235 results about "Radio telescope" patented technology

The invention relates to a free 6-UPS three-linkage parallel robot, belonging to the robot and mechanical producing area. The invention is characterized in that: three couples of straight driving branches are arranged in symmetry right triangle between the upper platform (1) and the base (2), while each couple comprises: two same SPU synchronous flexible driving branch while the upper end of each branch has a ball couple, the middle has a moving couple and the lower end has a universal couple connected to the base (2); the moving couple is formed by a mechanical or hydraulic synchronous flexible driver; the distance between two ball couples of each couple of straight driving branch is the same as the distance between two universal couple vertical axles (9). The invention is characterized in less freedom, easy control, large working space, simple structure and high accuracy. The invention can be used in large radio telescope, three-dimensional measure and sensor, etc.

The invention relates to an evaluating system and method based on radio astronomical instrument device electromagnetic radiation. The evaluating system comprises a microwave switch, a receiving antenna, a reference noise source, a signal source and an emitting antenna, wherein two normally-open contacts are arranged at one end of the microwave switch, the other end of the microwave switch is connected to a spectrometer through a pre-amplifier, the spectrometer is connected with a computer, the receiving antenna is connected to one normally-open contact of the microwave switch, the standard noise source is connected to the other normally-open contact of the microwave switch, the signal source is connected to the computer through the network, and the emitting antenna is connected to the output end of the signal source through a radio frequency cable. According to the system and method, by means of the technical index and observation requirements of a radio astronomical observation system, radio astronomical instrument device radiated emission is tested and evaluated, the influence of radio astronomical instrument device radiated emission on a radio telescope is analyzed, so that reference is provided for compatibility design, shielding design and site radio management of the radio astronomical observation system, and the engineering significance is high.

The invention discloses a method for manufacturing an antenna reflecting surface with an aluminum skin honeycomb sandwich structure, which relates to a technology for manufacturing the antenna reflecting surface in the fields of satellite communication, radio measurement and control, deep space exploration, large radio telescopes and the like. The method adopts a high-precision enveloping mold forrealizing the stretch forming of an inner skin and an outer skin, imposes the negative pressure through sealing and a vacuum device, presses and attaches the two layers of the skins, a honeycomb andother separating components on the mold, carries out adhesive curing and molding to form a whole by a bonding agent, and forms a high-precision aluminum skin honeycomb sandwich antenna reflecting surface unit after releasing vacuum negative pressure. The method has the advantages of high precision, light weight, great rigidness, great strength, simple processing technology, stable and reliable performances, low manufacturing cost, easy realization of production environment, mass production and the like, thereby being particular applicable to manufacturing the high-precision antenna reflectingsurfaces above ka frequency band and Q frequency band.

A lightweight reflector with a load bearing structure based on a tensile spoke-wheel. The spoke structure is especially compatible with dish parabolic mirrors, but has utility as a carrier structure for any round functional surface, including flat or slightly-curved mirrors used in central tower solar systems, parabolic dishes for radio telescopes and antennas, and for non-concentrating thin film solar panels. There are no radial members loaded in compression. All the spokes pull the rim inwards, and the rim is compressed in the circumferential direction. The imbalance in spoke tension results from the application of load provides the rigidity of the rim in respect to the hub, both for in-plane and out-of-plane forces. Ribs stiffen the spokes to resist wind and gravity, but are not structurally supported by either the hub or the rim. Lightweight reflector tiles match the wheel structure and create the reflective surface.

The invention relates to a multi-beam feedback automatic switch device and driving device, in large-scale flexible antenna, wherein said switch 10 is formed by rotation platform 14, multi-beam feedback source 13, and hollow support bearing 21; the multi-beam feedback source 13 is uniformly distributed on the platform 14, to be supported by hollow support bearing 21, to rotate relative to the fine adjusting platform 9; then switching the feedback source at any frequency, to adjust it at the center of fine adjusting platform, to receive the radio signal at one signal focus and large frequency range; said driving device is formed by a servo motor 23, a flexible coupler 25, a speed reducer 26, a secondary coupler 27, a bearing base 28, and a coiler 29, while they are connected to the ground via bottom frame 30. The invention has wider frequency range, to be used in large flexible antenna and large radio telescope.

