56 results about "Micro satellites" patented technology

A microsatellite comprising a propulsion module for moving and/or pointing said microsatellite and an imaging device (100) mounted to said propulsion module. Furthermore there is a fuel supply (210) located within said imaging device (100).

The invention relates to a phased array data transmission guide control method based on onboard real-time planning and relates to the field of spacecraft attitude determination and control. The method realizes a function of achieving fast data transmission after imaging of micro satellites and performing data transmission while imaging. The method comprises the following steps: if an imaging mode is used, setting the imaging priority and the data transmission priority as 1 and 0 respectively; if data transmission is simultaneously performed by two data transmission stations, ranking the priorities of the digital transmission stations, setting the priority of the digital transmission station with high priority as 1 and the other one as 0; if a single data transmission station performs the data transmission, setting the priority of the data transmission station as 1; calculating the expected orientation, the azimuthal angle and the off-axis angle of a phased array antenna; if the off-axis angles satisfies a constraint condition, requiring no posture maneuver, otherwise, setting a mode with a priority of 1 as dominant; and in the case of the mode with a priority of 1 as dominant, if the off-axis angle satisfies the constraint condition, enabling the satellite not to require attitude maneuver, otherwise using the data transmission station with high priority as an expectation and enabling the phased array antenna to point to a target point by controlling the attitude of the satellite. The method can realize fast data transmission and data transmission during imaging.

The invention provides an online dynamic task planning terminal and planning method for medium and low orbit micro satellites. The terminal of the invention adopts an online task planning module of aparallel processing structure, and when the satellite maintains communication with a ground measurement and control station, the communication and coordination among multiple satellites, and dynamic task planning are achieved in combination with a Beidou short message transceiver. The method of the invention adopts the form of an auction contract network, and comprises: processing auction rights,selecting a dominant satellite, and selecting the current auction task. The dominant satellite performs bidding on member satellites for the task. A bidder performs task bidding according to an own state. A tenderee completes bidding evaluation according to a bidding evaluation strategy and selects a contract satellite. Contract establishment, and process monitoring and contract information updateare completed, and the contract is terminated after the task is completed. By adoption of the online dynamic task planning terminal and planning method provided by the invention, the online dynamic task distribution and rational planning of a plurality of medium and low orbit micro satellites can be achieved, the efficiency is relatively high, the planning result is feasible, and it has practicalsignificance for improving the on-orbit autonomy and joint planning capability of the micro satellites.

The invention discloses a non-biased momentum single-flywheel magnetizing control method which includes the following steps that a flywheel is installed along a rolling axis, and the wheel control mode of the rolling axis and the magnetic field intensity used for magnetic control are determined; the flywheel is installed along a yaw axis, the wheel control mode of the yaw axis and the magnetic field intensity used for magnetic control are determined; the flywheel is installed in an inclined mode, a wheel control mode and the magnetic field intensity used for magnetic control are determined; non-biased momentum satellite three-axis stable control is achieved through three-axis magnetic-control current output and flywheel magnetic dumping fusion control of a pitch axis. The non-biased momentum single-flywheel magnetizing control method is simple in system configuration, only one flywheel and magnetic control can achieve the non-biased momentum satellite three-axis stable control, system reliability is improved, the method can be applied to flywheel fault control modes of micro-satellites and medium-and-large-sized satellites, switching of angular momentum exchange control and gyroscopic torque control can be achieved according to rolling intensity and yaw magnetic field intensity, algorithm and calculation are simple and the method is easy in engineering application.

A satellite communication system for an aircraft communicates with multiple satellite constellations. The communication system includes a phased array antenna system and a transceiver. The transceiver is configured to communicate with a number of satellite constellations and configured to support simultaneously links to two or more constellations via the phased array antenna system. The satellite constellations can be micro-satellite, MEO, LEO, and GEO constellations.

