48 results about "Minisatellite" patented technology

The present invention provides methods for use in identifying, analyzing and typing polymorphic DNA fragments, particularly minisatellite, microsatellite or STR DNA fragments. In particular, the invention provides methods using DNA polymerases, more particularly thermostable DNA polymerases, and most particularly Thermotoga polymerases or mutants or derivatives thereof, whereby minisatellite, microsatellite or STR DNA molecules may be amplified and analyzed for polymorphisms. The invention also relates to polymerases having reduced, substantially reduced or eliminated ability to add non-template 3′ nucleotides to a synthesized nucleic acid molecule. In accordance with the invention, such reduction or elimination may be accomplished by modifying or mutating the desired polymerase.

The invention relates to a satellite-earth communication integration system for a minisatellite, which is composed of a TT & C antenna network, a USB transponder, a remote control unit, a data processing unit, a data transmission ejector as well as a data transmission antenna. The system realizes the integration of the measurement and control and data transmission communication in the structure and the function, decreases the weight of the whole satellite, reduces the power consumption of the equipment and saves the manufacturing cost. The telemetering information and the load information share the same channel to download, which improves the utilization efficiency of the communications channel. Meanwhile, the remote control unit of the system is capable of demodulating to the uplink PSK signal, and also to the uplink acquisition data. The system has strong expansibility, which lays a basis for the application of the new data transmission technology in the satellite-earth communication integration system.

The invention discloses a cable testing system applied to a minisatellite. The cable testing system comprises a cable adapter module, a channel control module, a conduction testing module, an insulation testing module and a system self-inspection module. Cables to be tested with different port types are connected to internal channels of the system through the cable adapter module, the channel control module controls connection and disconnection of the internal channels, the conduction testing module measures conduction resistance value among the channels, the insulation testing module measures insulation resistance value among the channels, and the system self-inspection module inspects and calibrates the system. The cable testing system solves the problems of low conduction insulation testing efficiency, poor accuracy, long period and high strength in low-frequency cables on satellites and ground testing low-frequency cables, quick testing of conduction insulation characteristics of the cables can be realized, and the cable testing system is applicable to the low-frequency cables on the satellites and the ground testing low-frequency cables.

The invention relates to a system and method for carrying out automatic detection on small burning spots of forest or grassland fires by using the infrared (IRS) data of an environmental minisatellite HJ. The method comprises the following steps: radiometric correction, brightness temperature calculation, reflectivity calculation, cloud and water recognition, potential burning spot determination,absolute burning spot determination, background characteristic analysis, relative burning spot determination, burning spot confidence, and detecting burning spot output. According to the scheme provided by the invention, based on the characteristics of the environmental minisatellite HJ, the automatic detection on forest or grassland fires can be realized only by using the infrared (IRS) data, thereby enhancing the disaster prevention and reduction capacities of domestically-produced satellites in China, and promoting the industrialized application process of domestically-produced satellites.

The invention provides a data transmission antenna whole-satellite testing method based on a minisatellite information system. At first, orbital data are input to a satellite attitude control system and a GPS dynamic simulator, by regulating orbit parameters of the satellite attitude control system, controlling start-up time of the GPS dynamic simulator and satellite-arrow separating time, and combining a program control command and a program control data block sequence, time information, orbit information and attitude information of the satellite attitude control system, a GPS receiver and a satellite task distribution system are completely synchronized, testing data are obtained by controlling a data transmission antenna to carry out ground station tracking, and finally, by comparing theoretical data and the testing data of antenna tracking, actual antennal tracking angle errors under different orbit conditions and different satellite attitudes are obtained. According to the data transmission antenna whole-satellite testing method, the orbit and time information state of a minisatellite are accurately simulated, testing of the data transmission antenna under the whole-satellite state of the minisatellite is achieved, and the method is applied to other types of minisatellites at present.

