1011 results about "Astrophysics" patented technology

The invention discloses a morning orbit computing power satellite, and belongs to the field of aerospace technology and space infrastructure. The satellite comprises a satellite platform and a computing force load arranged on the satellite platform. The satellite platform is provided with a condensation type energy system and a space pump drive fluid loop system. The condensation type energy system adopts an expandable condensation type solar cell array to generate power, switches a power supply mode according to an illumination period and an earth shadow period of a morning and night orbit, and supplies power to computing force loads and platform equipment. The space pump drive fluid loop system adopts an expandable flexible radiation cooling plate for heat dissipation, heat dissipation is conducted on computing force loads through a fluid loop, and a heating assembly is arranged to prevent a working medium from being frozen under the low-temperature working condition. Through the expandable structure and the orbit environment adaptability design, continuous energy supply and effective heat management are provided for the computing power load in the morning and night orbit environment, and high-power-consumption computing power load in-orbit stable operation is supported.

The present disclosure relates to a solar plant with solar panels (2, 2′) which are prefabricated in a leporello folding (3) which can be unfolded in an unfolding direction (A), and a substructure on which the solar panels are arranged, wherein the substructure is designed to be flexible in the unfolding direction (A) and is connected to the solar panels in a positionally fixed manner in such a way that the leporello folding (3) of the solar panels can be unfolded with the substructure (8, 9, 10, 24) and determines angular positions of the solar panels (2, 2′) relative to one another.

A heat balance optimal satellite sun orientation control method comprises the following steps: firstly, determining sun orientation target parameters according to a sun vector direction calculated by an orbit, using preset sun orientation target parameters when regular preset parameters are set, and then calculating a sun orientation target attitude angle and angular velocity by using a formula provided by the method, and finally, the sun orientation of the satellite to the target attitude angle and angular velocity is realized according to the measurement of the terahertz gyroscope and the plane control of the jet phase.

The invention discloses a super-large plane array type space computing power center, and belongs to the field of space technologies and space infrastructures. The space computing power center is deployed in a morning and evening orbit and comprises a plurality of computing power satellites which are physically docked in orbit through a docking mechanism. Each computing power satellite comprises a satellite platform, and a computing power load, a condensation type energy system and a space pump drive fluid loop system which are arranged on the satellite platform, and a docking mechanism for inter-satellite in-orbit physical docking is also assembled on the satellite platform. A plurality of computing power satellites form a planar array type rigid whole body through the docking mechanism, and energy scheduling among the light condensation type energy systems is realized based on the docking mechanism. According to the space computing power center, through multi-satellite physical docking and energy collaborative scheduling, the energy utilization efficiency and the power supply reliability of the system are improved.

The invention provides a solar synchronous orbit quick response SAR satellite load platform integrated configuration, which comprises a satellite body, an SAR antenna, a solar array, a phased array data transmission antenna, a star sensor and a body-mounted solar cell, the satellite body is in a quadrangular prism shape, the cross section of the satellite body is an isosceles trapezoid, the satellite body comprises a group of opposite parallel surfaces and a group of opposite inclined surfaces, the phased array data transmission antenna and the star sensor are respectively arranged on two parallel surfaces, and the SAR antenna and the solar array are respectively arranged on two inclined surfaces; the body-mounted solar cell piece and the solar array are installed on the same inclined plane and located on the inner side of the solar array, and the solar array comprises two solar array plates and has an unfolded state and a folded state. According to the method, load platform integration is taken as a design thought, so that the AIT process of the SAR satellite and the time required by AIT are greatly shortened; meanwhile, the attitude requirements of energy and load work are met, and the reliability of the initial injection stage is improved through sufficient energy.

The invention discloses an earth surface downlink short-wave radiation space downscaling method based on a super-resolution reconstruction technology, belongs to the technical field of meteorological data analysis, and solves the problems of insufficient solar radiation data space resolution and weak earth surface heterogeneity characterization capability in the prior art. Carrying out super-resolution reconstruction on the radiation data set by adopting a super-resolution combination model, and carrying out weighted fusion on a reconstructed data set output by the super-resolution combination model; according to the method, the output results of the multiple models are subjected to weighted fusion, weight optimization of the super-resolution sub-models is performed in combination with the high-resolution terrain factors, spatial downscaling from 5km to 1km resolution is finally realized, the spatial precision of the solar radiation data is remarkably improved on the basis of keeping the hour-level time resolution of the original data, and the accuracy of the solar radiation data is improved. And more earth surface heterogeneity information can be captured, and meanwhile, the high-time-resolution application requirement is met.

