18 results about "Space technology" patented technology

The invention discloses a super-large plane array type space computing power center, and belongs to the field of space technologies and space infrastructures. The space computing power center is deployed in a morning and evening orbit and comprises a plurality of computing power satellites which are physically docked in orbit through a docking mechanism. Each computing power satellite comprises a satellite platform, and a computing power load, a condensation type energy system and a space pump drive fluid loop system which are arranged on the satellite platform, and a docking mechanism for inter-satellite in-orbit physical docking is also assembled on the satellite platform. A plurality of computing power satellites form a planar array type rigid whole body through the docking mechanism, and energy scheduling among the light condensation type energy systems is realized based on the docking mechanism. According to the space computing power center, through multi-satellite physical docking and energy collaborative scheduling, the energy utilization efficiency and the power supply reliability of the system are improved.

The invention concerns a spacecraft propellant tank designed for storing and supplying fuel to the propulsion system, as well as its application method, which is related to space technology and particularly to the design of tanks for storing liquid propellants within rocket engines. The tank in question comprises a body featuring at least one convex edge that creates a corner capillary and an intake port positioned on one of these convex edges. Additionally, the tank's interior surface is treated to be hydrophilic. The objective of this invention is to develop a spacecraft propellant tank characterized by its lightweight and straightforward design. It facilitates the creation of various propellant tank shapes while minimizing the quantity of internal components that reduce useful volume. It also ensures consistent and reliable functionality of the propellant system with continuous supply of propellant to the intake port, even in the absence of gravity and during multiple activations of the propulsion system. The claimed invention achieves its objective by implementing technical results that include enhancing the efficiency of propellant supply within the tank to the intake port, improving reliability, augmenting the useful internal volume, and offering a variety of tank shapes. The stated objectives are met in particular through the hydrophilic properties of the propellant tank's inner surface, the design of the propellant tank shape featuring at least one convex edge that forms a corner capillary, and positioning of the intake port on one of the convex edges that forms the corner capillary. The application method for the spacecraft propellant tank involves initially filling the tank with liquid propellant and pressurizing gas through the intake port prior to spacecraft launch. Subsequently, once the spacecraft is in orbit, propellant is conveyed from the tank to the propulsion system through the intake port. The movement of liquid propellant towards the intake port is facilitated by the pressure of the pressurizing gas and a localized pressure reduction generated during propellant discharge. This reduction occurs in the corner capillary near the intake port relative to the pressure of the propellant in other sections of at least one corner capillary, thus establishing a flow of propellant through the corner capillaries towards the intake port area.

The application relates to the field of manned space technology, in particular to a quick disconnection type bottle mouth valve for a space station combustion test, which comprises a gas cylinder interface, a quick disconnector fixed end and a pointer type pressure gauge interface arranged on a ball valve body, wherein the gas cylinder interface, the quick disconnector fixed end and the pointer type pressure gauge interface form a tee structure in the interior of the ball valve body; one end of the gas cylinder interface is fixed on the ball valve body, the other end is connected with a gas cylinder to form a first passage; one end of the quick disconnector fixed end is fixed on the ball valve body, the other end is connected with a free end of a quick disconnector of a downstream pipeline to form a second passage; one end of the pointer type pressure gauge is fixed on the ball valve body, the other end is connected with a pointer type pressure gauge to form a third passage. The application has high integration, effectively reduces the number of external pipelines, joints and the like of the bottle mouth valve, has a more compact structure, is lighter in quality, and can realize quick disconnection and communication of the bottle mouth valve with the downstream pipeline under microgravity.

The application discloses a kind of spacecraft ground microgravity simulation platform dynamics modeling and mass balancing method, belong to the technical field of space technology.The application includes the following steps: according to the component assembly relationship of spacecraft ground microgravity semi-physical simulation platform, distinguish each component and component group;According to the condition of each component and component group and whole, respectively, each component and component group are established coordinate system;Dynamics derivation is carried out based on coordinate system, and dynamics model is obtained;The complete dynamics model of ground simulation platform is obtained by analyzing dynamics model by Lagrange method;The complete dynamics model of ground simulation platform is simplified by hypothesis, and simplified dynamics model is obtained;Mass balancing is carried out to simplified dynamics model, and the spacecraft ground microgravity semi-physical simulation platform of approximate quasi-zero stiffness is obtained.The introduction of pivot system makes the system reach approximate quasi-zero stiffness, and then reconstructs microgravity environment on the ground.

A beamforming design method for intelligent metasurface arrays based on orthogonal time-frequency-space technology includes: aggregating multipath channels under direct illumination into cascaded channels with near-field direction vectors; randomly initializing the phase shift of intelligent metasurface units; establishing an effective channel matrix based on the cascaded channels; then establishing a multi-user and rate objective function; maximizing the objective function through phase shift optimization using a hierarchical search strategy; repeatedly executing the hierarchical search strategy to search and optimize subsequent blocks until the number of intelligent metasurface units in each block reaches a preset value; then performing an exhaustive search in the final block, thus completing one iteration; repeating the iteration until the maximum number of iterations is reached; outputting the final optimal phase shift; and implementing beamforming design based on the final optimal phase shift. This invention can reduce the complexity of beamforming design and ensure reliable transmission of high capacity during high-speed movement.

