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 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.

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.

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 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 present invention provides a flight model satellite test method and system of a minisatellite. The method comprises the steps of (S1) carrying out thermal modification on a flight model satellite, (S2) loading a satellite for the flight model satellite, (S3) carrying out vacuum testing on the flight model satellite, and (S4) carrying out multiple-layer heat insulation material coating finishing on the flight model satellite. According to the method and the system, the overall task targets of low cost, short cycle and large volume of the minisatellite are achieved, the flight model test verification of the minisatellite is simply and rapidly completed, and the development cost and development cycle of a flight model development phase thermal control satellite are reduced.

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.

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 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 design method of an umbilical cable for minisatellite electrical logging. The reliability and the universality of the umbilical cable are comprehensively considered; short-circuit processing of a cable point is designed at the satellite end of a falling-off electric connector. In the electric connectors with the same model of the branch ends, the equipment ends corresponding to the same cable point number are designed to be the same, so that the universality of the umbilical cable and the utilization rate of the cable core wire are greatly improved, the possibility ofcable wiring errors is fundamentally eliminated, and the reliability of small satellite electric measurement is further improved.