The invention relates to a distribution structure of an SPORT (Solar Polar Orbit Radio Telescope) clock scanning satellite. The SPORT clock scanning satellite comprises a satellite body, a subsatellite, a stretching arm, a solar cell paddle, a butt-joint ring, a geosynchronous communication antenna, adopts a main force-bearing structure which is a central force-bearing drum and a radial partition board force-transferring path, has a clear and concise force-transferring link and is beneficial to the design of structure strength and rigidity through configuration distribution; the invention can not cause excessive pressure on the control of a satellite attitude because the distribution position of a propelling module of the satellite body ensures that the position of a satellite geometric center is hardly changed with the decrease of fuel, thereby better keeping the stability of the satellite attitude; in addition, the SPORT clock scanning satellite ensures that relative positions among the earth, the sun and the satellite are changed at any time when the satellite moves on an orbit and the geosynchronous communication antenna is communicated with an earth communication link, and meets the requirements and the limit of carrying, the requirements of payloads on placement, fixing, directions, viewing fields, operation, replacement, thermal control, stability, and the like in a space and the requirements of the payloads on detecting to realize a scientific goal.

The invention discloses a broadband microwave power meter and an interference signal filtering method. The power meter comprises an A / D conversion module, an FFT (fast Fourier transform) module, a power spectrum estimation module, a power spectrum integration module, an interference detection module and a digital filter module, wherein the A / D conversion module is used for carrying out A / D conversion for an intermediate-frequency input signal, the signal is converted to a digital signal from an analog signal; the FFT module is used for converting the digital signal to a frequency domain from a time domain; the power spectrum estimation module is used for carrying out power spectrum estimation for the frequency domain signal; the power spectrum integration module is used for accumulating the power spectrum to improve the signal to noise ratio of the power spectrum estimation; the interference detection module is used for identifying an interference signal; and the digital filter moduleis used for filtering the interference signal. According to the broadband microwave power meter disclosed by the invention, the interference signal entering the frequency band is automatically identified and filtered; and meanwhile, filter parameters are manually configured so as to ensure that a radio telescope can normally observe in the presence of stronger interference signals.

The invention relates to a four-point support of quadrilateral subpanel based universal detection method of a radio telescope, comprising the following steps of: (1) arranging a target on at least one entire line of subpanels and at least one entire row of the subpanels which are positioned in the center of an antenna; (2) at least scanning the targets arranged on one entire line of the subpanels and one entire row of the subpanels which are positioned in the center of the antenna by a high-precision rotational tracking scanning laser receiving device or a laser emitting and receiving device; recording the positions of the laser emitting device aiming at different targets by a high-precision coder; (3) obtaining angle data by measuring the information of the image patch position of a spliced target surface which translates and rotates along with the laser emitting device; and (4) directly educing the positional deviation of all panels, the surface shape precision of the integral spliced antenna and supporting point displacement needed by correcting the surface shape precision, i.e. the correction of a promoter. Aiming at the radio telescope, the paraboloid antenna adopts the design based on the four-point support of the quadrilateral subpanel and realizes the real-time splicing detection and the regulation of batched panels at low manufacturing cost through simple and easy process.

An anti-backlash system comprising a single drive pinion and motor is disclosed. In an exemplary embodiment, the single drive pinion is situated between two idler gears and is allowed to move in the radial direction relative to the bull gear. A preload force provides for the substantial absence of backlash at low torque loads. The pinion moves to the center point between the two idler gears and balances the torque during high torque loads. The present anti-backlash system is well suited for use in drive and positioning systems that are subject to variable and reversing loads, such as those experienced by radio telescopes in variable wind conditions.