The invention discloses a planet generation method and system based on spherical display equipment. The method comprises the following steps: acquiring a planet material to be projected; based on preset UV coordinate mapping data, performing spherical projection on the planet material to generate a planet with two poles based on vertical projection and an equator based on cylindrical projection; the acquisition mode of the UV coordinate mapping data specifically comprises the following steps: generating a corresponding cylindrical projection through a cylindrical projection algorithm based on the auxiliary texture; corresponding spherical coordinates are obtained based on auxiliary texture mapping; converting the obtained spherical coordinates into 3D rectangular coordinates; the obtained 3D rectangular coordinates are mapped back to the 2D texture space again, and corresponding vertical projections are generated; determining an equator mask; and generating corresponding UV coordinate mapping data based on the equatorial mask, the cylindrical projection and the vertical projection. According to the invention, through the design of the UV coordinate mapping data, in the process of carrying out spherical projection on the planet material, the resource consumption is reduced, and the dynamic projection precision can be improved at the same time.

The invention relates to a satellite-borne microwave radiometer cold air calibration attitude planning method based on multi-objective optimization, and belongs to the field of satellite microwave remote sensing, and the method comprises the steps: building a satellite attitude kinematics model and an attitude dynamics model through a geocentric equator inertial coordinate system, an orbital coordinate system and a satellite body coordinate system; establishing a brightness temperature sum model received by the microwave radiometer in the cold air calibration process; according to the method, a microwave radiometer receiving brightness temperature sum, brightness temperature fluctuation, platform maneuvering capability, energy and a satellite sensor field of view are comprehensively considered, a multi-target optimization model of microwave radiometer cold air calibration consideration constraints is established, solving is performed, constraint conditions are established, and a solution or a solution set is obtained. According to the method, the brightness temperature sum and the brightness temperature fluctuation in the observation area of the microwave radiometer in the cold air calibration process are optimized by adopting multi-objective optimization, and the on-orbit cold air calibration effect and the system reliability of the satellite-borne microwave radiometer are improved.

The invention relates to a step-by-step winding and unfolding ultra-large flexible solar cell array and an unfolding method, and belongs to the technical field of space solar cell arrays. The battery array comprises a battery array body structure, a pressing and releasing mechanism, an unfolding and locking mechanism and an extension arm mechanism, the cell array body structure has a folded state and an unfolded state; under folding, pressing force is provided through the pressing and releasing mechanism, so that the device is folded on the side walls of the two sides of the satellite body and can bear the mechanical load of the launching section; during unfolding, under the action of the unfolding locking mechanism, the folding mechanism and the stretching arm mechanism, the folding mechanism is unfolded in a distributed manner according to a time sequence; and after being unfolded, the antenna can rotate by 360 degrees to provide energy for satellites. The invention has the advantages of small folding volume, large unfolding area and light weight, and solves the contradiction that the power demand of a spacecraft power supply is large and the envelope size of a launching section is small.

A steering drive includes an electric motor with a motor shaft and a steering lever rotatable about a pivot axis. A first planetary stage has a first sun gear, first planet gears, a first ring gear, and a first planet carrier. A final planetary stage has a final sun gear, final planet gears, a final ring gear, and a final planet carrier. A force flow runs from the motor shaft to the first sun gear, and from the first sun gear via the first planet gears to the first planet carrier and to the first ring gear. The force flow runs via the final sun gear and via the final planet gears to the final ring gear, runs from the first ring gear and from the final ring gear to the steering lever, and runs via a first sun gear shaft from the electric motor to the first sun gear.

