correction of movable-type observing equipment.

This invention relates to a control device for controlling an astronomical telescope and, specifically, to a control device for automatic locating of celestial bodies, and to a method for controlling an astronomical telescope. The control device comprises a power input interface, a master controller, and an intelligent motor drive controller. The master controller comprises a CPU, an optional RAM, a FLASH microprocessor, one or more buttons, an LCD, a buzzer, one or more backlight diode lamps, one or more LED lights, a serial to USB interface, and an internal serial bus. The intelligent motor drive controller comprises a chip microprocessor having IAP functions, a two-way reversible PWM driving circuit having an output end and a detection end, a direct current motor, an optical encoder, an optical encoder detection circuit, and an over-current protection circuit. By calculating the coordinates of target bodies and converting them to equatorial mount coordinates, the microprocessor in the intelligent motor controller controls the motor to run, realizing the tracking of target celestial bodies.

The invention discloses a super-mapping machine which comprises a remote sensing and telemetering system, a three-dimensional attitude system and a central control and positioning communication system, wherein the remote sensing and telemetering system comprises an infrared laser light source (2), a search imaging unit (3), an image processing unit (4), an astronomical telescope imaging unit (5) and a photoresistor (1); the three-dimensional attitude system comprises a pitching pose unit (6), a horizontal axis (9), a horizontal attitude unit (7), a heading attitude unit (8) and a vertical axis (10); the central control and positioning communication system comprises a central processing unit (11), a man-machine interaction unit (12), a storage unit (13), a global positioning unit (14), a communication unit (15), an image recognition unit (16) and a power supply unit (17). The invention provides a field portable machine system which can acquire high-precision three-dimensional images in a geodetic coordinate system under the range finder-free conditions.

A dual-redundancy telescope tracking device for an astronomical telescope comprises a pitch axis set and an azimuth axis set and is characterized in that two sets of tracking systems are respectively adopted for the pitch axis set and the azimuth axis set, and then an azimuth axis dual-redundancy axis set and a height axis dual-redundancy axis set are respectively formed; the two sets of tracking systems are automatically switched through a control system; the two sets of tracking systems in the pitch axis set jointly drive a height axis and share a set of feedback systems and a set of height limiting and braking systems; the two sets of tracking systems in the azimuth axis set jointly drive an azimuth axis and share a set of feedback systems and a set of azimuth limiting and braking systems. The dual-redundancy telescope tracking device has the advantages that bearing capacity is high, friction force is low, power consumption is small, transmission efficiency is high, and rotation accuracy is high; positioning accuracy can reach 20 degrees per second at high speed and reach 0.05'' per second at low speed, and no creeping phenomenon exists; emergency braking and mechanical shock protection can be achieved at the same time through braking and limiting, and the rotation range can be adjusted within the range from 0 degree to 360 degrees in the forward direction and in the reverse direction. The dual-redundancy telescope tracking device can be also used for other heavy high-precision rotating equipment.

The invention relates to an ultra-sensitive spectral imaging astronomical telescope based on second-order compressed sensing, which comprises an optical unit and an electric unit, wherein the optical unit comprises an astronomical telescope lens, a first spatial light modulator, a collimation part, a spectrometric part, a spectral convergence part, a second spatial light modulator and a collection part; the electric unit comprises a single-photon point detector, a counter, a random number generator, a control module, a data packet memory and a compressed sensing module; a celestial image is collected through the astronomical telescope lens, and is imaged to the first spatial light modulator; a randomly modulated light beam is collimated into parallel light, and the parallel light forms a spectral band through the spectrometric part; the spectral band is secondarily randomly modulated through the second spatial light modulator, and is finally collected in the single-photon point detector; and a compressed sensing algorithm is used for obtaining an astronomical target spectral image according to a photon count value and two groups of random matrixes.

