27 results about "Space power" patented technology

The invention discloses a multi-layer insulation space power equipment pile head warning lamp capable of being installed without power outage and an installation method, and aims to solve the problems that an existing insulation protective cover is fast in aging, poor in insulation, not firm in fixation and incapable of being installed without power outage, and the multi-layer insulation space power equipment pile head warning lamp comprises a cover body, a left sliding block, a right sliding block and two sets of turnover type locking mechanisms. According to the cover body, an inner layer plate, an outer layer plate and a connecting plate form a double-layer structure, a left sliding way and a right sliding way are formed, a sliding block adopts a double-layer insulation design and is matched with a one-way ratchet structure to achieve self-locking, two sets of overturning type locking mechanisms complete mechanical locking of a notch, a pressing rod is driven to operate through an insulating rod during installation, power failure is not needed, and installation is convenient. Fixing is completed through the three steps of positioning, locking and sliding block closing, the protective cover is arranged in a suspended mode, the insulation distance is increased, insulation is stable, wind resistance is high, aging is slow, warning can be achieved, and the protective cover is suitable for protection of various power equipment heads and excellent in practicability.

A free-space power receiver includes layouts of photovoltaic cells selected to optimize power extraction even when a power beam moves or changes profile on the receiver. The receiver may also include a circuit board, which may include suitable wiring for connecting the photovoltaic cells to one another and to a load for extraction of power. The receiver may include capacitors wired in parallel with the photovoltaic cells.

The application provides a preparation method of an isotropic Ti2AlNb / TiAl-based interpenetrating composite material and belongs to the technical field of intermetallic compound-based composite materials. First, a plurality of Ti2AlNb reinforcing body skeletons in a TPMS configuration are designed by using a hidden function modeling; then, anisotropy of the TPMS configuration is studied by using finite element simulation; secondly, the Ti2AlNb reinforcing body skeleton in the TPMS configuration is prepared by using a selective laser melting process SLM; finally, the Ti2AlNb / TiAl-based interpenetrating composite material in the TPMS configuration is prepared by vacuum hot pressing sintering HPS. Thus, the strong anisotropy of a traditional fiber reinforced composite material in mechanical properties is avoided, good matching of the strength, plasticity and toughness of the composite material is realized, and a new idea and solution are provided for breaking through the application bottleneck of a TiAl in a thermal end part of a space power system.

The application provides a deep space power supply system based on solar cell array power prediction, and is particularly suitable for deep space probes using electric propulsion. The deep space power supply system based on solar cell array power prediction comprises a solar cell array, a solar cell calibration piece, a solar cell calibration circuit, an electric propulsion gear adjuster, a series type power regulator and a central processing unit. The solar cell calibration circuit collects the I-V curve of the solar cell calibration piece, compares and processes the I-V curve of the solar cell array collected by the central processing unit, so as to obtain the correction coefficient and the irradiation coefficient of the solar cell array curve. The correction coefficient and the irradiation coefficient are used to correct and process the ground test solar cell piece curve, so as to meet the high-precision solar cell array power prediction requirement. The electric propulsion gear adjuster selects the appropriate electric propulsion thruster gear according to the accurate solar cell array predicted power, so as to meet the requirement of maximizing the use of the on-orbit output power of the solar cell array.

The application discloses a kind of lightweight high-reliability rotor position detection method and device of large hollow permanent magnet motor, belong to permanent magnet synchronous motor control technical field.The method includes: S1 in stator slot opening embedded installation 3N linear hall sensor, wherein N is positive integer and N≥1, according to slot pitch angle α Calculation common offset, 3N original signal is time shift processing, obtain 3 (N+M) reconstructed hall signal, M is integer and M≥0;S2 executes amplitude range detection and phase relationship detection, reconstructs fault signal using adjacent leading phase normal sensor signal;S3 is calculated rotor position by vector space decoupling transformation and phase extraction method;S4 upper motor controller carries out fault detection and feedback channel switching instruction, realizes system level fault tolerance.The application realizes structure lightweight, high-precision detection, sensor level fault tolerance and system level fault tolerance, is suitable for space power station solar sail etc. Motor drive system high-reliability control demand.