The invention relates to a light-weight type planetary line gear reducer which comprises a sun gear, a planetary gear, an inner gear ring and a planetary carrier which are all light-weight type line gears, the sun gear is located in the center of the inner gear ring, the sun gear and the planetary carrier are both coaxially and rotationally installed on the inner gear ring, and the planetary gear is installed on the planetary carrier in a heteroaxial rotation mode and can rotate around the axis of the planetary gear. And the tooth surface normal of any contact point of the planet gear is collinear with the tooth surface normal of the corresponding contact point of the sun gear and the inner gear ring at the same time, the contact line is a cylindrical spiral line, and the transmission ratio and the spiral radius are decoupled. Through the space curve meshing theory, the reduction ratio exceeding 30 can be achieved through a single stage, the stage number of the planetary reducer is reduced, the force flow transmission path is remarkably shortened, the overall weight is reduced, and meanwhile the bearing capacity and reliability are improved; the technical problems that in the prior art, when the large reduction ratio is achieved, the multi-stage series connection structure is complex, the weight is increased, the transmission and positioning precision is reduced, and the load dispersing capacity is limited are systematically solved.

The invention provides a solar wing device which is characterized in that one end of a flexible solar panel (6) is wound on a winding drum (3), the other end of the flexible solar panel (6) is connected with a uniform load rod (5), and the uniform load rod (5) is always parallel to a rotating shaft of the winding drum (3); the scissor mechanism (4) is formed by cascading four equal-length rods which form parallelograms when unfolded, the flexible solar panel is unfolded and folded in the bottom end-top end direction, elastic components are arranged at the bending positions of the left end and the right end, opposite to each other, of each parallelogram, and the scissor mechanism is driven by the elastic components to be unfolded. The elastic component enables the scissor mechanism (4) to always keep a force for pushing away the uniform load rod (5), and in the unfolding state or the folding state of the solar blanket, the torque generated by the motor adapts to the elastic force generated by the elastic component. The flexible solar wing can be repeatedly unfolded and folded in orbit for many times.

The invention discloses an unmanned aerial vehicle low-altitude target radar detection and recognition system, and belongs to the technical field of radar detection and target recognition. Comprising a quantum entanglement laser emission module, a quantum multi-dimensional receiving module, a multi-source heterogeneous data fusion module, a quantum-classical hybrid calculation module, a self-adaptive anti-interference module and an environment self-adaptive correction module, the quantum entanglement laser emission module is used for generating entanglement photon pairs carrying orbital angular momentum (OAM) and emitting the entanglement photon pairs to a detection airspace; and the quantum multi-dimensional receiving module demodulates the distance, the angle, the OAM attenuation spectrum, the polarization state and the reflection spectrum of the echo signal through coincidence measurement. The quantum entanglement-OAM combined modulation technology is adopted, and the non-locality of entanglement photon pairs and the multi-dimensional information bearing capacity of a 9-path orthogonal OAM mode are improved by more than three times compared with a traditional microwave radar; single-photon-level coincidence measurement is combined with quantum Fourier transform signal processing, the signal-to-noise ratio is increased by 3dB, and stable detection of a weak target is achieved.

The invention provides a dual-motor coupling driving robot joint module based on a planetary reducing mechanism, which comprises a first motor, a second motor, a first planetary reducing mechanism, a second planetary reducing mechanism and a gear ring, the first motor comprises a first casing and a first output shaft, and the second motor comprises a second casing and a second output shaft. The first planetary reducing mechanism comprises a first sun gear and a first planet gear, the first sun gear is connected with the first output shaft, the first planet gear is rotationally arranged on the first machine shell, and the first planet gear is meshed with the first sun gear; the second planetary reducing mechanism comprises a second sun gear and a second planet gear, the second sun gear is connected with the second output shaft, the second planet gear is rotationally arranged on the second machine shell, and the second planet gear is meshed with the second sun gear; and the gear rings are annularly arranged outside the first planet wheel and the second planet wheel correspondingly, the gear rings are engaged with the first planet wheel and the second planet wheel correspondingly, the gear rings are used for power output, and the compact design of the joint module is achieved.

A method of sun-synchronous orbit design for remote sensing satellite based on revisit characteristics is proposed. The relationship between revisit and ground synchronization is established by Q value. The mathematical model of Q is established by node revisit sequence in a certain interval. Then the coverage rate is obtained by the mixed node access sequence and coverage area of orbit altitude and observation angle. Finally, the coverage rate of remote sensing satellite in sun-synchronous orbit is demonstrated from three aspects of time-varying coverage rate, minimum coverage time and minimum observation angle, which provides a reference for the design of sun-synchronous orbit of remote sensing satellite.