This invention discloses a method for scheduling efficient resource of a minisatellite network based on earth observation tasks, and solves the problems that the end-to-end throughput capacity is low and the utilization efficiency of the network resource is low because the network resource is not fully considered during the scheduling process in the earth observation scene of the resource-limited minisatellite network. The method comprises the implementation processes of: according to an initial network topology, determining a node number; at the same time, initializing a network resource scheduling planning time set; according to current network state and resource scheduling conflict restraint, constructing a link scheduling conflict graph by a ground control center; solving a maximal independent set corresponding to the conflict graph to acquire a network conflict-free scheduling link set; by using the link set and a linear programming, solving a resource allocation scheme and a data transmission method capable of mostly optimizing the network efficiency till a time slot is ended. The method improves the resource utilization ratio, increases the returning efficiency of important task data, improves the earth observation network performance of the minisatellite, and is used for scheduling the efficiently transmitted resource of earth observation system data.

The invention discloses an optical imaging minisatellite attitude control system and an in-orbit working mode switching method, belongs to the field of satellite attitude control and aims at solving the problem that existing optical imaging satellites cannot be simply and effectively switched in the orbit. The optical imaging minisatellite attitude control system comprises an attitude measurement sensor, an actuating mechanism and an attitude controller, wherein the attitude measurement sensor comprises a sun sensor, a star sensor and a gyroscope; the actuating mechanism comprises a counteraction flywheel and a magnetorquer. According to an in-orbit working mode switching method of the optical imaging minisatellite attitude control system, the optical imaging minisatellite attitude control system has six working modes, namely a rate damping mode, a sun capture mode, a sun-orientated three-axis stabilization mode, an earth-orientated three-axis stabilization mode, a data transmission mode and a safety mode. The optical imaging minisatellite attitude control system and the in-orbit working mode switching method are suitable for all the optical imaging minisatellites.

A general simulation system of a measurement and control subsystem of a minisatellite spread spectrum system comprises a measurement and control signal processing simulation module, a measurement and control interface simulation module, a GPS simulation module and a simulation control platform. The general simulation system can achieve radio frequency processing, intermediate frequency processing and baseband processing of measurement and control signals, achieve simulation with physical interfaces of other lower computers, and achieve output or forwarding of GPS pulse per second signals and broadcasting of time and orbital data when being in a semi-physical working mode, wherein the physical interfaces comprises the CAN bus interface, the remote measurement and control interface, the direct instruction interface, the clock output interface and the star arrow separation signal output interface. The general simulation system can receive remote measurement and control data in an LAN bus for interface simulation and GPS simulation when being in a full-digital working mode. Configurable function board cards are selected, the PXI bus technology is adopted, the integration degree is high, configuration is flexible, cost is low, function extension of the system can be conveniently conducted, the requirement for verification of multiple new technologies of the minisatellite measurement and control subsystem can be met, and the electric performance test environment of the measurement and control subsystem can be provided for development of a novel minisatellite platform.

The invention discloses a multi-function combination lifting device for a minisatellite, comprising a triangular special-shaped lifting unit (1) at the upper portion and three straight beam lifting units (2) at the lower portion, wherein the triangular special-shaped lifting unit (1) comprises a three-leg combination lifting belt (3), a shackle (4), a large connection block (5), a pin roll (6) and a triangular beam (7); the straight beam lifting unit comprises a lifting belt (8), a small shackle (14), a small connection block (9), a beam (10), a small lifting belt (11), six turn buckles (12) and six quick-release stop pins (13); and the triangular special-shaped lifting unit (1) is connected with each straight beam lifting unit through the shackle (4). According to the invention, by combining the triangular special-shaped lifting unit with the three straight beam lifting units, the problem of lifting a minisatellite with six lifting points and six prisms is solved; simultaneously, the triangular special-shaped lifting unit has a stable triangular structure, thus the adaptive ability is strong, and uniform stress distribution of the six lifting points can be realized without adjusting the level of the minisatellite.