The invention relates to the field of wireless communication, and discloses a 210-220GHz radio frequency transmitting module, which comprises a case and a digital baseband processing unit, the case comprises a local oscillator interface which is arranged in the case and is used for introducing an external reference or monitoring an internal clock state; the intermediate frequency interface is arranged in the case and is used for receiving an intermediate frequency signal; the radio frequency interface is arranged in the case and is used for outputting a radio frequency signal; the power supply interface is arranged on the outer wall of the case and is used for supplying power to the operation of the whole circuit; and the radio frequency circuit system is integrated in the case. A three-dimensional stacked four-path synthesis topological structure is adopted in the power amplification unit, and the space power synthesis technology in a waveguide cavity is utilized to parallelly superpose the energy of a four-path solid-state power amplification tube core, so that the effect of improving the radio frequency output power in the 210-220GHz terahertz frequency band is achieved.

This invention relates to the field of spacecraft power technology, and in particular to a space power system with controllable power flow and its control method. It includes a spacecraft primary bus, a power electronic converter with controllable power flow, an energy storage unit, a logic control unit, a load, and a power distribution switch. The positive terminal of the spacecraft primary bus is connected to one end of the power distribution switch and one input terminal of the power electronic converter with controllable power flow. One end of the load is connected to the other end of the power distribution switch. The other input terminal of the power electronic converter with controllable power flow is connected to the other end of the load and the negative terminal of the spacecraft primary bus. The input terminal of the energy storage unit is connected to the output terminal of the power electronic converter with controllable power flow. The logic control unit is used to collect the voltage at the positive and negative terminals of the spacecraft primary bus and the current of the load. This invention features high power density, fast dynamic response, simple circuit structure, and avoids severe electromagnetic interference.

The invention discloses an aerospace power control electronic device accelerated life test method based on failure physics. The method comprises the following steps: firstly, determining a temperature stress level and a thermal correlation failure mechanism acceleration factor of an accelerated life test; determining initial acceleration test time according to the thermal correlation failure mechanism acceleration factor; in combination with the temperature stress level, sequentially cooperating with other failure mechanisms including an electrical correlation failure mechanism, a vibration correlation failure mechanism and a space radiation correlation failure mechanism to obtain stress levels and acceleration factors under the corresponding failure mechanisms, and on the basis of the initial acceleration test time, performing acceleration test time optimization; and finally, based on the determined acceleration factors and corresponding stress levels under each failure mechanism and the finally optimized acceleration test time, carrying out an acceleration life test. The method provided by the invention can provide a scientific basis for reliability evaluation of the electronic product in an on-orbit environment, and can accurately predict the life index of the product under a multi-stress comprehensive condition.

The invention discloses a substation locating and sizing method based on geographic information fusion and hybrid algorithms, and belongs to the field of power distribution network planning of a power system. The method comprises the following steps: firstly, establishing a power geographic information system of a to-be-planned region, generating a spatial power load distribution matrix and a land price matrix according to spatial power load and actual land information, and establishing a substation locating and sizing model considering land price factors; secondly, carrying out grid representation on a space power load, and carrying out partitioning by using a Voronoi-Kmeans hybrid algorithm; then, selecting standard transformer substation capacity configuration according to the total load amount and capacity-load ratio limitation of each power supply partition; and finally, constructing a locating and sizing planning model by taking the minimum total cost as a target, and solving by using an improved genetic algorithm. The method can improve the planning accuracy and reduce the planning cost.

The invention discloses a spatial power load prediction method based on interpretable artificial intelligence, which belongs to the field of power distribution network planning in a power system, and is a spatial load prediction method based on a time sequence generative adversarial network TimeGAN, a graph attention network GAT and an iTransform. Comprising the steps that a geographic information system is established, TimeGAN is adopted to carry out data enhancement on II-type cellular loads, a condition structure in a time sequence is fully utilized, and the limitation of a traditional data generation method can be well overcome; according to the space power load prediction model based on the GAT-iTransform, the time correlation and the space correlation of cellular loads are synchronously considered, the precision and the generalization ability of the prediction model are effectively improved, interpretability of the model in the time dimension and the space dimension is achieved through an attention mechanism, and stable and reliable data support can be provided for power system planning.