A self-spinning separation device is provided. one end of the self-spinning separation device is mounted on the vehicle end, one end of the self- spinning separation device fits with the star throughan axle hole, so that torque transmission is realized, separation angular velocity for microsatellite separation is provided. The device comprises a coil spring spinning assembly, wherein the coil spring spinning assembly comprises an adjustable torque coil spring and a detachable torque adjusting lever; the adjustable torque coil spring is used as an energy storage assembly, and the torque adjusting lever is rotated to different angles to realize the adjustment of the initial torque of the coil spring in different gears, so as to meet the different starting angular velocity requirements of different micro satellites. The self-spinning separation device provided by the invention has the characteristics of lightweight, compact structure and high reliability, and is a self-starting separation device with high application value in the field of micro satellites.

The invention relates to a sample machine on the basis of the principle of a nitrous oxide mono-component thruster and a use method thereof. The invention utilizes the characteristics of the nitrous oxide gas such as no toxicity, no pollution, high catalytic decomposition temperature and capability of self-maintaining decomposition reaction, and applies the nitrous oxide gas in the propulsion field of aerospace micro-satellites. Compared with the existing commonly-used hydrazine mono-component thruster, the invention can effectively reduce the risk and cost of land disposal with a propellant, and also can realize higher specific impulse performance compared with the cold gas thruster. The invention can conduct principle demonstration verification for mono-component thruster adopting the nitrous oxide as the propellant, and provide technical support for research and development of a non-toxic micro-thruster applied in posture control of the micro-satellite.

The invention provides a thermo-chromatic infrared emitting ability ceramic sheet material and a preparation method thereof, belonging to the technical field of function materials. The thermo-chromatic infrared emitting ability ceramic sheet material is a La1-xSrxMnO3 system ceramic sheet material with a perovskite structure. The preparation method of the material comprises the steps of mixing 2-hydroxy tricarballylic acid and pure water into raw materials of La2O3, SrCO3 and MnCO3 with a certain mole ratio, performing ball milling, and drying the mixture to obtain a presoma; presintering the presoma under the temperature of 700-1000DEG C, performing ball milling and frying again, and sintering under the temperature of 900-1450DEG C to obtain sintering powder; and rolling into a raw ceramic sheet, gluing, and sintering under the temperature of 900-1200DEG C to obtain a final product. The infrared emitting ability of the thermo-chromatic infrared emitting ability ceramic sheet material is improved with the increase of the temperature, so that the infrared emitting ability saltation near a room temperature can be realized, and the maximum variation range of the emitting ability reaches 0.47. Meanwhile, the material has the advantages of being high in reliability, free of power consumption and light in weight, can meet the thermal control requirement of micro-satellites, and can be widely used in technical fields of infrared camouflage and energy conservation.

The system and method represents a high-resolution, three-dimensional, multi-static precipitation RADAR approach that employs agile microsatellites, in formation and remotely coupled, via a new high-precision, ultra-low power, remote timing synchronization technology. This system and method uses multi-static RADAR interferometric methods implemented via a microsatellite formation to synthesize an effectively large (e.g., 15 m) aperture to provide about 1 km horizontal resolution and about 125 m vertical resolution in the Ku-band.

The invention discloses methods for acquiring a micro-satellite sequence and polymorphic micro-satellite markers of hucho taimen and the polymorphic micro-satellite markers of the hucho taimen, which relate to a method for acquiring the micro-satellite sequence and the polymorphic micro-satellite markers and the polymorphic micro-satellite markers. The method for acquiring the micro-satellite sequence comprises the following steps: firstly, extracting a hucho taimen genome DNA; secondly, performing enzyme cutting on the hucho taimen genome DNA and constructing a micro-satellite enrichment library; and thirdly, performing colony PCR amplification and performing positive clone detection and sequencing. The method for acquiring the polymorphic micro-satellite markers of the hucho taimen comprises the following steps: performing the first step to the third step the same as that of the method for acquiring the micro-satellite sequence; fourthly, analyzing the micro-satellite sequence of the hucho taimen and designing a primer; and fifth, performing polymorphic identification on the primer of the micro-satellite sequence. The method acquires seven pairs of the polymorphic micro-satellite markers of the hucho taimen. The biological materials obtained by the methods can be used for conservation genetics, genetic relationship analysis, linkage map construction and genetic management of cultured populations of the hucho taimen.