Disclosed is a multifunctional astronomical telescope integrating a sun observation function with a star observation function. A Gregore optical system is employed as a basis of a three-mirror system. The multifunctional astronomical telescope is characterized in that the optical system is internally provided with a coude reflector for transiting light reflected by a primary mirror and a secondary mirror to an altitude axis, and system focal ratio conversion is carried out through a flat spherical mirror on the altitude axis; three focuses are designed for a system: a main focus is provided with a view field diaphragm, a reflector and a refrigeration apparatus and is shared with a star observation optical path; a system focus provided with a magnetic analyzer calibrating apparatus; and a scientific focus which involves whole-reflector imaging; and a conversion apparatus is arranged at the focus position of the main mirror, and through switching between the view field diaphragm and an image field correction mirror, switching between a sun observation optical path and a star observation optical path is realized. The multifunctional astronomical telescope provided by the invention solves the problem that sun observation and star observation cannot be realized in the one astronomical telescope in the prior art, and realizes unification of wide spectrum, large view field, high-quality imaging and high-resolution spectrum measuring functions under the condition of sun and star observation.

The invention relates to an ultrasensitive astronomical telescope, which comprises an astronomical telescope lens, a spatial light modulator, a convergence light receiving component, a single-photon point detector, a counter, a data packet memory, a random number generator, a control module and a compression sensing module. Light signals are collected by the astronomical telescope lens and are imaged on the spatial light modulator; the spatial light modulator carries out random modulation on the astronomical image and reflects light of different positions to the convergence light receiving component; light signals collected by the convergence light receiving component form to-be-detected very weak light, and the light is transmitted to the single-photon point detector; the random number generator controls the spatial light modulator to carry out random modulation on the light signals; the single-photon point detector detects single photons in the to-be-detected very weak light and single photon signals are converted into electrical signals to be outputted; the counter records the number of electrical pulses in the signal photon number; the control module carries out control coordination on the whole ultrasensitive astronomical telescope; and the compression sensing module uses the single photon number, the random matrix and sparse matrix for realizing reconstruction of the astronomical image.

This invention relates to one space telescope visual frequency CCD automatic guide method, which comprises the following steps: fixing visual frequency CCD in guide lens cylinder and main lens cylinder; through CCD image process getting space object image; rotating CCD to make the space image parallel along X direction and rectascension or declination for space object imaging by CCD; computer uses visual frequency to catch image for guide according to visual image and its changes.

The invention relates to a lens construct which is filled with liquid and a solar energy board light concentrating system. A transparent solid outer shell with a convex lens shape is filled with liquid such as water to form a convex lens. A solar energy board is arranged between the convex lens which is filled with liquid and the focus of the convex lens to make the solar ray focus on a solar energy battery through the convex lens to generate strong light and increase electric energy. The weight of the convex lens is reduced, and the material cost is reduced. The invention can be used for light concentrating of the solar energy board system in great deals. The invention can have convex lens shapes with different uses, such as an astronomical telescope, a microscope and a triple prism, etc. The weight of the lens is decreased.

The invention relates to an arm type space astronomical telescope inertial pointing control method and control system and belongs to the industrial automation field. With the arm type space astronomical telescope inertial pointing control method and control system of the invention adopted, the problem of low inertial pointing control precision of an existing arm type space astronomical telescope inertial pointing control method can be solved. The control system comprises a controller, a telescope inertial position sensor electrically connected with the controller, joint position sensors of which the number is equal to the number of rotating joints, motor driving circuits, motor current sensors and joint inertial speed sensors, wherein the joint position sensors are electrically connected with the controller; a joint motor is fixed on each rotating joint; the joint motor and the joint position sensor on the same rotating joint are in mechanical connection with each other; and each joint motor is electrically connected with one motor driving circuit and one motor current sensor. Design of a control algorithm and completion of compensation for nonlinear terms can be realized according to a dynamics model of an arm type space astronomical telescope, and closed-loop feedback of each joint can be realized through the joint inertial speed sensors, and therefore, inertial pointing control precision can be improved.