The application belongs to the technical field of semiconductor devices, and relates to a diode circuit real-time current measurement method and application thereof. The method is characterized in that a voltage sampling circuit is connected to both ends of the diode to be measured to collect the voltage V across the diode; a temperature sensor is used to monitor the temperature T of the diode to be measured in real time; the reverse saturation current and the ideal factor n of the diode to be measured are called from the non-volatile memory of the controller according to the voltage V and the temperature T of the diode to be measured, and the real-time current i of the diode in the actual application circuit is calculated; since the rectifier diode is a necessary element in the power supply system, the current is measured without the need for additional devices, so the circuit size can be reduced and the power supply efficiency can be improved. It has important application value in modern aviation power supply, space power supply or computing power supply, and can meet the scene demand of small size and high efficiency of the power supply.

The invention relates to the technical field of chip heat management, and discloses a heat flow time sequence programmable chip heat dissipation system, which improves the heat dissipation of a chip to a heat flow time sequence programming height through the fusion of a programmable thermal diode array, a multi-stage phase change heat storage network and a predictive scheduling algorithm. The active, accurate and prospective management of the heat in the space-time dimension is realized, and the problems that the heat flow path is fixed and the space-time power consumption characteristic of the chip cannot be cooperatively utilized in the existing chip heat dissipation technology are solved.

This invention provides a multi-redundant space nuclear power source combined thermoelectric conversion system, belonging to the field of space power generation. It solves the problems of easy failure of liquid pumps in traditional space nuclear power systems and easy failure of compressors in closed Brayton systems, which in turn lead to the inability of detectors to function properly. It mainly includes a closed Brayton system and a liquid metal magnetohydrodynamic (MHD) power generation system. The closed Brayton system includes a compressor, generator, turbine, regenerator, radiator, and semiconductor thermoelectric generator. The liquid MHD power generation system includes a nuclear reactor, liquid metal pump, gas-liquid separator, MHD nozzle, gas-liquid two-phase mixing section, and MHD power generation channel. It effectively utilizes the advantages of high output power, strong system stability, and long service life of space nuclear power sources. This invention is also applicable to space missions such as deep space exploration.

The invention discloses a power system multi-time-space-guarantee power supply planning research method considering extreme weather influence, and relates to the technical field of power system planning and operation, and the method comprises the following steps: collecting plum rain irradiation data and hurricane path data; obtaining the rainfall intensity based on the Weber distribution, calculating a rainfall attenuation coefficient, and obtaining the actual irradiance according to the rainfall attenuation coefficient and the plum rain irradiation data; calculating node wind speed in combination with hurricane path data and preset terrain correction parameters; screening the actual irradiance and the node wind speed to obtain a typical meteorological year, and generating new energy output scene data; and according to the new energy output scene data, constructing a two-stage guarantee power supply planning model, and generating an optimal guarantee power supply planning scheme based on the two-stage guarantee power supply planning model. The method is used for solving the problem that extreme weather space-time characteristics and multi-source collaborative optimization are difficult to consider in the prior art.

The application discloses a SiC power device on-orbit single event hard error risk probability estimation method, relates to the anti-radiation guarantee technical field of power device space application, and is based on ground radiation test and Weibull data statistical law, combines simulation software simulation of space radiation environment, can low-cost estimate the probability of single event hard error of SiC device space on-orbit application, simultaneously realizes lower difficulty, reduces the cost of on-orbit task of a spacecraft, enhances reliability during on-orbit, guarantees safety of on-orbit flight, belongs to the anti-radiation guarantee technical field of power device space application, has very high economic value, and has important significance for promoting development of a new type of space power supply.

The invention discloses a heat flow time sequence programmable chip heat dissipation system, belongs to the technical field of chip heat management, and aims at solving the technical problem of how to overcome the defects that in an existing chip heat dissipation technology, a heat flow path is fixed, and the time-space power consumption characteristic of a chip cannot be cooperatively utilized. According to the technical scheme, the system comprises a chip, thermal diode units distributed in an array mode are integrated on the back face of the chip, a multi-stage phase change heat storage layer is arranged above the thermal diode units, and the thermal diode units are connected with the phase change heat storage layer. A micro-channel cold plate is arranged on the multi-stage phase change heat storage layer; and each thermal diode unit is an independent controllable thermal switch, has high on-off ratio and quick response capability, and is used for reconstructing a heat flow network and realizing one-way conduction and controllable turn-off of heat flow.

