4 results about "Micro satellites" patented technology

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.