42 results about "Star system" patented technology

The invention discloses a star sensor function test method based on electric injection star map, which comprises simulating the track parameter and attitude of satellite motion and simulating a star map shot by a star sensor, using the star point center to refresh and transmit part of the star map, laminating the part refreshes in the star map background of the star sensor, positioning star point, recognizing star map and calculating altitude, checking the results of the star map recognition and altitude calculation of the star sensor. The invention discloses a relative device. The invention has high refresh rate of star map, which can simulate the track altitude of star sensor and can process ground simulation test with whole star system, without additional external devices and special application condition demand, but with strong versatility.

General method for extracting source distance information from any kind of received radiation, including electromagnetic and acoustic, without involving round-trip time or phase in any form, and thus more truly passive than existing passive radars. The method exploits the facts that radiation from a real source must comprise wavepackets of nonzero bandwidth, that the individual frequency components of a wavepacket must have consistent phase at the source, and that their instantaneous phases must increase linearly along the path in proportion to the respective frequencies, so that the phase gradient across the components must be proportional to the distance travelled. The invention simplifies over naïve phase gradient measurement by scanning the phase gradient at a controlled rate, thereby converting the gradient into normalized frequency shifts proportional to the scanning rate and the source distance. It mimics the cosmological redshift and acceleration, but at measurable levels over any desired range and even with sound. Potential applications include stealth and “unjammable” radars for the military, ranging capability for emergency services, commodity low-power vehicular and personal radars, simplification and improvements in radar and diagnostic imaging, improved ranging in general all the way from ground to inter-galactic space, “interference-free” communication systems including radio and television receivers, source-distance (or range-division) multiplexing improved cellphone power control and battery life, and continuous, transparent diagnostics for optical fibres, integrated circuits and transmission lines.

The invention provides a system structure based on Rapid IO (Input Output) protocol packet exchange for meeting high-speed communication of Serial Rapid IO applied by an embedded system and further meeting interconnection communication requirement of the Rapid IO and effectively improving the system performance and the fault-tolerant capability. The system structure based on the Rapid IO protocol packet exchange comprises a plurality of Rapid IO exchange chips; and all Rapid IO exchange chips can be used for constructing a star system interconnection topology structure and a dual-loop system interconnection topology structure; and in a plurality of end nodes in all Rapid IO exchange chips, one end node is set as a Rapid IO main management node of the whole system. The invention has the advantages of simpleness for realization of system hardware, flexibility for software configuration, reliable performance, reconstruction support, fault tolerance, adjustable dynamic flow and configurable scale.

The invention provides a backup method and a backup system of a central node of a star topology network. The method comprises the following steps: sending a self address to a central node by a backup node, and sending the address of the backup node to each edge node by the central node; receiving keep-alive messages regularly and synchronously sent by the central node and recording own latest time for receiving the keep-alive messages by each edge node; regularly inquiring the own latest time for receiving the keep-alive messages and judging whether the time exceeds preset keep-alive period time or not; and if the time exceeds the preset keep-alive period time, switching the communication with the central node to the backup node. When the scheme is applied, because the central node and the backup node are in different host machines, even if the host machine of the central node is broken down, the stability of the whole star system cannot be influenced. In addition, the backup node is not a sub node of the central node, as long as the edge nodes detect out a fault of the central node, the communication can be automatically switched to the backup node. The invention is simpler to realize and greatly reduces the cost.

General method for extracting source distance information from any kind of received radiation, including electromagnetic and acoustic, without involving round-trip time or phase in any form, and thus more truly passive than existing passive radars. The method exploits the facts that radiation from a real source must comprise wavepackets of nonzero bandwidth, that the individual frequency components of a wavepacket must have consistent phase at the source, and that their instantaneous phases must increase linearly along the path in proportion to the respective frequencies, so that the phase gradient across the components must be proportional to the distance travelled. The invention simplifies over naïve phase gradient measurement by scanning the phase gradient at a controlled rate, thereby converting the gradient into normalized frequency shifts proportional to the scanning rate and the source distance. It mimics the cosmological redshift and acceleration, but at measurable levels over any desired range and even with sound.Potential applications include stealth and “unjammable” radars for the military, ranging capability for emergency services, commodity low-power vehicular and personal radars, simplification and improvements in radar and diagnostic imaging, improved ranging in general all the way from ground to inter-galactic space, “interference-free” communication systems including radio and television receivers, source-distance (or range-division) multiplexing improved cellphone power control and battery life, and continuous, transparent diagnostics for optical fibres, integrated circuits and transmission lines.