The invention belongs to the technical field of robots and discloses a 6-PSS parallel mechanism and a position forward and inverse solution method. A circular rail is arranged and provided with six sliding modules which move actively and precisely along the rail. The sliding modules are connected with the lower ends of connecting rods of a fixed length through spherical hinges correspondingly. Theupper ends of the connecting rods are connected with a motion platform through spherical hinges correspondingly. According to the 6-PSS parallel mechanism and the position forward and inverse solution method, six-degree-of-freedom motion of the motion platform can be achieved, the mechanism is remarkably characterized in that the motion platform can rotate at any angle around the vertical axis, the motion flexibility of the mechanism is improved, and the posture adjustment work space is expanded; and the mechanism can be applied to multiple occasions including light radar antenna pedestals, radiotelescope feed source supporting platforms, motion simulators and the like. The mechanism and method provided by the invention are easy to operate, and the problem that a Stewart platform traditional six-degree-of-freedom parallel robot is limited in work space is effectively relieved; and the motion platform moves by driving the six parallel sliding modules, and the motion speed of the motionplatform is increased.

The invention relates to a relatively real-time radio wave environment testing method, which comprises the steps of S0, providing a radio wave environment testing system; S1, installing the radio wave environment testing system on a radio telescope, and enabling a test antenna to be close to a feed source opening face of the radio telescope; S2, carrying out calibration on the radio wave environment testing system by adopting a standard noise source; S3, carrying out a horizontal polarization radio wave environment test and a vertical polarization radio wave environment test in daytime test time periods on weekdays and weekends respectively by adopting the radio wave environment testing system; S4, carrying out calibration on stored data; and S5, and drawing a radio wave environment spectrogram at different time in the same direction and a radio wave environment spectrogram in different directions at the same time of the test antenna according to the power of a test antenna opening face. The relatively real-time radio wave environment testing method provides important support for radio astronomical observation interference eliminating strategies, receiver transformation and station radio management.

The invention discloses an azimuth-pitch movement two-shaft seat rack which is provided with a circular rail. The vertical axis of a vertical column is at the center of the circular rail, and the vertical column is connected to a rotation platform through the first rotation pair with a horizontal axis and is connected to a rack or ground through a second rotation pair with a vertical axis. The upper ends of two connection rods are connected to the rotation platform through hookjoints, and a sliding mechanism and the lower end of the connection rod are connected by using a composite hinge with three degrees of rotation freedom. According to the azimuth-pitch movement two-shaft seat rack, 0-degree to 90-degree pitch movement and -180-degree to 180-degree azimuth movement can be realized, external equipment can be a radar antenna, an astronomy radio camera, a camera, a sunlight reflector, and a solar energy sailboard. The structure is simple, the operation is convenient, and the problems of a heavy structure, a large driving power, and driving joint error accumulation of a traditional series connection type azimuth-pitch seat frame for large-scale apparatus equipment with a large quality are solved.

The invention relates to a drive control method and system for a large-caliber telescope arc motor. A DSP (Digital Signal Processor) event manager outputs six paths of drive signals; the six paths of drive signals are output to an intelligent power module after being subjected to optocoupling isolation; the intelligent power module outputs three paths of UVW voltage signals which are approximate to a circular magnetic field and the three paths of UVW voltage signals are added to an arc motor; a current mutual inductor measures each path of current; the current is input into a DSP buffer serial port for processing after subjected to A / D (Analog-to-Digital) conversion; a CPLD (Complex Programmable Logic Device) is used for processing an increment position signal generated by a coder and finishing interfaces of keyboard display, and the like; a rough and fine combined rotating transformer outputs an absolute position signal of the arc motor after passing through a digital converter; the signal is combined with the increment position signal processed by the CPLD to confirm the precise mechanical position of the arc motor; and motor phase conversion is realized after DSP processing. The invention can meet the requirement on a large radio telescope for a super-low speed arc motor and realize long time, super low speed, wide speed regulation and high precision tracking of a large-caliber millimeter wave / submillimeter telescope to a celestial body and has no creeping phenomenon at low speed.