The invention belongs to the technical field of colony identification in aquaculture, and discloses a micro-satellite marker and specific primer for identifying female and male individuals of pseudobagrus ussuriensis, and application. One sex-specific micro-satellite site of the pseudobagrus ussuriensis is provided, and has a nucleotide sequence shown by any one of SEQ ID NO:1-2. The invention also provides a primer designed from the micro-satellite site, and the primer has a nucleotide sequence shown by SEQ ID NO:3-4. One micro-satellite site is screened out of a micro-satellite enriched library of the pseudobagrus ussuriensis, and a specific primer is designed according to flanking sequences at two ends of a micro-satellite, so that an amplification result has sex specificity, the female and male individuals of the pseudobagrus ussuriensis can be effectively identified, and the specific primer can also be used for performing real-time monitoring on sex structures of colonies in natural water areas and breeding places. The invention also discloses a kit for identifying the female and male individuals of the pseudobagrus ussuriensis. The identification method provided by the invention has the advantages of high accuracy, high resolution ratio and high speed.

The invention discloses a constructing method of micro-satellite marked scallop, which comprises the following steps: extracting DNA; connecting adapter cut by enzyme; preaugumenting before crossing; crossing to enrich micro-satellite sequence through micro-satellite marked by biotin and SAV magnetic bead; obtaining DNA segment with enriched micro-satellite sequence; augumenting the segment; constructing the enriched library with enriched micro-satellite sequence; utilizing PCR to sieve the micro-satellite sequence; obtaining the result of DNA sequence; comparing the quality of segment with enriched micro-satellite sequence; designing the primer of micro-satellite sequence; adopting PAGE to detect and sieve the augumentation, polymorphism and stability of micro-satellite; statisticallizing genetic parameter of corresponding group.

The invention discloses a non-biased momentum single flywheel magnetizing control algorithm. The non-biased momentum single flywheel magnetizing control algorithm comprises the following steps: step 1, a flywheel is mounted along a rolling axis (X axis); a wheel control mode and a magnetic density used for magnetic control are determined; step 2, the flywheel is mounted along a yaw axis ( Z axis ); a wheel control mode and a magnetic density used for magnetic control are determined; step 3, the flywheel is mounted in an inclined manner; a wheel control mode and a magnetic density used for magnetic control are determined; step 4, an integrated control is conducted on the triaxial (X axis, Y axis and Z axis) electrical current output and magnetic unloading of the flywheel on the Y axis; therefore, triaxial stable control of the non-biased momentum satellite is realized. The non-biased momentum single flywheel and magnetizing control algorithm is simple in the configuration requirements; all that is needed is to adopt a single flywheel and the magnetic control, so as to realize the triaxial stable control of the non-biased momentum satellite; the system reliability is improved; the non-biased momentum single flywheel and magnetizing control algorithm provided by the invention can be applied to flywheel fault control modes of micro satellites and medium and large-scale satellites; angular momentum exchange control and gyroscope torque control switch are conducted according to rolling and the yaw magnetic density; the calculation in the algorithm is simple, thereby being easy for engineering application.

A system and method of providing an affordable navigation, guidance and control system for arbitrary nano/micro launch vehicles by integrating commercial grade sensors with advanced estimation algorithms in a manner that provides sufficient accuracy of the resulting vehicle state estimates to inject nano/micro satellites into low earth orbits. The system and method uses commercial grade sensors and an advanced sensor-fusion estimator software that estimates and removes the estimated measurement errors and filters noise produced by the commercial grade sensors, resulting in estimated states with suitable accuracy. The filtered data are sent to a guidance and control system where actuator commands are formulated based on the filtered data. A simulated launch and flight of the launch vehicle is performed using the filtered data to validate that the GNC system and launch vehicle are ready for launch.