The present invention provides an innovative apparatus and system for onboard spacecraft location determination and celestial navigation by employing spectral observations of extrasolar planetary star system motion. In one apparatus embodiment a gas absorption cell is placed between a sensor and the light from a reference star system with at least one exoplanet, such that the sensor can detect the spectrum through the gas absorption cell. Radial velocities can be calculated via Doppler Spectroscopy techniques and incorporated into a spacecraft navigation solution. The present invention can enable and enhance significant mission capabilities for future manned and unmanned space vehicles and missions.

The invention provides an in-orbit identification method of a stasis position of a one-dimensional drive mechanism of a spacecraft panel. The in-orbit identification method comprises the steps that (1), the actual solar vector Sm of a system is determined by a sun sensor; (2), the theory sun vector Sb of the system is solved by integrating satellite attitude information, orbit information and solar ephemeris model information; and (3), the pitch stasis angle theta of the one-dimensional drive mechanism of the spacecraft panel is determined by Sb and Sm. The invention further relates to a correction method of the stasis position of the one-dimensional drive mechanism of the spacecraft panel, the correction method comprises the steps that S1, the pitch stasis angle is determined by the in-orbit identification method; and S2, a one-dimensional sun pointing guidance law of a satellite is designed, and by correcting the pitch stasis angle theta, the spacecraft panel after a failure can be realigned to the sun by correcting the attitude of the satellite. The in-orbit identification and correction method of the stasis position of the one-dimensional drive mechanism of the spacecraft panelhave the beneficial effects that the measurement is reliable and the safety is high, the cost is saved in the design of panel drive mechanism and whole star system, and in-orbit fault treatment measures are added to guarantee satellite energy.

The invention discloses a method for designing a non-circular gear planetary system through Fourier function segment transmission ratios. The method includes the steps that according to the structural symmetry characteristic of a planetary gear system of a rotary type transplanting mechanism, a transmission ratio between non-circular gears is segmented at the 180-degree position, and the relation among the segment transmission ratios of the planetary gear system is constructed; under the condition of meeting the total transmission ratio of the gear system, in order to solve the problem that effective equations for solving the segment transmission ratios are not enough, the Fourier hypothesis of the non-circular gear segment transmission ratios is provided, and other transmission ratios are distributed successfully; through mirror image, weighting, iterating and fitting processing performed on the segment transmission ratios, an ideal transmission ratio is obtained finally, and therefore a non-circular gear pitch curve is obtained. The method is simple in process, small in calculation amount and high in efficiency, and the designed non-circular gear transplanting mechanism is highly targeted.

The invention relates to a processing machine having a processing wheel, which is in particular continuously driven, comprising at least one processing station for processing containers; comprising only one star for feeding and removing containers into and out of the processing device, which has at least two gripper elements for feeding containers to be processed to the processing station and for removing the processed containers from the processing station; wherein the processing station has a processing position within the processing station; characterized in that the processing station has at least one processing element processing a container, which is designed so that it can move the fed containers to be processed and / or the processed containers to be removed at least partially out of the processing position and / or into the processing position, in particular in a vertical or horizontal manner.

The invention discloses a design method of a multifunctional space gravitational wave detector based on the TRIZ. Seven inventive principles recommended by the TRIZ serve as technological evolution paths, a ground laser interference gravitational wave detector can be evolved into a multifunctional space gravitational wave detector. The multifunctional space gravitational wave detector comprises devices such as spacecrafts. As shown in the figure, the multifunctional space gravitational wave detector is characterized in that the three spacecrafts form an equilateral triangle constellation with the 103-109km side length, the center of the equilateral triangle constellation moves on the earth orbit, an optical table on each spacecraft and an optical table on the adjacent spacecraft can have interference through coherent light beams generated by lasers, if gravitational waves scan the spacecrafts, the strength of light passing through photodiodes of photodetectors changes, a differentiator and a correlator are used for calculating the relation between the strength of the light and the phase position, and the value of the gravitational waves to be measured is obtained. The multifunctional space gravitational wave detector is characterized in that the low and medium frequency gravitational waves are detected, and a double-star system, large-mass black holes and random background gravitational waves are surveyed.

