16 results about "Orbiter" patented technology

The application discloses a small-sized separated penetrator for in-situ detection of celestial bodies, and relates to the technical field of penetrator equipment, comprising an aluminum honeycomb buffer module, which comprises an external protective shell and an aluminum honeycomb, and has the beneficial effects that the application is provided with in-situ detection of high-speed penetration of celestial bodies, and discloses a small-sized separated penetrator, which comprises a planet soil penetration module and a star table detection module, and realizes autonomous separation in the impact penetration process, the star table module can realize star table detection and communication with an orbiter, the penetration module is internally provided with an energy storage device and an impact hammer, and can continue to penetrate and dive relying on the energy storage device after impact; the star table module is connected with the penetration module through flexible wires, and can supply power and signal transmission to the latter, the technology enables the penetrator with the modular characteristic to have the in-situ detection capability of planet soil profile, aims to expand the application mode of the penetrator for celestial body detection, and provides a scientific basis for the research of star table structures.

A rocket propulsion and satellite deployment system, comprising a rocket comprising at least a base sector, an operating sector, and a transport sector; the base sector comprises a propellant and is configured to transport the sectors to a mission target; the operating sector comprises a rotating robotic arm pivoted to the operating sector; the transport sector is configured to hold a load intended to be delivered to the target by means of a rotation of the rotating robotic arm with respect to the operating sector, accelerating the load itself which is subsequently released in a direction opposite to the speed of the rocket, increasing, due to conservation of momentum, the speed of the rocket itself. The system is based on a so-called 'useful propellant', consisting of the satellites, rovers and orbiters themselves, which, through the rotational acceleration system, are used to increase the speed of the rocket in space. As well as providing an alternative to traditional propulsion, this system provides an innovative way of putting satellites into orbit, especially in non-earth orbit, which can also be used for longer missions with more than just one target.

The invention provides an atmospheric parameter inversion method and system for a high-speed orbiter. The method comprises the following steps: acquiring pressure data of a plurality of measuring points arranged on the surface of the high-speed orbiter; inputting the pressure data into a pre-established mapping relation model to obtain and output corresponding atmospheric parameters; wherein the mapping relation model is a nonlinear model obtained by training by adopting a neural network fused with extended Kalman filtering according to the corresponding relation between the measuring point pressure data of the high-speed orbiter in the flight envelope and the atmospheric parameters. On the basis of the theoretical basis of the one-to-one correspondence single-valued mapping relation between the surface pressure data and the corresponding atmosphere data, the design method for inversing the atmosphere data based on surface pressure reverse modeling is provided, and the technical problem that the surrounding environment parameters of the high-speed orbiter cannot be obtained in real time through a traditional design method is solved; meanwhile, the attack angle and the sideslip angle of the orbiter are solved, and the technical problem of obtaining the high-precision attitude angle of the high-speed aircraft is solved; the applicability is high, and the calculation precision is high.

The invention relates to the technical field of spacecraft telemetry data analysis, in particular to a telemetry data analysis method for deep learning of a motor West-odd-female-Peng spacecraft, and the method comprises the steps: collecting the telemetry data of the spacecraft through a sensor and a monitoring device, carrying out the cleaning, denoising, standardization and other preprocessing operations of the original telemetry data, and obtaining the telemetry data of the motor West-odd-female-Peng spacecraft. A silicon-based memory function is used for building network nerves to simulate human brain memory; feature extraction is carried out on the preprocessed telemetry data; a model is built based on the extracted features; training is carried out by using annotation data, model parameters are optimized, and the trained model is applied to actual telemetry data; tasks of fault prediction, anomaly detection, performance evaluation and the like are achieved, task results are displayed in the forms of charts, reports and the like, support is provided for decision making, and the problem that a traditional telemetry data analysis method is difficult to meet the requirements for real-time performance, accuracy and intelligence is solved.

This invention discloses a method for predicting the high-Mach aerodynamic characteristics of a Mars orbiter based on FLUENT, belonging to the aerospace field. This invention establishes a symmetrical geometric model of the Mars orbiter and uses a dual-temperature model based on FLUENT to achieve numerical simulation of the Mars orbiter under high-Mach conditions in CO2 medium. By setting a boundary layer based on O-Block mesh coupling, it achieves unified simulation prediction for different velocities and angles of attack, reducing the computational burden of re-partitioning the mesh for different conditions, thereby improving the efficiency of aerodynamic characteristic prediction. Simultaneously, it can accurately simulate and analyze the aerodynamic characteristics of the Mars orbiter under different conditions, enabling the corresponding aerodynamic performance evaluation of the Mars orbiter. This invention can analyze and construct the hypersonic aerodynamic characteristics of the Mars orbiter under different high-Mach conditions upon entering the Martian atmosphere, assisting in the optimization of the Mars orbiter and guidance and control commands.