The invention discloses a pneumatic type support system of a primary mirror of an astronomical telescope. The system comprises a pneumatic type force actuator system as a key member, wherein a force output end of the force actuator is linked with a mirror plane through a force sensor; the system is characterized in that the force actuator precisely outputs force by adopting a pneumatic theory. Gas pressures of the two ends of a piston in a cylinder are controlled by a control system through an electricity-air ratio valve according to a signal of the force fed back to the control system of the force sensor. The system comprises an ultralow friction cylinder, a high-precision electricity-air ratio valve and a force sensor closed loop; the size of the force output by the actuator is controlled precisely; the response frequency is up to 1HZ; and meanwhile a desired stroke range of the force sensor can be set; a larger force range can be achieved by setting up a pressure range of the air; and furthermore, the system can be used in an extremely severe environment such as the South Pole, and has low requirements on the environment.

The invention relates to an equatorial telescope and theodolite composite bracket which comprises a base, an hour angle mechanism and a deflection angle mechanism, wherein the hour angle mechanism is connected with the base and can rotate around a latitude shaft under the driving of a latitude regulating mechanism; the deflection angle mechanism is connected with the hour angle mechanism and can rotate around an hour angle shaft under the driving of an hour angle driving mechanism; two sides of the deflection angle mechanism are respectively connected with a lens barrel connection base, the lens barrel connection base can rotate around a deflection angle shaft under the driving of a deflection angle driving mechanism; and the hour angle shaft and the deflection angle shaft are mutually vertical. According to the invention, quick and accurate adjustment in a plurality of angles and positions can be realized, and the operation is easy; and the bracket provided by the invention can be used as an equatorial telescope and the theodolite, can be used for loading various types and specifications of astronomical telescopes, angle measuring equipment, camera shooting equipment and the like, and can erect two devices for observation or measurement at the same time when being used as the theodolite, and can be widely applied.

The invention discloses a tracking measurement robot which comprises a remote sensing remote measuring system, a three-dimensional posture system and a central control and positioning communication system. The remote sensing remote measuring system comprises a distance measurement unit (1), an infrared laser source (2), a searching imaging unit (3), an image processing unit (4), an astronomical telescope imaging unit (5) and a photoresistor (6). The three-dimensional posture system comprises a pitching posture unit (7), a transverse shaft (10), a horizontal posture unit (8), a course posture unit (9) and a vertical shaft (11). The central control and positioning communication system comprises a central processing unit (12), a man-machine interaction unit (13), a storage unit (14), a global positioning unit (15), a communication unit (16), an image identification unit (17) and a power unit (18). The tracking measurement robot is suitable for measurement on a ground target and a close-range aerial target by a ground measurement station, and can be applied to photography measurement and geodetic measurement.

The invention relates to an automatic star finder control apparatus for a portable astronomical telescope and its control method. The apparatus comprises power input interface, main controller, equatorial instrument driving controller. The main controller includes central processing unit (CPU), random accessing memory (RAM), flash memory (FLASH), press-key, graphical dot matrix liquid crystal display, buzzer, white light-emitting diode back lamp, white light-emitting lighting lamp, RS232 serial interface, internal serial bus; the equatorial instrument includes single chip micro processor, dual-direction reversible PWM driving circuit, direct current motor, photoelectricity code disc and photoelectricity code disc detecting circuit, current foldback circuit. The invention controls motion of the equatorial instrument driving controller via calculating coordinate of object celestial body in the equatorial instrument with the micro processor of the main controller, realizing pointing and tracking the object celestial body with telescope.

The invention relates to an electromagnetic force actuator for active support of an astronomical telescope mirror face. One end of the force actuator is connected with a supported mirror face through a force sensor, and the other end of the force actuator is fixed in a mirror cell. The electromagnetic force actuator is characterized in that a force output end of the force actuator is arranged on an axle at the center of the force actuator; two permanent magnets with strong magnetism are arranged on the center axle of the force actuator; a coil with an iron core is fixed on a shell of the force actuator; and the output of the force actuator is connected with a control system, and the control system is connected with the coil with the iron core. The electromagnetic force actuator for the active support of the astronomical telescope mirror face has the advantages that structure is simple, mass is low, energy consumption is low, control accuracy of input force is high, response speed is high, stroke of the force actuator is large, force adjusting range is wide, environment requirements are low, and the force actuator can be used in South Pole and even in space special environment. Connection of the force actuator and the mirror face is facilitated.