A connecting rod hook locking type locking separation mechanism for rocket stage separation relates to the field of space technology. The mechanism comprises an upper stage connecting plate, a lower stage fixing plate and a frame, the frame is fixed on the lower stage fixing plate, the mechanism further comprises a locking assembly, a transmission assembly and a driving assembly, the locking assembly comprises a hook lock and a first fixing shaft, the hook lock is hinged to the frame through the first fixing shaft; the transmission assembly is hinged between the frame and the hook lock; the driving assembly is connected with the transmission assembly, and is used for providing a driving force to drive the transmission assembly to rotate the hook lock around the first fixing shaft to realize locking and separation of the hook lock and the upper stage connecting plate. The mechanism realizes decoupling of locking force and unlocking force, has the advantages of compact structure, high reliability and strong environmental adaptability, and is suitable for stage connection and separation of a new generation of carrier rockets.

The invention discloses a space target long-time-sequence intelligent collision early warning method, and belongs to the technical field of space. The implementation method comprises the steps of constructing a double-branch multi-scale time convolution network long-time-sequence orbit forecasting model, and on the basis of a traditional time convolution network, establishing a relation between the model and perturbation of different time scales by establishing two branch expansion convolution structures and setting different expansion coefficients, so that the forecasting precision of the model is improved. On the basis, a voxel hash mapping rapid screening method is established, a Gaussian negative logarithm likelihood loss function is introduced, statistical characteristics of forecast errors are utilized, a voxel cube is constructed, only voxels where satellites are located and the distance between targets in neighborhoods of the voxels and the satellites need to be calculated during screening, the screening calculation scale is greatly reduced, and the screening speed is increased. The method does not depend on a high-precision dynamic model, can sense and extract the features of different time scales, improves the track forecasting precision and the collision risk screening efficiency, and accelerates the collision early warning speed.

In the current space navigation, communication, and defense technologies, it is difficult to integrate local control of time, gravity operation, use of dark matters, and communication with the outer space (the Buddhist monk Tenkai's gyrus), and intergalaxy communication, ultrahigh-speed movement, and creation of a time acceleration / deceleration space cannot be realized by modern technologies.SOLUTION: The present invention is a future note related to an ultra-future space technology capable of integrally operating time, gravity, and material behavior by performing local and large-scale dark matter control by a BHc / WHc gate based on a dark matter fluid space model and a space gate theory.SELECTED DRAWING: None

The invention relates to the technical field of spaceflight, and discloses an astronomical compass attitude drift correction method, device and equipment and a medium, the method comprises the following steps: determining a first measurement error corresponding to an accelerometer in an astronomical compass and a second measurement error corresponding to a sun sensor; determining an initial weight according to the first measurement error and the second measurement error; obtaining observation data of the astronomical compass in a preset time period; determining the attitude drift distance of the astronomical compass according to the initial weight and the observation data; determining whether the attitude drift amount meets a preset correction condition; if the attitude drift amount does not meet the preset correction condition, adjusting the initial weight to obtain an adjusted weight; and recalculating the attitude drift distance based on the adjusted weight until the recalculated attitude drift distance meets a preset correction condition. The correction precision of the astronomical compass can be improved.

The application relates to a satellite-ground ranging method suitable for a multi-satellite measurement and control situation, and relates to a satellite-ground ranging method. The application aims to solve the problem that a physical layer of advanced on-orbit system system service data stream and pseudo code data stream cannot be compatible in a multi-satellite measurement and control scene. The process is as follows: at a transmitting end: a downlink telemetry uplink remote control signal is directly sequence spread through a CA code at the transmitting end I path, so as to realize transmission of measurement and control information between a satellite and the ground; a pseudo code ranging sequence is directly sequence spread through the CA code at the transmitting end Q path, so as to realize a ranging function between the satellite and the ground; at a receiving end: 1, transmitting signals of different satellites are separated, and a pseudo code phase and a Doppler frequency shift are obtained; 2, a carrier tracking loop and a pseudo code tracking loop are realized to stably work; 3, I path coherent integration output is carried out to output continuous bits; Q path coherent integration output is carried out to output continuous bits, transmission time is solved, and then actual satellite-ground distance is obtained. The application is used in the field of space technology.

The application discloses a satellite adaptive discretization decomposition method and device for regional target observation planning, belongs to the field of space technology, and particularly relates to a strip decomposition of a satellite for a regional target. The method comprises the following steps: determining a discretization step of a regional target according to an observation range of a satellite load; and discretizing the regional target into a regional sub-node set based on the discretization step and the shape of the earth. The regional sub-node set comprises a plurality of sub-nodes. The satellite adaptive discretization decomposition method and device for regional target observation planning are suitable for single or multiple earth observation satellites to plan and calculate observation tasks for a single or multiple irregularly shaped regional targets.