In a simultaneous transmit and receive (STAR) communication system, an RF signal splitter couples an antenna to an RF transmitter and to an RF receiver, without using a circulator. An adaptive cancellation RF waveform generator generates an adaptive cancellation RF signal to cancel cross-talk from the RF transmitter to the RF receiver. Training signals are used to characterize signal paths within the STAR system and calculate filter coefficients for generating the adaptive cancellation signal.

A modular star system for grading, cleaning, and transporting produce includes opposing, first and second hub modules with opposing, tapered surfaces, and plural finger modules separated by the first and second hub modules. Each finger module has finger members that are color-coded and the finger module and first and second hub modules are disposed on a rotatable shaft. Outer surfaces of either of the finger or hub modules are color-coded, and are substantially perpendicular to the long axis of the shaft. There is also a method of using the modular star system for grading, cleaning, and transporting produce.

The invention discloses a four-subnode star server system capable of realizing hard disk sharing, and relates to the field of high-density servers. The system mainly comprises four server nodes, a hard disk module, a power panel and a system middle board, wherein the hard disk module comprises a hard disk backboard and hard disks inserted into the hard disk backboard; the power panel is communicated with the system middle board to supply power to the system middle board; the hard disk module and the four server nodes obtain electricity from the system middle board; a SAS (Serial Attached SCSI) exchange board is arranged between the system middle board and the hard disk module and obtains the electricity in the system middle board; and through a SAS exchange board server node, any hard disk in the hard disk module can be accessed. In the four-subnode star system, the read-write access of any node to 24 pieces of 2.5-inch hdds (Hard Disk Drives) can be realized, the pooling and the sharing of system storage resources can be realized, the use ratio of the hard disk storage space of the four-subnode star server system is improved, and the stable and quick operation performance of the system is improved.

The present invention provides an innovative apparatus and system for onboard spacecraft location determination and celestial navigation by employing spectral observations of extrasolar planetary star system motion. In one apparatus embodiment a gas absorption cell is placed between a sensor and the light from a reference star system with at least one exoplanet, such that the sensor can detect the spectrum through the gas absorption cell. Radial velocities can be calculated via Doppler Spectroscopy techniques and incorporated into a spacecraft navigation solution. The present invention can enable and enhance significant mission capabilities for future manned and unmanned space vehicles and missions.

This invention relates to one geography position determination and display method, which provides one electronic map communication device and use based on global position system, Galileo device, north star system, difference device, wherein, the device can provide accurate geography position to get device data through software establishing satellite guide system to determine detail geography coordinates on device to display its geography position and image.

The invention discloses a chip satellite based on an electrical activity polymer and the attitude control method of the chip satellite. According to the chip satellite disclosed by the invention, according to the principle of angular momentum conservation, through deformation of the electrical activity polymer arranged on the periphery of a chip satellite center platform, the mass distribution of a whole system is changed, so that attitude maneuver of the chip satellite is realized. According to the attitude control method of the chip satellite provided by the invention, a conventional chip satellite attitude control method gets away from the dependency of magnetic field and an ionosphere, so that the attitude maneuver of the chip satellite can be realized at any position in space, and the application range of the chip satellite is greatly extended; after the process of the attitude maneuver of the chip satellite is completed, the chip satellite system still keeps the plane condition before the attitude maneuver is performed, so that under the plane condition, an antenna structure formed by electrical activity polymer drivers is under a condition that electrifying is not needed, and the chip star system can maintain the realized attitude maneuver without consuming any energy after the attitude maneuver is performed.

The invention relates to a processing machine having a processing wheel, which is in particular continuously driven, comprising at least one processing station for processing containers; comprising only one star for feeding and removing containers into and out of the processing device, which has at least two gripper elements for feeding containers to be processed to the processing station and for removing the processed containers from the processing station; wherein the processing station has a processing position within the processing station; characterized in that the processing station has at least one processing element processing a container, which is designed so that it can move the fed containers to be processed and / or the processed containers to be removed at least partially out of the processing position and / or into the processing position, in particular in a vertical or horizontal manner.

The present invention is directed to a synergistic blend of a sunscreen agent, specifically avobenzone and a specific class of ester that results in substantially improved sunscreen effectiveness, improving the performance of the sunscreen formulation as determined by the star system.