The invention provides a dynamic evolution analysis method for a sub-orbital fragment risk area. The method comprises the following steps: acquiring fragment group data before and after a sub-orbital aircraft is disassembled; constructing a fragment dynamic model, and establishing a state function including position, speed and acceleration; the fragment group is grouped and processed, and an optimal grouping scheme is determined by adopting a Freedman-Diacois rule; performing state prediction and updating on each group by combining a Runge-Kutta method and a self-adaptive unscented Kalman filtering algorithm; constructing a probability distribution model of the fragment group based on a grouping processing result, and representing by adopting multivariate t distribution; and calculating the risk probability of the fragment group in the specific space region through probability density function integration. Through the adaptive grouping processing strategy, the limitation of overall approximate processing of the fragment group in a traditional method is broken through, the spatial distribution characteristics and the evolution law of the large-scale fragment group can be accurately described, and the accuracy of group behavior analysis is remarkably improved.

The invention discloses a multi-source information fused Mars entering integrated navigation method and system. The method comprises the following steps: acquiring multi-source measurement information of the Mars entering an aircraft in an entering stage, and performing time synchronization and coordinate conversion on the multi-source measurement information to obtain initial observation data; establishing a Mars entry dynamical model based on Mars rotation characteristics, and performing state prediction on the dynamical model by using the initial observation data to obtain a prediction state vector; constructing an observation model, associating the prediction state vector with the distance measurement and speed measurement information of the orbiter and the beacon to form a combined observed quantity, and performing estimation updating on the combined observed quantity by using a nonlinear filtering algorithm to obtain an updated state estimation result; and calculating the condition number of the observation matrix according to the updated state estimation result, and when the condition number is smaller than a preset threshold value, determining that the system is completely observable, and outputting a final navigation calculation result. The technical problem of inaccurate navigation in the Mars entering stage is solved.

This invention relates to the field of thermal protection structures for low Earth orbit (LEO) vehicles, specifically to a high-density thermoelectric conversion device and its design method. The high-density thermoelectric conversion device includes: a high-density thermal layer disposed on the inner side of the vehicle surface; a heat exchanger surrounding the inner side of the high-density thermal layer; and a thermoelectric converter disposed between the high-density thermal layer and the heat exchanger. The heat-absorbing end of the thermoelectric converter is connected to the high-density thermal layer, and the heat-releasing end of the thermoelectric converter is connected to the wall of the heat exchanger. Embodiments of this invention, by setting a high-density thermal layer and a heat exchanger on the surface of the vehicle, create a large temperature difference between the heat-absorbing and heat-releasing ends of the thermoelectric converter on the vehicle surface. This reduces the surface temperature of the vehicle and provides power to the vehicle, thereby solving the thermal protection and power supply problems of LEO vehicles.

The invention discloses a Mars fine terrain reconstruction method, system and device based on an atmospheric correction shadow method and a medium, and belongs to the technical field of terrain reconstruction. The Mars fine terrain reconstruction method comprises the steps that Mars orbiter remote sensing images and a low-resolution digital elevation model under different illumination conditions are acquired to serve as input data; based on the input data, constructing a terrain-atmosphere coupling reflection model to correct interference caused by Mars atmospheric scattering and earth surface albedo in image brightness; and estimating atmospheric parameters in the terrain-atmosphere coupling reflection model through the brightness information of the input multiple images and the radiation transmission model so as to realize parameter adaptive estimation without external atmosphere data. According to the method, by constructing the terrain and atmosphere coupling reflection model, the coupling effect of atmospheric scattering and earth surface albedo in the Mars image can be accurately quantified and corrected, the problem of terrain calculation misalignment caused by neglecting the atmospheric influence in a traditional method is solved, and thus the accuracy of a terrain reconstruction result is remarkably improved.