The invention relates to a double-planar-array three-dimensional plotting system, in particular to a double-planar-array three-dimensional plotting system based on a minosatellite platform, and aims to solve the problems that a processing method of an existing plotting system is complicated, requirements for attitude stability of a satellite platform is high, data cannot be transmitted in real time, processing is inconvenient and the like. The plotting system comprises a house-keeping system, a measurement and control system, an attitude and orbit control system, a power supply system, a thermal control system, a first star sensor, a second star sensor, a data transmission system, a three-axis gyroscope, a foresight planar array camera, a rearview planar array camera and a foresight and rearview optical system in-orbit included angle detection system. The foresight planar array camera and the rearview planar array camera share an imaging and focusing controller; the foresight and rearview optical system in-orbit included angle detection system is used for detecting the changes of a foresight and rearview optical system in-orbit included angle in orbit in real time. The system develops a large-scale double-planar-array three-dimensional plotting research based on a minisatellite in combination with satellite-borne integration and low-orbit operation techniques, reduces the requirements for satellite attitude and orbit measurement accuracy and can realize plotting without the aid of control points.

Provided is a control-limited minisatellite three-axis magnetic moment attitude control method based on an algebraic Lyapunov equation. The invention relates to a control-limited minisatellite three-axis magnetic moment attitude control method based on an algebraic Lyapunov equation. The method is used to realize global stability of a minisatellite three-axis magnetic moment attitude control under control-limited conditions. The method comprises: step 1, establishing attitude kinematics and attitude kinetic models of control-limited minisatellite three-axis magnetic moment attitude control, to obtain a state-space equation; step 2, solving explicit solution P0 of the algebraic Lyapunov equation A<T>P0+P0A=-D<T>D, wherein A is a system matrix, D is a matrix in arbitrary dimensions, the system matrix A being critical stable or Lyapunov stable, ensuring the algebraic Lyapunov equation have a positive definite solution P0; step 3, and through the positive definite solution P0 of the algebraic Lyapunov equation, designing linear feedback control law under explicit control-limited conditions. The method is applied in the field of satellite control.

The invention relates to a high-speed data communication method based on a minisatellite cluster ad-hoc network. According to the method, a hybrid network structure is adopted, a minisatellite cluster firstly adopts a centerless ad-hoc network structure, interaction of related information of networking operation control in the cluster is realized, and on the basis, services such routing, route building and control are provided for high-speed transmission of satellite sounding data in the cluster. The hybrid network structure combines advantages of a centerless structure and a centered structure, can realize high-speed transmission of the sounding data in the cluster under the conditions of different mission requirement and different formation configuration, and has a series of advantages of no center, self discovering, automatic configuration, self organization, fault self-recovery, self-adaptive formation changing, high reliability, high availability and the like of a wireless ad-hoc network.

The invention relates to a minisatellite electronic load task uploading method using a task template. The minisatellite electronic load task uploading method includes the steps: 1) when a satellite enters a detectable and controllable area, starting an electronic load lower computer; receiving a task template uploading data packet uploaded by a ground station; and storing a task template in the load lower computer, completing uploading of the task template, storing the task template and shutting down the computer; 2) when the satellite enters a detectable and controllable area again or repeatedly later, starting the electronic load lower computer, and reading the stored task template; 3) receiving a task uploading data packet uploaded by the ground station; and 4) storing the task packet in the load lower computer, completing in-orbit generation of the task packet, storing the task packet and shutting down the computer. The minisatellite electronic load task uploading method using a task template solves the problem that a traditional minisatellite electronic load needs uploading the complete task packet data to a satellite during every task uploading process so that the uploading efficiency is lower, and can reduce the task uploading quantity for minisatellite electronic load and improve the task uploading efficiency, and the reliability and safety of the satellite.

A minisatellite integration comprehensive test system based on an MAC Panel solves the problems that the number of minisatellite ground test devices is large, the size is large, the universality is poor, and the design and development cycle is long. Devices of three branch systems (a power supply and distribution branch system, a measurement and control system and a star service branch system) of the minisatellite comprehensive test system are integrated in one device, so that the size, the number, the cost and the development cycle of the test devices are greatly reduced. On the basis that PXI equipment of the NI company is used for achieving integration of the functions of the three test branch systems, a large-scale interconnection mechanism produced by the MAC Panel company is used for achieving satellite-to-ground interface adaption and free allocation of equipment inside signals, finally, the internal structure and external interface function of the minisatellite integration ground test system is achieved, and the integration and universalization of the minisatellite ground comprehensive test system are achieved.