A Shack-Hartmann wavefront sensor used for an adaptive optical system is suitable for a large-diameter astronomical telescope and comprises a beam-shrinking system and an array lens. The wavefront sensor is characterized in that a beam-dividing system, at least two sets of coupling object lens, at least two sets of CCD detectors and a signal synchronous collecting system are also adopted; after the wavefront information is divided into the wavefront sub-array by the array lens, the beam-dividing system is adopted to divide the wavefront sub-array into at least two sub zones in space and each sub-zone adopts one coupling object lens and one CCD detector for slope detection; the wavefront information of each sub-zone is collected and processed by the signal synchronous collecting system; the obtained slopes are combined and then are recovered to get a complete wavefront phase distribution; at least two sets of detector are adopted to work in parallel so as to reduce the capability requirement to the CCD detectors and effectively overcome the technical difficulties to the CCD detector by the excessive detection sub apertures; the wavefront sensor is insensitive to the optical path overall errors and the tilt errors which can not be easily overcome in the assembling-regulating process of the beam-dividing system, thus adding no the complexity to the sensor system.

The present invention relates to the control method of the arc motion of a large caliber astronomical telescope. The method comprises steps as follows: a DSP module is arranged in a hypogynous computer system; the control program of the hypogynous computer system comprises steps as follows: 1. the initial value of a control register in the DSP module is set; the current and the voltage at a motor stator end is measured and the DSP module is initialized; 2. an A / D is collected and kept; a direct torque control algorithm program is processed and a corresponding PWM signal is generated; 3. novel data collection and refreshing is finished and a voltage vector is reselected; 4. data exchange is carried out, which mainly comprises the steps of receiving from a host computer, refreshing the servo control parameter of a local host and setting the servo operation mode; the parameter in an EEPROM is saved; the keyboard value of the DSP module is read and displayed. The system can satisfy the requirements of long time, high precision tracking and observing various celestial bodies for the large caliber astronomical telescope. The present invention also satisfies the requirements of precision and wide speed control for astronomical observation.

The invention discloses a method for performing rapid celestial fix through a CCD (charge coupled device) zenith telescope on the ground. According to the method, the CCD zenith telescope is used for imaging a fixed star in a sky region near to the zenith of an observation point twice (the barrel of the telescope rotates by 180 degrees around a rotating shaft during the two times of imaging); precise astronomical longitudes and latitudes of the observation point can be rapidly obtained by processing the two shot fixed star images, the corresponding precise time and inclinometer data. Compared with the conventional generally used satellite positioning method, the method disclosed by the invention has the advantages of full autonomy, high reliability, high invisibility, working safety, no electromagnetic interference and the like. Compared with other celestial fix methods, the method disclosed by the invention has the advantage of high precision. Furthermore, star selection is not needed in the method, so that the observation process is simplified, and the observation efficiency is greatly improved; the shortcomings that the conventional astronomical telescope is complicated in observation and low in efficiency, needs an observation foundation pier and cannot perform mobile observation are overcome. The method has extremely good development and application prospects.