The invention relates to the technical field of rubber pad processing, in particular to a special cutter for processing a satellite orbiter gas cylinder rubber pad part, which comprises a satellite orbiter gas cylinder rubber pad, a plurality of groups of processing holes and a first milling cutter, a plurality of sets of machining holes are machined in the middle of the satellite orbiter gas cylinder rubber pad through the first milling cutter, a stepped layered cutting structure is formed through the first milling cutter and the second milling cutter, and the design of a cutting edge with the outer diameter being 10 + / -0.1 mm and the inner diameter being 9.6 + / -0.1 mm, a protruding block and a guide groove is matched. The problems that a satellite orbiter gas cylinder rubber pad is poor in machining surface smoothness, the size precision is difficult to control, part edges are prone to curling, and materials are layered or torn are effectively solved, machine tool vibration and rubber elastic deformation are restrained, and the use performance and assembly reliability of parts are guaranteed.

The application relates to a DRO orbit aircraft orbit design method for falling on the moon at a given angle and coordinates. The method comprises the following steps: DRO initial position and speed value integration, output of L2 coordinate system positions of the moon at different moments in a period, and mapping of the moon falling speed and transfer orbit and white plane intersection position. The mapping and DRO period position are combined to reversely coarsely calculate the moon falling moment, initial speed and transfer time length. The three are taken as iteration initial values and constraints are set to reversely accurately calculate the integral end moment, speed and orbit flight time length. The end moment is taken as the orbit transfer moment initial value, the end speed and the DRO speed difference value are taken as the orbit transfer speed increment initial value, the orbit flight time length is taken as the transfer time length initial value, the forward accurate calculation is carried out by setting the terminal constraint and the integral termination condition, and finally the transfer orbit transfer moment and speed increment projection are obtained. The method can be suitable for different task times and different DRO orbit sizes, the calculation result is high in precision, and the iteration is fast and reliable.

The application discloses a Mars remote sensing image enhancement method and device, which comprises the following steps: acquiring a plurality of clear Mars remote sensing images shot by a Mars orbiter; using a sand dust rendering method to generate a plurality of corresponding images with sand dust for each clear Mars remote sensing image; training a deep neural network by using each plurality of clear sand dust images; inputting a real image with sand dust into the trained neural network, reducing the spatial resolution of the real image with sand dust and expanding the channel dimension through a convolutional neural network layer and two two-fold downsampling layers to obtain a feature map; sequentially passing the feature map through three dense deep convolution modules to extract features; and passing the extracted features through twice upsampling operations and once convolution operation. The application can be applied to a Mars orbiter computer vision system and Mars image ground analysis, and provides convenience for ground data analysis and Mars observation work.

The invention discloses an accelerated analysis method for aerodynamic characteristics of a free molecular flow of an aircraft, belongs to the field of numerical simulation of rarefied gas dynamics, and aims to solve the problem of low shadow analysis calculation efficiency of a ray tracing surface element method in aerodynamic analysis of an extremely low earth orbit aircraft. The method comprises the following steps of: initializing parameters and reading a surface grid; establishing a uniform background grid as a spatial index, and quickly associating surface triangular surface elements to corresponding sub-grids; an OpenMP parallel instruction is adopted, and ray tracing-based shielding judgment is executed on a large number of surface elements at the same time; and calculating the aerodynamic contribution of the unshielded surface element according to the free molecular flow theory, and integrating to obtain the overall aerodynamic force. According to the method, the calculation complexity of shadow analysis is remarkably reduced from O (N) through cooperation of spatial index and parallel calculation, and efficient and high-precision prediction of the aerodynamic characteristics of the extremely-low-orbit aircraft is achieved on the premise that precision is guaranteed.

A layout design method for a long-term on-orbit large-volume ultralow-orbit aircraft belongs to the technical field of aerodynamic design of aerospace aircrafts, and comprises the following steps: designing a large-volume fuselage with a large slenderness ratio; designing a capture section molded surface of the air inlet duct; a compression section molded surface of the air inlet channel is designed; the machine body and the air inlet channel are integrated; arranging and fixing solar cell wings; and arranging the folded solar cell wing. The fuselage with the approximately-circular section can cooperate with an air suction type electric propulsion power system in a pneumatic assisting mode to achieve attitude adjustment and orbit maneuvering of the aircraft. The invention aims to develop an ultra-low orbit aircraft capable of residing for a long time, and develops a layout design method of the aircraft capable of residing for a long time on an ultra-low orbit, a large-volume fuselage can ensure sufficient load carrying space, multi-task requirements of the ultra-low orbit aircraft are met, and meanwhile, pneumatic assistance can be provided for in-orbit operation of the aircraft.