A minisatellite and its constellation availability evaluation method based on Monte Carlo simulation. The method includes following steps: 1, acquiring a fault list of faults of classes I and II in severity of classes I and II through FMEA analysis; dividing the faults in the list according to whether the faults are repairable or not; 2, for the repairable faults, utilizing the Poisson process tomodel fault laws, utilizing on-orbit data to calculate repairable fault failure rate, determining parameters of the Poisson process; for unrepairable faults, utilizing the Wiener process to model thefault laws, and utilizing ground test data or on-orbit failure data to determine parameters of the Wiener process; 3, determining minisatellite fault criteria and constellation fault criteria, and performing availability simulation on a minisatellite and its constellation; 4, through a simulation result, calculating a ratio of on-orbit normal working duration to service life of the minisatellite,and calculating on-orbit availability of the minisatellite and its constellation. By the method, complexity of availability evaluation can be effectively reduced while minisatellite availability evaluation result accuracy is ensured.

The invention discloses a universal ground power distribution testing cable system for minisatellites. The branch cables and contact distribution among a satellite umbilical cable and a power distribution testing device and an umbilical cable, among a solar cell square matrix simulator, a stabilized-voltage power supply and the umbilical cable and between a satellite equivalent device and a satellite-ground simulation connector assembly, reserves a part of standby contacts, improves the flexible of cable design, improves the universality to the maximum degree, and enlarges the application range. The system can be applied to all minisatellites under the condition that the design rule of a satellite-ground interface is not betrayed, changes a situation that a person needs to design and develop a dedicated satellite-ground power distribution testing cable for each satellite, and greatly saves the manpower, material resources and time cost.

The invention discloses a power supply interface detection method for a minisatellite comprehensive test. The power supply interface detection method includes 1, connecting a self-checking cable and an extension cable; 2, switching a system to a self-checking mode; 3, measuring standard voltage and performing data comparison; 4, connecting a cable to be detected with a system main unit; 5, powering up a minisatellite; 6, switching the system to a test mode; 7, measuring voltage of a cable to be detected on the minisatellite; 8, interpreting measuring data. The power supply interface detection method has the advantages that the traditional cable detection method is modified; compared with the traditional manual measurement method, the method of measuring minisatellite supply voltage and recording and interpreting the measurement data is greatly improved; during the minisatellite power supply interface detection, test process is simplified, and test efficiency is improved.

The invention provides an on-satellite energy control system based on an ARM (Advanced RISC Machine). The system utilizes an ARM microcontroller which is high in on-chip resource integration level, small in size and low in power consumption to form an intelligent component used as a core processing module for energy management; multiple on-chip resources such as an analog / digital converter and a CAN (Controller Area Network) which are integrated on an ARM processor are utilized, so that corresponding peripheral circuits are not required to be additionally established so as to realize the control function in a minisatellite energy management process. Therefore, the complexity of a minisatellite energy management system is simplified, the cost of the minisatellite energy management system is lowered, the real-time performance and the integrated level of energy management are improved; and in addition, dynamic management is carried out on loads, during an ontrack running period of a minisatellite, telemetry parameters such as the voltage of a storage battery, the current of a matrix and the load current are periodically monitored, slicing management is carried out on an energy space, and then the divided energy spaces are used by different loads, so as to guarantee the reasonable, safe and effective use of satellite energy and further improve the energy utilization.

The invention provides an FPGA (field programmable gate array)-based minisatellite-borne AIS (automatic identification system) signal acquisition system. Ship AIS signals received by a VHF (very high frequency) antenna are subjected to narrow-band filtering and amplification through a front-end radio-frequency processing module and then sent to an A / D (analog / digital) conversion circuit for analog-digital conversion to obtain medium-frequency digital signals, the medium-frequency digital signals are sent to an FPGA master control processing module for down conversion, filter extraction, zero-frequency adjustment, frequency mixing, decimation filtering and threshold setup, and extracted AIS digital signals are outputted after data coding. The FPGA-based minisatellite-borne AIS signal acquisition system has the advantages of high stability, high radiation resistance, stability in operation and simplicity in circuit design.