This invention discloses a lunar orbit space solar power station system, belonging to the field of spacecraft structure and energy system technology. Addressing the problems of traditional solar power generation failure in the lunar polar shadow regions and the inability of existing space power station structures to adapt to the lunar orbit environment, a novel system is proposed, comprising: a double-layered box-type central truss made of carbon fiber composite material; 12 thin-film solar subarrays, achieving independent solar tracking via a first conductive rotary joint; 5 laser transmitting antenna subarrays, achieving precise pointing via a second conductive rotary joint; and a rotary connection module. The system adopts a tree-like topological multibody structure, allowing independent attitude adjustment of the solar energy collection and laser transmitting modules, achieving decoupling between solar tracking and laser pointing. This invention offers advantages such as modular on-orbit assembly, lightweight and high rigidity, and flexible vibration suppression, providing continuous wireless energy transmission to the lunar polar regions.

The application discloses a space power high-voltage measurement and control programmable adjustable diode device, and belongs to the field of space power test control. The device comprises a containing space, a control mechanism, a high-voltage relay array and a diode packaging mechanism. The control mechanism is arranged inside the containing space and is used for controlling the switching of the diode array. The high-voltage relay array is arranged on the control mechanism and is used for switching different specifications of diodes in the diode array in response to the control mechanism. The diode packaging mechanism is connected with the control mechanism through high-voltage relay contact high-voltage lines, and is arranged inside the containing space. The application solves the technical problem that different specifications of diodes cannot be switched for automatic testing in the process of space power high-voltage measurement and control in the prior art, and achieves the technical effect that different specifications of diodes are automatically switched through a program control mode, and space power high-voltage measurement and control automatic testing is realized.

The invention relates to the field of space power supply and distribution, in particular to a load unit power distribution control method. In the spacecraft platform level, a first solid-state power controller and a first fuse are arranged in the spacecraft platform; wherein the first solid state power controller acts prior to the first fuse; in the test cabinet level, a second solid-state power controller with adjustable gears is arranged in the test cabinet, for each gear, the action time of the second solid-state power controller is inversely proportional to the overcurrent multiple, and the second solid-state power controller acts earlier than the first solid-state power controller; in the load unit level, a second fuse is arranged in the load unit, and the second fuse acts before the first solid-state power controller and after the second solid-state power controller. According to the invention, when a certain load unit in the test cabinet fails, the power supply of the load unit can be quickly cut off, and the failure is prevented from spreading to a spacecraft platform.

The invention relates to the technical field of space power supply, and particularly discloses a power supply method for a space computing power center and a power supply system thereof, and the power supply method for the space computing power center comprises the steps: receiving solar radiation energy; acquiring a bus voltage value of the DC bus, and determining a sunlight state identifier according to the solar radiation energy; and according to the bus voltage value and the sunlight state identifier, controlling a power supply system for the space computing power center to be switched to a target power supply mode matched with the current operation condition, so as to execute a power supply strategy corresponding to the target power supply mode. According to the invention, stable bus voltage value and stable and efficient operation of the space computing power center are guaranteed, and the energy utilization rate is improved.

The invention relates to the technical field of space power sources, in particular to a flexible gallium arsenide battery assembly for a low-orbit satellite and a packaging method of the flexible gallium arsenide battery assembly. A first layer of modified polyimide film; a transparent antistatic coating; a flexible gallium arsenide cell chip array; a second layer of modified polyimide film; a flexible metal substrate; wherein all the layers are pressed into a whole through an adhesive; the modified polyimide film is a polyimide film of which the surface is modified by silicon oxide or aluminum oxide; and integrated packaging is realized through the low-outgassing-rate adhesive, so that the long-term interface stability and the use reliability of the battery assembly in compound severe environments such as atomic oxygen, ultraviolet, plasma and high and low temperature circulation are remarkably improved while the structural flexibility and the light weight are ensured.