The invention relates to an ultra-wide-band dielectric-loaded four-ridge horn feed source. The feed source is a dielectric-loaded wide-band dual-polarized circular-opening four-ridge horn, with a working frequency band of 0.6-4GHz, and applied to a radio telescope ultra-wide-band receiver system. The feed source consists of a four-ridge horn, a four-ridge circular waveguide, ridge film sheets, a dielectric rod, a metal outer edge, a first coaxial probe, a second coaxial probe and a dielectric ring. By adding the ridge film sheets to the circular waveguide, the working bandwidth of the four-ridge circular waveguide is far higher than that of the circular waveguide; then the four-ridge waveguide is made into the four-ridge horn so as to realize the ultra-wide-band and dual-polarized functions and the like; by loading the dielectric rod, the high-frequency gain can be lowered, and by loading the metal outer edge, the low-frequency gain can be improved, so that gain consistency in the working frequency band can be realized; by loading the dielectric ring and changing the cross section of the ridges, the equalization radiation property of a directional diagram can be adjusted; the feed source directional diagram is relatively high in equalization; and an actually measured result is basically identical to a simulation result, so that radio astro observation requirement can be satisfied.

The invention belongs to the components of a large radio telescope, especially relates to a co-driving parallel mechanism array on an active reflector of a large radio telescope with the number of the control nodes reduced and the control difficulty decreased. N parallel mechanical units are distributed and fixed on a base by the distribution of equilateral triangle, thus forming the co-driving parallel mechanism array on the active reflector of the large radio telescope. An active telescopic driver unit drives three adjacent reflector units at the same time, implementing the coupling amongst the reflector units. The regular hexagon reflector units of the N parallel mechanical units fit into the rotating parabolic reflector. The parallel mechanical array of the invention can reduce the number of the driving motor by 2 / 3, and decrease control difficulty; the engineering cost is reduced with one constraint branched chain reduced on each reflector. The rotating parabolic reflector can be fitted out via the parallel mechanism array, thus solidifying the need for large scale surface fitting.

The invention discloses a real-time correction method for the pointing direction of a radio telescope. The method includes the following steps that the radio telescope is controlled to carry out at least one time of scanning on a radio source in the right ascensison direction and the declination direction respectively to obtain right ascensison scanning data and declination scanning data; based on a linear function and a Gaussian function, a parameterized model for describing the right ascensison scanning data and the declination scanning data is established, and parameters for describing pointing errors are contained in the parameterized model; the right ascensison scanning data and the declination scanning data are substituted into the parameterized model, pointing errors in the right ascensison direction and the declination direction are acquired through a fitting algorithm, and pointing errors of the orientation and the pitching direction are acquired through coordinate conversion; the pointing direction of the radio telescope is controlled to be corrected based on the pointing errors to eliminate the pointing errors. The real-time correction method for the pointing direction of the radio telescope can be used for real-time correction of the pointing direction of the radio telescope to eliminate the pointing errors in real time, and meanwhile can solve the problem that the orientation operating speed is too high in the high-elevation scanning process under the orientation and a pitching coordinate system.

The invention relates to an absolute calibration device and method for a radio telescope antenna surface type. The absolute calibration device for the radio telescope antenna surface type is composed of a PSD position sensor array, a supporting shaft, annular laser devices and a control circuit. The PSD position sensor array is composed of multiple coaxial PSD position sensor coils, each PSD position sensor coil is composed of multiple PSD position sensor units with multiple position points on a central axis as circle centers, and the photosensitive surfaces are dead against the central axis and are in parallel with the central axis. The supporting shaft is arranged on the central axis and provided with the annular laser devices, and the emitting surfaces of the annular laser devices are perpendicular to the central axis. The device is simple in structure, low in cost and easy to manufacture and assemble. The active reflecting surfaces of the radio telescope are convenient to upgrade, performance of the radio telescope is guaranteed in real time, and the implementation technology is simple.