The invention provides a method for determining flutter response of high-resolution minisatellites. Through a determination method of adopting a single frame to control disturbing torque produced by the dynamic imbalance of moment gyroscope rotors, the invention solves the problem of determining the flutter interference of the high-resolution minisatellites of the type. The method realizes the decoupling and degree reduction of a satellite-flutter vibration mechanical equation among degrees of freedom through appropriate state variable settings and replacement, transforms the vibration mechanical equation into a first order differential equation, and utilizes a numerical solution to determine attitude response produced by satellites under the action of flutter interference sources, so themethod is concise and normative. For the attitude response of the satellites caused by the action of flutter interference, the method combines satellite attitude control laws to eliminate controllable parts in flutter attitude response, and finally determines the flutter response of the satellites under the action of the flutter interference sources. The determination method can also adjust and control the disturbing torque of moment gyroscopes by regulating the installation modes and machining accuracy of the gyroscopes so as to achieve the aim of improving image quality.

A minisatellite splicing imaging ground simulation system relates to the technical field of minisatellite remote sensing simulation imaging, solves the problem that general ground simulation test equipment for minisatellite on-orbit splicing imaging is needed urgently, and comprises an air floating platform, a camera imaging unit, a moving guide rail and a target unit; the camera imaging unit is arranged on the air floating platform, and the target unit is arranged on the moving guide rail; the air floating platform simulates the space working environment of the small satellite camera imagingunit, the target unit can move up and down and left and right on the moving guide rail, an image can be displayed on the target unit, the displayed image can move left and right, and the camera imaging unit images the target unit. The system is easy to operate, high in accuracy, high in reliability and high in flexibility, small satellite splicing imaging ground simulation is achieved, universality is achieved for small satellite on-orbit splicing imaging ground simulation, and meanwhile the application field of the air floating platform is expanded.

The invention provides an optical imaging minisatellite power dissipation budgeting and energy balance analysis method. The method comprises the steps that firstly, on the basis of the using requirement of a user, the satellite power dissipation value under each working mode is calculated in a self-defined mode; then, according to the satellite working mode, the power dissipation value is reasonably considered according to the monorail working state, and the total energy dissipation of satellite monorail is calculated; according to the model selection of different battery arrays and design margin, and then, solar battery array parameters meeting the energy balance requirement are calculated and include solar battery array monorail minimum energy, solar battery array minimum power, solar battery array minimum effective area, solar battery array minimum design area, solar battery array design area obtained after margin is considered, solar battery array effective area obtained after margin is considered, solar battery array power obtained after margin is considered, and solar battery array monorail energy obtained after the margin is considered; finally, the energy requirement for the lithium battery pack is calculated, and battery model selection is performed. According to the method, on the basis of the actual using mode of satellites, whole-satellite energy satisfaction degreeanalysis is reasonably completed.

The invention discloses a minisatellite constant thrust orbit recursion method considering multiple perturbation forces. The method comprises the following steps: establishing a kinetic model containing constant thrust and multiple perturbation forces according to the on-orbit operation condition of a minisatellite, performing orbit deduction by using a Runge-Kutta RK45 method based on a kinetic component equation, and comparing with the result of SKT simulation software, controlling the error of the orbit recursion method under the constant thrust within 1km. By using the method, the orbit ofthe minisatellite can be accurately given, and the position information of the minisatellite can be determined in time.

The invention discloses a method for determining a random vibration power spectrum of a minisatellite optical camera environment test, and the method comprises the steps of obtaining a camera installation surface response power spectrum PSD1 through calculation according to the information of a minisatellite whole-satellite product and a mechanical environment random vibration test power spectrumPSD0 used by a whole satellite; according to the camera product information, obtaining the mass of the whole and internal components of the camera and a component tolerance power spectrum PSD2; formulating process random vibration test power spectrums PSD3 and PSD4 of the whole and internal components of the camera; and according to the random vibration test power spectrum PSD3 of the overall process of the optical camera, obtaining the response power spectrum PSD5 of the installation surface of the internal component of the optical camera. According to the invention, the environmental adaptability of the optical camera is fully verified, the process screening is assessed, the over-design and over-test of the optical camera can be effectively avoided, and a foundation is laid for the smooth development of product development.