The invention provides a follow-up tracking type dynamic and static isolation type double-super satellite platform and a manufacturing method thereof. A brand new idea of a platform follow-up tracking effective load is adopted, super-precise and super-stable control is performed on the platform with the effective load being the center, and a follow-up tracking effective load coarse control mode is adopted for the platform. Meanwhile, by means of the dynamic and static isolation method, a satellite is divided into a load cabin and a service cabin; the load cabin guarantees that the effective load reaches expected super-precise and super-stable control through a high-performance magnetic levitation flywheel arranged on the load cabin; the service cabin resists environment interference and performs follow-up tracking on the load cabin through an outer executing mechanism installed on the service cabin; and the two cabins can reach expected opposite poses. The load cabin and the service cabin are connected in a non-contact manner through a levitation device, vibration interference of the service cabin can be effectively isolated, and the vibration isolation effect is not affected by sensor performance. The double-super satellite platform can be applied to spacecrafts, such as high-resolution remote sensing satellites and deep space exploration astronomical telescopes carrying high-resolution sensitive effective loads.

The invention provides a large-aperture rolling shutter of an astronomical telescope CCD camera. The center of a shutter cloth is provided with an exposure window. Two ends of the shutter cloth are respectively rolled at two shutter rolling shafts which are connected with shutter motors respectively. The large-aperture rolling shutter is characterized in that the two shutter rolling shafts are connected with position encoders respectively, the outputs of the two position encoders are connected with a position motion controller respectively, the position motion controller is connected with a control computer and is connected with the shutter motors through a motor driving circuit respectively, the control computer controls the motion of the two shutter motors through the position motion controller and the motor driving circuit to control the opening and closing of the shutter. According to the large-aperture rolling shutter, the shortcoming in the prior art is compensated, the large-aperture shutter can satisfy the need of an astronomical telescope large visual field CCD camera, and at the same time, the large-aperture rolling shutter has the advantages of fast reaction rate, less light baffling, high mechanical strength, relatively large shutter transmission aperture, no shutter effect in exposure, and little possibility of fatigue.

The invention relates to an intelligent AC distribution monitoring system, in particular to an intelligent AC distribution monitoring system applied to the electric power distribution of an unattended operation type astronomical telescope, and consisting of five main parts including a system control unit, a distribution output unit, an electric quantity monitoring unit, a human machine interface module, an AC / DC power source and the like, wherein the system control unit is connected with the distribution output unit, the electric quantity monitoring unit and the human machine interface module, and the system control unit transmits the voltage information and the current information acquired by the electric quantity monitoring unit to the human-machine interface module for the local display treatment; simultaneously, the acquired electric quantity information and system existing state are transmitted to a remote control computer through an Ethernet network, thus the operation control of the distribution output unit is realized. The system can realize safe and flexible remote operation control and monitoring of the electricity distribution system of the unattended operation type astronomical telescope.

The invention discloses an asymmetric double three phase camber line permanent-magnet synchronous electrical machine. The electrical machine comprises two parts that are stator combinations (I) and arotor (IV), wherein the three stator combinations (I) form a camber line structure on a circumference outside the rotor (IV), each stator combination (I) comprises a 12-slot stator module (II) and a 9-slot stator module (III) arranged side by side on the circumference outside the rotor (IV), the 12-slot stator module (II) and the rotor (IV) form a 12-slot 10-pole unit motor, the 9-slot stator module (III) and the rotor (IV) form a 9-slot 8-pole unit motor, the stator combinations (I) and the rotor (IV) together form the two-phase three phase electrical machine, permanent magnets are arranged in the rotor in an embedded manner in such a way that a V shape structure is formed, strong assembled magnetic effects are exerted, main magnetic flux can be effectively improved, torque density of theelectrical machine can be improved, the permanent magnets form 120 pairs of electrodes, the electrical machine is enabled to be characterized by low speed and large torque, and the electrical machineis applied to low speed and large torque direct driving occasions and large aperture astronomical telescope driving occasions.

Large radio astronomy telescope co-driving parallel connection array mechanism belongs to physical construction designing technology field, in particular relating to co-driving parallel connection mechanism array having strong coupling character. It featuring that: each unit lower end connected with base through guiding constraint branched chain for restricting reflection plane unit rotating at horizontal direction, one active branched chain located below all nonadjacent peak, through one telescopic link flex action to control above three reflection plane units cooperation movement. The present invention can realize reflection plane long range matching movement on occasions of reducing drive motor number.