The invention discloses a high-accuracy antenna reflecting surface panel and a manufacturing method thereof, which relate to antenna reflecting surface unit manufacturing technology in the fields of satellite communication, radio measurement and control, deep space exploration, large radio telescopes and the like. The method comprises the following steps of: forming a rib beam by using a correction grooved Z-shaped section; forming a skin by grooving an aluminum alloy plate; applying negative pressure through sealing and vacuum devices; attaching separation components such as the Z-shaped section rib beam, the skin and the like to a mold and bonding, curing and molding the separation components and the mold into a whole by using an adhesive; and releasing vacuum negative pressure to form an antenna reflecting surface unit having a high-accuracy rib grooved bonded structure. The method has the advantages of high accuracy, light weight, high rigidity, high intensity, simple processing technology, stable and reliable performance, low manufacturing cost, easy realization of production environment, mass production and the like and is particularly suitable for manufacturing large and medium high-accuracy antenna reflecting surfaces in high-frequency sections.

The invention relates to a measuring method for a unit panel of a reflecting surface of a spherical radio telescope. The measuring method can effectively solve the problem of rapidly and accurately measuring the unit panel of the spherical radio telescope. The measuring method comprises the following steps of: laying circular directional reflective signs on 66 adjusting nodes of each panel, placing a code sign framework on a signal panel, and laying code signs on the code sign frameworks, and calculating the sizes of artificial signs; pushing unit antenna panels into the code sign frameworks, and moving a camera for measurement; calculating through a photographic surveying system, and finishing the splicing of images and the transfer of coordinate relationships between measuring points; and carrying out optimal calculation by using a measured data analysis system, a CAD (Computer-Aided Design) model and measuring data to obtain the profile accuracy of the panel, and leading out a three-dimensional displayed deviation value needle-like pattern and a deviation value data statement, thereby finishing the measurement of the unit panel of the spherical radio telescope. The measuring method has the advantages of simpleness, easiness in operation, small labor intensity, fast speed, time and labor saving and high accuracy.

The invention discloses a method for manufacturing a large-caliber high-precision antenna surface made of composite materials, and relates to an antenna reflection surface manufacturing technology in fields like satellite communications, wireless measurement and control, deep-space exploration and large-size radio telescopes. A main reflection surface is of a large-caliber paraboloid structure and is integrally formed on a mold according to a composite material vacuum filling technology. A back frame is of a composite material foam sandwich structure and is a supporting body provided with a space lattice structure and formed by cross ribs and longitudinal ribs in a longitudinal and cross orthogonal mode. Through the method, the large-caliber high-precision antenna reflection surface can be successfully manufactured and has the advantages of being light in weight, large in rigidity, good in vibration resisting performance and high in production efficiency, wherein the caliber phi of the antenna reflection surface is larger than 10m, and the precision delta of the antenna reflection surface is 0.3mmRMS.

The invention provides an electric actuator for actively adjusting a main reflection face of a large-size radio telescope. The electric actuator comprises a box body, a worm gear, a worm, an intelligent step motor, a screw nut, a ball screw, a cylinder guide sleeve, an upper guide sleeve, a supporting board, a supporting rod, a plastic bearing, a limiting stopper, a zero-position sensor, a screening box and an aviation socket, wherein the intelligent step motor is connected with the worm; the worm gear and the screw nut are fixed together; the ball screw is connected with the cylinder guide sleeve through a spline; the cylinder guide sleeve is fixedly arranged on the box body; the upper guide sleeve is fastened to and connected with the upper end of the ball screw; the supporting board is fixedly connected with the upper guide sleeve; the supporting rod is fixedly connected with the supporting board; the plastic bearing is sandwiched between the cylinder guide sleeve and the upper guide sleeve and is in interference fit with the upper guide sleeve; the limiting stopper is fixed at the lower end of the ball screw; the zero-position sensor is fixedly arranged on the box body and can be in contact with the limiting stopper; the screening box is fixedly arranged on the box body; and the aviation socket is connected with the screening box. The electric actuator provided by the invention has the advantages of high positioning precision, large power weight ratio, capability of bearing lateral force, water resistance and dust resistance, electromagnetic radiation resistance and high reliability and has a power supply-free self-locking function.