The present invention proposes an on-board router emulation method of a delay tolerant network, comprising: 1. Combining CCSDS and DTNRG to construct an on-board router model, and verifying feasibility and effectiveness in OPNET; 2. Realizing virtualization based on the SITL interface of OPNET Conversion of data streams and real data streams to verify gateway processing capabilities; 3. Use STK to obtain interstellar and star-to-earth link data in the network topology, and import simulation software to simulate interstellar networks; 4. Delay and error codes for network damage meters rate and other related settings to simulate space links. Therefore, the present invention has the following advantages: the integration of the existing space communication protocol system has proposed the router model on the star, and some preparatory work has been done for the system-level realization of my country's DTN protocol system and even the key technology research of the space information network; the combination of software and hardware is more real The environment of the satellite network is simulated, which is helpful to verify the applicability of the on-board router to the space environment.

The invention discloses a star system which comprises a body and a suspending structure. A control module is arranged in the suspending structure. The control module comprises a controller and a power module. The body comprises three auxiliary bodies which are arranged in parallel. One end of the suspending structure is fixed to a ceiling, and the other end of the suspending structure is connected with the three auxiliary bodies. The outer side of each auxiliary body is provided with an atmosphere lamp module and a star lamp module, and a purifying module is arranged in each auxiliary body. All the atmosphere lamp modules are connected to the controller in parallel. All the star lamp modules are connected to the controller in parallel. All the purifying modules are also connected to the controller in parallel. An air detection module, a loudspeaker module and an aromatherapy module are further arranged in each of the three auxiliary bodies, wherein the three modules are independently connected with the controller. By means of the star system, the requirements of users for air purifying, lighting, the environment starry sky feeling, sounds and tastes are met, the overall air environment of a user family is built through air mode control of application software at the mobile phone end, and the users can have more comfortable experiences.

The invention discloses a spacecraft three-super near-zero-error tracking control method based on combined filtering, and is suitable for the field of target tracking and having load super-high precision determination requirements. Different from traditional spacecraft star platform single-stage attitude control, the invention provides a star-load-fast steering mirror three-level attitude cooperative control method based on combined filtering for the spacecraft platform with three-super control performance such as super-high precision pointing, super-high stability control and super-sensitivecontrol. Pose calculation of a target is improved through deep learning, attitude control precision is improved step by step from a star system, a load system and a fast steering mirror system, and high-precision attitude control is provided for optical load fast tracking and high-quality imaging. The main idea of the method is as follows: establishing a three-level cooperative control system kinetic model; calculating the pose of the feature part of the target spacecraft based on deep learning; designing a multistage system fusion filter; and designing a three-stage cooperative control systemcontroller, including bandwidth design.

The invention provides a system used for short-distance flying target attitude measurement. The system comprises front-end starring systems and a rear-end processing and storage system, and an optical fiber transmission system connecting the two systems. The rear-end storage and operation system transmits an instruction before a flying target flies by or hits the bull's eye, and the instruction is transmitted to each front-end starring system via optical fibers. The laser lighting equipment and the high-speed video cameras of each starring system start to work. The photographed images are transmitted to the rear-end storage and operation system to be saved in real time. Multiple video cameras photograph the flying target at the same time in short distance. Parameters of attitude, speed, position and miss distance in hitting the bull's eye of the flying target can be measured according to certain known calculation methods. The front-end starring systems used for short-distance photographing are low in cost and particularly suitable for certain flying targets with destructiveness. The front-end starring systems within destructive range in miss distance explosion are allowed to be damaged and can act as consumables to be replaced and then the whole system can continuously work.

The invention discloses an SPEC-Net network architecture for multi-star spectrum automatic identification and an identification method. Belongs to the technical field of celestial body spectral data analysis and processing. The network architecture comprises a multi-star spectrum generation calculation model, a multi-star spectrum discrimination calculation model and a multi-star spectrum mapping calculation model. According to the method, feature extraction is carried out for different radial speeds of spectral lines of a multi-star system, multi-star spectral low-dimension representation with intra-class high cohesion and inter-class low coupling characteristics is obtained through an adversarial learning mechanism, and then automatic recognition is carried out on the representation; the SPEC-Net has good generalization generation performance; due to the existence of the multi-star spectrum mapping calculation model, the robustness and the stability of feature mapping are guaranteed; and an end-to-end solution for multi-star spectrum automatic identification is provided.