The invention discloses a minisatellite data time-choosing transmission method based on binary search. The minisatellite data time-choosing transmission method comprises the following steps: a storage process: dividing a read cache space and a write cache space in the memory of a minisatellite, and storing user frame data into the write cache space according to a sequence of sampling time; and a reading process: setting the time range of time choosing and the data category of target data, adopting a binary search algorithm to obtain an initial page address of the target data in a memory, reading original information in the memory according to a storage sequence of the initial page address, carrying out protocol encapsulation on the read original information, and issuing through a transmitter. The minisatellite data time-choosing transmission method is simple and effective, adopts hierarchical design and has the advantages of being low in coupling between modules, high in module transportability and high in reliability, and I / O operation and business control are mutually isolated; the binary search algorithm is adopted, so that search time is short, effective data which meets destination time requirements can be obtained in short time, the use ratio of a channel is high, and the minisatellite data time-choosing transmission method has an important application meaning in a minisatellite field.

The invention discloses a minisatellite delivery reliability problem screening rate calculation method, and belongs to the technical field of satellite overall design. The method includes: carrying out statistical analysis on reliability problems of a plurality of launched small satellites of the same type in a normal sample development stage; and obtaining delivery reliability problem distribution data and a reliability problem distribution formula of the minisatellites, substituting the accumulated power-up time of the whole satellite in the sample correction stage before delivery of the satellites into the reliability problem distribution formula, and calculating the delivery reliability problem screening rate of the satellites. The minisatellite reliability screening rate calculated bythe method can more visually represent the production reliability of the satellite, solves the problem that the reliability prediction does not exist and is disconnected with the actual development test and test activities of the satellite product, and can provide a more accurate, real and reliable evaluation effect for the satellite development and production activities.

The invention provides a data transmission antenna whole-satellite testing method based on a minisatellite information system. At first, orbital data are input to a satellite attitude control system and a GPS dynamic simulator, by regulating orbit parameters of the satellite attitude control system, controlling start-up time of the GPS dynamic simulator and satellite-arrow separating time, and combining a program control command and a program control data block sequence, time information, orbit information and attitude information of the satellite attitude control system, a GPS receiver and a satellite task distribution system are completely synchronized, testing data are obtained by controlling a data transmission antenna to carry out ground station tracking, and finally, by comparing theoretical data and the testing data of antenna tracking, actual antennal tracking angle errors under different orbit conditions and different satellite attitudes are obtained. According to the data transmission antenna whole-satellite testing method, the orbit and time information state of a minisatellite are accurately simulated, testing of the data transmission antenna under the whole-satellite state of the minisatellite is achieved, and the method is applied to other types of minisatellites at present.

The invention discloses a minisatellite data time-choosing transmission method based on binary search. The minisatellite data time-choosing transmission method comprises the following steps: a storage process: dividing a read cache space and a write cache space in the memory of a minisatellite, and storing user frame data into the write cache space according to a sequence of sampling time; and a reading process: setting the time range of time choosing and the data category of target data, adopting a binary search algorithm to obtain an initial page address of the target data in a memory, reading original information in the memory according to a storage sequence of the initial page address, carrying out protocol encapsulation on the read original information, and issuing through a transmitter. The minisatellite data time-choosing transmission method is simple and effective, adopts hierarchical design and has the advantages of being low in coupling between modules, high in module transportability and high in reliability, and I / O operation and business control are mutually isolated; the binary search algorithm is adopted, so that search time is short, effective data which meets destination time requirements can be obtained in short time, the use ratio of a channel is high, and the minisatellite data time-choosing transmission method has an important application meaning in a minisatellite field.