The invention relates to a method for quickly measuring the precision of a reflection face of a radiotelescope. The method can effectively solve the problems that in the large-caliber radiotelescope reflection face precision measurement process, measurement time is long, measurement precision is low, the angle of pitch of measurement is fixed, and external hardware equipment is needed for assistance. According to the method as a special phase retrieval microwave holography method, it is only needed that the amplitude of an antenna aperture field is measured, and the retrieval of the phase of the antenna aperture field is carried out according to a certain method. In the method, any stable astronomical radio source can serve as a signal source, and beam patterns are scanned under the antenna focusing condition or the antenna out-of-focus condition through an astronomic receiving machine and a terminal (power radiometer); an antenna aperture phase model is built according to the Zernike polynomials function, iterative operation is carried out on the residual error of a model value and a measured value through the minimization algorithm, and therefore the optimal solution corresponding to the minimum residual error vector is obtained to obtain a Zernike polynomials coefficient, backstepping is carried out to obtain the hole aperture phase distribution of an antenna, and the precision of the reflection face of the radiotelescope can be obtained.

The invention discloses a spatial five-equal partition reflecting face unit of an FAST (five-hundred-meter aperture spherical radio telescope). The spatial five-equal partition reflecting face unit of the FAST comprises a double-layer frame carrier. The double-layer frame carrier is integrally shaped in a triangle. Each layer of the frame carrier is formed by a plurality of triangular structure units. The triangular structure units are formed by connecting support rods via joint balls. Every edge of an upper layer of the frame carrier is partitioned into five equal partitions. Every edge of a lower layer of the frame carrier is partitioned into four equal partitions. Web diagonal bracings are arranged between the two layers and are connected to the joint balls. The upper layer of the frame carrier serves as a base seat and is provided with a plurality of triangular panel subunits. The panel subunits are fixedly mounted on the support rods and the joint balls of the upper layer of the frame carrier via joint support devices. Support heights of the panel subunits can be adjusted by the joint support devices. The support rods, the joint balls, the web diagonal bracings and the panel subunits are made of aluminum alloy.

The back-up structure of a parabolic dish antenna, which supports its reflecting surface, is formed in this invention by preloading its radial and circumferentially placed straight structural members and hence it is termed as preloaded parabolic dish antenna. Such a preloading results in considerable reduction in its weight and also to the effort involved in its assembly. The back-up structure of the preloaded parabolic dish antenna is made of a central hub, an assembly of a suitable number of elastically bent radial structural members connected rigidly to the central hub and to the same number of straight structural members which are connected to the tips of the radial members at the outer rim of the dish and also to straight bracing members placed circumferentially at intermediate locations, which are all tensioned to specified prestress values in the absence of wind loading. The outermost rim members placed at the periphery of the dish form the aperture of the dish. The backup structure of the preloaded parabolic dish antenna is given the parabolic shape by fixing the radial members at a suitable inclination angle and location at the hub and by applying an appropriate force with a normal component at their tips so as to bend the radial members elastically such that their curvature becomes approximately the same as that of the parabolic curve between the hub and the peripheral rim point. The invention incorporates a suitable rigid connection of the elastically bent radial members and other structural members in order to store sufficient initial elastic energy in the back-up structure of the dish for resisting gravitational and static and dynamic wind forces on the parabolic dish antenna for the survival wind condition at the antenna site. This configuration also reduces moment of the wind forces and torques on the mounting tower and gear drive system of the dish antenna. This invention is also applicable to structures of geometries other than that of the parabolic dishes. The method of constructing the preloaded parabolic dish and attaching reflector panels of lightweight is also disclosed.The preloaded parabolic dish antennas are useful in microwave communication, satellite communication, radar, radio telescope and other similar applications for receiving and / or transmitting radio waves.

The present invention discloses a radio telescope broadband electromagnetic shielding effectiveness detection system and a detection method thereof. The detection system comprises a transmitting module and a receiving module. The transmitting module comprises a signal source and a transmitting antenna. The signal source is used for emitting an electrical signal with specified frequency and the electrical signal is emitted by the transmitting antenna. The receiving module comprises a spectrum analyzer and a receiving antenna which is used for receiving the electrical signal emitted by the signal source and transmitting the received electrical signal to the spectrum analyzer. The spectrum analyzer is electrically coupled to the signal source to ensure the synchronization of sending and receiving the electrical signal. The spectrum analyzer receives electrical signals emitted before and after the signal source is placed into a shielding body, and thus the shielding performance of the shielding body is calculated. The detection system can detect a plurality of frequency points in a frequency band, the detection efficiency is high, the influence of a manual test on a tester is avoided, a detection result report is generated automatically, and time and labor are saved.