The invention discloses a method for verifying the collision algorithm of a space manipulator based on a microgravity simulation system, wherein the microgravity simulation system relied on includes hardware parts: an air flotation platform, a manipulator system, a target star system, and an industrial computer; and a software part : Robotic arm control software and data acquisition and analysis software. The bottom of the manipulator system and the target star system are respectively equipped with air feet, which can simulate the free floating state in space on the air floating platform after ventilation; the manipulator control software controls the manipulator to collide with the target star system, and the sensor collects the data before and after the collision. Various physical data are compared with the results obtained by the theoretical collision algorithm to verify the validity and correctness of the space collision algorithm.

The invention discloses a dynamic response analysis method and system of a satellite frame system, wherein the method includes: performing modal analysis on the support according to the finite element modeling results of the support, and satisfying the design requirements when the modal analysis results of the support When , conduct modal analysis on the satellite-frame coupling system to obtain the frequency of the satellite-frame coupling system; and when the frequency of the satellite-frame coupling system meets the set frequency, perform modal analysis on the satellite to obtain the Acceleration response value; determine the acceleration response value at the bracket installation place according to the acceleration response value at the characteristic point of the star-frame coupling body, and calculate the pull-out force at the bracket installation place; if the calculated pull-out force at the bracket installation place is less than the The pullout force of the embedded part is redesigned until it meets the requirements. The invention improves the structural design and dynamic analysis level of the satellite star frame system.

The invention discloses a dual-satellite system space track family searching method based on grid search, which relates to a dual-satellite system space track family searching method and belongs to the airspace technology field. The method comprises the following steps: conducting grid dividing to the initial state of a dual-satellite system space track for convenient search; through the comparison of the difference between the terminal state and the ideal state corresponding to the initial parameters and the relative position relation, obtaining the alternative initial state of an existing periodic track; through the use of the differential correction algorithm, obtaining the accurate initial state of the periodic track; and finally, according to the track energy, the track periods and the position distribution, obtaining different space track families. The invention can realize the search for the dual-satellite system space and the multi-orbit track, and with the method, more track families can be searched at higher efficiency so that track families whose initial parameters are sensitive can be conveniently obtained.

The invention relates to a relation model establishment method and system for intellectual property multi-dimensional data, relates to the technical field of data mining, and solves the problems thatprofessional data warehouse software is generally high in complexity, high in requirement on hardware and needs to be maintained by professional personnel; when a star model and a star system model are adopted, a central table becomes very large, and query efficiency and access efficiency are low. The method comprises the following steps: P101, determining a theme and a dimension; P102, constructing a dynamic Hash ring; P103, adjusting the Hash ring; P104, carrying out data positioning; and P105, completing data extraction and extracting data. Through a new center table construction mode, multiple center tables with the same theme are planned to be constructed to work cooperatively, the data size of a single center table is reduced, and the effect of improving the access efficiency of thecenter table is achieved.

The present invention proposes a calculation method suitable for pseudolite positions, including: judging whether it is a pseudolite system; if so, reading the coordinate constant of the pseudolite system; calculating normalized time; calculating the average angular velocity of the satellite; calculating respectively Mean anomaly angle, deviating anomaly angle, true anomaly angle, ascending node angular distance, perturbation correction item at the time of signal transmission; calculate ascending node angular distance after perturbation correction, satellite vector length and orbit inclination angle; calculate pseudolites Position on the orbital plane; calculate the right ascension of the ascending node at the time of signal launch; calculate the position of the pseudolite in the ground-fixed coordinate system. The invention only modifies the basic earth parameters in the satellite position algorithm, so that the space position of the pseudolite can be calculated by using four ephemeris parameters, and solves the problem that the original broadcast ephemeris cannot represent the coordinates of ground stationary objects.

The invention provides a health and elderly care big data cloud storage system. Wherein the cloud storage system adopts an unstructured data structure, and the unstructured data structure adopts an unstructured data star model based on subject behaviors; The cloud storage system adopts an integral service model which aims at health and elderly care data service requirements and can cover big datacharacteristics; The cloud storage system adopts a heat sensitive unstructured data retrieval ranking optimization algorithm; The cloud storage system adopts a hybrid prefetching algorithm based on data heat recognition. The cloud storage system adopts an unstructured data star system model and an integral service model, basic information and service information are comprehensively covered, and data retrieval adopts a heat sensitive unstructured data retrieval ranking optimization algorithm and a mixed prefetching algorithm based on data heat recognition, so that the accuracy of a data retrieval result is high, and the retrieval speed is high.