The utility model discloses a power distribution box with an adjustable internal space, which comprises a box body and two box doors rotatably connected to the front end of the box body, a plurality of guide rails are connected to two sides in the box body, the guide rails are movably connected with a support plate, the support plate is connected with a positioning mechanism for positioning the support plate, and the positioning mechanism is connected with a power supply. The positioning mechanism comprises a rotating handle, two positioning columns, two springs, two connecting plates and a rotating disc, the rotating handle is used for driving the rotating disc to rotate, the springs are used for driving the positioning columns to move in the direction close to the corresponding guide rails, and the two ends of the connecting plates are connected with the positioning columns and the rotating disc. According to the utility model, the positions of the plurality of support plates can be adjusted according to the heights of the electrical components, the utilization rate of the internal space of the box body is improved, the applicability is strong, the support plates can be conveniently and quickly positioned and installed, the connection stability of the support plates and the box body is improved, and the operation is flexible and convenient.

The invention discloses an analysis method, system and equipment of a space heat emission subsystem and a medium, and relates to the technical field of space power systems, and the analysis method comprises the following steps: building a coupling heat dissipation unit based on a heat pipe model, a fin model and a coolant pipeline model; based on an actual radiation panel structure and a fluid loop, different numbers of coupling heat dissipation units are spliced, and a physical model of the space heat emission subsystem is obtained; combining the physical model, the first transient heat conduction model, the second transient heat conduction model, the third transient heat conduction model, the coolant pipe wall model and the friction pressure drop model to obtain a transient simulation model of the space heat emission subsystem; and performing transient analysis on the transient simulation model under different working conditions to obtain a dynamic response result of the space heat emission subsystem. According to the invention, the overall transient simulation of the thermal emission subsystem in the space nuclear reactor power supply system is realized, and the real-time operation characteristics of the thermal emission subsystem can be obtained according to the change of the operation condition of the space power supply system.

The application discloses a kind of heaven and earth linkage inter-satellite microwave energy scheduling system, belong to space microwave energy transmission technical field.System includes inter-satellite transmission satellite layer and ground receiving scheduling layer, inter-satellite layer contains the standardized energy transmission satellite of multiple orbit flexible deployment, is equipped with the multi-frequency band active phased array antenna array of common-aperture subarea, ground layer is composed of regional microwave ground transceiver station, can be connected external space power generation device and ground network.System and each node are equipped with bidirectional standardized microwave energy interface, support full-duplex synchronous transmission and reception, multi-target synchronous parallel energy supply;Single node can be independently operated, multiple nodes can be autonomously networked, not limited by orbit level and node type transmission, can automatically select optimal transmission path, realize satellite-ground two-way energy transmission and cross-regional full energy scheduling.

The invention belongs to the technical field of spaceflight power supplies, and provides an isolated bus system for a spaceflight power supply, a control method of the isolated bus system and a spaceflight power supply system.The isolated bus system comprises a direct current bus, a detection circuit, a control device, an S3R circuit, an MPPT circuit and a storage battery circuit; the detection circuit detects voltage and current of the DC bus and transmits the voltage and current to the control device. And the control device selects a working mode according to the voltage and current of the direct current bus, and controls the S3R circuit, the MPPT circuit and the storage battery circuit according to the working mode. According to the isolated bus system, the utilization efficiency of a solar panel of a spaceflight power supply is improved, and meanwhile, the size of the spaceflight power supply is integrally reduced.

A multi-objective optimization method for cooling space power magnetic device structure based on phase change material, relates to the technical field of space power magnetic device cooling. The magnetic device cooling structure is designed, the phase change material is sealed and wrapped on the surface of the magnetic core of the magnetic device through the packaging shell, the model is established by relying on COMSOL Multiphysics, the thickness variable assignment range of the phase change material is set to obtain different sizes of the magnetic device cooling structure, the steady-state parameterization scanning is carried out, the unit volume effective cooling capacity and the unit mass effective cooling capacity of the winding and the magnetic core are calculated, the unit cooling cost of the winding and the magnetic core is calculated, and the best thickness value of the phase change material is obtained by relying on Origin to fit the curve and obtain the average value. Based on the high latent heat property of the phase change material, the space power magnetic device is cooled, and the multi-objective optimization considering the volume, mass, material cost and carrying cost is comprehensively considered, so that the better cooling effect is obtained.

A free-space power receiver includes layouts of photovoltaic cells selected to optimize power extraction even when a power beam moves or changes profile on the receiver. The receiver may also include a circuit board, which may include suitable wiring for connecting the photovoltaic cells to one another and to a load for extraction of power. The receiver may include capacitors wired in parallel with the photovoltaic cells.