The invention relates to the field of landslide, in particular to a method for predicting landslide mass motion. The invention relates to a method for predicting landslide mass motion by using a three-dimensional particle flow method. The method comprises the following steps: 1) macro and micro parameter calibration of particle flow calculation; 2) establishment of a three-dimensional geological sliding bed model and a real scene space model interaction and display technology; and 3) landslide particle flow simulation and landslide mass disaster-causing range inversion analysis and real scene result display. A new interdisciplinary method is adopted, a live-action space technology is applied to landslide mass disaster-causing range display, site information is obtained through unmanned aerial vehicle images, a landslide site live-action space model is generated by applying an oblique photography technology, and a disaster site is restored more visually in a three-dimensional form. Meanwhile, through online editing of a live-action model and coupling and interaction of a numerical calculation result and a live-action space model, a landslide mass disaster-causing range prediction result is displayed in a digital and three-dimensional manner, and a landslide disaster monitoring and prevention technical support is accurately and intuitively provided.

The utility model discloses a kind of multi-modal testing devices of simulated space environment, including vacuum chamber with vacuum module;Wherein, cooling module, heating module are respectively equipped in vacuum chamber, vacuum module, cooling module and heating module are respectively connected with the communication control module located outside;Vacuum chamber is also equipped with tray module, for placing sample to be measured;Cooling module can be relatively installed in vacuum chamber and displaced up and down, for adjusting the distance between it and sample to be measured;The utility model can greatly reduce the experimental time of cold and hot impact;While realizing the multi-modal testing effect of simulated space environment, reduce space solar cell array research and development test time and manufacturing cost of product control, help low-cost space technology development and application.

The invention belongs to the technical field of space, and particularly relates to a micro turbojet power generation system capable of being used for primary energy of a pulse power supply, which comprises a micro turbojet engine and a generator, the micro turbojet engine comprises a gas compressor, a combustion chamber and a first turbine; the gas compressor, the combustion chamber and the first turbine are sequentially connected through gas paths in the gas inlet direction. The gas compressor is coaxially and fixedly connected with the first turbine through a mechanical shaft; the micro turbojet engine further comprises a second turbine, the second turbine is coaxially and fixedly connected with the generator through a mechanical shaft, and the second turbine is connected with the air outlet end of the first turbine through an air path. According to the invention, the micro turbojet engine is adopted to provide stable high-frequency and high-power alternating current for the pulse power supply, and is safer; the problems of small volume power, low power generation efficiency, poor safety and low space utilization rate of primary energy of the pulse power supply are solved.

The invention discloses a cubesat group separation device, which relates to the technical field of spaceflight and comprises a cubesat cabin platform, a cubesat cabin and a cubesat cabin cover, wherein the cubesat cabin platform is arranged on the upper stage of the carrier rocket; the lower end of the cubesat cabin is arranged on the cubesat cabin platform; after the cubesat is placed in the cubesat cabin, the upper end of the cubesat cabin is connected with the cubesat cabin cover, and the cubesat cabin cover is used for applying pressing force to the cubesat. Cubesat launching can be completed in a large scale at a time, so that the launching frequency is reduced, and the launching risk and cost are reduced; and meanwhile, the networking period of the cubesat can be shortened, and the networking efficiency is improved.

An intelligent metasurface array beamforming design method based on an orthogonal time-frequency-space technology comprises the steps that multipath channels in a direct incidence state are aggregated into cascade channels with near-field direction vectors, and phase shifts of intelligent metasurface units are initialized randomly; the method comprises the following steps: establishing an effective channel matrix based on a cascade channel, then establishing a multi-user and rate objective function, realizing maximization of the objective function through phase shift optimization, and performing phase shift optimization by adopting a hierarchical search strategy; and repeatedly executing a hierarchical search strategy to carry out search optimization on subsequent levels of blocks until the number of intelligent metasurface units in each block after layering reaches a preset value, then adopting exhaustive search in the final block until one iteration is completed, repeating the iteration until the maximum iteration times, and outputting a final optimal phase shift. And realizing beam forming design based on the final optimal phase shift. According to the invention, the complexity of beam forming design can be reduced, and high-capacity reliable transmission during high-speed movement is ensured.

The invention discloses a long-life space bearing in-orbit operation state real-time monitoring and health maintenance device, and belongs to the technical field of space. According to the method, temperature field distribution characteristics are associated with bearing temperature, bearing supporting structure dependent variable, driving motor current, bearing rotating speed and air pressure change characteristics in a sealing cavity, so that a method for judging the lubricating state and operation stability of the bearing in a non-sensitive section by other signals is found; according to the method, on-orbit signal change which is not easy to find according to other signals is taken as a criterion of on-orbit fault diagnosis.

The application discloses a gravity simulation method for preventing low-gravity or weightlessness syndrome, belongs to the field of space medicine and manned space technology, and aims to solve the technical problems of low-gravity or weightlessness environment, loss of axial compression load of human body, limited effect of existing protection means, and obvious side effects. The application applies opposite forces between two or more axial load-bearing parts of the human body, constructs an axial compression mechanical load close to the physiological state of the earth gravity in the human body, and alleviates and improves the weightlessness syndrome from the mechanical root.