The invention relates to the technical field of antennas, in particular to a low-orbit satellite antenna board card. Comprising a first radiation unit, a second radiation unit and a PCB. The first radiation unit and the second radiation unit are circularly polarized antennas and respectively work in different frequency bands. The first radiation unit is of a cross-shaped structure, the second radiation unit is of a hollow structure, and the first radiation unit and the second radiation unit are both made of metal materials. The first radiation unit and the second radiation unit are nested on the PCB, the upper surface of the PCB is provided with a thermal control material, the lower surface of the PCB is provided with a heat conduction material, the antenna board card provided by the invention is suitable for being used outside a cabin, the application of the PCB to the outside of the cabin becomes possible, and thus light weight and low cost of a low-orbit satellite antenna are realized.

The utility model relates to an anti-backlash damping planetary gear transmission device in the technical field of planetary gear transmission, which comprises a sun gear, a planet carrier, a plurality of planetary gears and an inner gear ring, the plurality of planetary gears are arranged on the planet carrier in a staggered way, so that the front side surfaces of the tooth parts of part of the planetary gears are in contact with the tooth parts of the inner gear ring in the transmission process; the reverse side surfaces of the tooth parts of the other part of planetary gears are contacted with the tooth parts of the inner gear ring; when the sun gear is driven in the forward direction or the reverse direction, at least part of the planetary gears are meshed with the sun gear and the corresponding front face or the corresponding reverse face of the inner gear ring all the time, and therefore the purposes of eliminating backlash of a gear set, restraining vibration and reducing noise are achieved.

The invention discloses an optical satellite drift angle accurate calculation and attitude correction method and system, and relates to the technical field of satellite attitude control, and the method comprises the steps: calculating a prime unitary circle curvature radius according to a WGS84 ellipsoid parameter, and converting the geodetic coordinate of a ground target point into an ECEF rectangular coordinate; calculating Julian days based on UTC time, determining an age difference angle and a nutation angle, and converting an ECEF coordinate into a J2000 coordinate; calculating the projection of the earth rotation angular velocity in a J2000 coordinate system, and determining a relative velocity vector; determining an orthogonalized body coordinate system in combination with a unit vector from the target satellite to the ground target point; and projecting the relative velocity vector to a body coordinate system, calculating a drift angle and a double-rotation-sequence Euler angle, and correcting a real-time execution attitude by rotating a matrix around a Z axis. According to the method, high-precision image motion compensation can be realized, the imaging quality of a high-resolution optical satellite in a complex task scene is improved, and a technical foundation is laid for wide application of sub-meter remote sensing images.

The invention relates to the technical field of space satellite thermal control, in particular to a space satellite thermal control system based on self-adaptive thermal transport, which comprises a thermochromic intelligent thermal control coating coated on the whole outer surface of a space satellite, the variable-direction active heat compensation pump loop is arranged in the space satellite; the variable-direction active heat compensation pump loop is arranged between the satellite main illuminated face and the satellite main nightside and used for conducting heat transfer between the satellite main illuminated face and the satellite main nightside. The structure is simple, a basic frame of a heat control system is built, through cooperation of coating covering and a heat pump loop, regulation and transfer of satellite surface heat are preliminarily achieved, the temperature difference of the satellite outer surface is effectively reduced, the temperature uniformity of the outer surface is improved, effective guarantee is provided for a space satellite to avoid detection of an infrared detector, and the application range is wide. And the space satellite is safer and more hidden.

When a differential half shaft 11 on one side is not stressed due to slipping or suspension, and rotation of a differential shell 1 serves as input to drive a first planetary gear 12 and a second planetary gear 3 to revolve, the first planetary gear 12 and the second planetary gear 3 drive an inner gear ring 5 on a half shaft on the other side to rotate in the same direction. Due to the fact that the first planet bevel gear 8 and the second planet bevel gear 7 are fixedly connected and coaxially arranged, and the diameter of the inner gear ring 5 is far larger than that of the half shaft bevel gear 13, the differential mechanism shell 1 rotates to enable the inner gear ring 5, the first planet bevel gear 8 and the second planet bevel gear 7 on the other side to rotate, and the first planet bevel gear 8 and the second planet bevel gear 7 are driven to rotate. The first planet bevel gear 8 and the second planet bevel gear 7 are evenly distributed, force generated by locking of the inner gear ring 5 only pushes the second planet bevel gear 7 to rotate, and the direction of the force at the meshing position of the first planet bevel gear 8 and the second planet bevel gear 7 is the same as the rotating direction of the differential shell 1, so that the first planet bevel gear 8 and the second planet bevel gear 7 are in a locked state, and then the differential shell 1 is released. Therefore, the defect of a single cantilever of a free wheel in a free wheel type antiskid differential mechanism is overcome, and the whole structure is more durable.