Said method contains first setting electronic tachometer establish on one fixed baseplate and sticking target on post at specific intervals, before each measurement utilizing electronic tachometer to proceed once retest for determining initial position, sticking more than three targets on tested unit block and configuring in coordinate system, then respectively measuring following three items: actuator setting accuracy, papoose carrier and actuator reset quality after actuator up and down movement, papoose carrier and not lifting position relative amount of amount of turning after three actuator simultaneously rising certain of distance. The present invented method is simple and utility, solving testing and debugging technical matters for active optics astronomical telescope or radiotelescope neutron reflecting mirror module attitude control mechanism with active principal reflection surface.

The invention relates to the field of motion control of a large-calibre radio telescopes, specifically to a cascade vibration-absorbing planning method and system used for source change of a large-calibre radio telescope, and aims to reduce system vibration caused by acceleration / deceleration motion in a source change process, and cost can be prevented from being increased due to use of a physical damper. In the planning system, a task parameter instruction issuing module sends specified source change parameters to a cascade vibration-absorbing planning module, and the module has two sub processing processes: preliminary motion curve planning and ZVD input shaping, an output final motion planning curve solves a control instruction of each execution mechanism through an instruction resolver, and a source change task of the large-calibre radio telescope is completed through control of a driving mechanism. In addition, the cascade vibration-absorbing planning module needs to use system parameters generated by a system parameter estimator. According to the cascade vibration-absorbing planning system provided by the invention, the system vibration caused by acceleration / deceleration motion is remarkably reduced, the positioning accuracy of a feed source receiver is improved, and the rapidity of the system is guaranteed.

The invention discloses an edge sensor system for the active reflection plane of a radio telescope, and a detection method for the active reflection plane edge sensor system. The system is disposed on an active reflection panel of the radio telescope, and consists of an edge sensor, a plane reflector, a transmitting end and a receiving end for detecting light, and an image processing computer. Each two adjacent sub-panels in the whole active reflection panel serves as one group, and the edge sensor is disposed at the edge of the back surface of one sub-panel, and the plane reflector is disposed on the other sub-panel of the same group. A transmitting end point on the edge sensor transmits detection light. Two sub-panels are connected through detection light. The detection light is reflected by the plane reflector and is received by the receiving end, and then is transmitted to the image processing computer. The output end of the computer is connected with each displacement actuator. The edge sensor is designed for the active reflection panel of the radio telescope, achieves the real-time detection of a surface shape in an observation process, and achieves the real-time jointing detection and adjustment of batch panels.

The invention relates to a Q-waveband ridge transition ortho-mode transducer. The coupler is of a broadband double-ridge transition-branch synthetic structure, has a center frequency of 40GHz and relative bandwidth of 50% and is used for a radio telescope Q-waveband receiver system. The ortho-mode transducer is composed of a double-ridge transition-branch joint, a Y-shaped joint, a first E-shaped bend, a second E-shaped bend, a first sidewall branch port, a second sidewall branch port, double ridges, a double-ridge transition segment, a coupling screw, an inductive diaphragm, a first 90-degree bend, a second 90-degree bend and an impedance transformation segment, wherein the double-ridge transition-branch joint is mainly used for separating two orthogonally polarized signals, double-ridge transition in a straight channel employs three steps, and a sidewall branch channel introduces the coupling screw and the inductive diaphragm; the Y-shaped joint is used for combining two horizontally polarized signals output by the double-ridge transition-branch joint into one signal; and the E-shaped bends are used for connecting the double-ridge transition-branch joint with the Y-shaped joint. The actual measurement results of reflection loss and isolation of the coupler are basically consistent with simulation results, and thus the radio astronomical observation demand is satisfied.