42 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 invention discloses a modular lunar surface direct current micro-grid system architecture design method supporting dynamic expansion. The method comprises the steps that firstly, a DC-DC converter in a direct current micro-grid is divided into an interface type DC-DC converter directly connected with a load and a power generation end and a network construction type DC-DC converter supporting energy routing; an input-series and output-parallel modular expansion strategy based on voltage-sharing and current-sharing control is provided, and dynamic balance of input-series voltage sharing and output-parallel current sharing is realized, so that the targets of power mutual assistance and long-range networking operation in progressive evolution of the lunar base energy system are adapted. Through staged architecture evolution and standardized interface design, the modular control concept is emphasized, the reliability and networking interoperability of the system are remarkably improved, meanwhile, progressive access of lunar photovoltaic, energy storage and variable loads is compatible, an extensible technical framework is provided for lunar exploration energy supply, and the application range of the system is widened. The method has important engineering value and reference significance for construction of a deep space power system.

The utility model discloses a hot aerosol fire extinguishing device for small space power supply equipment, including shell, sealing gasket and apron, the apron sets up at one side of shell, and the sealing gasket sets up between shell and apron, the sidewall on shell bottom has a plurality of spouts, be equipped with the cartridge and cooling frame in the shell, the utility model discloses a vortex cooling channel is formed with sealing gasket and cooling frame, and the mixed gas of the burning of the medicine column generates the strong vortex and turbulence when flowing along the vortex cooling channel, greatly increase its contact area and contact time with the cooling wall surface, to strengthen heat transfer, accelerate cooling, make the final formation's fire extinguishing microparticle size smaller and distribute evenly, these small size aerosol particle diffusion speed is fast, is not easy to be blocked by component, more easily diffuses to the burning point in the component gap deep place and carries out the fire extinguishing, to promote the fire extinguishing efficiency of hot aerosol fire extinguishing device in small space power supply equipment.

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.

This invention discloses a highly reliable protection and locking circuit capable of withstanding single-particle transients, belonging to the field of satellite power technology. Its key feature is that it includes at least: a trigger module that receives a signal Pro. SET Amplitude and time signals, Pro SET Amplitude and time signals with reference V REF The system compares data and outputs a trigger signal; a locking module receives the trigger signal and outputs an instruction on whether to execute the locking signal based on the trigger signal; a reset module sends a reset instruction to the locking module. This system is suitable for protection circuit design in medium and high orbit space power controllers or in high-radiation ground environments, and has the advantages of good radiation resistance, high reliability, and stable operation.

The invention discloses a hardware MPPT (Maximum Power Point Tracking) control device and method for a space power supply, and belongs to the technical field of space power supplies. The hardware MPPT control device comprises a Buck circuit topology and an MTTP control circuit; the MTTP control circuit comprises a peak pickup circuit which picks up the maximum point of the power of the solar cell through charging and discharging of an RC circuit; the MPPT reference circuit is used for keeping the maximum power point of the solar cell and generating a reference signal Vmpp of MPPT; the MPPT modulation circuit is used for modulating Vsa to work on the maximum power of the solar cell by changing the duty ratio of Buck by taking a Vmpp signal representing the maximum power of the solar cell as a reference; the mirror current source sampling circuit is used for copying high-end current output by the solar cell array; and the pulse modulation multiplier realizes the product of the voltage and the current of the solar cell by using an MPPT modulation circuit and a mirror current source sampling circuit.

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 application discloses a kind of polar human habitat space power generation energy storage heat cycle integration maintenance system, comprising: foundation and support energy storage module, cavity energy storage module, cavity enclosure module, energy intelligent control module, based on the characteristics of long-term low temperature of polar climate environment, the electric energy generated by renewable energy production module is heat energy, stored in cavity energy storage module, foundation and support energy storage module, and the temperature of polar human habitat environment is maintained using cavity energy storage module and support energy storage module.The integrated maintenance system of the application reduces the amount of storage battery by a large amount of energy storage of renewable energy production and energy storage module;At the same time, the cavity enclosure module and the support energy storage module are used to form a primary space with high thermal insulation performance, and a secondary space is built in the primary space, which reduces the construction difficulty and the maintenance difficulty of the polar human habitat environment, saves the overall construction and operation cost, and provides a technical solution for the large-scale sustainable construction and operation of the polar human habitat environment.