The embodiment of the invention provides an orbit-based laser link dynamic capturing, tracking and establishing ground verification device and method, and relates to the technical field of satellite communication, the device comprises a laser platform, a two-dimensional turntable, a turntable controller, a laser terminal and a terminal ground detector, and the laser terminal is mounted on the two-dimensional turntable; the laser platform comprises a collimator and a control computer; the collimator provides a far-field environment for inter-satellite laser link light beams; the control computer sends track data to the terminal ground detector and the turntable controller; the turntable controller calculates the target control quantity of the two-dimensional turntable by using the track data, and drives the two-dimensional turntable to rotate to a position corresponding to the target control quantity; the terminal ground detector broadcasts track data to the laser terminal; and the laser terminal calculates an inter-satellite pointing vector by using the orbit data, drives a light beam emitted by the laser terminal to point to an opposite end according to the inter-satellite pointing vector, and emits the light beam to the opposite end. According to the scheme, the inter-satellite capturing and tracking link establishment capability of the laser terminal and the laser link stability can be fully verified.

The invention relates to the technical field of satellite communication, in particular to a high-gain phased array receiving antenna system for low-orbit satellite communication, which comprises a radiation feed integration module, a beam phase mapping module, a digital beam forming module, a signal amplification module, a protection packaging module and a performance verification module. Stacking strip line feed networks and performing electromagnetic coupling to obtain an initial radiation channel; receiving and analyzing a beam control instruction through an embedded circuit, extracting a target beam pointing angle and mapping the target beam pointing angle into a phase offset; generating a digital phase control word according to the phase offset, and applying the digital phase control word to the radio frequency signal to complete phase calibration; a transistor with a low-noise amplification structure is used for enhancing the calibrated signal energy; the wave-transparent front cover covers the radiator, and the electromagnetic shielding rear cover wraps the internal components to form an assembly in a sealing manner; and verifying the gain and beam switching rate of the assembly in the typical frequency band of the low-orbit satellite. According to the invention, the low-orbit satellite communication signal receiving efficiency can be improved.

The embodiment of the invention discloses a multi-platform common-view orbit determination method for an earth-moon space target, and relates to the technical field of space target orbit determination, and the method comprises the steps: enabling a plurality of observation platforms to observe the same earth-moon space target in the same observation time period, and obtaining a motion data sequence of the observation platforms in the observation time period, obtaining an observation data sequence obtained by observing the earth-moon space target; determining a relative position relationship between the observation platform and the earth-moon space target, constructing a first observation model for the earth-moon space target, and calculating the position and speed of the earth-moon space target at each moment in a corresponding observation time period; and constructing a second observation model, and calculating to obtain an orbit arc section of the earth-moon space target in the corresponding observation time period. The method is small in type limitation of earth-moon space targets, and can adapt to multiple types of orbits; after the initial orbit is successfully determined, orbit refinement can be carried out again by combining original observation data, so that the initial orbit precision is improved.

The invention relates to a sun tracking control method for a satellite solar panel, and the method comprises the steps: determining whether an orbit solar angle is between a first critical angle and a negative first critical angle or not, if yes, entering a one-dimensional panel control mode for sun tracking, returning a B axis to a zero position, and only controlling an A axis to rotate for sun tracking; if the orbital solar angle is out of the range from the first critical angle to a negative first critical angle, determining whether the orbital solar angle is greater than a second critical angle or less than a negative second critical angle, if so, entering a subsection control mode, and controlling the A axis and the B axis to rotate at a non-uniform speed for sun tracking; otherwise, entering a constant-speed rotation mode, and simultaneously controlling the A shaft and the B shaft to rotate at a constant speed for sun tracking, the second critical angle being greater than the first critical angle, and the first critical angle being greater than 0. According to the sun tracking control method, the sun vector information is used for calculation, the design strategy gives consideration to energy efficiency and attitude control, and the influence of frequent acceleration and deceleration of the solar wing on the satellite attitude is reduced.