A rigid-flexible bonding plate solar cell array the invention is integrated with a substrate through a solar cell module, A substrate and a substrate are connected with each other through a flexible board to realize circuit connection, so as to form a solar cell array in which the solar cell circuit and the substrate are completely integrated, This kind of solar array is a folding type, which saves wires and cables, makes full use of the limited envelope space of micro-satellites, maximizes the area of solar array, realizes the maximum output of solar array electric power in the limited envelope range, meets the satellite power supply demand, and solves the problem that the solar wing of micro-satellites is limited by the envelope size of stars.

The invention provides an electrical bus applicable to micro satellites, comprising physical topology, working mode and interface definition. According to the physical topology, a power bus and a data bus are connected in parallel and carry out transmission independently. In the aspect of working mode, hot backup is adopted. In the aspect of interface definition, the electrical bus leads out a power signal and a data signal through a three-way electrical connector, and the electrical bus and an on-satellite standalone device are interconnected by the same electrical connector. According to the invention, the power bus and the data bus are integrated on the same electrical connector, the contact is defined as the general cable standard, the design ensures that power signals and data signals are transmitted independently and do not interfere with each other, the complexity of whole-satellite power supply and data transmission is reduced, the degree of product standardization and interface unification is improved, the complexity and weight of a whole-satellite cable are reduced, and the design idea of 'plug and play' for micro satellite electronic products is realized.

The invention aims at providing a spaceborne VHF antenna device, which is a linearly-polarized spaceborne VHF antenna device with plane deformation loading IFA. The spaceborne VHF antenna device comprises a reflection plate, a feeding unit and an antenna radiation unit, wherein the antenna radiation unit comprises a planar inverted F antenna main body part formed by a left antenna radiation plateand an upper antenna radiation plate and multiple tail antenna radiation plates located at the tail end of the right side of the upper antenna radiation plate; and the feeding unit is arranged betweenthe reflection plate and the upper antenna radiation plate of the antenna radiation unit. While the main electrical performance index requirements of the existing antenna can be met, the spaceborne VHF antenna device has the advantages of miniaturization, light weight, high adaptability to all kinds of satellites (especially microsatellites and micro satellites) and the like.

The invention discloses a micro-field emission electric thruster with a blade type porous material emitter array. The micro-field emission electric thruster comprises a neutralizer and a thruster main body, the two of which are connected with each other; the thruster main body comprises a grid electrode, an insulating support and a propellant storage chamber, all of which are matched and connected with each other in order from top to bottom; the insulating support is of a frame-shaped structure; a blade type emitter array matched with the grid electrode is arranged within the insulating support; matched heater and propellant are arranged below the emitter array; the propellant and the heater both are located within the propellant storage chamber; as a result, the minimization of the structure of the field emission electric thruster is realized to meet the requirements of micro-satellites having a weight of less than 50kg.

The invention provides a method for determining satellite attitude based on a visible light earth sensor. The method employs the visible light earth sensor to determine the two-axis attitude of a satellite relative to the earth and comprises the following steps: processing an earth image produced by a CMOS imaging device so as to extract the effective boundary of the earth image; then extracting the center of the effective boundary by using least squares fitting; and on the hypothesis that the attitude angle of the satellite relative to the earth is a small angle, approximately calculating the roll angle and pitch angle of the satellite relative to the earth so as to eventually determine the two-axis attitude of the satellite relative to the earth. Compared with a traditional method using an infrared earth sensor for determination of the rolling and pitching two-axis attitude of satellites relative to the earth, the method provided by the invention has the advantages that the method improves the measurement precision of the two-axis attitude of the satellite relative to the earth, is applicable to measurement of the attitude miniature micro-satellites and conforms to the current development trend of micro-satellites.

A microwave radiometer with reduced volume, mass, phase noise, and power requirements and increased harmonic rejection, includes a fixed number of frequency banks configured to provide signals within separate, non-overlapping local oscillation frequency bands, a detection circuit configured to detect one or more microwave RF signals, and an RF downconverter configured to mix the signals within the separate, non-overlapping local oscillation frequency bands with the one or more microwave RF signals to provide a continuous range of down converted frequencies.