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 belongs to the technical field of semiconductor devices, and relates to a method for measuring real-time current of a diode circuit and application thereof. According to the method, voltage sampling circuits are connected to the two ends of a diode to be detected and used for collecting voltage V at the two ends of the diode; monitoring the temperature T of the diode to be measured in real time by using a temperature sensor; according to the voltage V and the temperature T of the to-be-tested diode, calling the reverse saturation current and the ideal factor n of the current to-be-tested diode in a nonvolatile memory of the controller, and calculating the real-time current i of the diode in the practical application circuit; the rectifier diode is a necessary element in a power supply system, and no additional device is needed for measuring the current, so that the circuit size can be reduced, and the power supply efficiency is improved. The power supply has important application value in modern aviation power supplies, aerospace power supplies or computing power supplies, and can meet the scene requirements of small size and high efficiency of the power supply.

The application discloses a kind of fast response pilot electromagnetic valve, belongs to electromagnetic valve technical field.It is especially suitable for space power system and other strict requirements of medium leakage harsh working conditions.Pilot channel entrance is extracted from main channel entrance upstream and is communicated to the same working medium source, and pressure relief flow channel is arranged in pilot valve, one end of pressure relief flow channel is communicated to gas cavity, and the other end is communicated to main valve outlet side, so that pilot medium is discharged in whole process in valve without external discharge;Only two sealing pairs are arranged in the whole valve.The application uses propellant as pilot medium, drives piston rod to open main valve by building pressure in gas cavity, and sets up sliding orifice plate made of magnetic material, which reduces the area of pressure relief flow channel to accelerate pressure building when energized, and increases the area of pressure relief flow channel to accelerate pressure relief when de-energized, so as to improve response speed in both directions;Pilot medium continuously flows around coil to dissipate heat, which significantly suppresses coil temperature rise and ensures fast response characteristics under long-time energized working conditions.

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.

The invention relates to a spaceflight distributor product development method based on digital twinning, belongs to the technical field of spaceflight electric appliance product development, and solves the problems of insufficient data integration and interaction, lack of historical data constraint and imperfect actual operation data feedback mechanism in the prior art. The method comprises the following steps: analyzing a technical index set of the spaceflight distributor product, and generating a spaceflight distributor product digital prototype model based on a product historical baseline database; product historical process data is injected for reconstruction to form a spaceflight distributor product digital twinborn model V0.0; off-line simulation analysis is executed, and a detailed design scheme is generated based on the technical index set; manufacturing a spaceflight distributor physical model V1.0, and collecting manufacturing process data of the spaceflight distributor physical model V1.0; performing real-time synchronous mapping on the acquired manufacturing process data of the spaceflight distributor physical prototype V1.0 and the spaceflight distributor product digital twinborn model V0.0 to generate a digital twinborn model V1.0; and the spaceflight distributor is produced by taking the digital twin model V1.0 of the spaceflight distributor product as a template.

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.

The invention discloses a millimeter wave broadband annular space power synthesis distributor, which comprises a similar double-ridge circular waveguide synthesis cavity, sub-port units, port units and a radio frequency coaxial connector (1), and is characterized in that the sub-port units are circumferentially and uniformly distributed at the periphery of the similar double-ridge circular waveguide synthesis cavity; the sum port unit is a single-ridge rectangular waveguide (4) and is arranged at the upper end of the similar double-ridge circular waveguide synthesis cavity, and the sum port unit and a coaxial feeder line (201) in the similar double-ridge circular waveguide synthesis cavity form a coaxial-to-waveguide circuit structure; the radio frequency coaxial connector (1) is connected with the sub-port units to form a coaxial-to-waveguide circuit structure. The invention has the advantages of high power capacity, excellent heat dissipation characteristic and compact structure, and can meet the urgent demand of a modern millimeter wave system on a miniaturized radio frequency signal emission source with high heat dissipation characteristic.

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.