The invention discloses a lubricating structure for a planetary gear set and a filter, and the lubricating structure for the planetary gear set comprises a planet carrier, a rotating shaft connected with an eccentric sun gear in a sleeving manner, a planetary gear engaged with the eccentric sun gear and rotatably mounted on the planet carrier, and a lubricating assembly arranged in the inner wall space of the planet carrier, the lubricating assembly comprises a control part and an extrusion part, and when the rotating shaft rotates, the control part is used for driving the extrusion part to directionally convey lubricating oil to the eccentric sun gear through the extrusion pipe and transmitting the lubricating oil to the planetary gear through the rotating motion of the eccentric sun gear, so that automatic lubrication between the eccentric sun gear and the planetary gear is achieved. Automatic lubrication between the eccentric sun gear and the planetary gear can be achieved, the problems that lubrication is insufficient, gear abrasion is accelerated and the like due to the fact that workers forget to add lubricating oil due to negligence are solved, and regular inspection of workers is not needed; the service life of the planetary gear set is prolonged, and the reliability and stability of equipment operation are improved.

The invention discloses a collimated direct-drive joint actuator, a robot joint and a robot in the technical field of robot joint actuators, and the collimated direct-drive joint actuator comprises a shell, a driving device and a planetary reducer, the planetary reducer comprises an input wheel, a planetary gear train, an output wheel and a mounting bracket, the planetary gear train comprises a sun gear, a planet gear, a planet carrier, an inner gear ring and a planet shaft; the sun gear is a continuous full-oval tooth profile gear, the planet gears are duplex planet gears and comprise the first planet gear and the second planet gear, the first planet gear is meshed with the sun gear in a conjugate mode, and the second planet gear is meshed with the inner gear ring in a conjugate mode. The collimation direct-drive joint actuator has the advantages of being high in torque density, high in bearing capacity and high in torque transparency.

1. Name of the designed product: candle stand (sun, moon, stars and constellations). 2. Use of the designed product: for lighting tools. 3. Design points of the designed product: in shape. 4. Picture or photo that best shows the design points: perspective view 1.

Electromotive assembly comprising a casing (CM), a differential mechanism (DF) and an electric machine (MEL) having a rotor (9) with a rotor shaft (1), the differential mechanism (DF) comprising a planet carrier element (2) rotated by the rotor shaft, pinion gears (23, 24) rotatably mounted on the planet carrier, a first sun gear (21) and a second sun gear (22), a short drive shaft (A1), bearing splines and mounted on the one hand in the first sun gear, and on the other hand in a first primary pinion, a long drive shaft (A2), bearing splines and mounted on the one hand in the second sun gear, and on the other hand in the second primary pinion, wherein the mounting of the rotating parts calls for two bearings (B1, B2) for rotatably mounting the rotor shaft, a bearing (B3) for rotatably mounting the first primary pinion, and a bearing (B4) for rotatably mounting the second primary pinion.

The invention relates to an arrangement comprising a planet carrier, a planet gear (101) rotatably mounted in the planet carrier, and one or more sliding segments (103) forming an axial bearing for the planet gear (101). The one or more sliding segments (103) are fixed in the planet gear (101).

The utility model provides wind power gear box planet carrier axle hole coaxial degree correction device relates to wind power gear box planet carrier axle hole correction technical field, including device seat, the top middle position fixed mounting of device seat has chuck clamp, the top middle position clamping of chuck clamp has planet carrier body, the periphery of planet carrier body is equipped with three mounting holes, and the top rear position of device seat is connected with the rear end position fixed connection of support frame bottom. Through comparing the detection data of different mounting holes, ensure the coaxial degree and position accuracy consistency between multiple axle holes, satisfy the high accuracy requirement of wind power gear box to planet carrier axle hole, and then guarantee the transmission efficiency, operation stability and service life of gear box. The current wind power gear box planet carrier axle hole coaxial degree correction lacks intuitive scale display and quantitative adjusting mechanism, cannot monitor deviation data in real time in the correction process, leads to the problem that the correction effect is unstable, and the rework rate is higher.