8 results about "Micro satellites" patented technology

The invention provides a moon orbit formation navigation microsatellite inter-satellite measurement system and method, and relates to the technical field of deep space exploration, the system comprises a master satellite and a slave satellite, and a Ka inter-satellite link is established between the master satellite and the slave satellite; the master satellite and the slave satellite both send timing inter-satellite measurement signals, receive timing inter-satellite measurement signals from the opposite side, measure the time difference between a local timing signal and the received timing signal of the opposite side to obtain the pseudo-range of the satellite, and the two satellites exchange the pseudo-range through an inter-satellite link to solve the inter-satellite distance and the time difference. Accurate time synchronization of two satellites is not needed, a measurement result can be directly obtained on the satellites, ground calculation is not needed, and ground resources are saved; the satellite platform and the antenna design of the slave satellite are simplified, and the weight and the cost of the satellite are reduced.

Examples of imaging microsatellites are described that have an imaging system and antenna system disposed within the microsatellite body when the microsatellite is in a non-deployed state. The properties of the antenna system can be adjusted such that the antenna system does not impact, contact, or displace the imaging system when the microsatellite is in the non-deployed state. The properties of the antenna system can be adjusted such that the antenna system does not contact or impact the body of the microsatellite or any other structure when the microsatellite transitions to a deployed state. The antenna system can be configured to achieve a desired gain and / or data transmission rate by adjusting properties of the antenna system based on the radiation pattern of an antenna feed and geometric constraints imposed by the imaging system. Examples of methods for designing such imaging microsatellites are provided.

A three-axis integrated intelligent attitude control component suitable for a micro-satellite has a simple design and can independently design the system without having to redesign the system according to different satellites. It occupies a small space, is relatively light in weight, and has high system reliability. The component comprises: an X-axis reaction flywheel (11), a Y-axis reaction flywheel (12), a Z-axis reaction flywheel (13), an X-axis magnetic torque device (21), a Y-axis magnetic torque device (22), a Z-axis magnetic torque device (23), an attitude sensor (3), a mounting frame (4), an attitude control box (5), and a magnetic torque controller (6). The number of the X-axis reaction flywheel, the Y-axis reaction flywheel, and the Z-axis reaction flywheel is three, and the height is smaller than the diameter. The X-axis magnetic torque device and the Y-axis magnetic torque device are both long magnetic torque devices, and the Z-axis magnetic torque device comprises a plurality of short magnetic torque devices (231).

The invention discloses a method for judging microsatellite instability based on fluorescent PCR capillary electrophoresis, which comprises the following steps of: acquiring a fluorescent PCR capillary electrophoresis detection result of a to-be-detected site and fluorescent PCR capillary electrophoresis of a microsatellite stable site, and converting the fluorescent PCR capillary electrophoresis detection result and the fluorescent PCR capillary electrophoresis detection result into matrix data through data processing; obtaining the matrix transverse displacement, the number of newly increased peaks and the number of peak increasing peaks when the minimum error fraction of the to-be-detected site is obtained; and inputting the matrix transverse displacement at the minimum error score, the number of newly increased peaks and the number of peak increasing peaks into a trained support vector machine to obtain a microsatellite instability result of the to-be-measured site. According to the method, the microsatellite instability of the to-be-detected site can be automatically judged based on the fluorescent PCR capillary electrophoresis of the to-be-detected site, subjective errors of traditional microsatellite instability judgment are eliminated, and then false positive and false negative are reduced.

The invention discloses a microsatellite structure based on a VPX standard cabin section, relates to the technical field of aerospace engineering and satellite structures, and solves the problems that an existing microsatellite structure is poor in universality, low in assembly efficiency, complex in thermal design, difficult to consider both light weight and rigidity and the like. The satellite main body structure adopts the structural form of the VPX standard equipment cabin and the non-standard equipment cabin, and the VPX standard equipment cabin, the non-standard equipment cabin and the solar wing all adopt modular design and are easy to disassemble, assemble and redistribute according to operation requirements; the solar wing can be a solar wing for top side installation or a solar wing for rear side installation and is installed above a VPX standard equipment compartment or behind a non-standard equipment compartment according to task requirements, the non-standard equipment compartment is in lap joint according to the task requirements, an embedded connection structure is adopted in the whole, the design of an external support is reduced, and therefore assembling is simplified, the mass of the whole satellite is reduced, and the overall performance of the satellite is improved. A separating mechanism is installed at the bottom of the non-standard equipment cabin and used for being matched with a carrier rocket connector.

The invention discloses a satellite-borne antenna pointing mechanism and a control method thereof, belongs to the technical field of spacecraft attitude control, and solves the problems of high cost and low control precision of an antenna pointing mechanism in the prior art. The device specifically comprises an antenna double-shaft pointing mechanism, and the bottom of the antenna double-shaft pointing mechanism is fixed to an antenna support. An antenna reflecting surface is mounted at the top of the antenna double-axis pointing mechanism; the locking and releasing device is connected with the antenna support and the antenna double-shaft pointing mechanism, and the locking and releasing device relieves the connection effect on the antenna support and the antenna double-shaft pointing mechanism after a satellite enters an orbit; the antenna double-axis pointing mechanism comprises a pitching data transmission mechanism and a horizontal data transmission mechanism. According to the invention, through output end full-closed-loop measurement and silent calibration, the pointing precision of the satellite-borne antenna pointing mechanism is improved from 1.8-degree magnitude of a stepping motor open loop to lt; + / -0.1 degree; the system is in an open-loop holding mode for a long time during working, the power consumption is far lower than that of a servo system in continuous closed-loop operation, and the system is especially suitable for small microsatellites with high power consumption requirements.

Provided are a micro-satellite instability detection method and apparatus based on a next-generation sequencing technology, belonging to the technical field of biological detection. The method comprises: selecting MSI sites, and designing capture probes and / or amplicon primers on the basis of any combination of the sites; selecting a plurality of samples, and calculating the proportion of deletion fragments and the proportion of normal fragments at each MSI site for each sample; selecting a plurality of samples that are determined to be in an MSI-L or MSS state by a PCR method as baseline samples, and setting different depth levels to construct baselines for each baseline sample; performing MSI state detection; selecting samples with an MSI state of MSI-H, and determining whether the samples are abnormal samples by using a Spearman rank correlation coefficient; and if yes, adjusting the baselines and re-determining the MSI state. The provided method has high stability and high accuracy, does not require a control sample, and can be simultaneously applied to micro-satellite instability detection for hybrid capture and amplicon sequencing data.

The application discloses a kind of spaceborne antenna pointing mechanism and control method thereof, belong to spacecraft attitude control technical field, solve the problem of high cost, low control accuracy in prior art antenna pointing mechanism;Specifically including antenna double-axis pointing mechanism, the bottom of antenna double-axis pointing mechanism is fixed on antenna support;Antenna double-axis pointing mechanism top is equipped with antenna reflector;Locking release device connects antenna support and antenna double-axis pointing mechanism, satellite into orbit after locking release device removes the connection effect of both;Antenna double-axis pointing mechanism includes pitch data transmission mechanism and horizontal data transmission mechanism.In the application, through "output end full closed loop" measurement and "silent calibration", the pointing accuracy of spaceborne antenna pointing mechanism is improved from 1.8 ° order of magnitude of open-loop stepper motor to <±0.1 °;Long-term in "open-loop maintenance" mode when working, power consumption is much lower than continuous closed-loop operation servo system, especially suitable for higher power consumption small microsatellite.